Washington, Wednesday, January 25, 1950
VOLUME 15 ■ NUMBER 16
Washington, Wednesday, January 25, 1950
TITLE 3— THE PRESIDENT in paragraph (a) last above, to the in CONTENTS vention is insufficient equitably to justify EXECUTIVE ORDER 10096 a requirement of assignment to the Gov THE PRESIDENT ernment of the entire right, title and P roviding for a U niform P atent P olicy Executive Order Pase for the G overnment W ith R espect to interest to such invention, or in any case where the Government has insufficient Inventions made by Government I nventions M ade by G overnment interest in an invention to obtain entire employees; providing, for uni E mployees and for the Administra form patent policy for Govern tion of Such P olicy right, title and interest therein (although the Government could obtain some under ment and for administration of WHEREAS inventive advances in paragraph (a), above), the Government such policy______389 scientific and technological fields fre agency concerned, subject to the ap quently result from governmental ac proval of the Chairman of the Govern EXECUTIVE AGENCIES tivities carried on by Government ment Patents Board (provided for in Agriculture Department employees; and paragraph 3 of this order and herein See Commodity Credit Corpora WHEREAS the Government of the after referred to as the Chairman), shall tion ; Forest Service; Production United States is expending large sums leave title to such invention in the and Marketing Administration. of money annually for the conduct of employee, subject, however, to the reser these activities; and vation to the Government of a non-ex Alien Property, Office of WHEREAS these advances constitute clusive, irrevocable, royalty-free license Notices: a vast national resource; and in the invention with power to grant Vesting orders, etc.: WHEREAS it is fitting and proper that licenses for all governmental purposes, Azzolini, Giuseppina, et al__ 446 the inventive product of functions of the such reservation, in the terms thereof, Balducci, Unita______445 Government, carried out by Government to appear, where practicable, in any Boesl, Gisela____'______445 employees, should be available to the patent, domestic or foreign, which may Primer, Dusine Marie______446 Government; and issue on such invention. Grabczewski, Feliks______446 WHEREAS the rights of Government (c) In applying the provisions of para Grumbach, Bertha______446 employees in their inventions should be graphs (a) and (b), above, to the facts Hopff, Mary______445 recognized in appropriate instances; and circumstances relating to the mak Rottenberg, Herman, et al__ 446 and ing of any particular invention, it shall Strauss, Hans______, 447 WHEREAS the carrying out of the be presumed that an invention made by Child Labor Branch policy of this order requires appropriate an employee who is employed or assigned See Wage and Hour Division. administrative arrangements : (i) to invent or improve or perfect any Civil Aeronautics Board NOW, THEREFORE, by virtue of the art, machine, manufacture, or composi authority vested in me by the Constitu tion of matter, (ii) to conduct or perform Notices: tion and statutes, and as President of the research, development work, or both, (iii) Golden North Airways, Inc.; United States and Commander in Chief hearing______443 to supervise, direct, coordinate, or review Proposed rule making: of the armed forces of the United States, Government financed or conducted re in the interest of the establishment and search, development work, or* both, or Airplane airworthiness, trans operation of a uniform patent policy for (iv) to act in a liaison capacity among port categories______405 the Government with respect to inven governmental or nongovernmental agen Commodity Credit Corporation tions made by Government employees, it cies or individuals engaged in such work, Rules and regulations: is hereby ordered as follows: or made by an employee included within Dairy products; milk and but- 1. The following basic policy is estab any other category of employees specified terfat price support program- 391 lished for all Government agencies with by regulations issued pursuant to section Federal Communications Com respect to inventions hereafter made by 4 (b) hereof, falls within the provisions mission any Government employee: of paragraph (a), above, and it shall be (a) The Government shall obtain the presumed that any invention made by Notices: entire right, title and interest in and to any other employee falls within the pro Statement of delegations of au thority-______443 all inventions made by any Government visions of paragraph (b), above. Either Rules and regulations: employee (1) during working hours, or presumption may be rebutted by the Radio broadcast services; FM (2) with a contribution by the Govern facts or circumstances attendant upon broadcast stations______ment of facilities, equipment, materials, the conditions under which any partic 404 funds, or information, or of time or serv ular invention is made and, notwith Federal Trade Commission ices of other Government employees on standing the foregoing, shall not pre Rules and regulations: official duty, or (3) which bear a direct clude a determination that the invention Autonator Laboratories Co. et relation to or are made in consequence falls within the provisions of paragraph al.; cease and desist order__ 392 of the official duties of the inventor. '(d) next below. Forest Service (b) In any case where the contribu (d) In any case wherein the Govern Notices: tion of the Government, as measured by ment neither (1) pursuant to the pro- National Forest Advisory Board any one or more of the criteria set forth (Continued on next page) of Appeals______443- 389 890 THE PRESIDENT
CONTENTS— Continued CONTENTS— Continued Interstate Commerce Commis- Page Wage and Hour Division— Con. Page federalmregister sion Rules and regulations—Continued \ 1934 Notices: Learners employment—Con. Applications for relief: Telephone industry, Commodities, various, from, independent------398 Published dally, except Sundays, Mondays, to and between points in Minors between 14 and 16 years and days following official Federal holidays, South______444 of age, employment; occupa by the Division of the Federal Register, the Grain from Texas to St. Louis, tions and periods and condi National Archives, pursuant to the authority Mo., and East St. Louis, Ill_ 444 tions of employment------395 contained in the Federal Register Act, ap Motor-rail rates; New York, Student learners ; conditions proved .July 26, 1935 (49 Stat. 500, as under which certificates will amended; 44 U. S. C., ch. 8B), under regula New HaVen and Hartford tions prescribed by the Administrative Com Railroad Co______444 be issued------396 mittee, approved by the President. Distribu Woodpulp from South to Me tion is made only by the Superintendent of nominee, Mich., and Mari CODIFICATION GUIDE Documents, Government Printing Office, nette, Wis______444 Washington 25, D. C. Rerouting or diversion of traf A numerical list of the parts of the Code The regulatory material appearing herein fic______444 of Federal Regulations affected by documents is keyed to the Code of Federal Regulations, published in this issue. Proposed rules, as which is published, under 50 titles, pursuant Justice Department opposed to final actions, are identified as to section 11 of the Federal Register Act, as See Alien Property, Office of. such. amended June 19, 1937. The Federal Register will be furnished by Labor Department Title 3 Page mail to subscribers, free of postage, for $1.50 See Wage and Hour Division. Chapter II (Executive orders): per month or $15.00 per year, payable in ad 9865 (see EO 10096)______389 vance. The charge for individual copies Maritime Commission (minimum 15tf) varies in proportion to the Rules and regulations: 10096______389 6ize of the issue. Remit check or money - Forms; domestic trade Title 6 order, made payable to the Superintendent addendum______403 Chapter IV: of Documents, directly to the Government Part 610______391 Printing Office, Washington 25, D. C. Narcotics Bureau There are no restrictions on the republica Proposed rule making : Title 7 tion of material appearing in the Federal Drug Nu-2206; addiction-form-' Chapter IX: Register. ing or addiction-sustaining Part 955______392 liability______405 Title 14 Production and Marketing Ad Chapter I: 1949 Edition ministration Part 4b (proposed)--- .------405 Rules and regulations: Grapefruit in Arizona and cer Title 16 CODE OF FEDERAL tain parts of California; lim Chapter I: Part 3______392 REGULATIONS itation of shipments______392 Public Housing Administration Title 21 The following books are now available: Rules and regulations: Chapter II: War housing program, policy; Proposed rules______405 Titles 35-37 ($3.00) disposition of federally owned Title 24 Title 38 ($3.50) war housing projects______393 Chapter IH: Previously announced: Title 3, 1948 Supp. Securities and Exchange Com Part 340______i------393 ($2.75); Titles 4-5 ($2.25); Title 6 ($3.00); mission Title 29 Title 7: Parts 1-201 ($4.25); Parts 210- Notices : Chapter IV: 874 ($2.75); Parts 900 to end ($3.50); Indiana Service Corp. et al.; Part 441______395 Title 8 ($2.75); Title 9 ($2.50); Titles supplemental order approving Chapter V: 10-13 ($2.25); Title 14: Parts 1-399 extension of time______445 Part 520______396 ($3.50); Parts 400 to end ($2.25); Title Part 521______397 15 ($2.50); Title 16 ($3.50); Title 17 Treasury Department Part 522 (6 documents)_____ 398-400 ($2.75); Title 18 ($2.75); Title 19 ($3.25); See also Narcotics Bureau. Part 549______401 Title 20 ($2.75); Title 21 ($2.50); Titles Notices : Part 550______402 22-23 ($2.25); Title 24 ($2.75); Title 25 iy4 percent Treasury notes of ($2.75); Title 26: Parts 1-79 ($4.00); Series A-1951 ; offering_____ 443 Title 36 Parts 80-169 ($2.75); Parts 170-182 Chapter II: Wage and Hour Division ($3.25); Parts 183-299 ($3.50); Parts 300 Part 211______403 Rules and regulations: to end, and Title 27 ($3.50); Titles 28-29 Title 46 ($2.50); Titles 30-31 ($3.25); Titles 32 Apprentices, employment ; train and 34 ($4.50); Title 33 ($3.50) ing of veterans------397 Chapter II: Defining and delimiting terms : Part 299______403 Order from Superintendent of Documents, Bona fide profit-sharing plan Title 47 Government Printing Office, Washington or trust______401 Chapter I: 25, D. C. Talent fees______402 Part 3______404 Learners employment: Apparel industry; single pants, shirts and allied gar visions of paragraph (a) above, obtains CONTENTS— Continued ments, women’s apparel, entire right, title and interest in, and sportswear and other odd to an invention nor (2) pursuant to the Forest Service— Continued Page outerwear, rainwear, robes Rules and regulations: and leather and sheep-lined provisions of paragraph (b) above, re Appeals from administrative garments divisions______399 serves a non-exclusive, irrevocable, roy action______403 Cigar industry______400 alty-free license in the invention with Glove industry------400 power to grant licenses for all govern Housing and Home Finance Knitted wear industry______398 mental purposes, the Government shall Agency Millinery, apparel, artificial leave the entire right, title and interest See Public Housing Administra flower and feather, and in and to the invention in the Govern tion. woolen industries______398 ment employee, subject to law. Wednesday, January 25,1950 FEDERAL REGISTER 391 (e) Actions taken, and rights ac Appropriation Act, 1946, 59 Stat. 134, ment of Commerce under the provisions quired, under the foregoing provisions 31 U. S. C. 691. The Department of of Executive Order No. 9865 of June 14, of this section, shall be reported to the Commerce shall provide necessary office 1947 are hereby transferred to the Chair Chairman in accordance with procedures accommodations and facilities for the man and the whole or any part of such established by him. use of the Board and the Chairman. functions and duties may be delegated 2. Subject to considerations of na (d) The Chairman shall establish such by him to any Government agency or tional security, or public health, safety, committees and other working groups officer: Provided, That said Executive or welfare, the following basic policy is as may be required to advise or assist him Order No. 9865 shall not be deemed to established for the collection, and dis in the performance of any of his func be amended or affected by any provision semination to the public, of information tions. of this Executive order other than this concerning inventions resulting from (e) The Chairman of the Government paragraph 5.. Government research and development Patents Board and the Chairman of the 6. Each Government agency shall take activities: Interdepartmental Committee on Scien all steps appropriate to effectuate this (a) When an invention is made under tific Research and Development (pro order, including the promulgation of circumstances defined in paragraph 1(a) vided for by Executive Order No. 9912 of necessary regulations which shall not be of this order giving the United States the December 24, 1947) shall establish and inconsistent with this order or with reg right to title thereto, the Government maintain such mutual consultation as ulations issued pursuant to paragraph 4 agency concerned shall either prepare will effect the proper coordination of (b) hereof. and file an application for patent there affairs of common concern. 7. As used in this Executive order, the for in the United States Patent Office or 4. With a view to obtaining uniform next stated terms, in singular and plural, make a full disclosure of the invention application of the policies set out in this are defined as follows for the purposes promptly to the Chairman, who may, if order and uniform operations there hereof: he determines the Government interest under, the Chairman is authorized and (a) “Government agency” includes so requires, cause application for patent directed: any executive department and any inde to be filed or cause the invention to be (a) To consult and advise with Gov pendent commission, board, office; fully disclosed by publication thereof: ernment agencies concerning the appli agency, authority, or other establish Provided, however, That, consistent with cation and operation of the policies ment of the Executive Branch of the present practice of the Department of outlined herein; Government of the United States (in Agriculture, no application for patent (b) After consultation with the Gov cluding any such independent regula shall, without the approval of the Secre ernment Patents Board, to formulate and tory commission or board, any such tary of Agriculture, be filed in respect of submit to the President for approval such wholly-owned corporation, and the any variety of plant invented by any proposed rules and regulations as may be Smithsonian Institution), but excludes employee of that Department. necessary or desirable to implement and the Atomic Energy Commission. (b) Under arrangements made and effectuate the aforesaid policies, together (b) “Government employee" includes policies adopted by the Chairman, all in with the recommendations of the Gov any officer or employee, civilian or mili ventions or rights therein, including li ernment Patents Board thereon; tary, of any Government agency, except censes, owned or controlled by the United (c) To submit annually a report to the States or any Government agency shall President concerning the operation of such part-time consultants or employees be indexed, and copies, summaries, anal such policies, and from time to time such as may be excluded by regulations pro yses and abstracts thereof shall be recommendations for modification there mulgated pursuant to paragraph 4 (b) maintained and made available to all of as may be deemed desirable; hereof. Government agencies and to public (d) To determine with finality any (c) “Invention" includes any art, ma libraries, universities, trade associations, controversies or disputes between any chine, manufacture, design, or composi scientitsts and scientific groups, indus Government agency and its employees, to tion of matter, or any new and useful trial and commercial organizations, and the extent submitted by any party to the improvement thereof, or any variety of all other interested groups of persons. dispute, concerning the ownership of plant, which is or may be patentable 3. (a) A Government Patents Board inventions made by such employees or under the patent laws of the United is established'consisting of a Chairman rights therein; and States. of the Government Patents Board, who (e) To perform such other or further H arry S. T ruman shall be appointed by the President, and functions or duties as may from time to of one representative from each of the time be prescribed by the President or by T he W hite H ouse, following: statute. January 23, 1950. Department of Agriculture 5. The functions and duties of the IP. R. Doc. 50-722; Piled, Jan. 23, 1950; Department of Commerce Secretary of Commerce and the Depart- 1:16 p. m.] Department of the Interior Department of Justice Department of State Department of Defense Civil Service Commission Federal Security Agency ¿3/ RULES AND REGULATIONS National Advisory Committee for Aero nautics General Services Administration TITLE 6— AGRICULTURAL CREDIT of approximately $3.07 per hundred Each such representative, together with weight for manufacturing milk of 3.95 an alternate, shall be designated by the Chapter IV— Production and Market percent butterfat (yearly average test) head of the agency concerned. ing Administration and Commodity and approximately 60 cents per pound of (b) The Government Patents Board Credit Corporation, Department of butterfat. The program will support the shall advise and confer with the Chair Agriculture price of all milk. As a means of carry man concerning the operation of those ing out this program, Commodity Credit aspects of the Government’s patent pol Subchapter C— Loans, Purchases, and Other Corporation (hereinafter called CCC) icy which are affected by the provisions Operations will purchase manufactured dairy prod of this order or of Executive Order No. P art 610—D airy P roducts ucts as provided herein. 9865, and suggest modifications or im § 610.125 Price support program for provements where necessary. SUBPART—MILK AND BUTTERFAT PRICE SUPPORT PROGRAM milk and butterfat. (a) CCC will pur (c) Consonant with law, the agencies chase, during the period January X, 1950, referred to in paragraph 3 (a) hereof The U. S. Department of Agriculture through March 31, 1951, butter, nonfat shall as may be necessary for the purpose will support the general levels of prices dry milk solids, Cheddar cheese, and of effectuating this order furnish assist to producers for manufacturing milk and evaporated milk, f. o. b. offered delivery ance to the Board in accordance with butterfat, from January 1,1950, through points at any location in the continental section 214 of the Independent Offices March 31, 1951, at a national average United States, at the following prices; 392 RULES AND REGULATIONS County, California; or in that part of Commodity Description Unit Price Riverside County, California, situated (dollars) south and east of the San Gorgonio Pass which grade lower than U. S. No. 2 grade: TT. S. Grade A nr higher_____ .. ______$0.60 Do. . U. S. Grade B...... 7...... 58 Provided, That the tolerance for grade Nonfat dry milk solids__ .125 defects permitted for such U. S. No. 2 Do...... 105 .31 grade shall not include serious damage IT, 8. Dt A. Specifications ______3.95 due to dryness or mushy condition; how ever, with respect to each lot of such (b) The butter shall be salted cream of 1937, as amended, and upon the basis grapefruit 10 percent, by count, of the ery butter of U. S. Grade B or higher, of the recommendations of the Admin grapefruit in such lot may fail to meet solid-packed in commercial containers. istrative Committee (established under the requirements, of such U. S. No. 2 The nonfat dry milk solids shall be the aforesaid amended marketing agree grade, relating to freedom from serious U. S. Extra Grade, packed in export ment and order), and upon other avail damage caused by dryness or mushy containers. The Cheddar cheese shall able information, it is hereby found that condition: Provided further, That in be U. S. Grade A or higher, packed in the limitation of shipments of grape cluded in such 10 percent there may be commercial domestic containers. The fruit, as hereinafter provided, will tend not more than 5 percent, by count, of the evaporated milk shall meet U. S. Depart to effectuate the declared policy of the grapefruit in such lot which show dryness ment of Agriculture specifications, and act. or mushy condition to the extent that shall be packed in commercial domestic (2) It is hereby further found that it more than 40 percent of the pulp is cases. is impracticable and contrary to the pub affected; or (c) The products purchased shall be lic interest to give preliminary notice, (ii) From the State of California or produced and located in the continental engage in public rule making procedure, the State of Arizona to any point outside United States. Purchases will be made and postpone the effective date of this thereof in the United States or Canada, in units of not less than tariff minimum section until 30 days after publication any grapefruit, grown as aforesaid, carlots for the area where the product thereof in the F ederal R egister (60 Stat. which are of a size smaller than 3%e is located. Grades and weights shall be 237; 5 U. S. C. 1001 et seq.) because the inches in diameter (“diameter” to be evidenced by inspection certificates is time intervening between the date when measured midway at a right angle to a sued by the U. S. Department of Agri information upon which this section is straight line running from the stem to culture. based became available and the time the blossom end of the fruit), except (d) Purchases will be made by CCC when this section must become effective that a tolerance of 5 percent, by count, subject to the terms and conditions of in order to effectuate the declared policy of grapefruit smaller than such mini purchase announcements issued by the of the act is insufficient; a reasonable mum size shall be permitted which tol Dairy Branch, Production and Marketing time is permitted, under the circum erance shall be applied in accordance Administration, U. S. Department of Ag stances, for preparation for such effec with the provisions for the application riculture, Washington 25, D. C. tive time ; and good cause exists for mak of tolerances, specified in the revised (Sec. 4, 62 Stat. 1070, as amended; 15 U. S. C. ing the provisions hereof effective not United States Standards for Grapefruit Sup., 714b. Interpret or apply secs. 4, 5, 62 later than January 25, 1950. Shipments (California and Arizona), 7 CFR 51.241; Stat. 1070, 1072, sec. 1, Pub. Law 897, 80th of grapefruit, grown as aforesaid, have 14 F. R. 7369: Provided, That, in deter Cong., 15 U. S. C. Sup., 714b, 714c) been subject to regulation by grades and mining the percentage of grapefruit in sizes, pursuant to the amended market any lot which are smaller than 3%e Issued this 20th day of January 1950. ing agreement and order, since October inches in diameter, such percentage shall [seal] E lmer P. K ruse, 23,1949, and will so continue until Janu be based only on the grapefruit in such Vice President, ary 25, 1950; the recommendation and lot which are of a size 31%e inches in Commodity Credit Corporation. supporting information for continued diameter and smaller. Approved : regulation subsequent to January 24, (3) As used in this section, “handler,” 1950, was promptly submitted to the De “variety,” “grapefruit,” and “ship” shall R alph S. T rigg, partment after an open meeting of the have the same meaning as when used in President, Administrative Committee on January said amended marketing agreement' and Commodity Credit Corporation. 18; such meeting was held to consider order; and the term “U. S. No. 2” shall [P. R. Doc. 60-698; Filed, Jan. 24, 1950; recommendations for regulation, after have the same meaning as when used in 8:59 a. m.] giving due notice of such meeting, and the revised United States Standards for interested persons were afforded an op Grapefruit (California and Arizona), 7 portunity to submit their views at this CFR 51.241; 14 F. R. 7369. TITLE 7— AGRICULTURE meeting; the provisions of this section, (Sec. 5, 49 Stat. 753, as amended; 7 U. S. C. including the effective time thereof, are and Sup., 608c) Chapter IX— Production and Mar identical with the aforesaid recommen keting Administration (Marketing dation of the committee, and informa Done at Washington, D. C., this 23d Agreements and Orders), Depart tion concerning such provisions and day of January 1950. ment of Agriculture effective time has been disseminated [seal] S. R. Sm ith, among handlers of such grapefruit; it is [Grapefruit Reg. 68] Director, Fruit and Vegetable necessary, in order to effectuate the de Branch, Production and Mar P art 955—G rapefruit G rown in Ari clared policy of the act, to make this keting Administration. zona; in I mperial County, Califor section effective during the period here n ia ; and in T hat P art of R iverside inafter set forth so as to provide for [F. R. Doc. 50-729; Filed, Jan. 24, 1950; County, California, Situated South the continued regulation of the handling 8:59 a. m.] and E ast of the San G orgonio P ass of grapefruit; and compliance with this section will not require any special prep LIMITATION OF SHIPMENTS aration on the part of persons subject 3 3 -tHLE 16— COMMERCIAL § 955.329 Grapefruit Regulation 68— thereto which cannot be completed by PRACTICES (a) Findings. (1) Pursuant to the mar the effective time hereof. keting agreement, as amended, and (b) Order. (1) Grapefruit Regulation Chapter I— Federal Trade Commission Order No. 55, as amended (7 CFR Part 67 (7 CFR 955.328; 14 F. R. 7876) is here 955; 14 F. R. 6803), regulating the han by terminated as of the effective time of [Docket No. 5638] dling of grapefruit grown in the State this section. P art 3—D igest of Cease and D esist of Arizona; in Imperial County, Cali (2) During the period beginning at Orders fornia; and in that part of Riverside 12:01 a. m„ P. s. t., January 25,1950, and County, California, situated south and ending at 12:01 a. m., P. s. t., February AUTONATOR LABORATORIES CO. AND HARRY east of the San Gorgonio Pass, effective 19, 1950, no handler shall ship : ABELSON under the applicable provisions of the (i) Any grapefruit of any variety grown Subpart—Advertising falsely or mis Agricultural Marketing Agreement Act in the State of Arizona; in Imperial leadingly: § 3.15 Business status, advatn- Wednesday y January 25,1950 FEDERAL REGISTER 393 tages, or connections—Producer status be entered as the order to cease and de TITLE 24— HOUSING AND of dealer—Laboratory; § 3.170 Qualities sist in this proceeding; and respondents or properties of product or service; having not appeared in response to such HOUSING CREDIT § 3.195 Safety. Subpart —• Neglecting, leave to show cause and the Commission unfairly or deceptively, to make mate having thereafter made its findings as Chapter III — Public Housing Ad rial disclosure: § 3.1890 Safety. Sub 4 to the facts and its conclusion that re ministration, Housing and Home part—Using misleading name—Vendor: spondents have violated the Federal Finance Agency § 3.2445 Producer or laboratory status of Trade Commission Act: P art 340—W ar H ousing P rogram ; dealer or seller. In connection with the It is ordered, That respondents, Au offering for sale, sale, and distribution tonator Laboratories Co., a corporation, . P olicy in commerce, of respondents’ electric its officers, representatives, agents, and disposition of federally owned war water heating device, “Hot Donut Water employees, and Harry Abelson, his HOUSING PROJECTS Heater”, or any substantially similar de agents, and employees, directly or Effective November 4,1949, paragraphs vice, whether sold under the same name through any corporate or other device, (a), (b), and (c) of § 340.5 Disposition or any other name, (1) representing that in connection with the offering for sale, of federally owned war housing projects, said device will produce boiling hot water sale, and distribution in commerce, as are amended as follows: or steaming hot water “in a jiffy”, or “commerce” is defined in the Federal afford hot water in any other period of Trade Commission Act, of respondents’ § 340.5 Disposition of federally owned time less than is actually required; (2) electric water heating device, “Hot Donut war housing projects. The Public Hous using the word “Laboratories”, or any Water Heater”, or any substantially ing Administration is responsible for the other word of similar import or meaning, similar device, whether sold under the disposition of war housing projects, or to designate, describe, or refer to re same name or any other name, do forth parts thereof, upon their termination by spondents’ business, or representing with cease and desist from: the Administrator of the Housing and through any other means that either of (1) Representing that said device will Home Finance Agency. said respondents owns, operates, or con produce boiling hot water or steaming (a) Definitions. (1) “Government trols a laboratory or establishment con hot water “in a jiffy”, or afford hot water agency” and “Federal agency” mean any taining substantial equipment and in any other period of time less than is executive department, board, bureau, apparatus for use in study and experi actually required; provided, however, commission, or other agency in the exec mentation by scientists or technicians that nothing herein shall prohibit use of utive branch of the Federal Government, employed for such purposes or for the the word “jiffy” to designate the period or any corporation wholly owned conduct of research in connection with required to heat water if in immediate (directly or through one or more corpo the application of electricity to water and conspicuous conjunction therewith rations) by the United States. (The pri heating facilities; or, (3) distributing or respondents truthfully state the time re orities of Government agencies include selling said device unless the word “cau quired to raise one or more designated the priority awarded to RFC to aid sales tion” or “warning”, together with ade volumes of water of stated temperature to veterans and owner-operators of small quate directions for safe use of the to a specified temperature level. businesses.) device, is indelibly impressed, imprinted, (2) Using the word “Laboratories”, or (2) “State and local governments” or affixed thereon, informing the user any other word of similar import or means any state, territory, or possession that unless the directions for use are meaning, to designate, describe, or refer of the United States, the District of Co strictly followed dangerous electric shock to respondents’ business, or representing lumbia, and any political subdivision or may result; prohibited, subject to the through any other means that either of instrumentality of any of them. provision, however, as respects said first said respondents owns, operates, or con (3) “Non-profit institution” means prohibition, that nothing therein shall trols a laboratory or establishment con any scientific, literary, educational, pub prohibit use of the word “jiffy” to desig taining substantial equipment and lic health, public welfare, charitable, or nate the period required to heat water apparatus for use in study and experi eleemosynary institution, or hospital or if in immediate and conspicuous con mentation by scientists or technicians similar institution, or any volunteer fire junction therewith respondents truth employed for such purposes or for the company (i) which is supported in whole fully state the time required to raise one conduct of research in connection with or in part through the use of funds de or more designated volumes of water of the application of electricity to water rived from taxation by the United States, stated temperature to a specified temp heating facilities, its territories or possessions, or by any erature level; and to the further pro 2* Jt3) Distributing or selling said device State or political subdivision thereof, or vision, as respects said third prohibition, «'"unless the word “caution” or “warning”, (ii) which is exempt from taxation under that the word “caution” or “warning”, together with adequate directions for section 101 (6) of the Internal Revenue whichever is used, may be accompanied safe use of the device, is indelibly im Code. by reference to adequate directions for pressed, imprinted, or affixed thereon, (4) “Public bodies” means educational safe use separately but securely at informing the user that unless the direc institutions and local public bodies. tached to the device and which inform tions for use are strictly followed dan “Educational Institutions” means (i) any the user that unless such directions are gerous electric shock may result: public educational institution, or (ii) any strictly followed dangerous electric Provided, however, That the word “cau private educational institution, no part shock may result. tion” or “warning”, whichever is used, of the net earnings of which shall inure may be accompanied by reference to to the benefit of any private shareholder (Sec. 6, 38 Stat. 722; 15 U. S. C. 46. Interpret adequate directions for safe use sepa or individual. “Local public bodies” in or apply sec. 5, 3P Stat. 719, as amended; 15 rately but securely attached to the de cludes state and local governments and U. S. C. 45) [Cease and desist order, Autonator non-profit corporations which officially Laboratories Co. et al., Docket 5638, Dec. 6, vice and which inform the user that 1949] unless such directions are strictly fol represent a local governing body and lowed dangerous electric shock may which will comply with the same terms This proceeding having been heard by result. and conditions in resale or rental as the Federal Trade Commission upon the It is further ordered, That the respond would a local public body. complaint of the Commission, the answer ents shall, within sixty (60) days after (5) “Veteran” shall include (i) a per of respondents, certain stipulations of service upon them of this order, file with son (or his family) who has served in the fact submitted for the record in lieu of the Commission a report in writing set military or naval forces of the United other evidence by counsel for the re ting forth in detail the manner and form States for any period of time on or after spondents and counsel supporting the in which they have complied with this September 16,1940, and prior to July 26, complaint together with a form of order order. 1947, and who has been discharged or re leased therefrom under conditions other to cease and desist which counsel jointly Issued: December 6, 1949. recommended to the Commission for than dishonorable, (ii) a person (or his By the Commission. family) serving in the active military adoption, and the tentative order to or naval forces of the United States who cease and desist issued subsequently by [seal] D. C. Daniel, has served therein on or after September the Commission in connection with which Secretary. 16, 1940, and prior to July 26, 1947, and respondents were afforded opportunity [F. R. Doc. 00-680; Filed, Jan. 24, 1950; (iii) the family of a person who served In to show cause why such order should not 8:49 a. m.] the military or naval forces of the United 7 394 0 RULES AND REGULATIONS States on or after September 16, 1940,
(b) With respect to learners hired F. R. 7941) that the Administrator pro It is the judgment of the Administrator prior to and on the payroll of an em posed to amend §§ 522.201 to 522.211 so that the effective administration of the ployer on January 15, 1950, the learning as to provide, among other things, higher Fair Labor Standards Act requires that period authorized in Column B of para subminimum learner rates in the in these amendments become effective si graph (a) of this section may be ex dustry. Interested persons were given multaneously with the effective date of tended by 160 hours, provided such ten days in which to submit data, views, the Fair Labor Standards Amendments learners are paid at a rate of not less or arguments pertaining to the proposed of 1949. Therefore, compliance with the than 70 cents per hour for the additional amendments. This period has now ex requirement of the Administrative Pro 160 hours of the learning period, and pired. No data, views, or arguments cedure Act that publication of rules be provided further that the number of have been received. made not less than 30 days prior to the such learners shall not be counted in de I find that it is necessary, in order to effective date thereof is not feasible. termining the number or proportion of prevent the curtailment of opportunities These amendments accordingly shall be learners provided in Column D of para for employment, that such proposed come effective on January 25, 1950, and graph (a) of this section. amendments be adopted. shall continue in full force and effect (c) No experienced worker shall be Now, therefore, pursuant to the au until July 25, 1950, unless modified, employed under the terms of a special thority vested in me by section 14 of the superseded or rescinded prior to such learner certificate, except as provided in Fair Labor Standards Act, as amended date. Column C of paragraph (a) of this sec (Sec. 14, 52 Stat. 1068, 29 U. S. C. 214; (Sec. 14, 52 Stat. 1068; 29 U. S. C. 214) tion. as amended 63 Stat. 910), and in accord (d) No learner shall be hired under a ance with § 522.12 of this part, §§ 522.201 Signed at Washington, D. C., this 20th special learner certificate if an experi-, to 522.211, are hereby amended as set day of January 1950. enced worker who is capable of equaling forth in the F ederal R egister of Decem W m . R. M cCom b, the performance of a worker of ordinary ber 31, 1949 (14 F. R. 7941). Administrator, Wage and Hour or minimum skill is available for employ 1. Rovoke last sentence of § 522.201. Division, United States De ment. 2. Amend § 522.204 (a) to read as partment of Labor. (e) A special learner certificate au follows: thorizing the employment of learners for [F. R. Doc. 50-685; Piled, Jan. 24, 1950; normal labor turnover may be issued for § 522.204 Subminimum rates. . (a) 8:48 a. m.] a period of one year. A special learner The subminimum rates which may be certificate authorizing the employment authorized in special certificates issued of learners by new or expanding plants in the Cigar Industry shall be not less shall be issued for a period not longer than 60 cents per hour in the occupa P art 522—E mployment of Learners than necessary to complete the training tions of cigar machine operating and GLOVE INDUSTRY of the total number of additional cigar packing; not less than 60 cents per learners. hour for the first 480 hours and 65 cents On January 18,1950, a notice was pub per hour for the second 480 hours in the lished in the F ederal R egister (15 F. R. It is the judgment of the Administra occupations of hand rolling and hand 297) that the Administrator proposed to tor that the effective administration of bunch making; not less than 60 cents per revise the ■ determination and order of the Fair Labor Standards Act requires hour for the first 320 hours and 65 cents February 8, 1940, prescribing terms and that these amendments become effective per hour for the second 320 hours in the conditions under which certificates may simultaneously with the effective date of occupation ofi making Italian stogies; be issued authorizing employment of the Fair Labor Standards Amendments and not less than 60 cents per hour in learners in the Glove Branch of the Ap of 1949. Therefore, compliance with the the occupations of hand stripping and parel Industry at wages below the min requirement of the Administrative Pro machine stripping. imum wage established by section 6 of cedure Act that publication of rules be the Act. Interested parties were given made not less than 30 days prior to the 3. Revoke § 522.205 (c). 5 days in which to file data, views or ar effective date thereof is not feasible. 4. Revoke § 522.211. guments pertaining thereto. This period These amendments accordingly shall be 5. Add new § 522.211 to read as has now expired, and all material re come effective on January 25, 1950, and follows: ceived has been given careful considera the regulations as amended and any cer § 522.211 Revocation and cancella tion. tificates which might be issued there tion. (a) The Administrator or his au The revision of the provisions of the under shall continue in force and effect thorized representative may cancel any determination and order was made nec until modified, superseded or rescinded. certificate for cause. Cancellation may essary by the Fair Labor Standards (Sec. 14, 52 Stat. 1068; 29 U. S. C. 214) be affected (1) as of the date of issu Amendments of 1949 raising the mini ance if it is found that the applicant set mum wage from 40 cents to 75 cents an Signed at Washington, D. C., this 20th forth any fact or facts in the application hour and constitutes an interim measure day of January 1950. which he knew or had reasonable cause to prevent curtailment of opportunities W m . R. M cComb, to believe to be false; (2) as of the date for employment. It provides terms and Administrator, Wage and Hour of violation if it is found that any of its conditions under which learners may be Division, United States De terms have been violated; and (3) pros employed in the glove industry for a partment of Labor. pectively if it is found that the condi period of 6 months following January tions of employment of the learner have 25,1950, during which period the Admin [P. R. Doc. 50-683; Filed, Jan. 24, 1950; 8:49 a. m.] changed or that the purposes for which istrator will hold a public hearing to the certificate was originally issued no determine the necessity for special longer obtain. learner regulations for the glove in \ (b) Except in cases of willfulness or dustry after that time. ' P art 522—E mployment of Learners those in which the public interest Accordingly, pursuant to the authority requires otherwise, before any contem vested in me by section 14 of the Fair CIGAR INDUSTRY plated action for cancellation or revoca Labor Standards Act, as amended (Sec. Pursuant to section 14 of the Fair tion of any special certificate for the 14, 52 Stat. 1068, as amended; 29 U. S. C. Labor Standards Act the Administrator employment of a learner will be consid and Sup., 214), I find that it is neces has heretofore promulgated regulations ered, facts or conduct which may war sary, in order to prevent curtailment of (§§ 522.201 to 522.211) setting forth terms rant such action will be called to the opportunities for employment, that the and conditions under which special cer revision of the determination and order tificates may be issued to plants in the attention of the employer and he shall Cigar Industry in the continental United be afforded an opportunity to achieve or governing employment of learners in the States authorizing employment of demonstrate compliance, or to show that Glove Branch of the Apparel Industry, learners at wages below the minimum the conditions of employment of the as published in the F ederal R egister on wage established in section 6 of the act. learner have not changed or that the January 18, 1950 (15 F. R. 297), be, and On December 31, 1949, a notice was purpose for which the * certificate was such revision hereby is, adopted, as published in the F ederal R egister (14 originally issued still exist. follows: Wednesday y January 25,1950 7 l FEDERAL REGISTER 401
Sec. be afforded an opportunity to achieve or ing plan or trust” for purposes of this 522.220 Terms of special certificates. demonstrate compliance. section. 522.221 Cancellation of certificates. In connection with the formulation of 522.222 Definitions. § 522.222 Definitions. In §§ 522.220 to 522.222, the term “learner” means: said regulations the Administrator ap •Authority : §§ 522.220 to 522.221 issued pointed an Advisory Committee composed under sec. 14, 52 Stat. 1068, as amended; (a) In the leather dress branch, a of representatives of the Council of Profit 29 U. S. C. and Sup. 214. person who has not been employed dur ing the preceding three years for more Sharing Industries, the Congress of In § 522.220 Terms of special certificates. than 480 hours in the aggregate in hand dustrial Organizations and the American When necessary in order to prevent the or machine stitching operations on Federation of Labor. The Advisory Com curtailment of opportunities for employ leather dress gloves. mittee met in Washington, D. C., on ment, special certificates permitting the (b) In the knit fabric branch, a per December 6, 1949 and January 18, 1950, employment of learners, at subminimum son who has not been employed during with the Administrator and members of rates may be issued under the conditions the preceding three years for more than his staff and advised and assisted in the set forth below to all plants in the Glove 480 hours in the aggregate in machine preparation of the regulations herein Branch of the Apparel Industry making stitching operations on leather dress or after set forth. application therefor representing that knit fabric gloves. In view of the fact that section 7 (d) experienced workers are not available to (c) In the work glove branch, a person (3) (b) of the Fair Labor Standards Act, the plant, unless experienced workers who has not been employed during the as amended, becomes effective oh Janu are found to be available. preceding three years for more than 480 ary 25, 1950, the Administrator deems it (a) Learners employed under the cer hours in the aggregate in machine to be in the public interest that the ap tificates shall not exceed 10 percent of stitching operations in any type of glove propriate regulations thereunder should the total nùmber of workers in the plant manufacture. become effective simultaneously on said engaged in hand and machine stitching (d) In the knit wool branch, a person date. Consequently, notice and public operations on leather dress gloves; and who has not beer! employed during the procedure pursuant to section 4 (a) of in machine stitching operations on knit preceding three years for more than 480 the Administrative Procedure Act, is fabric and work gloves; and in finger hours in the aggregate on finger knit found by the Administrator to be imprac knitting and finger clpsing operations on ting and finger closing operations; ticable. knit wool gloves, provided that as many Now, therefore, pursuant to the au as 10 learners may be authorized in any and, the term “Glove Branch of the Ap thority vested in the Administrator by certificate. parel Industry” includes leather dress section 7'(d) (3) (b) of the Fair Labor (b) No person shall be employed as a gloves, knit fabric gloves, work gloves, Standards Act, as amended, the regula learner under the certificate, longer than and knit wool gloves. tions set forth below are hereby adopted, 480 hours. It is the judgment of the Administra effective January 25, 1950. (c) Learners employed under the cer tor that the proper administration of Interested persons are invited to sub tificate shall be paid not less than 55 the Pair Labor Standards Act requires mit data, views or comments pertaining cents for the first 320 hours and 65 cents that the determination and order, as re to these regulations to the Administra for the last 160 hours of the learning vised, become effective simultaneously tor, Wage and Hour Division, United period. In plants where experienced with the effective date of the Fair Labor States Department of Labor, Washing operators are paid on a piece-work rate, Standards Amendments of 1949. There ton 25, D. C., within 15 days from the learners shall be paid at least the same fore, compliance with the requirement date of publication hereof in the F ederal piece-work rate and shall receive earn of the Administrative Procedure Act that R egister. If, upon the basis of any such ings paid on this rate if they earn in publication of rules be made not less data, views or comments súbmitted, the excess of the subminimum wage rates than 30 days prior to the effective date Administrator finds it necessary or de provided herein. thereof is not feasible. Accordingly, sirable to revise the regulations, appro (d) Only learners shall be employed the determination and order, as revised priate notice thereof will be published at a subminimum wage under the cer herein, shall become effective on Janu in the F ederal R egister. tificate and no learner shrill be employed ary 25, 1950. Sec. under the certificate unless hired when Signed at Washington, D. C., this 23d 549.1 Essential requirements for qualifica an experienced worker was not available. day of January, 1950. • tion. (e) No learners shall be employed at 549.2 Disqualifying provisions. a subminimum wage under the certifi W m, R. M cComb, 549.3 Distinction between plan and trust. cate until and unless the certificate is Administrator, 549.4 Petition for amendment of regula posted and kept posted in a conspicuous Wage and Hour Division. tions. place in the plant in which learners are [F. R. Doc. 50-741; Filed, Jan, 24, 1950; Authority: §§ 549.1 to 549.4 issued under employed. 9:20 a. m.] 52 Stat. 1060, as amended; 29 U. S. C. and Sup., 201 et seq. § 522.221 Cancellation of certificates. (a) The Administrator or his authorized § 549.1 Essential requirements for representative may cancel any certificate qualification. The term “bona fide for cause. Cancellation may be effected P art 549—D efining and D elimiting the profit-sharing plan or trust” as used in (1) as of the date of issuance if it is T erm “Bona F ide P rofit-S haring P lan section 7 (d) (3) (b) of the Fair Labor found that the applicant set forth any or T rust” 1 Standards Act, as amended, means a fact or facts in the application which he definite program or arrangement in writ knew or had reasonable cause to believe Section 7 (d) (3) (b) of the Fair Labor ing, communicated and made available to be false; (2) as of the date of viola Standards Act, as amended, effective to the employees, which meets the fol tion if it is found that any of its terms January 25,1950, provides that payments lowing standards: have been violated; and (3) prospec made pursuant to a bona fide profit- (a) It is established and maintained tively if it is found that the conditions of sharing plan or trust shall be excluded in good faith for the purpose of dis employment of the learner have changed from an employee’s regular rate of pay, tributing to the employees a share of or that the purposes for which the cer and further provides that the Adminis profits as additional remuneration over tificate was originally issued no longer trator of thé Wage and Hour Division and above the wages or salaries paid to obtain. shall issue regulations defining and de employees, which wages or salaries are (b) Except in cases of willfulness or limiting the term “bona fide profit-shar- not dependent upon or influenced by the those in which the public interest existence of such profit-sharing plan or requires otherwise, before any contem 1 The regulations in this part do not relate trust or the amount of the payments to or affect contributions irrevocably made made pursuant thereto; and plated action for cancellation or revoca •by an employer to a trustee or third person tion of any special certificate for the pursuant to a bona fide plan for providing (b) All contributions or allocations employment of a learner will be con old-age, retirement, life, accident, or health by the employer to the fund or trust to sidered, facts or conduct which may insurance or similar benefits for employees as be distributed to the employees are (1) warrant such action will be called to the provided in section 7 (d) (4) of the Fair Labor derived solely from profits of the em attention of the employer and he shall Standards Act, as amended. ployer’s business, enterprise, establish- \ 402 RULES AND REGULATIONS ment or plant as a whole, or an § 549.3 Distinction between plan and (a) of the Administrative Procedure Act established branch or division of the trust. As used in the regulations in this is found by the Administrator to be im business or enterprise which is recog part: practicable. nized as such for general business pur (a) “Profit-sharing plan" means any Now, therefore, pursuant to the au poses and for which profits are such program or arrangement as quali thority vested in the Administrator by separately and regularly calculated in fies hereunder which provides for the section 7 (d) (3) (c) of the Fair Labor accordance with accepted accounting distribution by the employer to his em Standards Act, as amended, the regula practice and (2) made periodically, but ployees of their respective shares of tions set forth below are hereby adopted, not more frequently than is customary profits; effective January 25, 1950. or consonant with accepted accounting (b) “Profit-sharing trust’’ means any Interested persons are invited to sub practice to make periodic determina such program or arrangement as quali mit data, views or comments pertaining tions of profits; and fies hereunder which provides for the to these regulations to the Administra (c) Eligibility to share in profits ex irrevocable deposit by the employer of tor, Wage and Hour * Division, United tends at least to all employees who are his employees’ distributive shares of States Department of Labor, Washing subject to the minimum wage and over profits with a trustee for deferred dis ton 25, D. C., within 15 days from the time provisions of the act, or to all such tribution to such employees of their date of publication hereof in the F ederal employees in an established part of the respective shares. R egister. If, upon the basis of any such employer’s business as described in par § 549.4 Petition for amendment of data, views or comments submitted, the agraph (b) of this section: Provided, regulations. Any person wishing a revi Administrator finds it necessary or de however, That such eligibility may be sion of any of the terms of the foregoing sirable to revise the regulations, appro determined by factors such as length of regulations may submit in writing to the priate notice thereof will be published service or minimum schedule of hours of Administrator a petition setting forth in the F ederal R egister. w work which are specified in the plan or the changes desired and the reasons for Sec. trust, or such classification of employees proposing them. If, upon inspection of 550.1 "Talent fees” as used in section 7 (d) as the employer may designate with the (3) (c) of the Fair Labor Standards approval of the Administrator upon a the petition, the Administrator believes Act, as amended. finding, after notice to interested persons that reasonable cause for amendment 550.2 Definitions. and an opportunity to present their of the regulations is set forth, the Ad 550.3 Petition for amendment of regula ministrator will either schedule a hear tions. views either orally or in writing, that it ing with due notice to interested parties, is in accord with the meaning and in Authority: §§ 550.1 to 550.3 issued under tent of the provisions of this section of or will make other provision for afford 52 Stat. 1060, as amended; 29 U. S. C. and ing interested parties an opportunity to Sup., 201 et seq. the act and the regulations in this part; present their views, either in support of and or in opposition to the proposed changes. § 550.1 "Talent fees” as used in sec (d) The shares of profits to be dis tion 7 (d) (3) ¿c) of the Fair Labor tributed to individual employees are Signed at Washington, D. C., this 23d Standards Act, as amended. The term determined in accordance with a formula day of January 1950. “talent fees” in section 7 (d), (3) (c) of or method of calculation specified in the W it. R. M cComb, the act shall mean extra payments made plan or trust, which formula or method Administrator, to performers, including announcers on of calculation may be based, among Wage and Hour Division. radio and television programs, where the other factors, on the straight-time horns payment is made: or total hours or straight-time earnings [P. R. Doc. 50-740; Piled, Jan. 24, 1950; (a) To an employee having regular or total earnings or base rate of pay of 9:28 a. m.] duties as a staff performer (including the employee, but the employee’s share announcers), as an extra payment for so determined, may not be diminished services as a performer on a particular because of any other remuneration commercial program or a particular received by him; and P art 550—D efining and D elimiting the series of commercial programs (includ (e) Provision is made for payment to T erm “T alent F ees” ing commercial spot announcements) or the individual employees of their respec Section 7 (d) (3) (c) of the Fair Labor for special services as a performer on a tive shares or profits either within a rea Standards Act, as amended, effective particular sustaining program or a par sonable period after the determination January 25, 1950, provides that talent ticular series of sustaining programs; of the amount of profits to be distributed fees paid to performers, including an (b) In pursuance of an applicable em or upon the occurrence of.appropriate nouncers, on radio and television pro ployment agreement or understanding contingencies specified in the plan or grams shall be excluded from computa or an applicable collective bargaining trust: Provided, however, That the right tion of the performer’s regular rate of agreement, in a specific amount agreed of an employee to receive his share is pay, and further provides that the Ad upon in advance of the performance of not made dependent upon his cohtinuing ministrator of the Wage and Hour Divi the services or special services for which In the employ of the employer after the sion shall issue regulations defining and the extra payment is made. period for which the determination of delimiting the term “talent fees’’ for § 550.2 Definitions. As used in the profits has been made. purposes of this section. regulations in this part: § 549.2 Disqualifying provisions. No In connection with the formulation of (a) The term “extra payment” shall plan or trust which contains any one of said regulations, the Administrator ap mean a payment, in a specific amount, the following provisions shall be deemed pointed an Advisory Committee com made in addition to the straight-time to be a bona-fide profit-sharing plan or posed of representatives of the American and overtime compensation which would trust within the meaning of section Federation of Radio Artists and the Na be due the performer under the agree 7 (d) (3) (b) of the Fair Labor Standards tional Association of Broadcasters. The ment applicable to his employment and Act, as amended: Advisory Committee met in Washington, under the act if the time spent in per (a) If an individual employee’s share D. C., on November 22, 1949 and Decem forming the services or special services of profits is determined by any formula or ber 21, 1949 with members of the Ad referred to in paragraph (a) of § 550.1 method of calculation which is based to a ministrator’s staff and advised and had been devoted exclusively to duties substantial extent on the quality or quan assisted in the preparation of the regu as a staff performer; but shall not in tity of work performed by any individual lations hereinafter set forth. clude any payment any part of which is employee or group or class of employees; In view of the fact that section 7 (d) credited or offset against any remunera or (3) (c) of the Fair Labor Standards Act, tion otherwise payable to the performer (b) If the amount to be paid period as amended, becomes effective on Janu under any contract or statutory ically by the employer into the fund to ary 25, 1959, the Administrator deems provision; be distributed to his employees is a fixed It to be in the public interest that the (b) The term “performer” shall mean sum; or appropriate regulations thereunder a person who performs a distinctive, per (c) If periodic payments of minimum should become effective simultaneously sonalized service as a part of an actual amounts to the employees are guaran on said date. Consequently, notice and broadcast or telecast including an actor, teed by the employer. public procedure pursuant to section 4 singer, dancer, musician, comedian, or Wednesday, January 25,1950 FEDERAL REGISTER 403 any person who entertains, affords unless appeal is taken therefrom within ing subsequent to June 30, 1947, shall be a reasonable time. The decision ap computed, accounted for, and paid sepa amusement to, or occupies the interest of rately on such domestic trade, and shall be a radio or television audience by acting, pealed from shall be reviewed by the im computed, accounted for and paid sepa singing, dancing, reading, narrating, mediate superior of the officer by whom rately on such foreign trade. All voyages performing feats of skill, or announcing, the decision was rendered; that is, in the which are subject to the provisions of this or describing or relating facts, events following order: Supervisor, Regional Addendum shall be treated for accounting and other matters of interest, and who forester, Chief of the Forest Service, purposes only as if this Addendum consti actively participates in such capacity in Secretary of Agriculture. Appeals from tuted a separate charter between the parties. the Chief of the Forest Service to the It is specifically understood and agreed that the actual presentation of a radio or tele the provisions of this clause do not require vision program. It shall not include such Secretary of Agriculture shall, upon the the separation of accountings for foreign persons as script writers, stand-ins, or written request of the appellant, be re trade voyages subsequent to June 30, 1947, directors who are neither seen nor heard ferred to the National Forest Advisory from accountings due for such voyages prior by the radio or television audience; nor Board of Appeals. The Board shall con to that date. shall it include persons who participate sider appeals referred to it on the merits II. Basic charter hire. The following pro in the broadcast or telecast purely as and furnish the Secretary of Agriculture visions shall be applicable to the vessels listed technicians such as engineers, electri with its advice and recommendations. on the attached schedule marked Exhibit B, which is made a part hereof by reference, and cians and stage hands; (30 Stat. 35, as amended, sec. 1, 33 Stat. 628; supplements and amendments thereto: (c) The term “special services” shall 16 TJ. S. C. 551, 472) (a) The basic charter rate stipulated In mean services beyond the scope of a per Clause C (1), Part I, shall be computed on former’s regular or ordinary duties as Done at Washington, D. C., this 17th day of January 1950. Witness my hand the basis of 8%% per annum of either the a staff performer under the agreement unadjusted statutory sales price or the floor applicable to the employment. and the seal of the Department of price of each of the vessels, whichever is Agriculture. § 550.3 Petition for amendment of higher; and the footnote pertaining to the [seal] Charles F. B rannan, charter rate shall be amended to read as regulations. Any person wishing a revi follows: sion of any of the terms of the foregoing Secretary of Agriculture. regulations may submit in writing to the [F. R. Doc. 50-700; Piled, Jan. 24, 1950; 18y2 % per annum of either the unadjusted 8:49 a. m.] statutory sales price or the floor price of the Administrator a petition setting forth vessel, whichever is higher, which is the the changes desired and the reasons for minimum basic monthly charter hire, subject proposing them. If, upon inspection of to upward adjustment to a maximum basic the petition, the Administrator believes TITLE 46— SHIPPING monthly charter hire of 15% per annum of that reasonable cause for amendment of Chapter II— United States Maritime either the unadjusted statutory sales price the regulations is set forth, the Admin Commission or the floor price of the vessel, whichever is istrator will either schedule a hearing higher, as provided in Clause 12 (b), Part II. with due notice to interested parties, or Subchapter F— Merchant Ship Sales Act of 1946 (b) Clause 12, Part II, shall be deleted and will make other provisions for affording [General Order 60, Amdt. 3 to Supp. 5] the following paragraphs substituted in lieu interested parties an opportunity to pre thereof for the purpose of determining basic P art 299—R ules and R egulations, F orms charter hire: sent their views, either in support of or and Citizensh ip R equirements in opposition to the proposed change. Clause 12. Basic charter hire, (a) The Signed at Washington, D. C., this 23d forms; domestic trade addendum Charterer shall pay to the Owner basic char day of January 1950. Section 299.82 Uniform bareboat char ter hire at the monthly rate provided for in ter of a war-built dry-cargo vessel under Part I hereof, (hereinafter referred to as the W m. R. M cComb, (“minimum basic charter rate”) from the day Administrator, the Merchant Ship Sales Act of 1946, and hour of delivery of the Vessels until and Wage and Hour Division. “SHIPS ALE SDEMISE 303”, is amended including the day and hour of redelivery to as follows; the Owner pursuant to the terms of this [P. R. Doc. 50-739; Filed, Jan. 24, 1950; The form of Domestic Trade Adden Agreement; or if any Vessel,shall be lost, hire 9:28 a. m.] dum, as authorized by the Commission shall continue until the time of her loss, if known, or if the time of loss be uncertain, on July 29, 1948, and published in the then up to and including the time last heard F ederal R egister issue of August 14,1948 from. Payment of such minimum basic riTLE 36— PARKS, FORESTS, AND (13 F. R. 4710) is hereby superseded and charter hire shall be made to the Owner at MEMORIALS revised to read as follows: Washington, D. C., on delivery of the Vessel SHIPSALESDEMISE 303 for the remainder of the calendar month in Chapter II— Forest Service, Depart (Domestic Trade Addendum) which delivery is made, and thereafter ment of Agriculture (Revised) monthly in advance on the first day of each Contract No. MCc______month. P art 211—Administration Addendum N o.______(b) It is specifically agreed that the min imum basic monthly charter hire prescribed APPEALS FROM ADMINISTRATIVE ACTION 1 Addendum to Bareboat Charter Agreement in Part I of this Agreement (8 y2 % per annum (herein called the “Agreement”) dated as of of either the unadjusted statutory sales By virtue of the authority vested in the ______between the United States price or the floor price of the Vessels covered Secretary of Agriculture under the pro of America, acting by and through the United by this Agreement, whichever is higher) shall visions of the act of March 3, 1891, as States Maritime Commission (hereinafter be deemed to be an unconditional payment amended (16 U. S. C. 471), and the act called the “Owner”) a n d ______to the Owner, and th at the balance of 6 y2% of June 4, 1897, as amended (16 U. S. C. (hereinafter called the “Charterer”). shall be payable from earnings before any Witnesseth participation in such earnings by the 551), I; Charles F. Brannan, Secretary Whereas, separate accountings for foreign of Agriculture, do hereby amend the Charterer. If, therefore, at the end of any trade and domestic trade (coastwise or inter calendar year, or other accounting period, first paragraph of § 211:2, Part 211, coastal) have been prescribed by legislation the total cumulative net voyage profits of all Chapter II, Title 36, Code of Federal (Public Law 127, 80th Congress) with respect of such vessels before basic hire are in excess Regulations as follows; to all voyages commencing subsequent to of such minimum basic hire, the basic hire The first paragraph of § 211.2 is June 30, 1947, and shall be increased by the amount by which amended to read as follows: Whereas, the parties have agreed upon new such net voyage profits beiore basic hire terms and conditions applicable to vessels exceed the minimum basic hire, provided th at § 211.2 Appeals from administrative chartered hereunder for operation on Char such increase shall not operate to increase action. An appeal may be taken from terer’s certificated coastwise and intercoastal the basic hire to in excess of 15% per annum any administrative action or decision by routes, effective as of July 1, 1947, and of either the unadjusted statutory sales price, filing with the officer who rendered the Whereas, the parties desire to amend this or the floor price of the vessels, whichever, Agreement accordingly. is higher. decision a written request for reconsid Now, therefore, effective as of July 1, 1947, eration thereof or notice of appeal. De this Agreement is hereby amended as follows: III. Additional charter hire. For the pur cisions of forest officers shall be final I. Separate accountings. Where the Char pose of determining additional charter hire terer is engaged both in the foreign trade on the vessels listed on the attached schedule 1 See P. R. Doc. 50-699 under Department and the domestic trade (coastwise or inter marked Exhibit B, which is made a part of Agriculture, Forest Service in Notices sec coastal) additional charter hire pursuant to hereof by reference, and supplements and tion. Clause 13, Part II, for all voyages commenc- amendments thereto, Clause 13, Part II, shall 404 RULES AND REGULATIONS
be deleted and the following paragraphs ment, shall be .applicable to the remaining behalf of said corporation, was then the duly substituted in lieu thereof: portions of such voyages. q u alified ______of said corpora V. Net voyage profit. With respect to the tion; th at said officer affixed his manual Clause 13. Additional charter hire. If a t vessels listed on Schedule B, as supplemented signature to said Agreement in his official the end of the calendar year 1947, or any and modified, an additional paragraph shall capacity as said officer for and on behalf of subsequent calendar year or at the termina be inserted following the first paragraph of said corporation by authority and direction tion of this Agreement, as amended, the sub-paragrah (a), Clause 23, Fart II, entitled: of its governing body duly made and taken; cumulative net voyage profit (after the pay “Net Voyage Profit," reading follows: th at said Agreement is within the scope of ment of the maximum basic charter hire the corporate and lawful powers of this provided herein and payment of the char Upon application of the Charterer sup corporation. terer’s fair and reasonable overhead expenses ported by adequate data based on past ex applicable .to operation of the Vessels) shall perience, the Owner will permit the inclusion [CORPORATE SEAL] ______exceed 10 per centum per annum on the in vessel operating expenses of such charges Secretary Charterer’s capital necessarily employed in as the Owner determines to be fair and rea (Sec. 12, 60 Stat. 50, sec. 2, 61 Stat. 191, the business of the Vessels (all as herein sonable to provide reserves for vessel repair Pub. Law 147, 81st Cong.; 50 U. S. C. App. after defined) the Charterer shall pay over expenses and/or P. and I. insurance deducti and Sup. 1745, 1738) to the Owner at Washington, D. C., within ble average losses on all voyages terminating 30 days after the end of such year or other after December 31, 1946, provided that at the By order of the United States Maritime period, as additional charter hire for such time of final accounting hereunder each of year or other period, an amount equal to such reserves shall be adjusted to actual by Commission. one-half of such cumulative net voyage distributing the balances therein to net voy [seal] A. J. W illiams, profit in excess of 10 per centum per annum age profit for the accounting periods involved on such capital (but such cumulative net in the same ratio as the reserve charges to Secretary. profit so accounted for shall not be included vessel operating expenses in each such period J anuary 12, 1950. In any calculation of- cumulative net profit bears to the total thereof for the. entire [F. R. Doc. 50-670; Filed, Jan. 24, 1950; _in any subsequent year or period). period. 8:49 a. m.] The Charterer agrees to make preliminary VI. Bills of. lading or voyage charters. Not — ------payments to the Owner on account of such withstanding the provisions of Clause 17, additional charter hire at such times and in Part II, of the Agreement, Charterers engaged such manner and amounts as may be required TITLE 47— TELECOMMUNI by the Owner: Provided, however, That such in coastwise or intercoastal trades will be permitted to use the standard form of bill of CATION payment of additional charter hire shall be lading set forth in the tariffs published by deemed to be preliminary and subject to the Charterer and filed with the Interstate adjustment either at the time of the rendi Commerce Commission. Chapter I— Federal Communications tion of preliminary statements or upon the VII. Period of vessel’s use. As to each ves Commission completion of each final audit by the Owner, sel listed on the attached schedule marked at which times such payments shall be made Exhibit B, as supplemented and modified, a P art 3—R adiobroadcast S ervices to the Owner as such preliminary statements maximum period of about twenty-four or final audit may show to be due, or such, FM BROADCAST STATIONS overpayments refunded to the Charterer as months, it being expressly agreed that no may be required. voyage shall be commenced after June 30, In the matter of amendment of 1949. Standards of Good Engineering Practice IV. Mixed voyages—(a) Accounting. In VIII. Definition. For the purposes of this Instances where single voyages encompass Addendum, the term “domestic trade (coast concerning PM broadcast stations to re both foreign trade and domestic trade, as wise and intercoastal) ” as used in Public Law vise lists of approved equipment in sec hereinafter defined, it is agreed that, for the 127, 80th Congress, is deemed to include only tions 16,17, and 18. purposes of this Addendum, the capital nec trade between Continental United States At a session of the Federal Communi essarily employed and net voyage profit ports and to exclude domestic offshore trades. cations Commission held at its offices in applicable to each such trade shall be allo IX. That, except as herein specifically mod Washington, D. C., on the 18th day of cated separately on such basis as the Owner ified, all the terms and conditions of the January 1950. may determine to be fair and reasonable, Agreement, as heretofore amended, shall re provided that, for the purposes of this allo main in full force and effect. Whereas, sections 16,17, and 18 of the cation, (1) vessel operating revenue shall be X. Special provisions. Standards of Gqod Engineering Practice allocated to the respective trades in which In witness whereof, the Owner has executed concerning PM broadcast stations pro earned on an actual basis, (2) port expense, this Addendum in quadruplicate th e _____ vide that lists of approved equipment cargo expense, brokerage expense, and other day o f ------194__ and the Charterer will be issued from time to time for voyage expense shall be Allocated to the has executed this Addendum th e ____ day incorporation in these Standards, respective trades in which incurred on an o f ...... 194... actual basis wherever practicable, and (3) Whereas, the Commission has ap vessel expense and such voyage expense as By: _____------proved certain equipment in accordance is not susceptible to direct allocation shall Execution for Charterer: with sections 13, 14, and 15 of these be allocated on the basis of the relation that Standards, and the revenue earned in each trade, separately, Attest: Whereas, the Commission has been ad bears to the total revenue earned in both vised by certain manufacturers that they trades. For the purposes qf this paragraph, or if not incorporated the references to revenues and expenses shall do not intend to proceed with the manu be deemed to be as described in the instruc In the presence of: facture of equipment heretofore pro tions embodied in the form of "General posed and given tentative approval, and Financial Statement” prescribed by the Witness Whereas, the Commission has found Commission (Budget Bureau approval Num that it will be in the public interest to ber 62—R—10-42). United States of America, By: United States Maritime amend the Standards of Good Engineer (b) Hire. In instances where single voy Commission, ing Practice concerning PM broadcast ages encompass both foreign trade and B y :------______stations so as to revise these lists in ac domestic trade, as hereinafter defined, it is For the Commission agreed that, for the purposes of this Adden cordance with changes and additions dum, the provisions of Clause 12 (Basic Hire) Execution for Owner: that have been made since last amended, and Clause 13 (Additional Hire), as amended Approved as to form: and by this Addendum, shall be applicable only to B y :------Whereas, these amendments do not the coastwise and intercoastal portions of Assistant General Counsel preclude the approval of additional such voyages as hereinafter defined which I , ------certify that I equipment in accordance with these portions shall be determined on the basis of am the duly chosen, qualified, and acting Standards, and the ratio of the total revenues earned from Secretary o f ______a party to the coastwise and intercoastal passengers this Agreement, and, as such, I am the cus Whereas, the amendments are issued and cargo to the total revenue of the voyage, todian of its official records and the minute under the authority of sections 303 (e) and the original provisions of Clauses 12 and books of its governing body; th a t ______and 303 (r) of the Communications Act 13, as contained in the basic charter agree------who signed this Agreement on of 1934, as amended, and Wednesday, January 25,1950 FEDERAL REGISTER 405
Whereas, in view of the foregoing, the 16. Approved T ransmitters— Continued 16. Approved T ransmitters— Continued Commission is of the opinion that it is unnecessary that the procedure for pro Manufacturer’s name Type No. Rated Manufacturer’s name Type No. Bated posed rule making prescribed in section power power 4 of the Administrative Procedure Act Gates Radio Co., Quincy, BF-250A-_ 250 watts. Western Electric Co., Inc., 504 B-2...... 3 kw. be followed, and that for the same rea 111. New York, N. Y. sons the amendments may become ef Do...... BF-1A...... 1 kw. Do...... 506 B-2...... 10 kw. Do...... BF-3A...... 3 kw. Westinghouse Electric & MO/MP.... Exciter. fective immediately, Do...... BF-3B 3 kw. Manufacturing Co., Balti It is therefore ordered, That sections Do BF-30 3 kw. more, Md. 16, 17, and 18 of the Standards of Good Do...... BF-10A...... 10 kw. Do FM-1...... 1 kw. General Electric Co., Sche- BT-l-A___ 250 watts. Do FM-3...... 3 kw. Engineering Practice concerning FM nectady, N. Y. Do FM-10...... 10 kw. broadcast stations be and are hereby Do BT-1-B Do FM-50...... 50 kw. Do...... BT-2-A...... 1 kw. amended to read as set forth below. Do...... BT-2-B Do...... BT-3-A 3 kw. 17. Approved F requency. M onitors (Sec. 303 (r), 50 Stat. 191; 47 U. S. C. 303 (r). Do BT-3-R 3 kw. Applies sec. 303 (e), 48 Stat. 1082; 47 U. S. C. Do BT-4-A 10 kw. 303 (e)) Do...... BT-4-B___ 10 kw. Manufacturer’s name Type No. Harvey Radio Laborato- FM-500...... 250 watts. Released: January 18, 1950. ries, Inc., Cambridge, Mass. Doolittle Radio, Inc., Chicago, 111...... FD-11. F ederal Communications Radio Corporation of MI-7016...... Exciter. .General Electric Co., Schenectady, N. Y.. BM-l-A. America, New York, General Radio Co., Cambridge, Mass...... 1170-A. Commission, N. Y. Hewlett-Packard Co., Palo Alto, Calif___ 335B. [seal] T. J. S lowie, Do...... BTF-250A— 250 watts. Radio Engineering Laboratories, Long Is 600R. Secretary. Do...... BTF-1C._ 1 kw. land City, N. Y. Do...... BTF-3B-_ 3 kw. Western Electric Co., Inc., New York, 5A. 16. Approved T ransmitters Do...... BTF-5A__ 5 kw. N. Y. Do...... BTF-10B... ' 10 kw. Do...... BTF-50A... 50 kw. Rated Radio Engineering Labo- 549A-DL__ 250 watts. 18. Approved M odulation M onitors Manufacturer’s name Type No. power ratories, Long Island City, City, N. Y. Doolittle Radio, Inc., Chicago, 111...... FD-11. Do...... 618B-DL__ 1 kw. General Electric Co., Schenectady, N. Y .. BM-l-A. 731 A_____ 250 watts. Do...... 618D-DL__ 1 kw. General Radio Co., Cambridge, Mass...... 1170-A. Rapids, Iowa. Do 519-DL...... 3 kw. Hewlett-Packard Co., Palo Alto, Calif..... 335B. Do...... 732A...... 1 kw. Do...... ■...... 520-DL...... 10 kw. Radio Engineering Laboratories, Long Is- 600R. Do ______733A...... 3 kw. Raytheon Manufacturing RF-250...... 250 watts. ' land City, N. Y. Do ___ 737A...... 5 kw. Co., Waltham, Mass. Western Electric Co., Inc., New York, 5A. Do...... 734A...... 10 kw. Do...... RF-1000__ 1 kw. N. Y. Federal Telephone & Radio 101A___ 1 kw. Do...... RF-3...... 3 kw. Corp., Newark, N. J. Do...... • RF-10...... 10 kw. Do 192 A...... 3 kw. Western Electric Co.. Inc., 503 B-l...... 1 kw. [F. R. Doc. 50-688; Filed, Jan. 24, 1950; Do 192AZ...... 3 kw. New York, N. Y. Do...... 193 A...... 10 kw. Do...... 503 B-2...... 1 kw. 8:52 a. m.]
PROPOSED RULE MAKING
DEPARTMENT OF THE TREASURY NW., Washington, D. C., at 10:00 a. m., reau of Safety Regulation, notice is February 20, 1950: Provided, That such hereby given that the Bureau has under Bureau of Narcotics person furnish written notice of his de consideration a revision of Part 4b as sire to be heard, to the Commissioner hereinafter set forth. [21 CFR, Ch. Ill of Narcotics, Washington 25, D. C., not Interested persons may participate in Addiction-F orming or Addiction-S us later than 20 days from the publication the making of the proposed rule by sub taining Liability of D rug Nu-2206 of this notice in the F ederal R egister. mitting such written data, views, or ar If no written notice of desire to be heard guments as they may desire. Commu- NOTICE OF PROPOSED RULE MAKING shall be received within 20 days from the mitting such written data, views, or Notice is hereby given, pursuant to the date of publication of this notice in the arguments as they may desire. Commu provisions of section 1 of the act of F ederal R egister, no hearing shall be nications should be submitted to the March 8, 1946 (60 Stat. 38; 26 U. S. C. held, but the Commissioner of Narcotics Civil Aeronautics Board, attention 3228), section 4 of the Administrative shall proceed to make a recommendation Bureau of Safety Regulation, Washing Procedure Act (60 Stat. 238; 5 U. S. C. to the Secretary of the Treasury for a ton 25, D. C. All communications re 1003), and by virtue of authority vested finding under section 1 of the act of ceived within 30 days from the date of in me by the Secretary of the Treasury March 8, 1946. this publication will be considered by (21 CFR 205.1), that a determination (60 Stat. 38; U. S. C. 3228) the Board before taking further action is proposed to be made that the new on the proposed rule. drug Nu-2206 (3-hydroxy-N-methylmor- [SEAL] H. J. ANSLINGER, The proposed revision of Part 4b phinan) has an addiction-forming or Commissioner of Narcotics. which is attached hereto is basically an addiction-sustaining liability similar to [F. R. Doc. 50-689; Filed, Jan. 24, 1950; editorial revision of the part in line with morphine and is an opiate. 8:50 a. m.] current F ederal R egister requirements Consideration will be given to any writ and the new regulation format recently ten data, views, or arguments, pertaining established for the Civil Air Regulations. to the addiction-forming or addiction- CIVIL AERONAUTICS BOARD There has been some rearrangement of sustaining liability of Nu-2206, which are material, some clarification of language, received by the Commissioner of Narcot [ 14 CFR, Part 4b ] and a few substantive modifications ics prior to February 20, 1950. Any per Airplane W orthiness, T ransport which have been fully discussed with the son desiring to be heard on the addiction Categories industry and with which, we believe, forming or addiction-sustaining liability there is no disagreement. It is believed of Nu-2206 will be accorded the oppor NOTICE OF PROPOSED RULE MAKING that the revision will aid the industry in tunity at a hearing in the office of the Pursuant to authority delegated by complying with current transport cate Commissioner of Narcotics, 1300 E Street the Civil Aeronautics Board to the Bu gory requirements and will be useful in No. 16----- 3 406 PROPOSED RULE MAKING
considering any changes in airworthiness There is also attached an explanatory which should be explored fully before regulations to be proposed in the annual statement setting forth some of the de any definite change is proposed. plan for reviewing this part of the tails of the changes from current Part 4b regulations. - in the proposed revision. SUBPART A—GENERAL In order to permit the revision to sup This revision is proposed under the au Applicability plant fully the current part and thus thority of Title VI of the Civil Aeronau § 4b.O General. This part establishes save the industry and the government tics Act of 1938, as amended. standards with which compliance shall from the necessity of having available (Secs. 205 (a), 601-610, 52 Stat. 984, 1007, be demonstrated for the issuance of a two parts containing substantially iden 1012; 49 U. S. C. 425 (a), 551-560) tical regulations, we have changed the type certificate for transport category applicability clause of the part from Dated December 20,1949, at Washing airplanes. This part, until superseded ton, D. C. or rescinded, shall apply to all transport that of the previous part. We do not category airplanes for which application thereby intend to depart from the in By the Bureau of Safety Regulation. dustry-sponsored principle of future is made for type certification in the applicability only for airworthiness re [seal] J ohn M. Chamberlain, transport category. All applications for quirements. Thus, the revised part Director. amendment or modification of currently would apply to applications for new type valid type designs of transport category certificates received after its effective Explanatory statement. This state aircraft certificated in whole or in part date, which is proposed to be ninety days ment will explain briefly the more im under the provisions of Part 4b, as here after the date of adoption to permit suffi portant changes made in the proposed tofore amended, received after the ef cient time for printing and distribution revision of Part 4b. There is included fective date of this part shall be subject of the part, and to amendments or mod a new provision (§ 4b.l03) which will to those provisions contained herein ifications of existing type designs in so require a manufacturer to consider the which are appropriate to such amend far as such amendments or modifica effect of span wise weight distribution on ment or modification. No provision con tions are covered by the provisions of the the controllability of the aircraft. This tained herein shall otherwise affect cur part. It is provided that nothing in the change is considered appropriate in view rently valid type designs of transport part shall otherwise affect current type of the fact that spanwise weight distri category aircraft or aircraft manufac designs or certificates, and that amend bution is more critical in the larger type tured under the transport category ments to the part shall, unless otherwise of transport category airplane. unless it is specifically required by such In Subpart C there has been included provision. specifically provided, be applicable only a provision permitting proof of strength to applications for type certificates re Definitions ceived more than 60 days after the adop by means of dynamic tests in addition to tion of the amendment. Thus an the currently provided static test § 4b.1 Definitions. Unless otherwise amendment of the part would not, unless (§ 4b. 201). A new requirement designed noted, terms used in this part of the specifically so stated therein, affect the to assure the proper mating of propeller Regulations are defined as follows: then currently valid type designs or cer and powerplant has been added to Sub (a) Administration—(1) Administra tificates. In view of the fact that the part E (see § 4b.402) and the fuel tank tor. The Administrator is the Adminis substantive changes of this revision are strainer requirements have been revised trator of Civil Aeronautics. few and rioncontroversial in nature, the to require a somewhat, finer mesh screen (2) Applicant. An applicant is a per basic principle for implementation of in accordance with the current practice son or persons applying for approval of airworthiness parts previously adhered under this provision.- In addition, a an airplane or any part thereof. to is, in our opinion, not departed from change has been made in the maximum (3) Approved. Approved, when used by the proposed revision. altitude for which an engine-driven alone or as modifying terms such as It will also be noted that the proce pump will be considered adequate; the means, deVices, specifications, etc., shall dural provisions for changes in type de change is from 10,000 feet to 6,000 feet mean approved by the Administrator. signs have been modified to describe (see § 4b.430 (h)). The de-icer require (b) General design—(1) Standard at current practice more adequately. Thus, ment of Subpart P has been changed to mosphere. The standard atmosphere is specific authority is provided for man require two Independent sources of power an atmosphere defined as follows: datory changes in type design (e. g. CAA and a positive means for deflation when (1) The air is a dry perfect gas, airworthiness directives) only in those air pneumatic boot-type de-icers are (ii) The temperature at sea level is instances where service experience indi used. In Subpart G additional provi 59° F., cates that a definite hazard exists. In sions have been inserted requiring entry (iii) The pressure at sea level is 29.92 other situations changes may be recom in the Airplane Flight Manual of two inches Hg, mended but there is no authority given new speed limitations, the landing gear (iv) The temperature gradient from operating speed and the landing gear sea level to the altitude at which the to exact compliance. extended speed. temperature equals —67° F. is —0.003566° We have also tried to include in the Major editorial revisions have been F./ft. and zero thereabove, revision any requirements which the Ad made of all subparts in order to clarify (v) The density p0 at sea level under ministrator has established as manda current requirements. Provisions requir the above conditions is 0.002378 pounds tory for aircraft to be certificated in the ing compressibility to be taken into ac sec.Vft.4 transport category. We have previously count, presently under the definition of (2) Maximum anticipated air temper- expressed our intention that the Civil Air the descent dive speed, have now been ture. The maximum anticipated air Regulations contain all airworthiness placed in § 4b.210, and the strength re temperature is a temperature specified requirements which are in the nature of quirements for pressure cabin loads pres for the purpose of compliance with the standards for type certification. We ently contained in Subpart D have been powerplant cooling standards. (See wish to reaffirm our intention in this re placed in Subpart C (see § 4b.216 (c)). § 4b.451 (b).) gard without in any way implying any (3) Airplane configuration. Airplane It should be noted that the provisions configuration is a term referring to the disapproval of any past action of the affecting center of gravity limitations do position of the various elements affect Administrator which, in many instances, not vary in substance from the current ing the aerodynamic characteristics of was effected with our concurrence to pro Part 4b. While it has been called to our the airplane (e. g. wing flaps, landing vide for items not covered in the regu attention that varying interpretations gear). lations whose importance did not become have been made of these provisions, it (4) Aerodynamic coefficients. The apparent until after the part was appears to us that there are controversial aerodynamic coefficients as used herein adopted. substantive considerations involved are nondimensional coefficients for forces Wednesday, January 25,1950 FEDERAL REGISTER 407 and moments. They correspond with speed indicator as installed in the air (7) Checked pitching maneuver: A those adopted by the U. S. National Ad-, plane, without correction for air-speed checked pitching maneuver is one in visory Committee for Aeronautics. indicator system errors. (See §§ 4b.612 which the pitching control is suddenly (5) Critical engine(s). The critical (a) and 4b.710.) displaced in one direction and then sud engine is that engines (s) the failure of (5) VA: The design maneuvering denly moved in the opposite direction, which gives the most adverse effect on speed. (See § 4b.210 (b) (2).) the deflections and timing being such as the airplane flight characteristics rela (6) VB: The design speed for maxi to avoid exceeding the limit maneuvering tive to the case under consideration. mum gust intensity. (See '§ 4b.210 (b) load factor. (6) C ritical-engine-failure speed. (3).) (8) Design wing area. The design Th6 critical-engine-failure speed is the (7) Vc: The design cruising speed. wing area is the area enclosed by the airplane speed used in the determination (See § 4b.210 (b) (4).) wing outline (including wing flaps in the of the take-off at which the critical (8) VD: The design diving speed. retracted position and ailerons, but ex engine is assumed to fail. (See § 4b.ll4.) (See § 4b.210 (b) (5).) cluding fillets or fairings) on a surface (c) Weights—(1) Maximum weight. (9) VDF: The demonstrated flight containing the wing chords. The outline The maximum weight of the airplane is diving speed. (See § 4b.l90.) is assumed to be extended through the that maximum at which compliance (10) VF: The design flap speed for nacelles and fuselage to the plane of with the requirements of this part of the flight loading conditions with wing flaps symmetry in any reasonable manner. Civil Air Regulations is demonstrated. in the landing position. (See § 4b.210 (9) Balancing tail load. A balancing (See § 4b. 101 (a).) (b) (D.) tail load is that load necessary to place (2) Minimum weight. The minimum (11) VFE: The wing flap extended the airplane in equilibrium with zero weight of the airplane is that minimum speed is a maximum speed with wing pitch acceleration. at which compliance with the require flaps in a prescribed extended position. (10) Fitting. A fitting is a part or ments of this part of the Civil Air Reg (See § 4b.714.) terminal used to join one structure ulations is demonstrated. (See § 4b.101 (12) VLE: The landing gear extended member to another. (See § 4b.307 (d).) (c).) speed is the maximum speed at which (f) Power installation1—(1) Brake (3) Empty weight. The empty weight the airplane can be flown safely with the horsepower. Brake horsepower is the of the airplane is that weight which is landing gear extended. (See § 4b.716.) power delivered at the propeller shaft of used in the determination of the oper (13) VL0: The landing gear operating the engine. ating weights, being readily reproducible, speed is a maximum speed at which the (2) Take-off power. Take-off power and including such items as the airplane landing gear can be raised or lowered is the brake horsepower developed under structure, powerplant installations, un- safely. (See § 4b.715.) standard sea level conditions, under the drainable fuel and oil, normal operating (14) VMC: The minimum control maximum conditions of crankshaft rota equipment, etc. (See § 4b.l04.) speed with any one engine inoperative. tional speed and engine manifold pres (4) Design maximum weight. The (See § 4b.l33.) sure approved for use in the normal design maximum weight is the maximum (15) VNE: The never-exceed speed. take-off, and limited in use to a maxi weight of the airplane used in structural (See § 4b.711.) mum continuous period as indicated in design for flight load conditions. (See (16) VN0: The normal operating limit the approved engine specification. § 4b.210.) speed. (3) Maximum continuous power. (5) Design minimum weight. The de (17) Vs0: The stalling speed or the Maximum continuous power is the brake sign minimum weight is the minimum horsepower developed in standard at weight of the airplane at which com minimum steady flight speed with wing flaps in the landing position. (See mosphere at a specified altitude under pliance is shown with the structural the maximum conditions of crankshaft loading conditions. (See § 4b.210.) §§ 4b. 112 (a) and 4b.l60.) (18) ySl: The stalling speed or the rotational speed and engine manifold (6) Design take-off v>eight. The de pressure approved for use during periods sign take-off weight is the maximum minimum steady flight speed obtained in a specified configuration. (See § 4b.ll2 of unrestricted duration. airplane weight used in structural design (4) Manifold pressure. Manifold for taxying conditions, and for landing (b).) (19) Vtl The critical-engine-failure pressure is the absolute pressure meas conditions at a reduced velocity of ured at the appropriate point in the in descent. (See § 4b.210.) speed. (See § 4b.ll4.) duction system, usually in inches of (7) Design landing weight. The de (20) V2: The take-off safety speed. mercury. sign landing weight is the maximum air (See § 4b.ll4 (b).) (5) Critical altitude. The critical plane weight used in structural design (e) Structural—(1) Limit load. A for landing conditions at the maximum limit load is the maximum load antici altitude is the maximum altitude at velocity of descent. (See § 4b.230 (b).) pated in normal conditions of operation. which in standard atmosphere it is pos (8) Design unit weight. The design (See § 4b.200.) sible to maintain, at a specified rota unit weight is a representative weight (2) Ultimate load. An ultimate load tional speed without ram, a specified is a limit load multiplied by the appro power or a specified manifold pressure. used to show compliance with the struc priate factor of safety. (See § 4b.200.) Unless otherwise stated, the critical alti tural design requirements. (3) Factor of safety. The factor of tude is the maximum altitude at which (1) Gasoline 6 pounds per U. S. gallon. safety is a design factor used to provide (ii) Lubricating oil 7.5 pounds per it is possible to maintain without ram, U. S. gallon. , for the possibility of loads greater than at the maximum continuous rotational (iii) Crew and passengers 170 pounds those anticipated in normal conditions speed, one of the following: per person. of operation and for uncertainties in (i) The maximum continuous power, (d) Speeds. (1) TAS: The true air design. (See § 4b.200 (a).) in the case of engines for which this speed of the airplane relative to the un (4) Load factor. The load factor is power rating is the same at sea level or disturbed air. the ratio of a specified load to the total at the rated altitude, (2) EAS: Equivalent air speed is weight of the airplane; the specified load (11) The maximum continuous rated equal to: TAS (p/p0)i. may be expressed in terms of any of the manifold pressure, in the case of engines following: aerodynamic forces, inertia (3) CAS: Calibrated air speed is equal forces, or ground or water reactions. the maximum continuous power of to the air-speed indicator reading cor (5) Limit load factor. The limit load which is governed by a constant manifold rected for position and instrument errors. factor is the load factor corresponding pressure. (CAS is equal to TAS in the standard with limit loads. atmosphere at sea level.) * For engine airworthiness requirements see (6) Ultimate load factor. The ulti Part 13 of this chapter, for propeller air (4) IAS: Indicated air speed is equal mate load factor is the load factor corre worthiness requirements see Part 14 of this to the reading of the pitot static air sponding with ultimate loads. chapter. 408 PROPOSED RULE MAKING
(6) Pitch setting. Pitch setting is the level of safety: Provided, That the Ad flight tests shall depend upon the com propeller blade setting determined by ministrator finds no feature or charac plexity of the airplane, the number and the blade angle measured in a manner, teristic of the airplane which renders it nature of new design features, and the and at a radius, specified in the in unsafe for the transport category. record of previous tests and experience struction manual for the propeller. for the particular airplane model, its (7) Feathered pitch. Feathered pitch § 4b. 11 Amendment. Unless other components, and equipment. If prac is the pitch setting, chosen by the ap wise specified, an amendment of this ticable, these flight tests shall be con plicant, which in flight, with the engines part shall be effective with respect to ducted on the same airplane used in the stopped, gives approximately the mini airplanes for which application for type flight tests specified in paragraph (a) of certificates are filed more than 60 days this section. mum drag, and corresponds with a wind after the adoption date of the amend milling torque of approximately zero. ment. § 4b. 16 Airworthiness certificates. An (8) Reverse pitch. Reverse pitch is airplane manufactured in accordance the propeller pitch setting for any blade § 4b. 12 Type certificate. An appli with a type certificate (see § 4b.l2) and angle used beyond zero pitch (e. g. the cant shall be issued a type certificate conforming to the type design shall be negative angle used for reverse thrust). when he demonstrates the eligibility of come eligible for an airworthiness cer (g) Fire protection—(1) Fireproof. the aircraft by complying with the re tificate under paragraphs (a) and (b) Fireproof material means a material quirements of §§ 4b.l3 through 4b.15 in of this section when, upon inspection of which will withstand heat at least as addition to those contained in Part 2 of the .airplane, the Administrator finds well as steel in dimensions appropriate the Civil Air Regulations. that it so conforms and that it is in a for the purpose for which it is to be used. § 4b. 13 Data required. The applicant condition for safe operation. For each When applied to material and parts used for a standard type certificate shall sub newly manufactured airplane this find to confine fires in designated fire zones, mit to the Administrator such descriptive ing shall include a flight check by the ap fireproof means that the material or part data, test reports, and computations as plicant. will perform this function under the are necessary to demonstrate that the (a) Standard certificate. To become most severe conditions of fire and dura airplane complies with the airworthiness eligible for a standard certificate an air tion likely to occur in such zones. requirements. The descriptive data plane shall comply with all of the re (2) Fire-resistant. When applied to shall be known as the type design and quirements of this part found by the sheet or structural members, fire-resist shall consist of drawings and specifica Administrator to be applicable ant material means a material which tions disclosing the configuration of the (b) Restricted certificate. An air will withstand heat at least as well as airplane and all design features covered plane intended to be operated for a aluminum alloy in dimensions appro in the airworthiness requirements as restricted purpose for which full com priate for the purpose for which it is to well as sufficient information on dimen pliance with the transport category re be used. When applied to fluid-carrying sions, materials, and processes to define quirements would be impracticable, shall lines, other flammable fluid system com the strength of the structure. The type be eligible for a restricted airworthiness ponents, wiring, air ducts, fittings, and design shall describe the airplane in certificate if it complies with all the re powerplant controls, this term refers to sufficient detail to permit the airworthi quirements of this part which are not a line and fitting assembly, component, ness of subsequent airplanes of the same rendered inapplicable by the nature of wiring or duct, or controls which will type to be determined by comparison the special purpose involved. The Ad perform the intended functions under With the type design. the heat and other conditions likely to ministrator shall establish such operat occur at the particular location. § 4b. 14 Inspection and tests. Inspec ing restrictions for the airplane as he (3) Flame-resistant. Flame-resistant tions and tests shall include all those finds will provide a level of safety equiv material means material which will not found necessary by the Administrator to alent to that established for the trans support combustion to the point of insure that the airplane complies with port category. propagating, beyond safe limits, a flame the applicable airworthiness require (c) Experimental certificate. An air after the removal of the ignition source. ments and conforms with the following: plane shall become eligible for a type and (4) Flash-resistant. Flash-resistant (a) All materials and products are in airworthiness experimental certificate material means material which will not accordance with the specifications in the when the applicant presents evidencè burn violently when ignited. type design: (b) All parts, of the airplane are con that the airplane is intended only for (5) Flammable. Flammable pertains experimental purposes, and the Admin to those fluids or gases which will ignite structed in accordance with the draw readily or explode. ings in the type design; istrator finds that with appropriate re (h) Miscellaneous—(1) Supplemental (c) All manufacturing processes, strictions it can be so operated without breathing equipment. Supplemental construction, and assembly are such that endangering the general public. The breathing equipment is equipment de the design strength and safety contem applicant shall submit data to identify signed to supply the supplementary oxy plated by the type design will be realized the airplane together with any other per gen required to protect against anoxia in service. tinent information found by the Ad at altitudes where the partial pressure § 4b. 15 Flight tests. After proof of ministrator necessary to safeguard the of oxygen in ambient air is reduced. compliance with the structural require general public. (See § 4b.651.) ments contained in this part and upon § 4b.l7 Production certificate. (For (2) Protective breathing equipment. completion of all necessary inspections requirements with regard to production Protective breathing equipment is equip and testing on the ground, and proof of ment designed to prevent the breathing the conformity of the airplane with the certificates see Part 2 of this chapter.) of noxious gases which may be present type design, and upon receipt from the § 4b. 18 Approval of materials, parts, as contaminants in the air within the applicant of a report of flight tests per processes, and appliances, (a) Materials, airplane in emergency situations. (See formed by him, the following shall be parts, processes, and appliances shall be § 4b.651.) conducted: approved upon a basis and in a manner Certification (a) Such official flight tests as the found necessary by the Administrator to Administrator finds necessary to deter implement the pertinent provisions of 4b.10 Eligibility for type and air mine compliance with the requirements worthiness certificates. An airplane of this part. the Civil Air Regulations. The Admin shall be eligible for type and airworthi (b) After the conclusion of flight tests istrator may adopt and publish such ness certification under the provisions of specified in paragraph (a) of this sec specifications as he finds necessary to this part if it complies with the airwor tion, such additional flight tests as the administer this section, and shall in thiness provisions hereinafter estab Administrator finds necessary to ascer corporate therein such portions of the lished, or if the Administrator finds that tain whether there is reasonable assur aviation industry, Federal, and military the provision or provisions not complied ance that the airplane, its components, specifications respecting such materials, with are compensated for by other design and equipment are reliable and function parts, processes, and appliances as he features which provide an equivalent properly. The extent of such additional finds appropriate. Wednesday, January 25,1950 FEDERAL REGISTER 409 (b) Any material, part, process, or ap type certificate may submit appropriate (1) The weight selected by the appli pliance shall be deemed to have met the design modifications for the approval of cant; requirements for approval when it meets the Administrator. Upon approval of (2) The design weight for which the the pertinent specifications adopted by such modifications, the type design of structure has been proven; the Administrator, and the manufac the type certificate shall be amended ac (3) The maximum weight at which turer so certifies in a manner prescribed cordingly, and all airplanes manufac compliance with all the applicable flight by the Administrator. tured thereafter shall be modified in requirements has been demonstrated. accordance with such amended type cer (b) It shall be acceptable to establish Changes tificate. The manufacturer shall make maximum weights for each altitude, § 4b.20 General. When the type de available to all operators of the same temperature, and for each practicable sign is changed, the applicant or holder type of airplane information on the de separable operating condition (e. g. take of the type certificate shall demonstrate sign modifications. off, en route, landing.) (c) Minimum weights shall not be less that the airplane complies with the ap SUBPART B—FLIGHT plicable airworthiness requirements. than any of the following: (See § 4b.0.) General (1) The minimum weight selected by § 4b.100 Proof of compliance, (a) the applicant; § 4b.21 Classification of changes. (2) The design minimum weight for Changes shall be classified as minor and Compliance with the requirements pre which the structure has been proven; major. A minor change shall be one scribed in this subpart shall be estab (3) The minimum weight at which which has no appreciable effect on the lished by flight or other tests conducted upon an airplane of the type for which a compliance with all the applicable flight weight, balance, structural strength, requirements has been demonstrated. powerplant operation, flight characteris certificate of airworthiness is sought or tics, or other characteristic affecting the by calculations based on such tests, pro § 4b.l02 Center of gravity limitations. airworthiness of the airplane. A major vided that the results obtained by calcu Center of gravity limits shall be estab change shall be one not classified as a lations are equivalent in accuracy to the lished as the most forward position per minor change. results of direct testing. missible for each weight in accordance (b) Compliance with each require with § 4b.101 and the most aft position § 4b.22 Approval of minor changes. ment shall be established at all appropri permissible for each of such weight. Minor changes to type designs may be ate combinations of airplane weight and Limits of the center of gravity range approved by an authorized representative center of gravity position within the shall not exceed any of the following: of the Administrator prior to the submit range of loading conditions for which (a) The extremes selected by the ap tal to the Administrator of any revised certification is sought by systematic plicant; drawings. investigation of all these combinations, (b) The extremes for which the struc § 4b.23 Approval of major changes. except where compliance can be inferred ture has been proven; Major changes to type designs shall be reasonably from those combinations (c) The extremes at which compli approved only after receipt by the Ad which are investigated. ance with all the applicable flight re ministrator of substantiating data and (c) The controllability, stability, trim, quirements has been demonstrated. necessary descriptive data for inclusion and stalling characteristics of the air § 4b. 103 Additional limitations on in the type design. plane shall be established at all altitudes weight distribution. If a weight and up to the maximum anticipated operat § 4b.24 Service experience changes. ing altitude. center of gravity combination is permis (a) Where the Administrator finds, as (d) The applicant shall provide a sible only within certain load distribu a result of service experience, that an person holding an appropriate pilot tion limits (e. g. spanwise) which could unsafe condition exists with respect to certificate to make the flight tests, but be exceeded inadvertently, such limits a design feature, part, or characteristic a designated representative of the Ad shall be established together with the of any airplane certificated under this ministrator shall pilot the airplane when corresponding weight and center of part, he shall furnish notice2 thereof to gravity combinations, and shall not ex it is found necessary for the determina ceed any of the following: all operators of airplanes of that type tion of compliance with the airworthi and the airplanes shall not thereafter (a) The limits selected by the appli ness requirements. cant; be operated until the unsafe condition (e) Official type tests shall be discon has been corrected, unless otherwise au tinued until corrective measures have (b) The limits for which the structure thorized by the Administrator under has been proven; been taken by the applicant when either: (c) The limits for which compliance specified conditions and limitations. (1) The applicant’s test pilot is unable (1) When the Administrator finds that with all the applicable flight require or unwilling to conduct any of the re ments has been demonstrated. design changes are necessary to correct quired flight tests; or, the unsafe condition of the airplane, the (2) It is found that requirements § 4b.l04 Empty weight, (a) The holder of the type certificate, upon re which have not been met are so substan empty weight, and the corresponding quest of the Administrator, shall submit tial as to render additional test data center of gravity position, shall be de appropriate design modifications for the meaningless or are of such nature as to termined by weighing the airplane. This approval of the Administrator. make further testing unduly hazardous. weight shall exclude the weight of the (2) Upon approval, such changes shall (f) Adequate provision shall be made crew and payload, but shall include the be made a part of the type design of the for emergency egress and for the use of weight of all fixed ballast, unusable fuel type certificate, and descriptive data parachutes by members of the crew supply (see §4b.416), undrainable oil, covering the changes shall be made avail during the flight tests. total quantity of engine coolant, and able by the holder'of the type certificate (g) The applicant shall submit to the total quantity of hydraulic fluid. to all operators of airplanes previously Administrator’s representative a report (b) The condition of the airplane at certificated under such type certificate. covering all computations and tests re thq time of weighing shall be one which (3) All airplanes of the same type quired in connection with calibration of can be easily repeated and easily de shall be modified in accordance with instruments used for test purposes and fined, particularly as regards the con such amended type certificate. correction of test results to standard at tents of the fuel, oil, and coolant tanks, (b) Where no current unsafe condi mospheric conditions. The Administra and the items of equipment installed. tion exists but the Administrator or the tor’s representative shall conduct any holder of the type certificate finds flight tests which he finds necessary to § 4b.105 Use of ballast. Removable through service experience that changes check the calibration and correction ballast may be used to enable the air in type design will contribute to the report. plane to comply with the flight require safety of the airplane, the holder of the § 4b. 101 Weight limitations. The ments. (See §§ 4b.738 and 4b.741 (c) .) * Operators of airplanes are notified of any maximum and minimum weights at Performance unsafe condition, of the required corrective which the airplane will be suitable for action, and of compliance dates through the operation shall be established as follows: § 4b.110 General. The performance medium of Airworthiness Directives issued (a) Maximum weights shall not ex prescribed in this subpart shall be deter toy the Administrator. ceed any of the following: mined, and compliance shall be shown 410 PROPOSED RULE MAKING for standard atmospheric conditions and of true indicated air speed, shall be height of 50 feet above the take-off still air. selected by the applicant, but shall riot surface, § 4b.lll Wing flap positions, (a) be less than the minimum speed at which (2) The airplane speed is equal to V2, The wing flap positions denoted respec the controllability is demonstrated dur (3) The landing gear is retracted, tively as the take-off, en route, approach, ing take-off run to be adequate to permit (4) The inoperative propeller is wind and landing positions shall be selected proceeding safely with the take-off, using milling with the propeller control in a by the applicant. (See also § 4b.323.) normal piloting skill, when the critical position normally used during take-off. (b) The flap positions may be made engine is suddenly made inoperative. (d) The horizontal distance traversed variable with weight and altitude. (b) The minimum take-off safety and the height attained by the airplane speed, V2, in terms of true indicated air in the time elapsed from the end of ele 5 4b.112 Stalling speeds, (a) The speed shall be selected by the applicant ment (c) until the time limit on the use speed, Vs0, denotes the true indicated so as to permit the rate of climb required of take-off power is reached, while op stalling speed, or the minimum steady in § 4b. 120, but shall not be less than: erating at the speed V2, with: flight speed at which the airplane is con (1) 1.20 Vs1 for two-engine airplanes, (1) The inoperative propeller stopped. trollable, in miles per hour, with: (2) 1.15 Vs1 for airplanes having more (2) The landing gear retracted. (1) Engines idling, throttles closed (or than two engines, (e) The slope of the flight path fol not more than sufficient power for zero (3) 1.10 times the minimum control lowed by the airplane in the configura thrust at a speed not greater than 110 speed, VMG, established under § 4b. 133. tion of element (d), but drawing not percent of the stalling speed); (c) If Vx is equal to or greater than Vv more than maximum continuous power (2) Propeller pitch controls in the demonstration of controllability during on the operating engine (s). position normally used for take-off; take-off for Vlt as provided in paragraph (3) Landing gear extended; § 4b.ll7 Temperature accountability. (4) Wing flaps in the landing posi (a) of this section, shall not be required. Operating correction factors for take-off tion; § 4b.ll5 Accelerate-stop distance. The weight and take-off distance shall be de (5) Cowl flaps closed; accelerate-stop distance shall be the sum termined to account for temperatures (6) Center of gravity in the most un of the following: above and below standard, and when ap favorable position within the allowable (1) The distance required to acceler proved by the Administrator shall be in landing range; ate the airplane from a standing start cluded in the Airplane Flight Manual. (7) The weight of the airplane equal to the speed Vx. These factors shall be obtained as fol to the weight in connection with which (2) Assuming the critical engine to lows: Vsn is being used as a factor to determine fail at the speed Vv the distance required (a) For any specific airplane type, the a required performance. to bring the airplane to a full stop from average full temperature accountability (b) The speed, VSl, denotes the true the point corresponding with the speed shall be computed for the range of Indicated stalling speed, or the minimum Vv weights of the airplane, altitudes above steady flight speed at which the airplane (b) In addition to, or in lieu of, wheel sea level, and ambient temperatures re is controllable, in miles per hour, with: brakes, the use of other braking means quired by the expected operating con (1) Engines idling, throttles closed, (or shall be acceptable in determining the ditions. Account shall be taken of the not more than sufficient power for zero accelerate-stop distance, provided that temperature effect on both the aerody thrust at a speed not greater than 110 such braking means shall have been namic characteristics of the airplane and percent of the stalling speed); proven to be safe and reliable, that the on the engine power. The full tempera (2) Propeller pitch controls in the manner of their employment is such that ture accountability shall be expressed position normally used for take-off, the consistent results can be expected under per degree of temperature in terms of a airplane in all other respects (flaps, normal conditions of operation, and that weight correction, a take-off distance cor landing gear, etc.) in the particular con exceptional skill is not required to con rection, and a change, if any, in the crit dition existing in the particular test in trol the airplane. ical engine failure speed, V,. connection with which FSl is being used; (c) The landing gear shall remain ex (b) The operating correction factors (3) The weight of the airplane equal tended throughout the accelerate-stop for the airplane weight and take-off dis to the weight in connection with which distance. tance shall be at least one-half of the V$t is being used as a factor to deter full accountability values. The value of mine a required performance. § 4b.116 Take-off path. The take-off V1 shall be further corrected by the (c) These speeds shall be determined path shall be considered to consist of the average amount necessary to assure that by flight tests using the procedures out following five consecutive elements. the airplane can stop within the runway lined in § 4b.l60 (b). (a) The distance required to acceler length at the ambient temperature, ex ate the airplane to the speed V2, assum cept that the corrected value of V1 shall § 4b.ll3 Take-off; general, (a) The ing the critical engine to fail at the not be less than a minimum at which the take-off data in §§ 4b.ll4 to 4b.ll6, in speed Vv airplane can be controlled with the clusive, shall be determined under the (b) The horizontal distance traversed critical engine inoperative. following conditions: and the height attained by the airplane (1) At all weights and altitudes se in the time required to retract the land § 4b. 118 Climb; general. Compli lected by the applicant; ing gear when operating at the speed ance with the climb requirements of (2) With a constant take-off flap posi V2, with: §•§ 4b. 119 through 4b. 121, shall be shown for standard atmospheric conditions, tion for the particular weight and alti (1) The critical engine inoperative, its tude; propeller: still air, and specified altitudes. (3) With the operating engines not (1) Windmilling with the propeller § 4b. 119 All engines operating; exceeding their approved limitations at control in a position normally used dur climb—(a) General. The steady rate of the particular altitude. ing take-off until (if applicable) its ro climb shall be determined at any alti (b) All take-off data, when corrected, tation has been stopped (see paragraph tude at which the airplane is expected to shall assume a level take-off surface, and (c) (1) of this section), operate and at any weight within the shall be determined on a smooth, dry, (ID If applicable, stopped for the re range of weights to be specified in the hard-surfaced runway, in such a manner mainder of the gear retraction time. airworthiness certificate. that reproduction of the performance (2) The landing gear extended. (b) Cruising configuration. The does not require exceptional skill or (c) If applicable, the horizontal dis steady rate of climb at 5,000 feet shall alertness on the part of the pilot. tance traversed and the height attained not be less in feet per minute than 8 Vt0 (c) For temperature accountability by the airplane in the time elapsed from with: data see § 4b.ll7. For wind and runway the end of element (b) until the rota (1) Landing gear fully retracted, gradient ''corrections see appropriate tion of the inoperative propeller has been (2) Wing flaps in the most favorable operating parts of the Civil Air Regu position, lations. stopped when: (3) Cowl flaps (or other means of con ( 1 ) The operation of stopping the pro trolling the engine cooling) in the posi § 4b.ll4 Take-off speeds, (a) Hie peller is initiated not earlier than the tion which provides adequate cooling in critical-engine-failure speed, Vv in terms Instant the airplane has attained a total the hot-day condition. Wednesdayt January 25,1950 FEDERAL REGISTER 411 (4) Center of gravity in the most un (6) All remaining engines operating § 4b.l23 Landplanes. The landing favorable position, at the maximum continuous power avail distance referred to in § 4b.122 shall be (5) All engines operating within the able at the altitude. determined on a dry, hard-surfaced run maximum continuous power limitations, (d) Flaps in approach position. The way in accordance with the following: (6) Maximum take-off weight. steady rate of climb in feet per minute (a) The operating pressures on the (c) Landing configuration. The shall not be less than 0.04 Vs0* at any braking system shall not be in excess of steady rate of climb in feet per minute altitude within the range forwhich land those approved by the manufacturer of shall not be less than 0.07 Vs0a at any ing weight is to be specified in the cer the brakes, altitude within the range for which tificate, with: (b) The brakes shall not be used in landing weight is to be specified in the (1) The landing gear retracted, such manner as to produce excessive certificate, with: (2) Wing flaps set in position such wear of brakes or tires, (1) Landing gear extended, that VSl does not exceed 1.10 Vs0, (c) Means other than wheel brakes (2) Wing flaps in the landing posi (3) Cowl flaps in the position normally may be used in determining the landing tion (see §§ 4b. I ll and 4b. 323), used during an approach to a landing, distance, providing that: (3) Cowl flaps in the position nor (4) Center of gravity in the most un (1) Exceptional skill is not required to mally used in an approach to a landing, favorable position permitted for landing, control the airplane, (4) Center of gravity in the most un (5) The critical engine inoperative, its (2) The manner of their employment favorable position permitted for landing, propeller stopped, is such that consistent results could be (5) All engines operating at the take (6) All remaining engines operating expected under normal service, off power available at such altitude, at the take-off power available at such (3) They are regarded as reliable. (6) The weight equal to maximum altitude, § 4b.l24 Seaplanes or float planes. landing weight for that altitude. (7) The weight equal to the maximum The landing distance referred to in § 4b.120 One -engine - inoperative landing weight for that altitude. § 4b. 122 shall be determined on smooth climb—(a) Flaps in take-off position; § 4b.l21 Two-engine-inoperative climb. water. landing gear extended. The steady rate For airplanes with four or more engines, § 4b.l25 Skiplanes. The landing dis of climb shall not be less than 50 ft./min. the steady rate of climb at any altitude tance referred to in § 4b.122 shall be de at any altitude within the range for at which the airplane is expected to op termined on smooth, dry snow. which take-off weight is to be specified in erate, and at any weight within the range the certificate, with: of weights to be specified in the Airplane Controllability (1) Wing flaps in the take-off position Flight Manual, shall be determined with: § 4b. 130 Controllability; general, (a) (see §§ 4b.lll and4b.323), (a) The landing gear retracted, The airplane shall be safely controllable (2) Cowl flaps in the position nor (b) Wing flaps in the most favorable and maneuverable during take-off, climb, mally used during take-off, position, level flight, descent, and landing. (3) Center of gravity in the most un (c) Cowl flaps or other means of con (b) It shall be possible to make a favorable position permitted for take-off, . trolling the engine cooling air supply in smooth transition from one flight con (4) The critical engine inoperative, the position which will provide adequate dition to another, including turns and its propeller windmilling with the pro cooling in the hot-day condition, slips, without requiring an exceptional peller control in a position normally used (d) Center of gravity in the most degree of skill, alertness, or strength on during take-off, unfavorable position, the part of the pilot and without danger (5) All other engines operating at the (e) The two critical engines on one of exceeding the limit load factor under take-off power available at such altitude, side of the airplane inoperative and their all conditions of operation probable for (6) The speed equal to the minimum propellers stopped, the type, including those conditions take-off safety speed Vi, used in § 4b.114 (f) All remaining engines operating at normally encountered in the event of (b), the maximum continuous power avail sudden failure of any engine. (7) The weight equal to maximum able at that altitude. take-off weight for that altitude. § 4b.131 Longitudinal control, (a) (b) Flaps in take-off position; land,- § 4b. 122 Determination of the land It shall be possible at all speeds between ing gear retracted. The steady rate of ing distance; general. The horizontal 1.4 Vjj and Vst to pitch the nose down climb in feet per minute shall not be distance required to land and to come ward so that a prompt recovery to a to a complete stop (to a speed of approxi speed equal to 1.4 Vs1 can be made with: less than 0.035 Vs * with all other condi mately 3 m. p. h. for seaplanes or float tions as described in paragraph (a) of planes) from a point at a height of 50 feet (1) The airplane trimmed at 1.4 V$t this section. above the landing surface shall be deter with landing gear extended, (c) Flaps in en route position. The mined for a range of weights and alti (2) The wing flaps in a retracted and steady rate of climb in feet per minute tudes selected by the applicant. In extended position, at any altitude at which the airplane is making this, determination the following (3) Power off and maximum continu expected to operate, at any weight conditions shall apply: ous power on all engines. within the range of weights to be spec (a) A steady gliding approach shall (b) During each of the controllability ified in the airworthiness certificate, have been maintained down to the 50- demonstrations outlined in this para shall be determined and shall, at a foot altitude with a true indicated air graph, it shall not require a change in standard altitude of 5,000 feet and at the speed of not less than 1.3 Vs0. the trim control or the exertion of more maximum take-off weight, be at least (b) The nose of the airplane shall not control force than can be readily applied 0.02 Vs02 for airplanes with a maximum be depressed, nor the forward thrust in with one hand for a short period. Each take-off weight of 40,000 pounds, 0.04 creased by application of power after maneuver shall be performed with the Vs0a for airplanes with a maximum take reaching the 50-foot altitude. landing gear extended. off weight of 60,000 pounds or more, with (c) At all times during and immedi (1) With power off, flaps retracted, a linear variation of the coefficient of ately prior to the landing, the flaps shall and the airplane trimmed at 1.4 V$v Vsq between 40,000 pounds and 60,000 be in the landing position, except that the flaps shall be extended as rapidly pounds, with: after the airplane is on the landing sur as possible while maintaining the air (1) The landing gear retracted, face and the true indicated air speed speed approximately 40 percent above (2) Wing flaps in the most favorable has been reduced to not more than 0.9 the stalling speed prevailing at any in position, Vs0 the flap position may be changed. stant throughout the maneuver. (3) Cowl flaps or other means of con (d) The landing shall be made in such (i) The maneuver of this subpara trolling the engine cooling air supply in manner that there is no excessive vertical graph shall be repeated, except that it the position which provides adequate acceleration, no tendency to bounce, nose shall be started with flaps extended and cooling in the hot-day condition, over, ground loop, porpoise, or water loop, the airplane trimmed at 1.4 Vsv after (4) Center of gravity in the most un- • and in such manner that its reproduction which the flaps shall be retracted as favorable position, shall not require any exceptional degree rapidly as possible. (5) The critical engine inoperative, its of skill on the part of the pilot, or excep (ii) The maneuver of subdivision (i) propeller stopped, tionally favorable conditions. of this subparagraph shall be repeated, 412 PROPOSED RULE MAKING except that maximum continuous power speed equal to 1.4 Vt± with maximum V>t to VLE with the landing gear ex shall be used. continuous power and with the airplane tended. (2) With power off, flaps retracted, in the configuration of paragraph (b) of § 4b.143 Longitudinal and directional and the airplane trimmed at 1.4 V$x, this section. trim. The airplane shall maintain longi take-off power shall be applied quickly § 4b. 133 Minimum control speed, tudinal and directional trim at a speed while maintaining the same air speed. Vmc- (a) A minimum speed shall *be equal to 1.4 V»x, during climbing flight (i) The maneuver of this subpara determined under the conditions spec with the critical engine inoperative, with: graph shall be repeated, except that the ified in this paragraph, so that, when (a) The other engine(s) at maximum flaps shall be extended. one engine is suddenly made inoperative continuous power, (3) With power off, flaps extended, at that speed, it shall be possible to re (b) The landing gear retracted, and the airplane trimmed at 1.4 Vtv air cover control of the airplane, with one (c' Wings flaps retracted. speeds within the range of 1.1 Vtt to 1.7 engine still inoperative, and maintain it § 4b.l44 Trim for airplanes with four Vh or VFE, whichever is the lesser, shall in straight flight at that speed, either be obtained and maintained. or more engines. The airplane shall with zero yaw or, at the option of the maintain trim in rectilinear flight at the (c) It shall be possible without the applicant, with an angle of bank not in use of exceptional piloting skill to pre climb tpeed, configuration, and power excess of 5°. Such speed shall not ex used in establishing the rates of climb in vent loss of altitude when flap retraction ceed 1.2 VSl with: from any position is initiated during (1) Take-off or maximum available § 4b. 121, with the most unfavorable steady horizontal flight at 1.1 VSl with center of gravity position, and at the power on all engines, weight at which the two-engine-inop simultaneous application of not more (2) Rearmost center of gravity, than maximum continuous power. (3) Flaps in take-off position, erative climb is equal to at least 0.01 V» * (See also § 4b.323.) (4) Landing gear retracted. at an altitude of 5,000 feet. § 4b. 132 Directional and lateral con (b) In demonstrating the minimum Stability trol—(a) Directional control; general. speed of paragraph (a) of this section, §• 4b.150 General. The airplane shall It shall be possible, while holding the the rudder force required to maintain be longitudinally, directionally, and lat wings approximately level, to execute control shall not exceed 180 pounds, nor erally stable in accordance with §§ 4b.l51 reasonably sudden changes in heading shall it be necessary to throttle the re through 4b.l57. Suitable stability and in either direction without encountering maining eiigines. control “feel” (static stability) shall be dangerous characteristics. Heading (c) During recovery of the maneuver required in other conditions normally changes up to 15° shall be demonstrated, of paragraph (a) of this section, the air encountered in service if flight tests show except that the heading change at which plane shall not assume any dangerous such stability to be necessary for safe the rudder pedal force is 180 pounds atitude, nor shall it require exceptional operation. need not be exceeded. The control shall skill, strength, or alertness on the part be demonstrated at a speed equal to 1.4 of the pilot to prevent a change of head § 4b. 151 Static longitudinal stability. Vtv under the following conditions: ing in excess of 20° before recovery is In the configurations outlined in §§ 4b.152 (1) The critical engine inoperative complete. through 4b. 155, and with the airplane Trim trimmed as indicated, the characteristics and its propeller in the minimum drag of the elevator control forces and fric condition, § 4b. 140 General. The means used tion shall comply with the following. (2) Power required for level flight at for trimming the airplane shall be such (a) A pull shall be required to obtain 1.4 V*!, but not greater than maximum that after being trimmed and without and maintain speeds below the specified continuous power, further pressure upon, or movement of, trim speed, and a push shall be required (3) Most unfavorable center of grav either the primary control or fts corre to obtain and maintain speeds above the ity position, sponding trim control by the pilot or the specified trim speed. This criterion shall (4) Landing gear retracted, automatic pilot, the airplane shall com apply at any speed which can be obtained (5) Wing flaps in the approach posi ply with the trim requirements of without excessive control force, except tion, §§ 4b. 141 through 4b.l44. that such speeds need not be greater than (6) Maximum landing weight. § 4b. 141 Lateral and directional trim. the appropriate operating limit speed or (b) Directional control; four or more The airplane shall maintain lateral and need not be less than the minimum speed engines. Airplanes with four or more directional trim under the most adverse in steady unstalled flight. engines shall comply with paragraph (a) lateral displacement of the center of (b) The air speed shall return to with of this section, except that: gravity within the relevant operating in 10 percent of the original trim speed (1) The two critical engines shall be limitations, under all normally expected when the control force is slowly released inoperative, their propellers in the mini conditions of operation, including opera from any speed within the limits defined mum drag position, tion at any speed from 1.4 FSl to 90 per in paragraph (a) of this section. (2) The center of gravity shall be in cent of the maximum speed in level flight (c) The stable slope of stick force the most forward position, at maximum continuous power. curve versus speed of §§ 4b.l52 through (3) The wing flaps shall be in the most 4b-155 shall be such that any substan favorable climb position. § 4b. 142 Longitudinal trim. The air tial change in speed is clearly perceptible (c) Lateral control; general. It shall plane shall maintain longitudinal trim to the pilot through a resulting change be possible to execute 20° banked turns under the following conditions: with or against the inoperative engine (a) During a climb with maximum in stick force. from steady flight at a speed equal to continuous power at a speed not in ex § 4b.l52 Stability during landing. 1.4 VSl with: cess of 1.4 Fsj with the landing gear The stick force curve shall have a stable (1) The critical engine inoperative retracted and the wing flaps both re slope, and the stick force shall not ex and its propeller in the minimum drag tracted and in the take-off position; ceed 80 pounds at any speed between condition, (b) During a glide with power off at 1.1 Vs1 and 1.8 VSl with: (2) Maximum continuous power on a speed not in excess of 1.4 Vsx with the (a) Wing flaps in the landing position, the operating engines, landing gear extended and the wing flaps (b) The landing gear extended, (3) Most unfavorable center of grav both retracted and extended, with the (c) Maximum landing weight, ity position, forward center of gravity position ap (d) Throttles closed on all engines, (4) Landing gear retracted and ex proved for landing with the maximum (e) The airplane trimmed at 1.4 tended, landing weight, and with the most for with throttles closed. (5) Wing flaps in the most favorable ward center of gravity position approved climb position, for landing regardless of weight; § 4b. 153 Stability during approach. (6) Maximum take-off weight. (c) During level flight at any speed The stick force curve shall have a stable (d) Lateral control; four or more en from 1.4 Vti to 90 percent of the maxi slope at all speeds between 1.1 Vsx and gines. It shall be possible to execute 20° mum speed in level flight at maximum 1.8 Vsj with: banked turns with or against the inop continuous power with the landing gear (a) Wing flaps in sea level approach erative engines from steady flight at a and wing flaps retracted, and from 1.4 position. Wednesday, January 25,1950 FEDERAL REGISTER 413 (b) Landing gear retracted, sidered appropriate to the operation of (b) The operating engines may be (c) Maximum landing weight, the type. throttled back during the recovery from (d) The airplane trimmed at 1.4 (1) At greater angles up to that at the stall. and with power sufficient to maintain which thè full rudder control is em level flight at this speed. ployed or a rudder pedal force of 180 § 4b.l62 Stall warning. Clear and pounds is obtained, the rudder pedal distinctive stall warning shall be appar § 4b.l54 Stability during climb. The forces-shall not reverse, and increased ent to the pilot at a speed at least 5 per stick force curve shall have a stable slope rudder deflection shall produce increased cent above the stalling speed, with flaps at all speeds between 85 and 115 percent angles of sideslip. and landing gear in all possible positions, of the speed at which the airplane is (2) Sufficient bank shall accompany both in straight and turning flight. The trimmed with: sideslipping to indicate clearly any de warning may be furnished either (a) Wing flaps retracted, parture from steady unyawed flight un through the inherent aerodynamic quali (b) Landing gear retracted, less a yaw indicator is provided. ties of the airplane, by a suitable instru (c) Maximum take-off weight, (d) Any short period oscillation occurment, or by other means which will give (d) 75 percent of maximum continu ring between stalling speed and maxi clearly distinguishable indications under ous power, mum permissible speed shall be heavily all conditions of flight which are to be (e) The airplane trimmed at the best damped with the primary controls free expected in airline operations. rate-of-climb speed, except that the and in a fixed position.' speed need not be less than 1.4 V»v Ground Handling Characteristics Stalling Characteristics § 4b. 170 Longitudinal stability and § 4b.l55 Stability during cruising— control, (a) There shall be no uncon (a) Landing gear retracted. Between § 4b.160 Stalling; symmetrical power. trollable tendency for landplanes to nose 1.3 V*x and Vne the stick force curve (a) Stalls shall be demonstrated with: over in any reasonably expected operat shall h^ve a stable slope at all speeds ob (1) Power off, ing condition, or when rebound occurs tainable with a stick force not in excess (2) The power necessary to maintain during landing or take-off. of 50 pounds with: level flight at a speed of 1.6 V«x with flaps (b) Wheel brakes shall operate (1) Wing flaps retracted, in the approach position, landing gear smoothly and shall exhibit no undue (2) Maximum take-off weight, retracted, and at maximum landing tendency to induce nosing over. (3) 75 percent of maximum continu weight, ous power, (3) The wing flaps and landing gear § 4b.l71 Directional stability and con (4) The airplane trimmed for level in any likely combination of positions, trol. (a) There shall be no uncontrol flight with 75 percent of the maximum (4) All appropriate airplane weights, lable ground-looping tendency in 90° continuous power. (5) The center of gravity in the most cross winds of velocity up to 0.2 V«0 at (b) Landing gear extended. The adverse position for recovery, any ground speed at which the airplane stick force curve shall have a stable (6) The airplane in straight flight and is expected to operate. slope at all speeds between 1.3 Vsx and in turns with bank up to 30°. (b) All landplanes shall be demon the speed at which the airplane is (b) With trim controls adjusted for strated to be satisfactorily controllable trimmed, except that the range of speeds straight flight at a speed of 1.4 Va1 the with no exceptional degree of skill or need not exceed that obtainable with a speed shall be reduced by means of the alertness on the part of the pilot in stick force of 50 pounds with: elevator control until it is steady at power-off landings, at normal landing (1) Wing flaps retracted, slightly above stalling speed; then the speed, during which brakes or engine (2) Maximum take-off weight, elevator control shall be pulled back at power are not used to maintain a straight (3) 75 percent maximum continuous a rate such that the airplane speed re path. power, or the power for level flight at duction does not exceed one mile per (c) Satisfactory means shall be pro the landing gear exterided speed, VLE, hour per second until a stall is produced vided for directional control of the air whichever is the lesser, as evidenced by an uncontrollable down plane during taxying. (4) The airplane trimmed for level ward pitching motion of the airplane, or § 4b. 172 Shock absorption. The shock flight with the power specified in sub- until the control reaches the stop. Nor-., absorbing mechanism shall not produce paragraph (3) of this paragraph. mal use of the elevator control for re damage to the structure when the air covery may be made after Such pitching plane is taxied on the roughest ground § 4b.l56 Dynamic longitudinal sta motion is unmistakably developed. which it is reasonable to expect the air bility. Any short period oscillation (c) In conditions of paragraphs (a) plane to encounter in normal operation. occurring between stalling speed and and (b) of this section it shall be pos maximum permissible speed shall be. § 4b. 173 Demonstrated cross wind. sible to produce and correct roll and There shall be established a cross com heavily damped with the primary con yaw by unreversed use of the aileron and trols free and iff a fixed position. ponent of wind velocity at which it has rudder controls up to the moment when been demonstrated to be safe to take off § 4b. 157 Directional and lateral sta the airplane pitches^ or land. bility. (a) The Static directional sta (d) In straight flight stalls, the aver bility, as shown by the tendency to age roll occurring between the initiation Water Handling Characteristics recover from a skid with rudder free, of the pitching motion and the comple § 4b.180 Stability and control, (a) shall be positive with all landing gear tion of the recovery shall not exceed 20°. Seaplanes shall exhibit no uncontroll and flap positions and symmetrical power (e) In turning flight stalls, the roll able porpoising at any speed at which the conditions, at all speeds from 1.2 up following the stall shall not be so violent airplane is normally operated on the to the appropriate operating limit speed. or extreme as to make it difficult, with water. (b) The static lateral stability, as normal piloting skill, to make a prompt (b) There shall be no uncontrollable shown by the tendency to raise the low recovery and regain control of the air looping tendency in 90° cross winds of wing in a sideslip with all landing gear plane. velocity up to 0.2 Vs0 at any speed at and flap positions and symmetrical power which the airplane is expected to op conditions shall: § 4b.l61 Stalling; asymmetrical power. erate on water. (1) Be positive at the appropriate oper (a) The airplane shall be safely recov (c) Satisfactory means shall be pro ating limit speed, erable without applying power to the vided for directional control of the air (2) Not be negative at a speed equal inoperative engine when stalled with: plane during taxying on water. to 1.2 Vh. (1) The critical engine inoperative, § 4b.l81 Spray characteristics. Spray (c) In straight steady sideslips (unac- (2) Flaps and landing gear retracted, during taxying, take-off, or landing shall celerated forward slips) the aileron and (3) The remaining engines operating at no time dangerously obscure the rudder control movements and forces up to 75 percent of maximum continuous vision of the pilots nor produce damage shall be substantially proportional to the power, except that the power need not be to the propeller or other parts of the air angle of sideslip, and the factor of greater than that at which the use of plane. • proportionality shall lie between satis maximum control travel does not hold § 4b. 182 Demonstrated cross vHnds. factory limits up to sideslip angles con- the wings level laterally. There shall be established a cross cornpo- No. 16------4 414 PROPOSED RULE MAKING nent of wind velocity at which it has (c) In all cases certain portions of the is greater, where VSl is the stalling speed been demonstrated to be safe to take off structure shall be tested as specified in with fla^s retracted at the design land and land. § 4b.300. ing weight1;xand Vs0 is the stalling speed Miscellaneous Flight Requirements Flight Loads with flaps in the landing position at the design landing weight. (See § 4b.212 § 4b.190 Flutter and vibration, (a) § 4b.210 General. Flight load re (d) regarding automatic flap operation.) All parts of the airplane shall be demon quirements shall be complied with at (2) Design maneuvering speed, VA. strated in flight to be free from flutter critical altitudes within the range for The design maneuvering speed VA shall and excessive vibration under all speed which certification is desired, at all and power conditions appropriate to the weights from the design minimum weight be equal to VSl Vn where n is the operation of the airplane up to -at least to the design maximum weight, the limit maneuvering load factor used (see the minimum value permitted for VD in latter not being less than the design § 4b.211 (a), and Vsx is the stalling §"4b.210(b) (5). The maximum speeds take-off weight, with any practicable speed with flaps retracted at the design so demonstrated will be used in estab distribution of disposable load within take-off weight. (See fig. 4b-2.) lishing the operating limitations of the prescribed operating limitations stated (3) Design speed for maximum gust airplane in accordance with § 4b.711. in the Airplane Flight Manual. (See intensity, VB. VB shall be the speed at (b) There shall be no buffeting con § 4b.740.) At all speeds in excess of which the 40 foot per second gust line dition in normal flight severe enough to those corresponding with a Mach num intersects the positive Cwmax curve on the interfere with satisfactory control of the ber of 0.65, compressibility effects shall gust V-n envelope (see § 4b.211 (b) and airplane, to cause excessive fatigue to the be taken into account. fig. 4b-3). crew, or to cause structural damage.3 (a) Flight load factor. The flight (4) Design cruising speed, Vc. The (See also §§ 4b.308 and 4b.309.) load factors specified in this subpart minimum design cruising speed Vc shall shall represent the component of accel be sufficiently greater than VB to provide SUBPART C—STRUCTURE eration in terms of the gravitational for inadvertent speed increases likely to constant. The flight load factor shall General occur as a result of severe atmospheric be assumed to act normal to the longi turbulence. In the absence of a rational § 4b.200 Loads. Strength require tudinal axis of the airplane, shall be investigation substantiating the use of ments of this subpart are specified in equal in magnitude and shall be opposite other values, V0 shall not be less than terms of limit and ultimate loads. Un in direction to the airplane inertia load Fb+50 (m. p. h.), except that it need less Otherwise stated, the specified loads factor at the center of gravity. not exceed the maximum speed in level shall be considered as limit loads. In (b) Design air speeds. The design air flight at maximum continuous power determining compliance with these re speeds shall be “equivalent air speeds” for the corresponding altitude. At al quirements the following factors shall be and shall be chosen by the applicant, ex titudes where VD is limited by Mach applicable. cept that they shall not be less than the number, Vc need not exceed 0.8 VD, as (a) The factor of safety shall be 1.5 speeds defined in subparagraphs (1) through (5) of this paragraph. Where shown in figure 4b-l, except that is unless otherwise specified. shall not be less than 1.3 VSl with the (b) Unless otherwise provided, the estimated values of the speeds Vt0 and specified air, ground, and water loads Vh are used, such estimates shall be con flaps retracted at the maximum alti shall be1 placed in equilibrium with servative. tude for which certification is desired. inertia forces, considering all items of (1) Design flap speed, VF. The mini (5) Design dive speed, VD. The mini mass in the airplane. mum value of the design flap speed shall mum design dive speed VD shall be suf (c) All loads shall be distributed in a be equal to 1.4 or 1.8 Vs0 whichever ficiently greater than V0 to provide for manner closely 4 approximating or con servatively representing actual condi tions. (d) If deflections under load signifi cantly change the distribution of exter nal or internal loads, such redistribution shall be taken into account. § 4b.201 Strength and deformation. (a) The structure shall be capable of supporting limit loads without suffering detrimental permanent deformations. (b) At all loads up to limit loads the, deformation shall be such as not to inter fere with safe operation of the airplane. (c) The structure shall be capable of supporting ultimate loads without fail ure. It shall support the load for at least 3 seconds, unless proof of strength is demonstrated by dynamic tests simu lating actual conditions of load applica tion. § 4b.202 Proof of struct ur e. (a) Proof of compliance of the structure with the strength and deformation require ments of § 4b.201 shall be made for all critical loading conditions. (b) Proof of compliance by means of structural analysis shall be acceptable only when the structure conforms to types for which experience has shown such methods to be reliable. In all other cases substantiating tests shall be re quired.
*It is not the intent of this requirement to discourage such stall warning buffeting as does not contradict these provisions. Wednesday, January 25,1950 FEDERAL REGISTER m safe recovery from inadvertent upsets (1) The positive maneuvering load (5) In the absence of a more rational occurring at Vc. In the absence of a factor n for any flight speed up to VD analysis the gust load factors shall be rational investigation the minimum shall be selected by the applicant, ex computed by the following formula: value of VD, in the altitude range be cept that it shall not be less than 2.5. tween sea level and an altitude selected (2) The negative maneuvering load by the applicant, shall not be less than factor shall have a minimum value of where 1.25 V0 or V0 + 70 (m. p. h.), whichever — 1.0 at all speeds up to Vc and shall /W \V‘ . is greater. The altitude range chosen K — 1/2 i y ) (for W/S<16 p. b. f.), or shall be adequate for the safe operation vary linearly with speed from the value of the airplane. At higher altitudes at Vc to zero at VD. 2.67 than that selected by the applicant VD (b) Gust load factors. The airplane E=1'33- (PV/S)8/* (iorW / s ) >16p.s.f.), may be limited to a Mach number selected shall be assumed to be subjected to sym 17= nominal gust velocity, ft. per sec by the applicant. (See fig. 4b-l.) metrical vertical gusts while in level ond. (Note th a t the “effective § 4b.211 Flight env elope s. The flight. The resulting limit load factors sharp-edged” gust equals KU), strength requirements shall be met at all shall correspond with the following con V= airplane speed (m. p. h.), ditions. 1V/S= wing loading, pounds per square combinations of air speed and load factor (1) Positive (up) and negative (down) foot, ' on and within the boundaries of the V-n 0= slope of the airplane normal force diagrams of figures 4b-2 and 4b-3 which gusts of 40 f. p. s. nominal intensity at a coefficient curve CNA per radian, represent the maneuvering and gust speed VB shall be applicable where the if the gust loads are applied to envelopes. These envelopes will also be positive 40 f. p. s. gust line intersects the the wings and horizontal tail sur used in determining the airplane struc positive Cjvmax curve. If this gust in faces simultaneously by a rational tural operating limitations as specified in tensity produces load factors greater method. The wing lift curve slope than those obtained in condition (2), it CL per radian ^may be used when § 4b.710. the gust load is applied to the (a) Maneuvering load factors. (See may be modified at altitudes above wings only and the horizontal tail fig. 4b-2.) The airplane shall be assumed 20,000 feet in such a manner as to pro gust loads are treated as a sep to be subjected'to symmetrical maneuvers duce a load factor not less than that ob arate condition. resulting in the limit load factors pre tained in condition (2). scribed in subparagraphs (1) and (2) of (2) Positive and negative gusts of 30 § 4b.212 Effect of high lift devices. this paragraph, except where limited by f. p. % at Vc. When flaps or similar high lift devices maximum (static) lift coefficients. (3) Positive and negative gusts of 15 intended for use at the relatively low Lower values of maneuvering load factor f. p. s. at VD. air speeds of approach, landing, and may be employed only if it is shown that (4) Gust load factors shall be assumed take-off are installed, the airplane shall the airplane embodies features of design to vary linearly between the specified be assumed to be subjected to sym which make it impossible to exceed such conditions as shown on the gust envelope metrical maneuvers and gusts with the values in flight. of figure 4b-3. flaps in landing position at the design flap speed VF resulting in limit load fac tors within the range determined by the following conditions: (a) Maneuvering to a positive limit load factor of 2.0. (b) Positive and negative 15 fps nom inal intensity gusts acting normal to the flight path in level flight. (c) In designing the flaps and sup porting structures, slipstream effects shall be taken into account as specified in § 4b.221. (d) When automatic flap operation is provided, the airplane shall be designed for the speeds and the corresponding flap positions which the mechanism permits. (See § 4b.323.) § 4b.213 Symmetrical flight condi tions—(a) Procedure of analysis. In the analysis of symmetrical flight condi F igure 4b-2—Maneuvering envelope maneuvering load factor vs. speed, (V-n) diagram. tions at least those specified in para graphs (b), (c), and (d) of this section shall be considered. The following pro cedure of analysis shall be applicable. (1) A sufficient number of points on the maneuvering and gust envelopes shall be investigated to insure that the maximum load for each part of the air plane structure is obtained. A conserva tive combined envelope may be used for this purpose. (2) All significant forces acting on the airplane shall be placed in equilibrium in a rational or a conservative manner. The linear inertia forces shall be con sidered in equilibrium with wing and horizontal tail surface loads, while the angular (pitching) inertia forces shall be considered in equilibrium with wing and fuselage aerodynamic moments and horizontal tail surface loads. (3) Where sudden displacement of a control is specified, the assumed rate of displacement need not exceed that which actually would be applied by the pilot. 416 PROPOSED RULE MAKING (4) In determining elevator angles (d) Gust conditions. The gust con loads shall be considered. In computing and chordwise load distribution in the ditions B' through J ' on figure 4b-3 shall these loads the yawing velocity may be maneuvering conditions of paragraphs be investigated. assumed zero. (b) and (c) of this section in turns and (1) The air load increment due to a (1) With the airplane in unacceler pull-ups, account shall be taken of the specified gust shall be added to the initial ated flight at zero yaw, it shall be effect of corresponding pitching veloci balancing tail load corresponding with assumed that the rudder control is ties. Steady unaccelerated flight. suddenly displaced to the maximum de (b) Maneuvering balanced conditions, (2) The alleviating effect of wing flection as limited by the control stops The maneuvering conditions A through down-wash and of the airplane’s motion or by a 300-pound rudder pedal force, I on the maneuvering envelope (fig. in response to the gust may be included whichever is critical. 4b-2) shall be investigated, assuming in computing the tail- gust load ; in- (2) -With the rudder deflected as speci the airplane to be in equilibrium with crsniGiit fied in subparagraph (1) of this para zero pitching acceleration. (3) The gust factor K (§ 4b.211 (b)) graph it shall be assumed that the (c) Maneuvering 'pitching conditions. may be applied to the specified gust in airplane yaws to the resulting sideslip The following conditions on figure 4b-2 tensity for the horizontal tail, in lieu of angle. involving pitching acceleration shall be a rational investigation of the airplane (3) With the airplane yawed to the investigated. response. static sideslip angle corresponding with the rudder deflection specified in sub- (1) A±, Unchecked pull-up at speed § 4b.214 Rolling conditions. The air VA. The airplane shall be assumed to be paragraph (1) of this paragraph, it shall plane shall be designed for rolling loads be assumed that the rudder is returned flying in steady unaccelerated flight resulting from the conditions specified (point Ax on figure 4b-2) and the pitch to neutral. in paragraphs (a) and (b) of this sec (b). Lateral gusts. The airplane shall ing control suddenly moved to obtain tion. Unbalanced aerodynamic moments be assumed to encounter gusts of 30 extreme positive pitching (nose up), about the center of gravity shall be re f. p. s. nominal intensity, normal to the except as limited by pilot effort, § 4b .220 acted in a rational or a conservative plane of symmetry while in unacceler (a). manner considering the principal masses ated flight at speed Vc. In the absence (2) Az, Checked maneuver at speed, furnishing the reacting inertia forces. . of a rational investigation of the air VA. (i) The airplane shall be assumed (a) Maneuvering. The conditions, plane’s response to a true gust, the gust to be maneuvered to the positive maneu aileron deflection, and speeds, except as loading on the vertical tail surfaces may vering load factor by a checked maneuver the deflections may be limited by pilot be computed by the following formula: from an initial condition of steady unac effort (see § 4b.220 (a)), specified as fol celerated flight (point A1 on fig. 4b-2). lows shall be considered in combination w= KUVr a The initial positive pitching portion of with an airplane load factor of at least 575 “ this maneuver may be considered covered two-thirds of the positive maneuvering where by subparagraph (1) of this paragraph. factor used in the design of the airplane. W= average lifnit unit pressure in pounds (ii) A negative pitching acceleration In determining the required aileron de per square foot. 4 5 (nose down) of at least the following flections, torsional flexibility of the wing K—1.33------g except that K shall not value shall be assumed to be attained shall be taken into account in accord concurrently with the airplane maneu ance with § 4b.200 (e). vering load factor (point A2 on Fig. (1) Conditions corresponding with be, less than 1.0. A value of K 4b-2), unless it is shown that a lesser steady rolling velocity shall be investi obtained by rational determination value could not be exceeded: gated. In addition, conditions corre may be used, 30 sponding with maximum angular U= nominal gust intensity in feet per — y - n (n -r-1.5) (radians/sec.2) acceleration shall be investigated for air second, planes having engines or other weight V0= design cruising speed- in miles per where n is equal to the value of the posi concentrations outboard of the fuselage. hour, tive maneuvering load factor as defined o=slope of lift curve of the vertical For the angular acceleration conditions, surface, CL per radian, corrected for by point A2 on figure 4b-2. zero rolling velocity may be assumed in aspect ratio, (3) Dx and D2 checked maneuver at the absence of a rational time history W = design take-off weight, pounds, VD. The airplane shall be assumed to be investigation of the maneuver. vertical surface area sq. ft. subjected to a checked maneuver from (2) At speed VA a sudden deflection of steady unaccelerated flight (point D1 on the aileron to the stop shall be assumed. § 4b.216 Supplementary flight condi fig. 4b-2) to the positive maneuvering (3) At speed Vc the aileron deflection tions—(a)' Engine torque effects. En load factor (point D2 on fig. 4b-2) as shall be that required to produce a rate gine mounts and their supporting of roll not less than that obtained Jn con structures shall be designed for engine follows: torque effects combined with basic flight (i) A positive pitching acceleration dition (2) of this paragraph. (4) At speed VD the aileron deflection conditions as described in subparagraphs (nose up), equal to at least the following (1) and (2) of this paragraph. The value, shall be assumed to be attained shall be that required to produce a rate limit torque shall be obtained by multi concurrently with the airplane load fac of roll not less than, one-third of that plying the mean torque by a factor of 1.33 tor of unity, unless it is shown that lesser in condition (2) of this paragraph. in the case of engines having 5 or more values could not be exceeded: (b) Unsymmetrical gusts. The con dition of unsymmetrical gusts shall be cylinders. For 4, 3, and, 2-cylinder en 45 gines, the factors shall be 2, 3, and 4, + v ^ n (n — 1-5) (radians/sec.2) considered by modifying the symmetrical respectively. v D flight conditions JB'. or C’ of figure 4b-3, (1) The limit torque corresponding where n is equal to the value of the posi whichever produces the greater load fac with take-off power and propeller speed tive maneuvering load factor as defined tor. It shall be assumed that 100 per acting simultaneously with 75 percent of by point D2 on figure 4b-2. cent of the wing air load acts on one side the limit loads from flight condition A (ii) A negative pitching acceleration of the airplane, and 80 percent acts on (see fig. 4b-2). (nose down), equal to at least the fol the other side. (2) The limit torque corresponding lowing value, shall be assumed to be § 4b.215 Yawing conditions. The air with maximum continuous power and attained concurrently with the airplane plane shall be designed for yawing loads propeller speed, acting simultaneously positive maneuvering load factor (point resulting from the conditions specified in with the limit loads from flight condi D2 on fig. 4b-2), unless it is shown that paragraphs (a) and (b) of this section. tion A (see fig. 4b-2). lesser values could not be exceeded: Unbalanced aerodynamic moments about (b) Side load on engine mount. The 30 the center of gravity shall be reacted in limit load factor in a lateral direction —-rf—n (n — 1.5) (radians/sec.2) a rational or a conservative maner con for this condition shall be equal to the • D sidering the principal masses furnishing maximum obtained in the yawing con where n is equal to the value of the the reacting inertia forces. ditions, but shall not be less than either positive maneuvering load factor as de (a) Maneuvering. At all speeds from 1.33 or one-third the limit load factor for fined by point D, on figure 4b-2. VMC to VA the following vertical tail flight condition A (see fig. 4b-2). Engine Wednesday, January 25,1950 FEDERAL REGISTER 417 mounts and their supporting structure side of the plane of symmetry, and 80 Acceptable maximum and minimum shall be designed for this condition percent of that loading shall be applied pilot loads for elevator, aileron, and rud which may be assumed independent of loathe opposite side. der controls are shown in figure 4b-5. other flight conditions. (d) Outboard fins. (1) When out These pilot loads shall be assumed to afct (c) Pressure cabin loads. When presboard fins are carried on the horizontal at the appropriate control grips or pads surized compartments are provided for tall surface, the tail surfaces shall be in a manner simulating flight condi the occupants of the airplane, the fol designed for the maximum horizontal tions and to be reacted at the attach lowing requirements shall be met. (See surface load In combination with the ment of the control system to the control § 4b.373.) corresponding loads induced on the ver surface horn. (1) The airplane structure shall have tical surfaces by end plate effects. Such (b) The loads shall in any case be sufficient strength to withstand the flight Induced effects need not be combined sufficient to provide a rugged system, for loads combined with pressure differential with other vertical surface loads. service use, including considerations of loads from zero up to the maximum re (2) To provide for unsymmetrical jamming, ground gusts, taxying tail to lief valve setting. Account shall be taken loading when outboard fins extend above wind, control inertia, and friction. of the external pressure distribution in and below the horizontal surface, the 8 4b.225 Dual primary flight control flight. critical vertical surface loading (load per systems, (a) When dual controls are (2) If landings are to be permitted unit area) as determined by the provi provided, the system shall be designed With the cabin pressurized, landing loads sions of this section shall also be applied for the pilots operating in opposition, shall be combined with pressure differ as follows: using individual pilot loads equal to 75 ential loads from zero up to the maxi (i) 100 percent to thë area of the ver percent of those obtained in accordance mum to be permitted during landing. tical surfaces above (or below) the hor with 8 4b.224, except that the individual (3) The airplane structure shall have izontal surface, and pilot loads shall not be less than the sufficient strength to withstand the pres (ii) 80 percent to the area below (or minimum loads specified in figure 4b-5. sure differential loads corresponding above) the horizontal surface. with the maximum relief valve setting (b) The control system shall be de multiplied by a factor of 1.33 to provide § 4b.221 Wing flaps, (a) Wing flaps, signed for the pilots acting in conjunc for such effects as fatigue and stress their operating mechanism, and sup tion, using individual pilot loads equal concentration. porting structure shall be designed for to 75 percent of those obtained in ac (4) Where a pressurized cabin is sep critical loads prescribed by § 4b.212 with cordance with 8 4b.224. arated into two or more compartments the flaps extended to any position from 8 4b.226 Ground gust conditions. by bulkheads or floor, the primary fully retracted to the landing position. The following conditions, intended to structure shall be designed for the ef (b) The effects of propeller slipstream simulate the loadings on control surfaces fects of sudden release of pressure in corresponding with take-off power shall due to ground gusts and when taxying any compartment having external doors be taken into account at an airplane downwind, shall be investigated. or windows. This condition shall be in speed of not less than 1.4 Vt#. where (a) The loads in the systems between vestigated for the effects resulting from is the stalling speed with flaps as follows the stops nearest the surfaces and the the failure of the largest opening in a (for automatic flaps see 8 4b.212 (d) ) : cockpit controls need not exceed those compartment. Where intercompart (1) Landing and approach settings at corresponding with the maxima of figure ment venting is provided, it shall be ac the design landing weight, 4b-5 for each pilot alone, or with 75 per ceptable to take into account the effects (2) Take-off and en route settings at cent of these maxima for each pilot when of such venting. the design take-off weight. the pilots act in conjunction. (c) It shall be acceptable to assume Control Surface and System Loads (b) The control system stops nearest the airplane load factor to be equal to the surfaces, the control system locks, 8 4b.220 Control surface loads; gen- . 1.0 for investigating the slipstream con and the portions of the systems, if any, eral. The control surfaces shall be de dition. between such stops and locks and the signed for the limit loads resulting from 8 4b.222 Tabs, (a) At all speeds up control surface horns shall be designed the flight conditions prescribed in to VD, elevator trim tabs shall be de for limit hinge moments if obtained from §§4b.213 through 4b.215, taking into signed for the deflections required to the following formula: account the following provisions: trim the airplane at any point within H=KcSq, (a) Effect of pilot effort. (1) In the the positive portion of the maneuvering where: control surface flight loading condi V-n diagram (fig. 4b-2), except as lim if= limit hinge moment (ft. Jb.) tions, the air loads on the movable sur ited by the stops. c=mean chord (a. f. t.) of the control faces and the corresponding deflections surface aft of the hinge line, need not exceed those which could be (b) Aileron and rudder trim tabs S = area of the control surface (sq. ft.) obtained in flight by employing the max shall be designed for deflections required aft of the hinge line, imum pilot control forces specified in fig to trim airplane in appropriate unsym q k dynamic pressure (p. s. f.) based on ure 4b-5, except that two-thirds of the metrical lateral loading and rigging, and a design speed not less than maximum values specified for the aileron symmetrical and unsymmetrical power 1 0 y W /S + 1 0 (mph), except that and elevator shall be acceptable when conditions. the designed speed need not exceed (c) Balancing and servo tabs shall be 60 mph, control surface hinge moments are based K = factor as specified in figure 4b-4. on reliable data. In applying this cri designed for deflections consistent with terion, proper consideration shall be the primary control surface loading con 8 4b.227 Secondary control systems. given to the effects of servo mechanisms, ditions. Secondary controls, such as wheel brake, tabs, and automatic pilot systems in 8 4b.223 Special devices. The load spoiler, and tab controls shall be de assisting the pilot. ing for special devices employing aerody signed for the loads based on the maxi (b) Effect of trim tab. The effects of mum which a pilot is likely to apply to namic surfaces, such as slots and spoilers, the control in question. The values of trim tabs on the control surface design shall be based on test data. conditions need be taken into account figure 4b-0 are considered acceptable. only in cases where the surface loads 8 4b.224 Primary flight control sys are limited on the basis of maximum tems. Elevator, aileron, and rudder Surface K Position of controls pilot effort in accordance with the pro control systems and their supporting structures shall be designed for loads cor » +0. 75 Control column locked or vision of paragraph (a) of this section. lashed in mid-position. In such cases the tabs shall be consid responding with 125 percent of the com >±0.50 Ailerons at full throw; + ered to be deflected in the direction puted hinge moments of the movable moment on one aileron, — moment on the other. which would assist the pilot and the control surface in the conditions pre /Elevator (c) full up (—), deflections shall be those specified in scribed in 8 4b.220, subject to the follow ®jElevator...... >±0.75 \ and (d) full down (+)• /Rudder (e) in neutral, and § 4b.222. ing provisions: (f)J Rudder------...... ±0.75 \ (f) at full throw. (c) Unsymmetrical loads. The maxi (a) The system limit loads, except the mum horizontal tail surface loading loads resulting from ground gusts, 1A positive value of K indicates a moment tending to (load per unit area) as determined by 8 4b.226, need not exceed those which can depress the surface, while a negative value of K indicates the provisions of this section shall be be produced by the pilot or pilots and a moment tending to raise the surface. applied to the horizontal surface on one automatic devices operating the controls. Figure 4b-4—Limit hinge moment factor. 418 PROPOSED RULE MAKING
Limit Pilot Loads (Onb P ilot) shall be assumed to be subjected to forces airplane shall be assumed to contact the and descent velocities prescribed in para ground with the rates of descent speci Control Maximum load Minimum load graph (b) of this section. (The basic fied in § 4b.230 (b) (1) at a forward landing gear dimensional data are givdn velocity component parallel to the ground AHorom in fig. 4b-7.) equal to 1.2 F«0. The following two com Stick...... 100pounds...... 40 pounds. binations of vertical and drag com Wheel ‘...... 80 B inch-poundss 40 D inoh-pounds. (a) Centersof gravity positions. The Elevator: critical'center of gravity positions within ponents shall be considered acting at the 250 pounds_____ 100 pounds. axle center line: Wheel...... 300 pounds...... 100 pounds. the certification limits shall be selected Rudder...... 800 pounds...... 130 pounds. so that the maximum design loads in (1) Condition of maximum wheel each of the landing gear elements are spin-up load. Drag components simulat i The- critical portions of the aileron control system obtained in the landing and the ground ing the forces required to accelerate the shall also be designed for a single tangential force having handling conditions. wheel rolling assembly up to the specified a limit value equal to 1.25 times the couple force de ground speed shall be combined with the termined from these criteria. (b) Load factor for landing conditions. »!)■*wheel diameter. , (See § 4b.332 (a) for requirements on vertical ground reactions existing at the instaht of peak drag loads. It shall be F igure 4b-5—Pilot control force limits (Primary energy absorption tests which determine controls). the minimum limit inertia load factors acceptable to apply this condition only corresponding with the required limit to the landing gear and the directly af descent velocities.) fected attaching structure. Control' Limit pilot loads (1) In the landing conditions the (2) Condition of maximum wheel limit vertical inertia load factor at the vertical load. An aft acting drag com Miscellaneous: 1 ponent not less than '25 percent of the crank wheel or — X50 lb., but not less than 50 center of gravity of the airplane shall lever. lb. nor more than 150 lb. (R= be chosen by the applicant, except, that maximum vertical ground reaction shall radius). it shall not be less than the value which be combined with the maximum ground Applicable to any angle within 20° of plane of control. would be obtained when landing the air reaction of § 4b.230 (b). Twist...... 133 inches-pounds. plane with a limit descent velocity of (b) Level landing; tail-wheel type. Push-pull. To be chosen by applicant. either 10 fps at the design landing weight The airplane horizontal reference line or 6 fps at the design take-off weight. shall be assumed horizontal. The con i Limited to flap, tab, stabilizer, spoiler, and lauding (2) It shall be acceptable to assume a ditions specified in paragraphs (a) (1) gear operating controls. wing lift not exceeding two-thirds of the and (a) (2) of this section shall be in F igure 4b-&—Pilot control force limits (secondary airplane weight to exist throughout the vestigated. (See. fig. 4b-9.) controls). landing impact and to act through the (c) Level landing; nose wheel type. Ground Loads center of gravity of the airplane. The following airplane attitudes shall be (3) -The provisions of subparagraph considered: (See fig. 4b-9.) § 4b.230 General. The limit loads ob (1) and (2) of this paragraph shall be <1) Main wheels contacting the tained in the conditions specified by predicated on conventional arrange ground with the nose wheel just clear of §§4b.231 through 4b.236 shall be con ments of main and nose gears, or main the ground. The two conditions speci sidered as external forces applied to the and tail gears, and on normal operating fied in paragraphs (a) (1) and (a) (2) airplane structure and shall be placed in techniques. It shall be acceptable to equilibrium by linear and angular iner of this section shall be investigated. modify the prescribed descent velocities (2) Nose and main wheels contacting tia forces in a rational or conservative if it is shown that the airplane embodies manner. In applying the specified con the ground simultaneously. Conditions features of design which make it impos in this attitude need not be investigated ditions the provisions of paragraph (a) sible to develop these velocities. of this section shall be complied with. if this attitude cannot reasonably be at In addition, for the landing conditions § 4b.231 Level landing conditions.— tained at the specified descent and for of §§ 4b.231 through 4b.234 the airplane (a) General. In the level attitude, the ward velocities. The two conditions Wednesday y January 25,1950 FÉDÉRAL REGISTER 419 specified in paragraphs (a) (1) and (a) of the airplane in a rational or conserva reaction equal to the vertical reaction (2) of this section shall be investigated, tive manner. multiplied by a coefficient of friction of except that in condition (a) (1) it shall § 4b.234 Lateral drift landing condi 0.8 shall be combined with the vertical be acceptable to investigate the nose and tion. (a) The airplane shall be in the ground reaction and applied at the main gear separately neglecting the level attitude with only the main wheels ground contact point. (See fig. 4b—12.) pitching moments due to wheel spin-up contacting the ground. (See fig. 4b-ll.) (2) Nose-wheel type. The limit loads, while in condition (a) (2) the (b) Side loads of 0.8 of the vertical vertical load factor shall be 1.2 for the pitching moment shall be assumed to be reaction (on one side) acting inward airplane at the design landing weight, resisted by the nose gear. and 0.6 of the vertical reaction (on the and 1.0 for the airplane at the design § 4b.232 Tail-down landing condi other side) acting outward shall be com take-off weight. A drag reaction equal bined with one-half of the maximum to the vertical reaction multiplied by a tions. The following conditions shall be coefficient of friction of 0.8 shall be com investigated for the load factor obtained vertical grouhd reactions obtained in the bined with the vertical reaction and in § 4b.230 with the vertical ground reac level landing conditions. These loads applied at the ground contact point of tions applied to the landing gear axles. shall be assumed to be applied at the each wheel having brakes. The following (a) Tail-wheel type. The main and ground contact point and to be resisted two airplane attitudes shall be consid tail wheels shall be assumed contacting by the inertia of the airplane. It shall ered. (See fig. 4b-12.) the ground simultaneously. (See fig. be allowed to assume the drag loads as (i) The airplane in the level attitude 4b-8.) Two conditions of ground reac zero. with all wheels contacting the ground tion on the tail wheel shall be assumed § 4b.235 Ground handling conditions. and the loads distributed between the to act in the following directions: The landing gear and airplane structure main and nose gear. Zero pitching ac (1) Vertical, shall be investigated for the conditions celeration shall be assumed. (2) Up and aft through the axle -at of this section with the airplane at the (ii) The airplane in the level attitude 45° to the ground line. design take-off weight, unless otherwise with only the main gear contacting the (b) Nose-wheel type. The airplane prescribed. No wing lift shall be con ground and the pitching moment re shall be at an attitude corresponding sidered. It shall be allowed to assume sisted by angular acceleration. with either the stalling angle or the the shock absorbers and tires to be de (c) Turning. The airplane in the maximum angle permitting clearance flected to their static position. static position shall be assumed to exe with the ground by all parts of the air (a) Take-off run. The landing gear cute a steady turn by nose gear steering plane other than the main wheels, which and airplane structure shall be designed or differential power such that the limit ever is the lesser. (See fig. 4b-8.) for loads not less than those resulting load factors applied at the center of § 4b.233 One-wheel landing condi from the condition specified in § 4b.l72. gravity are 1.0 vertically and 0.5 laterally. tion. The main landing gear on one side (b) Braked roll—(1) Tail-wheel type. (See fig. 4b-13.) The side ground re of the airplane center line shall contact The airplane shall be assumed in the action of each wheel shall be 0.5 of the the ground in the level attitude. (See level attitude with all load on the main vertical reaction. fig. 4b-10.) The ground reactions on this wheels. The limit vertical load factor (d) Pivoting. The airplane shall be side shall be the same as those obtained shall be 1.2 for the airplane at the design assumed to pivot about one side of the in § 4b.231 (a) (2). The unbalanced ex landing weight, and 1.0 for the airplane main gear, the brakes on that side being ternal loads shall be reacted by inertia at the design take-off weight. A drag locked. The limit vertical load factor
& • ANGLE FOR MAIN GEAR AND TAIL STRUCTURE CONTACTING GROUND EXCEPT NEED NOT EXCEED STALL ANGLE
TAIL WHEEL TYPE NOSI WHEEL TYPE Figure 4b-8—Tail down landing data.
TWO CONDITIONS ARE USED:
(I) Dm *UVM w h e r e vm is v e r t i c a l w h e e l r e a c t io n AT INSTANT WHEELS ARE UP TO SPEED AND ti IS COEFFICIENT OF FRACTION, u MAY BE ASSUMED EQUAL TO 0.8. i\W- VALUE NECESSARY FOR BALANCE. A-C0N0ITI0N OF MAXIMUM WHEEL SPIN UP LOAD (E) - 0.85 VM WHERE i^W IS DETERMINED BY ENERGY ABSORPTION REQUIREMENTS FOR LANDING.
TAIL WHEEL TYPE
F igure 4b-9—Level landing data. 420 PROPOSED RULE MAKING shall be 1.0 and the coefficient of friction 0.8.. The airplane shall be assumed to be in static equilibrium, the loads being applied at the ground contact points. (See fig. 4b-14.) (e) Nose-wheel yawing. (1) A verti cal load factor of 1.0 at the airplane c. g. and a side component at the nose wheel ground contact equal to 0.8 of the vertical ground reaction at that point shall be assumed. (2) The airplane, shall be placed in static equilibrium with the loads result ing from the application of the brakes on one side of the main gear. The ver tical load factor at the c. g. shall be 1.0. The forward acting load at the airplane c. g. shall be 0.8 times the vertical load HOSt OR TAIL WHEEL TYPE on one main sear. The side vertical loads at the ground contact point on the Figure 4b-10—One wheel landing. - nose gear shall be those required for static equilibrium. The side load factor at the airplane c. g. shall be assumed zero. (f) Tail-wheel yawing. (1)A verti cal ground reaction equal to the static load on the tail wheel, in combination with a side component of equal magni tude shall be assumed. (2) When a swivel is provided, the tail wheel shall be assumed swiveled 90° to the airplane longitudinal axis with the resultant load passing through the axle. When a lock, steering device, or shimmy- damper is provided, the tail wheel shall also be assumed in the trailing position with side load acting at the ground con tact point. § 4b.236 Unsymmetrical loads on Vfc" 0.25 <«-0.67) W dual-wheel units. In dual-wheel units, 60 percent of the total ground reaction * NOSE GEAR GROUND REACTION »0 for the unit shall be applied to one wheel and 40 percent to the other. To provide NOSE OR TAIL WHEEL TYPE AIRPLANE IN LEVEL ALTITUDE for the case of one tire flat, either wheel Figure 4b-ll—Lateral drift landing.
T>MERTIA FORCE NECESSARY TO BALANCE THE WHEEL ORAS FORCES * 0 , *9 UNLESS NOSE WHEEL IS EQUIPPED WITH BRAKES. FOR DESIGN OF MAIN BEAR V„ >0 FOR DESIGN OF NOSE BEAR t >0
TAIL WHEEL TYPE NOSE WHEEL TYPE Figure 4b-12—Braked roll. THE AIRPLANE MERTIA FACTORS XT CENTER OF GRAVITY ARE COMPLETELY BALANCED BY THE WHEEL REACTIONS
F igure 4b-13—Ground turning Wednesday, January 25, 1950 FEDERAL REGISTER 421 shall be capable of withstanding 60 per pressure conditions shall be investigated chine (beamwise) shall be assumed, ex cent of the load which would be assigned at the design take-off weight. cept when the chine flare indicates the to the unit in the specified conditions, § 4b.252 Boat seaplane bottom pres advisability of higher pressures at the except that the vertical ground reaction sures—(a) Maximum local pressure. chine. shall not be less than the full static The maximum value of the limit local (c) Application of local pressure. The value. pressure shall be determined from the local pressures determined in paragraphs Water Loads following equation: (a) and (b) of this section shall be applied over a local area in such a man § 4b.250 General. The water load Pmax =0.04 V.1*; * ner as to cause the maximum local loads requirements shall apply to the entire where: in the hull bottom structure. airplane. At least the hull structure, the p = pressure, pounds per square inch, (d) Distributed bottom symmetrical wing, the nacelles, and any float sup Vs=stalling speed with flaps fully re pressures. For the purpose'of designing porting structure shall be investigated. tracted at tlie design take-off weight. frames, keels, and chine structure, a § 4b.251 Design weight. The design (b) Variation in local pressure. The maximum limit pressure shall be com weight used in the water landing condi- local pressures to be applied to the hull puted according to paragraph (a) of tionfc shall not be less than the design bottom shall vary in accordance with this section, except that, the stalling landing weight, except that local bottom figure 4b-15. No variation from keel to speed used in the computation shall be based upon the design landing weight, and the resulting pressure value shall be reduced to one-half. The pressure shall be applied simultaneously over the en tire hull bottom according to the dis tribution of figure 4b-15. The resulting loads shall be carried into the side-wall structure of the hull proper, but need not be transmitted in a fore-and-aft di rection as shear and bending. (e) Distributed bottom unsymmetri- cal pressures. Each floor member or frame shall be designed for a load on one side of the hull center line equal to the most critical symmetrical loading as obtained in paragraph (d), combined with a load on the other side of the hull center line equal to one-half the most critical symmetrical loading. § 4b.253 Boat seaplane loading condi tions—(a) Step loading condition—(1) Application of load. The resultant water load shall be applied vertically in the plane of symmetry so as to pass through the center of gravity of the airplane. (2) Magnitude of load. The limit ac celeration shall be 4.0, unless a lower value is shown by tests to be more appli-- cable. (3) Hull shear and bending loads. The hull shear and bending loads shall be computed from the inertia loads pro duced by the vertical water load. To avoid excessive local shear loads and bending moments near the point of water load application, it shall be accept able to distribute the water load over the hull bottom using pressures not less than those specified in § 4b.252 (d). (b) Bow loading cpndition—(1) Ap plication of load. The resultant water load shall be applied in the plane of sym metry at a point one-tenth of the dis tance from the bow to the step and shall be directed upward and rearward at an angle of 30° from the vertical. (2) Magnitude of load.. The magni tude of the limit resultant water load shall be determined from the following equation: P b= V 2 n sW e; where: P6=the load in pounds, ns=the step landing load factor, We=an effective weight assumed to be equal to one-half the design land ing weight of the airplane. VN AND VM ARE STATIC GROUND REACTIONS. FOR TAIL (3) Hull shear and bending loads. „ WHEEL TYPE THE AIRPLANE IS IN THE THREE POINT The hull shear and bending loads shall be ATTITUDE* WITH STATIC LANDING GEAR REACTIONS determined by appropriate consideration PIVOTING ABOUT ONE MAIN LANDING GEAR UNIT. of the inertia loads which resist the linear and angular accelerations in F igure 4b-14—Pivoting, nose or tail wheel type. volved. To avoid excessive local shear 422 PROPOSED RULE MAKING loads, It shall be acceptable to distribute inertia loads. This condition need not determined by appropriate considera the water reaction over the hull bottom be applied to the fittings or to the por tion of the inertia loads or by introduc using pressures not less than those tion of the hull ahead of the rear at ing couples at the wing attachment specified in § 4b.252 (d). . tachment fittings. points. To avoid excessive local shear (c) Stern loading condition—(1) Ap (d) Side loading condition—(1) Ap loads, it shall be acceptable to distribute plication of load. The resultant water plication of load. Thé resultant water the water reaction over the hull bottom load shall be applied vertically in the load shall be' applied in a vertical plane using pressures not less than those speci- plane of symmetry and shall be distrib through the center of gravity. The ver field by § 4b,252 (d). uted over the hull bottom from the tical component shall be assumed to act § 4b.254 Float seaplane bottom pres second step forward with an intensity in the plane of symmetry and the hori- sures. Main float seaplane bottoms equal to the pressures specified in zontol component at a point half-way shall be designed for the following: § 4b.252 (d). between the bottom, of the keel and the (a) Maximum local pressure. The (2) Magnitude of load. The limit load water line at design landing weight maximum value of the limit local pres resultant load shall equal three-fourths (at rest). sure shall be as determined by the equa of the design landing weight of the air (2) Magnitude of load. The limit tion in § 4b.252 (a). plane. vertical component of acceleration shall (3) Hull shear and bending loads. be 3.25, and the side component shall be (b) Variation in local pressure. The The hull shear and bending loads shall be equal to 15 percent of the vertical com local pressures to be applied to the float determined by assuming the hull struc ponent. bottom shall vary in accordance with ture to be supported at the wing attach (3) Hull shear and bending loads. the following: The hull shear and bending loads shall be (1) A pressure of the value prescribed ment fittings and by neglecting internal by paragraph (a) of this section shall be applied over the portion of the bottom lying between the main step and a sec tion at 25 percent of the distance from the step to the bow. (2) A pressure equal to one-half the value prescribed by paragraph (a) of this section shall be applied over the portion of the bottom lying between the section at 25 percent of the distance from the main step to the bow and a section at 75 percent of the distance from the main step to the bow. (3) A pressure equal to 0.3 times the value prescribed by paragraph (a) of this section shall be applied over the portion of the bottom aft of the main step. (c) Application of local pressure. The local pressures determined in para graphs (a) and (b) of this section shall be applied over a local area in such a manner as to cause the maximum local loads in the float bottom structure. (d) Distributed bottom pressures. For the purpose of designing frames, keels, and chine structure, distributed pressures equal to one-half of the values specified in paragraphs (a) and (b) of this section shall be applied simultane ously over the entire affected float bot tom. § 4b.255 Float seaplane landing con ditions—(a). Landing with inclined re actions. The vertical component of the limit load factor shall be 4.0, unless a lower value is shown by tests to be more applicable. The propeller axis (or equivalent reference line) shall be as sumed horizontal. The resultant water reaction shall be assumed to act in the plane of symmetry and to pass through the center of gravity of the airplane in clined so that its horizontal component is equal to one-fourth of its vertical component. Inertia forces shall be as sumed to act in a direction parallel to the water reaction. (b) Landing with vertical reactions. The limit load factor shall be 4.0 acting vertically, unless a lower value is shown by tests to be more applicable. The pro peller axis (or equivalent reference line) shall be assumed horizontal. The result ant water reaction shall be assumed to act vertically*and to pass through th« center of gravity of the airplane. (c) Landing with side load. The ver tical component of the limit load factor Wednesday, January 25, 1950 FEDERAL REGISTER 423 shall be 4.0. The propeller axis (or a minor crash landing (with wheels up strength and proper functioning of par equivalent reference line) shall be as if the airplane is equipped with retract ticular parts are specified. sumed horizontal. The resultant water able landing gear) in which the occu reaction shall be assumed to act in a pants experience the following ultimate § 4b.301 Materials. The suitability vertical plane which passes through the inertia forces relative to the surrounding and durability of all materials used in the center of gravity of the airplane and structure. airplane structure shall be established which is perpendicular to the propeller on the basis of experience or tests. All (1) Upward------2.0g (Downward— 4.5g) materials used in the airplane structure axis. The vertical load shall be applied (2) Forward______6.0g through the keel or keels of the float or (3) Sideward__ 1.5g shall conform to approved specifications floats and evenly divided between the which will insure their having the floats, if twin floats are used. A side (b) The useof a lesser value of the strength and other properties assumed load equal to one-fourth of the vertical downward inertia force specified in in the design data. load shall be applied along a line ap paragraph (a) of this section shall be § 4b.302 Fabrication methods. The proximately halfway between the bottom allowed if it is shown that the airplane methods of fabrication employed in con of the keel and the level of the water structure could absorb the landing shock structing the airplane structure shall be line at rest. When twin floats are used, corresponding with the design landing such as to produce a uniformly sound the entire side load specified shall be weight and an ultimate descent velocity structure. When a fabrication process applied to the float on the side from of 5 f. p. s. without exceeding the value such as gluing, spot welding, or heat which the water reaction originates. chosem (c) The specified inertia forces shall treating requires close control to attain § 4b.256 Seaplane float loads. Each be applied to all items of mass which this objective, the process shall be per float of a float seaplane shall be capable would be apt to injure the passengers formed in accordance with an approved of carrying the following load£ when or crew if they came adrift under such process specification. supported at the attachment fittings as conditions, and the supporting struc § 4b.303 Standard fastenings. A ll installed on the airplane. ture shall-be designed to restrain these bolts, pins, screws, and rivets used in the (a) A limit load acting upward at the items. structure shall be of an approved type. bow of the float equal to th^,t portion of The use of an approved locking device the airplane’s weight which is normally § 4b.261 Ditching provisions. At the or method is required for all such bolts, supported by the float. request of the applicant, the type cer pins, and screws. Self-locking nuts (b) A limit load acting upward at the tificate may include certifiction that shall not be used on bolts which are sub stern of the float equal to 0.8 times that adequate provision has been made for ject to rotation in operation. portion of the airplane’s weight which is emergency landings during overwater normally supported by the float. flights. § 4b.304 Protection, (a) All m e m - (c) A limit load acting upward at the (a) In order that landplanes may bers o£ the structure shall be suitably step of the float equal to 1.5 times that qualify for such a certification, satis protected against deterioration or loss of portion of the airplane’s weight which factory evidence must be submitted that strength in service due to weathering, is normally supported by the float. all practicable measures compatible with corrosion, abrasion, or other causes. the general characteristics of the type (b) Adequate provisions for ventila § 4b.257 Wing tip float loads, (a) have been taken to minimize the change tion and drainage of all parts of the Wing tip floats and their attach of any behavior of the airplane in an structure shall be made. ment, including the wing structure, shall emergency landing on water which (c) In seaplanes, special precautions be capable of carrying the following would be likely to cause immediate in shall be taken against corrosion from loads: jury to the occupants or to make it im salt water, particularly where ¿arts made (1) A limit load acting upward possible for them to escape from the from different metals are in close prox through the completely submerged cen airplane. imity. These precautions shall include ter of buoyancy of the float equal to (b) In demonstrating compliance with the following: three times the completely submerged the provisions of this section, the prob (1) Unless otherwise protected, fit displacement. able behavior of the airplane in a water tings, hinges, attachment bolts, etc., (2) A limit load inclined upward at landing shall be investigated by model shall be; covered with a corrosion-pre 45° to the rear acting through the com tests or by comparison with airplanes of ventive material. pletely submerged center of buoyancy of similar configuration for which the > (2) Nonstainless cables, such as con the float equal to three times the com ditching characteristics are known. trol cables, shall be covered with a corro pletely submerged displacement. (1) In making such tests or compari sion-preventive material. (3) A limit load acting parallel to the sons, proper consideration shall be given water surface (laterally) applied at the to scoops, flaps, projections, and all other § 4b.305 Inspection provisions. center of area of the side view equal to factors likely to affect the hydrodynamic Means shall be provided to permit the 1.5 times the completely submerged dis characteristics of the actual airplane. close examination of such parts of the placement. (2) External doors and windows shall airplane as require periodic inspection, (b) The primary wing structure shall be designed to withstand the probable adjustments for proper alignment and incorporate a sufficient strength margin maximum local pressures, unless the ef functioning, and lubrication of moving to insure that failure of wing tip float fects of the collapse of such parts are parts. attachment members -occurs before the taken into account in the model tests § 4b.306 Material strength properties wing structure is damaged. or airplane comparison. and design values, (a) Material strength § 40.258 Seawing loads. Seawing de (c) Airplanes which are to receive properties shall be based on a sufficient sign loads shall be based on appropriate such certification shall also comply with number of tests of material conforming test data. provisions of § 4b.361. to specifications to establish design val (d) Where an airplane is certificated« ues on a statistical basis. Emergency Landing Conditions to include the ditching provisions speci (b) The design values shall be so § 4b.260 General. The following re fied in this section, the ditching proce chosen that the probability of any struc quirements deal with emergency condi dures shall be set forth in the Airplane ture being understrength because of ma tions of landing on land or water in Plight Manual. terial variations is extremely remote. which the sa'fety of the occupants shall SUBPART D— DESIGN AND CONSTRUCTION . (c) ANC-5a and ANC-18 values shall be considered, although it is accepted be used unless shown to be inapplicable that parts of the airplane may be General in a particular case.* damaged. § 4b.300 Scope. The airplane shall (a) The structure shall be designed to not incorporate design features or de 4 ANC-5a, “Strength of Aircraft Elements,’* give every reasonable probability that all tails which experience has shown to be and ANO—18, “Design of Wood Aircraft of the occupants, if they make proper hazardous or unreliable. The suitabil Structures,” are published by the Army- use of the seats, belts, and other provi Navy-Civil Committee on Aircraft Design ity of all questionable design details or Criteria and may be obtained from the sions made in the design (see § 4b.358), parts shall be established by tests. Superintendent of Documents, Government will escape serious injury in the event of Minimum tests required to prove the Printing Office, Washington 25, D. C. 424 PROPOSED RULE MAKING (d) The structure shall be designed in compliance with this requirement the bearings, shall incorporate a multiplying so far as practicable, to avoid points of following shall apply: factor of not less than 6.67 with respect stress concentration where variable (a) Satisfactory analytical and/or ex to the Ultimate bearing strength of the stresses above the fatigue limit are likely perimental evidence shall be submitted softest material used as a bearing. to occur in normal service. to show that dangerous flutter condi (b) For hinges incorporating ball or tions will not develop at any speed up roller bearings, the approved rating of § 4b.307 Design factors; general. The to 1.2VD selected in accordance with the bearing shall not be exceeded. following requirements shall be consid | 4b.210 (b) (5), except that the speed (c) Hinges shall provide sufficient ered in the structural design. , need not exceed the terminal velocity in strength and rigidity for loads parallel (a) Special factors. Where there may to the hinge line. be uncertainty concerning the actual a 30° dive. (b) The airplane shall comply with: Control Systems strength of particular parts of the struc the flight demonstration requirements ture, or where the strength is likely to specified in § 4b. 190. § 4b.320 General. All controls shall deteriorate in service prior to normal re (c) The natural frequencies of all operate with sufficient ease, smoothness, placement, or where strength is subject main structural components, control sur and positiveness to permit proper per to appreciable variability due to uncer faces, and systems shall be determined formance of their function. All controls tainties in manufacturing processes and . by vibration tests or other reliable meth shall be arranged arid identified to pro inspection methods, the factor of safety ods, and shall be shown to be within the vide convenience in operation and in a prescribed in § 4b.200 (a) shall be multi range of values appropriate for the pre manner tending to prevent inadvertent plied by a special factor to make the vention of flutter. operation. probability of any part being under (d) The mass balance of moyable con § 4b.321 Two-control airplanes. Two- strength from these causes extremely trol surfaces shall be shown to preclude control airplanes shall be capable of con remote. flutter. tinuing safely in flight and landing in (b) Casting factors. (1) Where vis (e) Control surface tabs not equipped the event of failure of any one connect ual inspection only is to be employed, the with an irreversible actuating mecha ing element in the directional-lateral casting factor shall be 2.0, except that it nism, as specified in § 4b.322, shall be flight control system. need not exceed 1.25 for bearing stresses, properly mass balanced and shown by a (2) The casting factor may be reduced rational flutter analysis or equivalent § 4b.322 Trimming controls, (a) The to 1.25 for ultimate loads and 1.15 for testing that they are free from flutter trimming controls shall be conveniently limit loads when at least three sample tendencies. located and each shall operate in the castings are tested to show compliance plane and with the sense of the motion with these factors, and all sample and § 4b.309 Stiffness. Wings and tail of the airplane which its operation is production castings are visually and ra surfaces shall be shown to be free from Intended to provide, as specified in diographically inspected in accordance aero-elastic divergence, and control sur § 4b.353. with an approved inspection specifica faces to be free from reversal of effect, (b) Proper precautions shall be taken tion. at all speeds up to 1.2 VD selected in ac against the possibility of inadvertent or (3) Other inspection procedures and cordance with § 4b.210 (b) (5), except abrupt tab operation. casting factors shall be acceptable, If that the speed need not exceed the ter (c) Means shall be provided adjacent approved by the Administrator. minal velocity in a 30° dive. In showing to the control to indicate to the pilot the (c) Bearing factors. Bearing strength compliance with this requirement, the direction of the control movement rela shall be provided for the following con torsional rigidity of wings and tail sur tive to the airplane motion. ditions (bearing factors nqed not be ap faces shall be determined by tests or (d) Means shall be provided to indi plied when covered by other special other acceptable methods. cate the position of the trim device with factors): ' - ■ Control Surfaces respect to the range of adjustment. The (1) Relative motion in operation. indicating device shall be clearly visible (Control surface and system Joints are § 4b.310 General. The requirements to the pilots and located to preclude the covered in §§ 4b.313, 4b.327, and 4b.329 of §§ 4b.311 through 4b.313 shall apply possibility of confusion. (b).) to the design of the control surfaces. (e) Trimming devices shall be capa (2) Joints with clearance (free fit) § 4b.311 Proof of strength, (a) ble of continued normal operation in the subject to pounding or vibration. Limit load tests shall be required to prove event of failure of any one connecting (d) Fitting factors. (1) A fitting compliance with limit load requirements. or transmitting element of the primary factor of at least 1.15 shall be used in the (b) Control surface tests shall include flight control system. analysis of all fittings whose strength is the horn or fitting to which the control (f) Tab controls shall be irreversible, not proven by limit and ultimate load system is attached. unless the tab is properly balanced and tests in which the actual stress condi (c) Analysis or individual load tests shown to be free from flutter. tions are simulated in the fitting and the shall be conducted to demonstrate com (g) Irreversible tab systems shall pro surrounding structure. This factor ap pliance with the multiplying factor re vide rigidity and reliability in the portion plies to all portions of the fittings, the quirements for control surface hinges as of the system from the tab to the attach means of attachment, and bearing on the provided in § 4b.313 (a) . ment of the irreversible unit to the air members joined. (d) Rigging loads due to wire bracing plane structure. (2) In the case of integral fittings, the shall be taken into account in a rational § 4b.323 Wing flap controls, (a) The part' shall be treated as a fitting up to or conservative manner. controls shall operate in a manner to per the point where the section properties (e) The end connections of brace mit the flight crew to place the flaps in become typical of the member. wires shall be such as to minimize re any of the take-off, .en route, approach, (3) The fitting factor need not be ap straint against bending or vibration. or landing positions established under plied where a type of joint design based § 4b.lll, and to maintain these positions on comprehensive test data is used. The § 4b.312 Installation* (a) Movable tail surfaces shall be so installed that thereafter, without further attention on following are examples: continuous the part of the crew, except for flap joints in metal plating, welded joints, there is no interference between the sur movement produced by an automatic flap and scarf joints in wood, all made in ac faces when each is held in its extreme positioning or load limiting device. cordance with approved practices. position and all others are operated (b) The flap control shall be located through their full angular movement. and designed to render improbable its § 4b.308 Flutter and vibration pre (b) When an adjustable stabilizer is inadvertent operation. vention measures. In all conditions of used, stops shall be provided which will (c) The rate of motion of the flap in operation within the limit V-n envelope, limit its travel, in the event of failure of response to the operation of the pilot’s the wings, tail surfaces, control surfaces, the adjusting mechanism, to a range control and the characteristics of the control systems, and other structural equal to the maximum required to trim automatic flap positioning or load limit parts shall be free from flutter and dan the airplane in accordance with § 4b. 140. ing device shall be such as to obtain gerous vibration, including that result § 4b.313 Hinges, (a) Control sur satisfactory flight and performance char ing from gust impulses. In showing face hinges, excepting ball and roller acteristics under steady or changing con- Wednesday, January 25, 1950 FEDERAL REGISTER 425 ditions of air speed, engine power, and * trol system by operating the controls strated by operational tests prescribed airplane attitude, from the pilot compartment with the in § 4b.l72. (d) The flap control shall be designed entire system loaded to correspond with to retract the flaps from the fully ex 80 percent of the limit load specified for § 4b.332 Landing gear tests. The tended position during steady flight at the control system. In this test there landing gear shall withstand the follow maximum continuous engine power at shall be no jamming, excessive friction, ing tests. all speeds less than VF plus 10 m. p. hi or excessive deflection. (a) Shock absorption tests. (1) It (e) Means shall be provided to indicate shall be demonstrated by energy absorp to the pilot the take-off, en route, ap § 4b.329 Control system details; gen tion tests that the limit load factors se proach, and landing flap positions. eral. All details of control systems shall lected for design in accordance with (f> If any extension of the flaps be be designed and installed to prevent jam § 4b.230 (b) for take-off and landing yond the landing position is possible, the ming, chafing, and interference from weights, respectively, will not be ex flap control shall be clearly marked to cargo, passengers, and loose objects. ceeded. identify such range of extension. Precautionary means shall be provided in (2) In addition to the provisions of (g) Instructions for the proper opera the cockpit to prevent the entry of for subparagraph (1) of this paragraph,, a tion of the wing flaps shall be included eign objects into places where they might reserve of energy absorption shall be in the Airplane Plight Manual required jam the control systems. Provisions demonstrated by a test simulating an by § 4b.740. shall be made to prevent the slapping of airplane descent velocity of 12 f. p. s. at cables or tubes against other parts of the design landing weight, assuming wing lift $ 4b.324 Flap interconnection, (a) airplane. not greater than the airplane weight act The motion of flaps on opposite sides of (a) Cable systems. (1) Cables, cable ing during the landing impact. In. this the plane of symmetry shall be syn fittings, turnbuckles, splices, and pulleys test the landing gear shall not fail. chronized by a mechanical interconnec shall be of an approved type. (See paragraph (c) of this section.) tion unless the airplane is demonstrated (2) Cables smaller than Vs-inch diam (b) Limit drop tests. (1) If compli to have safe flight characteristics while eter shall not be used in the aileron, ance with the limit landing conditions the flaps are retracted on one side and elevator, or rudder systems. specified in paragraph (a) (1) of this extended on the other. (3) The design of cable systems shall section is demonstrated by free drop (b) Where ' an interconnection is be such that there will not be a hazar tests, these shall be conducted on the used, it shall be designated to account dous change in cable tension throughout complete airplane, or on units consisting for appropriate unsymmetrical loads, the range of travel under operating con of wheel, tire, and shock absorber in their including those resulting from flight ditions and temperature variations. proper relation. The free drop heights with the engines on one side of the plane (4) Pulley types and sizes shall corre shall not be less than the following: of symmetry inoperative and the re spond with the cables used. (1) 18.7 inches for the design landing maining engines at take-off power. (5) All pulleys shall be provided with weight conditions, § 4b.325 Stops, (a) All control sys satisfactory guards which shall be closely (ii) 6.7 inches for the design take-off tems shall be provided with stops which fitted to prevent the cables being mis weight conditions. positively limit the range of motion of placed or fouled. (2) If wing lift is simulated in free the control surfaces. (6) The pulleys shall lie in the plane drop tests the landing gear shall be (b) Stops shall be so located in the passing through the cable within such dropped with an effective mass equal to: system that wear, slackness, or take-up limits that the cable does not rub against h + ( 1— L) adjustments will not seriously affect the the pulley flange. range of surface travel. (7) Fairleads shall be so installed that h-\-d (c) Stops shall be capable of with they do not cause a change in cable di where : standing the loads corresponding with rection of more than 3°. W e= th e effective weight to be used in the the design conditions for the control sys (8) Clevis pins (excluding those not drop test, tem. subject to load or motion) retained only h =specified height of drop in inches, by cotter pins shall not be used in the d =deflection under impact of the tire § 4b.326 Control system locks. If a control system. (at the approved inflation pressure) device is provided for locking a control (9) Turnbuckles shall be attached to plus the vertical component of the surface while the airplane is on the parts having angular motion in a man axle travel relative to the drop ground or water: ner to prevent positively any binding mass (the value of d used in the (a) The locking device shall provide throughout the range of travel. computation of W e shall not ex unmistakable warning to the pilot when (10) Provision for visual inspection ceed the value actually obtained in it is engaged. the drop test), shall be made at all .fairleads, pulleys, V 7= W U for main gear units, equal to the (b) Means shall be provided to pre terminals, and turnbuckles. static weight on the particular unit clude the possibility of the lock becoming (b) Joints. (1) Control system joints with the airplane in the level atti engaged during flight. subjected to angular motion in push-pull tude (with the nose wheel clear in (c) Locks shall be designed for the systems, excepting ball and roller bearing the case of nose wheel type air ground gust conditions prescribed in systems, shall incorporate a multiplying planes), § 4b.226. factor of not less than 3.33 with respect W = W T for tail gear units, equal to the static weight on the tail unit with § 4b.327 Static tests. Tests shall be to the ultimate bearing strength of the the airplane in the tail-down conducted on control systems to show softest material used as a bearing. attitude, compliance with limit load requirements (2) The factor specified in subpara W = W M for nose wheel units, equal to in accordance with the following provi graph (1) of this paragraph may be re the vertical component of the sions: duced to a value of 2.0 for joints in static reaction which would exist (a) The direction of the test loads cable control systems. at the nose wheel, assuming the (3) The approved rating of ball and mass of the airplane acting at the shall be such as to produce the most center of gravity and exerting a severe loading of the control system roller bearings shall not be exceeded. force of l.Og downward and 0.25g structuré. Landing Gear forward, (b) The tests shall include all fittings, L=the ratio of the assumed wing lift pulleys, and brackets used in attaching § 4b.330 General. The requirements to the airplane weight, not in ex the control system to the main structure. of §§4b.331 through 4b.338 shall apply cess of 0.667. (c) Analyses- or individual load tests to the complete landing gear. (3) The attitude in which a landing shall be conducted to demonstrate com § 4b.331 Shock absorbers, (a) The gear unit is drop tested shall simulate the pliance with the multiplying factor re shock absorbing elements for the main, airplane landing condition critical for quirements specified for control system the unit. joints subjected to angular motion. nose, and tail wheel units shall be sub (See §4b.329 (b).) stantiated by the tests specified in (c) Reserve energy absorption drop §§ 4b.332 and 4b.333. tests. (1) If compliance with the re § 4b.328 Operation tests. An opera (b) The shock absorbing ability of the serve energy absorption condition speci tion test shall be conducted for each con- landing gear in taxying shall be demon fied in § 4b.332 (a) (2) is demonstrated 426 PROPOSED RULE MAKING by free drop tests, the landing gear units continuously when all throttles are closed that the leakage of hydraulic nuia re shall be dropped from a free drop height if the gear is not fully extended and sulting from failure of the sealing ele of not less than 27 inches. locked. ments in these units would not reduce (2) If wing lift equal to the airplane (3) If a manual shutoff for the warn the braking effectiveness below that weight is simulated, the units shall be ing device prescribed in subparagraph specified in subparagraph (2) of this dropped with an effective mass equal to: (2) of this paragraph is provided, it shall paragraph. be installed so that reopening the throt (b) Brake controls. Brake controls w>=w(hTd)- tles will reset the warning mechanism. shall not require excessive control forces (f) Control. The location and opera in their operation. where the symbols and other details are tion of the landing gear retraction con (c) Parking brake controls. A park the same as in § 4b.332 (b) (2). trol shall be according to the provisions ing brake control shall be provided and of § 4b.353. so installed that it may be set by the pilot § 4b.333 Limit load factor determina and, without further attention, will tion. (a) In determining the limit air § 4b.335 Wheels, (a) Main landing maintain, sufficient braking to prevent plane inertia load factor n from the free gear wheels (i. e. those nearest the air the airplane from rolling on a paved, drop tests specified in § 4b.332, the plane center of gravity) shall be of a level runway while take-off power on the following formula shall be used: type approved in accordance with Part 15 of this chapter. critical engine is being applied. (b) The rated static load of each main § 4b.338 Skis. Skis shall be of an aP7 wheel shall not be less than the design proved type. The approved rating of where: * take-off weight of the airplane divided n,= th e load factor during impact devel the skis shall not be less than the maxi oped on the mass used in the drop by the number of main wheels. mum take-off weight of the airplane. test (i. e., the acceleration d v /d t in (c) Nose wheels shall be tested in ac (a) Installation. In addition to any g’s recorded in the drop test plus cordance with Part 15 of this chapter shock cords installed, front and rear 1.0) (see § 4b.332 (b) (2) for defi for an ultimate radial load not less than check cables shall be provided on skis nition of W e, W , and L). the maximum nose wheel ultimate loads which are not equipped with special sta obtained in the ground loads require bilizing devices. (b) The value of n so determined shall ments and for the corresponding side (b) Tests. It shall be demonstrated not be greater than the limit load factor and burst loads. that the airplane has safe landing and used in the landing conditions, § 4b.230 taxying characteristics, and that the air (b). § 4b.336 Tires, (a) Landing g e a r tires shall be of a proper fit on the rim plane’s flight characteristics are not im § 4b.334 Retracting mechanism—(a) of the wheel, apd their approved rating paired by the installation of the skis. General. (1) The landing gear retract shall be such that it is not exceeded Hulls and Floats ing mechanism and supporting structure under the following conditions: shall be designed for the loads occurring (1) Airplane weight equal to the de § 4b.340 General. The requirements in the flight conditions when the gear is sign take-off weight. of §§ 4b.341 and 4b.342 shall apply to the in the retracted position, and for the (2) Load on main wheel tires equal to design of hulls and floats. combination of friction, inertia, brake the airplane weight divided by the num § 4b.341 Buoyancy (main seaplane torque, and air loads occurring during ber of main wheels. floats), (a) Main seaplane floats shall retraction and extension at any air (3) Load on nose wheel tires (to be have a buoyancy in excess of that re speed up to 1.6 Vilt (flaps in the approach compared with the dynamic rating estab quired to support the maximum weight position at design landing weight) and lished for such tires) equal to the of the airplane in fresh water as follows : any load factor up to those specified for reaction obtained at the nose wheel, (1) 80 percent in the case of single the flaps extended condition, § 4b.212. assuming the mass of the airplane con floats, (2) The landing gear, the retracting centrated at the center of gravity and (2) 90 percent in the case of double mechanism, and the airplane structure exerting a force of l.Og downward and floats. including wheel well doors shall be de 0.31g forward, the reactions being dis (b) Each main seaplane float shall signed to withstand the flight loads oc tributed to the nose and main wheels by contain at least 5 watertight compart curring with the landing gear in the the principles of statics with the drag ments of approximately equal volume. extended position at any speed up to reaction at the ground applied only at § 4b.342 Buoyancy (boat seaplanes) . 0.67 Vc, unless other means are provided those wheels having brakes. to decelerate the airplane in flight at this (a) The hulls of boat seaplanes and am (b) When specially constructed tires phibians shall be divided into watertight speed. are used, the wheels shall be plainly (b) Landing gear lock. A positive compartments so that with any 2 ad and conspicuously marked to that effect. jacent compartments flooded the hull means shall be provided for the purpose Such markings shall include the make, of maintaining the landing gear in the and auxiliary floats (and wheel tires, if size, number of plies, and identification used) will retain sufficient buoyancy to extended position. marking of the proper tire. (c) Emergency operation. Emer support the maximum weight of the air gency means of extending the landing § 4b.,337 Brakes—(a) General. (1) craft in fresh water without capsizing. gear shall be provided, so that the land All airplanes shall be equipped with ap (b) For the purpose of communication ing gear can be extended in the event of proved brakes. between compartments, bulkheads with any reasonably probable failure in the (2) The brake system shall be so de watertight doors shall be allowed. normal retraction system. In any case signed and constructed that in the event Personnel and Cargo Accommodations the emergency system shall provide for of a single failure in any connection or the failure of any single source of hy transmitting element in the brake sys § 4b.350 Pilot compartment; general. draulic, electric, or equivalent energy tem (excluding the operating pedal or (a) The arrangement of the pilot com supply. handle) or the loss of any single source partment and its appurtenances shall (d) Operation test. Proper function of hydraulic or other brake operating provide a satisfactory degree of safety ing of the landing gear retracting energy supply, it shall be possible to and assurance that the pilot will be able mechanism shall be demonstrated by bring the airplane to rest under condi to perform all his duties and operate the operation tests., tions specified in § 4b.l22 with a mean controls in the correct manner without (e) Position indicator and warning de deceleration during the landing roll of at unreasonable concentration and fatigue. vice. (1) When a retractable landing least 50 percent of that obtained in de- (b) The primary flight controls listed gear is used, means shall be provided for termning the landing distance as pre on figure 4b-16, excluding cables and indicating to the pilot when the gear is scribed in that section. control rods, shall be so located with re secured in the extended and in the re (3) In applying the requirement of spect to the propellers that no portion tracted position. subparagraph (2) of this paragraph to of the pilot or the controls lies in the re (2) In addition to the requirement of hydraulic brakes, the brake drum, shoes, gion between the plane of rotation of any subparagraph (1) of this paragraph, and actuators (or their equivalents) inboard propeller and the surface gen landplanes shall be provided with an shall be considered as connecting or erated by a line passing through the aural warning device which will function transmitting elements, unless it is shown center of the propeller hub and making Wednesday, January 25,1950 FEDERAL REGISTER 427 an angle of 5° forward or aft of the against the impairment of the pilot’s can be readily located and operated, even plane of rotation of the propeller. ‘vision. In darkness. § 4b.352 Pilot windshield and win- (c) Reasonable provisions shall be Controls Movement and actuation made to prevent the jamming of any dews. (a) All internal glass panes shall external door as a result of fuselage de be of a nonsplintering safety type. formation in a minor crash. P rim a ry (b) The windshield, its supporting (d) External doors shall be so located Aileron______Right (clockwise) for right wing structure, and other structure in front of that persons using them will not be en down. the pilots shall have sufficient strength Elevator______Rearward for nose up. to withstand without penetration the dangered by the propellers, when ap Rudder______Right pedal forward for nose right. propriate operating procedures are em impact of a four-pound bird when the ployed. Secondary relative velocity of the bird to the air Flaps (or auxiliary Down to extend. plane along the flight path of the latter § 4b.357 Door louvres. Where inter lift devices). is equal to the value of V0 at sea level nal doors are equipped with louvres or Trim tabs (or Rotate to produce similar rotation equivalent). of the airplane about an axis selected in accordance with § 4b.210 (b) other ventilating means, provision con parallel to the axis of the control. (4). venient to the crew shall be made for stopping the flow of air through the door § 4b.353 Controls, (a) A ll cockpit when such action is found necessary. Figure 4b-16—Aerodynamic controls. controls shall be located and identified (c) When a second pilot is required (except those the function of which is § 4b.358 Seats, berths, and safety for particular operations by the obvious) to provide convenience in oper belts—(a) Arrangement. At all stations operating parts of the Civil Air Regula ation and in a manner tending to prevent designated as occupiable during take-off tions, the airplane shall be controllable inadvertent operation. The direction of and landing, the seats, berths, belts, with equal safety from both seats. movement of aerodynamic and certain harnesses, and adjacent parts of the air (d) The pilot compartment shall be powerplant, accessories, and auxiliary plane shall be arranged so that a person constructed to prevent leakage likely to controls shall be according to figures 4b- making proper use of these facilities will be distracting to the crew or harmful to 16 and 4b-17. Wherever practicable not suffer serious injury in the emer the structure when flying in rain or snow. the sense of motion involved in the oper gency landing conditions of § 4b.260 (a). (e) A door shall be provided between ation of other controls shall correspond (1) Passengers and crew shall be af the pilot compartment and the passenger with the sense of the effect of the oper forded protection from head injuries by compartment. ation upon the airplane or upon the part one of the following or equivalent means: (f) The door prescribed in paragraph operated. (1) Safety belt and shoulder harness (e) of this section shall be equipped with which will prevent the head from con a locking means to prevent passengers Controls Movement and actuation tacting any injurious object, from opening the door without the pilot’s (ii) Safety belt and the elimination of permission. P o w erplan t all injurious objects within striking radius of the head in a fore and aft di (g) Vibration and noise characteris Throttles______Forward to increase power. tics of cockpit appurtenances shall not Propellers...... Forward to increase r. p. m. rection, Interfere with the safe operation of the Mixture...... Forward for rich. (iii) Safety belt and a cushioned rest airplane. Carburetor air heat. Forward for cold. which will support the arms, shoulders, A u x ilia ry head, and spine. § 4b.351 Pilot compartment vision— (2) For arrangements which do not (a) Nonprecipitation conditions. (1) Landing gear.. Down to extend. provide a firm hand hold on seat backs, The pilot compartment shall be arranged hand grips or rails shall be provided to afford the pilots a sufficiently exten F igube 4b-17—Powerplant and auxiliary controls. along aisles to enable passengers or crew sive, clear, and undistorted view to per (b) The controls shall be so located members to steady themselves while us form safely all maneuvers within the and arranged with respect to the pilots’ ing the aisles in moderately rough air. operating limitations of the airplane, in seats that there exists full and unre (3) All projecting obj ects which would cluding taxylng, take-off, approach, and stricted movement of each control with be apt to cause injury to persons seated landing. or moving about the airplane in normal (2) It shall be demonstrated by day out interference from either the cockpit structure or the pilots’ clothing when flight shall be padded. and night flight tests that the pilot seated. This shall be demonstrated for (b) Strength. (1) All seats, berths, compartment is free of glare and reflec-' and supporting structure shall be de tions which would tend to interfere with individuals ranging from 5'2" to 6'0" in height. signed for an occupant weighing at least the pilots’ vision. 170 lbs. and for critical* loads resulting (b) Precipitation conditions. (1) (c) Identical powerplant controls for each engine shall be located to prevent from all specified flight load conditions. Means shall be provided for maintaining (2) All seats and berths designated as a sufficient portion of the windshield any misleading impression as to the en gine to which they relate. occupiable during landing and take-off, clear so that at least the first pilot is and their supporting structure, shall be afforded a sufficiently extensive view (d) The wing flap (or auxiliary lift device) control and the landing gear designed for the loads resulting from all along the flight path in all normal flight specified ground load conditions includ attitudes of the airplane. Such means control shall be separated sufficiently to prevent inadvertent operation. ing the emergehey landing conditions of shall be designed to function under the § 4b.260. Reactions from safety belts following conditions without continuous § 4b.354 Instrument arrangement. and harnesses shall be taken into attention on the part of the crew: (See § 4b.611.) account. (1) In heavy rain at speeds up to 1.0 § 4b.355 Instrument marking. (The (3) Pilots’ seats shall be designed for V*lf flaps retracted, operational markings, instructions, and the reactions resulting from application (ii) In the most severe icing condi placards required for the instruments, of the pilot forces to the flight controls tions for which approval of the airplane controls, etc., are specified in §§ 4b.730 as prescribed in § 4b. 224. is desired. through 4b.738.) § 4b.359 Cargo and baggage com (2) In addition to the means pre § 4b.356 Doors, (a) Airplane cabins partments. (a) Each cargo and bag scribed in subparagraph (1) of this para shall be provided with at least one easily gage compartment shall be designed for graph at least the first pilot shall be accessible external main door. the placarded maximum weight of con provided with a window which, when the (b) It shall be possible to open exter tents and critical load distributions at cabin is not pressurized, is openable nal doors from either Inside or outside the appropriate maximum load factors under the conditions prescribed in sub- by the operation of only one handle in corresponding with all specified flight paragraph (1), and which provides the side or one handle outside even though and ground load conditions, excluding view specified in that subparagraph. persons may be crowding against the the emergency landing conditions of The design shall be such that when the door from the Inside. The means of § 4b.260. window is opened sufficient protection opening shall be simple and obvious and (b) Provisions shall be made to pre from the elements will be provided shall be so arranged and marked that it vent the contents in the compartments 428 PROPOSED RULE MAKING from becoming a hazard by shifting (2) Where the number of persons for such compartments, provision con under the loads specified in paragraph whom seats are provided exceeds 36, 1 venient to the crew shall be made for (a) of this section. exit per 8 persons shall be the minimum stopping the flow of air through the (c) Provisions shall be made to pro required. louvres or other means when such action tect the passengers and crew from injury (3) The external main door specified is found necessary. by the contents of any compartment in § 4b.356 shall be considered as one § 4b.372 Combustion heaters. Gaso when the ultimate inertia force acting emergency exit if it meets the detail re line combustion heater installations shall forward is 6g. quirements of paragraph (c). comply with applicable parts of the Emergency Provisions (4) The number of exits in any one powerplant installation requirements compartment need not exceed 4 if an pertaining to fire prevention. All per § 4b.360 General. The requirements adjacent compartment can be reached tinent requirements concerning fuel of §§ 4b.361 and 4b.362 shall apply to the through a passageway without a door tanks, lines, and exhaust systems shall be emergency provisions. and if the total number of exists in the applicable. 2 compartments equals 1 exit per 8 pas § 4b.361 Flotation, (a) When certifi sengers. Deviation from these numbers § 4b.373 Pressure cabins -— general. cation of ditching provisions is desired shall be allowed if it is demonstrated that The design of the pressure cabins shall by the applicant under the provisions of the airplane can be evacuated within the comply with the requirements of §§ 4b.374 § 4b.261, evidence shall be submitted to time specified in paragraph (a) of this through 4b.376. (See § 4b.216 (c) for prove that there is every reasonable strength requirements.) probability that the airplane, after land section. ing in the water, will remain afloat, as (c) Exit arrangement. (1) Emergency § 4b.374 Pressure supply. If cabin follows: exits shall be located to give the maxi pressurization is to be used, the pressure (1) In the case of airplanes equipped mum likelihood that they will be usable supply shall be capable of maintaining with life rafts having capacity for all in an emergency landing with wheels up. a cabin pressure corresponding with an persons aboard the airplane, the floata (2) When certification of ditching pro altitude of not more than 10,000 feet in tion time and trim will permit all oc visions is desired by the applicant, it shall standard atmosphere when the air cupants to leave their ditching stations be shown that at least one emergency plane’s flight altitude is the maximum exit for every 16 passengers is located for which certification is desired. and occupy the rafts. above the water line. (2) In the case of airplanes not (3) In airplanes for which two or more § 4b.375 Pressure control. Pressure equipped with life rafts having capacity emergency exits are required, the ratio of cabins shall be provided with at least for all persons aboard the airplane, the the number of exits on either side of the the following valves, controls, and indi airplane will float indefinitely with suf airplane to the total number required cators for controlling cabin pressure. ficient compartments above the water line Shall be not less than 1:3. At least one (a) At least two pressure relief valves, to accommodate all persons aboard the exit on the opposite side from the ex one or both of which may be the nor airplane. ternal main door shall be operable from mal regulating valve, shall be installed to (b) Compliance with the requirements the outside and shall be marked accord limit automatically the positive pressure of paragraph (a) of this section may be ingly for the guidance of rescue person differential to a predetermined value at demonstrated by buoyancy and trim nel. the maximum rate of flow delivered by computations in which suitable allow (4) The emergency exits shall be the pressure source. The combined ca ances are made for probable structural readily accessible, shall not require ex pacity of the relief valves shall be such damage and leakage. For airplanes ceptional agility of a person using them, that the failure of any one valve would equipped with fuel dump valves, the and shall be distributed so as to facilitate not cause an appreciable rise in the pres volume of fuel which could be dumped evacuation without crowding. sure differential. The pressure differen may be considered as buoyancy volume. (5) Each emergency exit shall provide tial shall be considered positive when the § 4b.362 Emergency exists. Passenger a clear and unobstructed opening to the internal pressure is greater than the and crew compartments designated as outside, the minimum dimensions of external. occupiable during .take-off and landing which shall be such that a 19 by 26 inch (b) At least one reverse pressure dif shall be provided with emergency exits ellipse can be inscribed therein. ferential relief valve (or equivalent) as prescribed in the following para (6) Reasonable provisions shall be shall be installed to prevent automati graphs. Individual compartments shall made against the jamming of emergency cally a negative pressure differential be considered as those closed spaces to exits as a result of fuselage deformation. which would damage the structure. which normal access is by a door, pas (7) The method of opening of emer (c) Means shall be provided by which sageway, or stair, any of which might re gency exits shall be simple and obvious. the pressure differential can be rapidly strict rapid evacuation of the airplane. (See § 4b.738 (c).) equalized. (a) Evacuation. In case of question (8) The proper functioning of emer (d) An automatic or manual regula concerning the adequacy of emergency gency exits shall be demonstrated by tor for controlling the intake and/or ex exists, it shall be demonstrated that the test. haust air flow shall be installed so that airplane can be completely evacuated in (9) For all landplane emergency exits the required internal pressures and air 30 seconds, or in a time equal to one sec which are more than 10 feet from the flow rates can be maintained. ond per occupant, whichever is greater, ground with the airplane on the ground (e) Instruments shall be provided at under conditions simulating a forced and wheels retracted, suitable means an appropriate crew station showing the landing. The following shall be ob shall be provided by which the occupants pressure differential, the absolute pres served during the demonstration: can safely descend to the ground. sure in the cabin, and the rate of change (1) The maximum number of persons Ventilation, Heating, and Pressurization of the absolute pressure. for whom seats are provided shall par (f) Warning indication shall be pro ticipate in the demonstration. § 4b.370 General. The requirements vided at an appropriate crew station to (2) The persons demonstrating the of §§ 4b.371 through 4b.376 shall apply to indicate when the safe or preset limits evacuation procedure shall not be briefed the ventilation, heating, and pressuriza on pressure differential and absolute more than once prior to the official dem tion of the aircraft. cabin pressure are exceeded. onstration. § 4b.371 Ventilation, (a) All passen (g) If the structure is not designed for (b) Number of exits. (1) The mini ger and crew compartments shall be pressure differentials up to the maximum mum number of exists per compartment suitably ventilated. relief valve setting in combination with shall be as follows : (b) Provision shall be made to prevent landing loads (see § 4b.216 (c)), a suit Minimum able warning placard shall be placed at Number of persons for number carbon monoxide concentration in excess whom seats of exits of one part in 20,000 parts of air. an appropriate crew station. are provided required (c) Provision shall be made to exclude § 4b.376 Tests. The complete pres 5 or less______1 fuel fumes. surized cabin, including doors, windows, More than 5, but not more than 15__ 2 More than 15, but not more than 22___ 3 (d) Where partitions between com and all valves, shall be tested as a pres More than 22, but not more than 29___ 4 partments are equipped with louvres or sure vessel for the pressure differential More than 29, but not more than 36_ 5 other means allowing air to flow between specified in § 4b.216 (c). The following Wednesday, January 25,1950 FEDERAL REGISTER 429 functional tests shall be performed up to the “A” category, if the presence of a eration of smoke or fire detectors In the working pressures: possible fire therein would be easily dis adjacent or other compartments within (a) Functional and capacity tests of cernible to a member of the crew while the airplane would occur as a result of the positive and negative pressure differ at his station, and if all parts of the fire contained in any one compartment, ential relief valves and the emergency compartment are easily accessible in either during or after extinguishment, release valve, simulating the condition flight. A hand fire extinguisher shall unless the extinguishing system floods of regulator valves closed; be available for each compartment. such compartments simultaneously. (b) Tests showing that all parts of (b) “B” category. Cargo and bag Miscellaneous the pressurization system will function gage compartments shall be classified properly under all possible conditions of in the “B” category, if sufficient access § 4b.390 Reinforcement near propel pressure, temperature, and moisture up is provided while in flight to enable a lers. Surfaces near propeller tips shall to the maximum altitude for which cer member of the crew to move by hand all have sufficient strength and stiffness to tification is desired; contents and-to reach effectively all parts withstand the effects of the induced vi (c) Flight tests demonstrating the of the compartment with a hand fire ex bration and of ice thrown from the pro performance of the pressure supply, tinguisher. Compliance shall be shown peller. Windows shall not be located in pressure and flow regulators, indicators, with the following: this area unless shown capable of with and warning signals in steady and (1) The design of the compartment standing the most severe ice impact stepped climbs and descents at rates cor shall be such that, when the access pro likely to occur. responding with the maximum attain visions are being used, no hazardous § 4b.391 Leveling marks. Reference able without exceeding the operating quantity of smoke, flames, or extinguish marks shall be provided for use in level limitations of the airplane, up to the ing agent will enter any compartment ing the airplane when making weight maximum altitude for which certifica occupied by the crew or passengers. and balance determinations on the tion is desired; (2) Each compartment shall be ground. (d) Tests showing that all doors and equipped with a separate system of an emergency exits operate properly after approved type smoke detector or fire SUBPART E— POWERPLANT INSTALLATION being subjected to the tests specified in detector other than a heat detector to {RECIPROCATING ENGINES) paragraph (c) of this section. give warning at the pilot or flight en General gineer station. Fire Prevention (3) Hand fire extinguishers shall be § 4b.400 Scope, (a) The powerplant readily available for use in each com installation shall be considered to include § 4b.380 General. Compliance shall partment. all components of the airplane which are be shown with the fire prevention re (4) The compartment shall be com necessary for its propulsion. It shall quirements of §§4b.381 through 4b.384. pletely lined with fire-resistant material, also be considered to include all compo § 4b.381 Cabin interiors. All com except that additional service lining of nents which affect the control of the partments occupied or used by the crew flame-resistant material may be em major propulsive units or which affect or passengers shall comply with the fol ployed. their safety of operation between nor lowing provisions. (c) “C” category. Cargo and baggage mal inspections or overhaul periods. (a) The materials in no case shall be compartments shall be classified in the (See §§ 4b.604 and 4b.613 for instrument less than flash-resistant. “C” category, if they do not conform to installation and marking.) (b) The wall and ceiling linings, the the prerequisites for the “A” or “B” cate (b) All components of the powerplant covering of all upholstering, floors, and gories. Compliance shall be shown with installation shall be constructed, ar furnishings shall be flame-resistant. the following. ranged, and installed in such a manner (c) Compartments where smoking Is (1) Each compartment shall be as will assure their continued safe oper to be permitted shall be equipped with equipped with:. ation between normal inspections or ash trays of the self-contained type (1) A separate system of an approved overhaul periods. which are completely removable. All type smoke detector or fire detector other (c) Accessibility shall be provided to other compartments shall be placarded than heat detector to give warning at permit such inspection and maintenance against smoking. the pilot or flight engineer station; as is necessary to assure continued air (d) All receptacles for used towels, (ii) An approved built-in fire-extin worthiness. papers, and waste shall be of fire-resist guishing system controlled from the pilot (d) Electrical interconnections shall ant material, and shall incorporate or flight engineer station. be provided to prevent the existence of covers or other provisions for containing (2) Means shall be provided to exclude differences of potential between major possible fires. hazardous quantities of smoke, flames, components of the powerplant installa § 4b.382 Cargo and baggage compart or extinguishing agent from entering tion and other portions of the airplane. ments. (a) Cargo and baggage com into any compartment occupied by the § 4b.401 Engines—(a) Type certifica partments shall include no controls, crew or passengers. tion. All engines shall be type certifi wiring, lines, equipment, or accessories (3) Ventilation and drafts shall be cated in accordance with the provisions the damage or failure of which would af controlled within each compartment so of Part 13 of the Civil Air Regulations. fect the safe operation of the airplane, that the extinguishing agent provided (b) Engine isolation. The engines unless such items are adequately can control any fire which may start shall be so isolated, each from the other, shielded, isolated, or otherwise protected within the compartment. that the failure or malfunctioning of any so that they cannot be damaged by move (4) The compartment shall be com one engine, or any part of the powerplant ment of cargo in the compartment, and pletely lined with fire-resistant material, installation serving any one engine, will so that any breakage or failure of such except that additional service lining of not prevent the safe operation of the item will not create a fire hazard. flame-resistant material may be em remaining engine or engines. (b) Provision shall be made to pre ployed, (c) Control of engine rotation. Means vent cargo or baggage from interfering § 4b.384 Proof of compliance, (a) shall be provided for stopping and re with the functioning of the fire-protec Compliance with those provisions of starting the rotation of any engine in tive features of the compartment. paragraphs (a) and (b) of § 4b.383. which dividually in flight. All components (c) All materials used in the con refer to the compartment accessibility, provided for this purpose which are lo struction of cargo or baggage compart the entry of hazardous quantities of cated on the engine side of the fire wall ments, including tie-down equipment, smoke or extinguishing agent into com and which might be exposed to fire, shall shall be flame-resistant. partments occupied by the crew or pas be of fire resistant construction. (See 14b.383 Cargo compartment classi sengers, and the dissipation of the ~ also § 4b.449.) fication. All cargo and baggage com extinguishing agent in category “C” com § 4b.402 Propellers. Propellers shall partments shall include provisions for partments shall be demonstrated by tests be type certificated in accordance with safeguarding against fires according to in flight. the provisions of Part 14 of the Civil Air the following classifications: (b) It shall also be demonstrated dur Regulations. The maximum propeller (a) "A” category. Cargo and bag ing the tests prescribed in paragraph (a) shaft rotational speed and the engine gage compartments shall be classified in of this section that no inadvertent op power permissible for use in the airplane No. 16----- 6 430 PROPOSED RULE MAKING shall not exceed the corresponding limits (3) Positive clearance shall be pro (4) The attitude of glide at a speed of for which the propeller has been cer vided between other rotating portions of 1.3 Vs0. at landing weight. tificated. the propeller or spinner and stationary (b) During the test prescribed in § 4b.403 Propeller vibration. The portions of the airplane. paragraph (a) of this section, fuel shall magnitude of the propeller blade vibra § 4b.406 Propeller de-icing provisions. be delivered to the engine at a pressure tion stresses under all normal conditions (a) Airplanes intended for operation un not less than the minimum established of operation shall be determined by ac der atmospheric conditions conducive to for proper engine operation. In addition tual measurement or by comparison with the formation of propeller ice shall be the following shall be met. similar installations for which such provided with means for tha prevention (1) The quantity of fuel in the tank measurements have been made. The and removal of such ice accumulations. being tested shall not exceed the amount vibration stresses thus determined shall (b) If combustible fluid is used for established as the unusable fuel supply not exceed values which have been dem propeller de-icing, the provisions of for that tank, as determined by demon onstrated to be safe for continuous §§ 4b.480 through 4b.483, inclusive, shall stration of compliance with the provi operation. sions of § 4b.416 (see also §§4b.420 and be complied with. 4b.613 (c)), together with whatever § 4b.404 Propeller pitch and speed Fuel System Operation and Arrangement minimum quantity of fuel it may be nec limitations, (a) The propeller pitch § 4b.410 General, (a) The fuel sys essary to add for the purpose of con and speed shall be limited to values ducting the flow test. which will assure safe operation under tem shall be constructed and arranged in such a manner as to assure a flow of (2) If a fuel flowmeter is provided, the all normal conditions and which will as meter shall be blocked during the flow sure compliance with the performance fuel to each engine at a rate and pressure which have been established for proper test and the fuel shall flow through the requirements specified in §§4b.ll0 meter by-pass. through 4b.125. engine functioning under all normal conditions, including all maneuvers for (c) The test prescribed in paragraph (b) A propeller speed limiting means (a) of this section may be demonstrated shall be provided at the governor. Such which the airplane is intended. (For fuel system instruments see § 4b.604.) by a ground test on the airplane or on a means shall be set to limit the maximum representative mock-up of the fuel possible governed engine speed to a value (b) The fuel system shall be so ar system. not exceeding the maximum permissible ranged that no one fuel pump can draw r. p. m. fuel from more than one tank at a time § 4b.414 Pump systems, (a) The (c) The low pitch blade stop in the unless means are provided to prevent fuel flow rate for pump systems (main propeller, or other means used to limit introducing air into the system. and reserve supply) shall be 0.9 pound the low pitch position, shall be set so § 4b.411 Fuel system independence. per hour for each take-off horsepower that the propeller speed does not exceed The fuel system shall be arranged to per or 125 percent of the actual take-off fuel 103 percent of the maximum permissible mit operation in such a manner that the consumption of the engine, whichever is engine r. p. m. under the following con failure of any one component will not greater. ditions: result in the irrecoverable loss of power (b) The fuel flow rate specified in (1) Propeller blades at the low pitch of more than one engine. paragraph (a) of this section shall be limit and governor inoperative; applicable to both the primary engine- (2) Engine operating at take-off man § 4b.412 Pressure cross-feed arrange driven pump and to emergency pumps. ifold pressure with the airplane station ments. (a) Pressure cross-feed lines It shall be available when the pump is ary under standard atmospheric condi shall not pass through portions of the running at the speed at which it would tions. airplane intended to carry personnel or normally be operating during take-off. cargo, unless means are provided to per In the case of hand operated pumps, the § 4b.405 Propeller clearance. With mit the flight personnel to shut off the speed shall be considered to be not more the airplane loaded to the maximum supply of fuel to these lines, or unless than 60 complete cycles (120 single weight and at the most adverse center the lines are enclosed in a fuelproof and strokes) per minute. of gravity position and the propellers fumeproof shroud which is ventilated in the most adverse pitch position, the and drained to the exterior of the § 4b.415 Transfer systems. The pro propeller clearances shall not be less airplane. visions of § 4b.414 shall also apply to than the following, unless smaller clear (b) The shrouds specified in para transfer systems, except that the required ances are substantiated for the particu graph (a) of this section need not be fuel flow rate for the engine or engines lar design involved. used if the lines incorporate no fittings involved shall be established upon the (a) Ground. Seven inches of clear within the personnel or cargo areas and basis of maximum continuous power and ance (for airplanes equipped with nose- if they are suitably routed or protected its corresponding speed instead of take wheel type landing gears) or 9 inches of to safeguard against accidental damage. off power and its corresponding speed. clearance (for airplanes equipped with (c) Lines which can be Isolated from § 4b.416 Determination of unusable tail-wheel type landing gears) shall be the remainder of the fuel system by fuel supply and fuel system operation on provided with the landing gear statically means of valves at each end shall in low fuel, (a) Upon presentation of the deflected and the airplane in the level, corporate provisions for the relief of ex airplane for test, the applicant shall normal take-off, or taxying attitude, cessive pressures which may result from select the quantity of fuel with which to whichever is most critical. In addition, exposure of the isolated line to high demonstrate compliance with this pro there shall be positive clearance between ambient temperatures. vision. He shall indicate which of the the propeller and the ground when, with conditions specified in paragraph (b) of the airplane in the level take-off atti § 4b.413 Fuel flow rate, (a) The this section are most likely to be critical tude, the critical tire is completely de ability of the fuel system to provide the from the standpoint of establishing the flated and the corresponding landing required fuel flow rate shall be demon unusable fuel supply and the order in gear strut is completely bottomed. strated when the airplane is in the at which the other conditions .may be (b) Water. A minimum clearance of titude which represents the most adverse critical. 18 inches shall be provided unless com condition from the standpoint of fuel (b) The ususable fuel supply for each pliance with § 4b. 181 can be demon feed which the airplane is designed to tank used for take-off and landing shall strated with less clearance. attain. The following shall be considered be established as not less than the quan (C) Structure. (1) One inch radial in this respect: tity at which the first evidence of mal clearance shall be provided between the (1) The normal ground attitude, functioning occurs under the following blade tips and the airplane structure, or conditions: (See § 4b.420.) < whatever additional radial clearance is (2) Climb with take-off flaps, landing (1) Level flight at maximum continu necessary to preclude harmful vibration gear up, using take-off power, at speed ous power or at the power required for of tt *3 propeller or airplane. V. as determined in § 4b.ll4 (b) at land level flight at Vc, whichever is less ; (2) One-half inch longitudinal clear ing weight, (2) Climb with take-off flaps and land ance shall be provided between the pro (3) Level flight at maximum continu ing gear up, using take-off power, at peller blades or cuffs and stationary ous power or the power required for level speed V2 as determined in § 4b.ll4 (b), portions of the airplane. flight at Vc, whichever is less, at landing weight; Wednesday, January 25,1950 FEDERAL REGISTER 431 (3) Rapid application of maximum Fuel System Construction and operating range of speeds of the engine continuous power and subsequent transi Installation is more critical, in which case the latter tion to climb at speed Vv with retrac § 4b.420 General, (a) Fuel tanks speed shall be employed and the time of tion of flaps and. landing gear, from a shall be capable of withstanding without test shall be adjusted to accomplish the power-off glide at 1.3 V«0, with flaps and failure all vibration, inertia, fluid, and same number of vibration cycles. landing gear down, at landing weight. structural loads to which they may be (4) In conjunction with the vibration (c) If an engine can be supplied with subjected in operation. test, the tank assembly shall be rocked fuel from more than one tank, it shall be ‘ (b) Flexible fuel tank liners shall be through an angle of 15° on either side of possible to regain the full fuel pressure of an acceptable type or shall be proven the horizontal (30° total) about, an axis of that engine in not more than 20 sec suitable for the particular application. parallel to the axis of the fuselage. onds after switching to any fuel tank (c) The fuel tanks, as installed, shall (5) The assembly shall be rocked at after engine malfunctioning becomes ap be designed to withstand a minimun the rate of 16 to 20 complete cycles per parent due to the depletion of the fuel internal pressure of 3.5 p. s. i. minute. supply in any tank from which the (d) Integral type fuel tanks shall be (c) In the case of tanks with non engine can be fed. Compliance with this provided with facilities for the inspection metallic liners a specimen liner of the provision shall be demonstrated in level and repair of the tank interior. same basic construction as that to be flight. (e) The total usable capacity of the used in the airplane, when installed in a (d) TJie unusable fuel supply for all fuel tanks shall not be less than 0.15 gal suitable representative test tank, shall tanks other than those used for take-off lon for each maximum continuous horse withstand satisfactorily the slosh test as and landing shall be established as not power for which the airplane is specified in paragraph (b) of this section less than the quantity at which the first certificated. with fuel at a temperature of 110° F. evidence of malfunctioning occurs under (f) The unusable fuel capacity shall § 4b.422 Fuel tank installation: (a) the conditions specified in paragraph (b) be the minimum quantity of fuel which The method of support for fuel tanks (1) of this section. It shall be accept will permit compliance with the provi shall not be such as to concentrate loads, able to demonstrate compliance with sions of § 4b.416. resulting from the weight of the fuel in this requirement by a ground test. (g) The fuel quantity, gauge shall be the tank, on unsupported tank surfaces. § 4b.417 Fuel system hot weather op adjusted to account for the unusable .The following shall be applicable. eration. (a) To prove satisfactory hot fuel supply as specified in § 4b.613 (c). (1) Pads shall be provided to prevent weather operation the airplane shall be (h) The weight of the unusable fuel chafing between the tank and its sup climbed from the altitude of the airport, supply shall be included in the empty ports. chosen by the applicant, to the altitude weight of the airplane. (2) Materials employed for padding corresponding with that at which the § 4b.421 Fuel tank tests, (a) Fuel shall be nonabsorbent or shall be treated one-engine-inoperative best rate of climb tanks shall be capable of withstanding to prevent the absorption of fluids. is not greater than the appropriate en the following pressure tests without fail (3) If flexible tank liners are em route climb specified in § 4b.l20 (c). ure or leakage. The pressures may be ployed, they shall be so suported that There shall be no evidence of vapor lock applied in a manner simulating the ac the liner is not required to withstand or other malfunctioning. The climb tual pressure distribution in service. fluid loads. . , test shall be conducted under the follow (1) Conventional metal tanks and (4) Interior surfaces of compartments ing conditions. nonmetallic tanks the walls of which are for such liners shall be smooth and free (1) All engines shall operate at maxi not supported by the airplane structure of projections which may cause wear of mum continuous power, except that take shall be submitted to a pressure of the liner, unless provisions are made for off power shall be used for the altitude 3.5 p. s. i., or the pressure developed dur protection of the liner at such points or range extending from 1,000 feet below ing the maximum ultimate acceleration unless the construction of the liner it the critical altitude through the critical of the airplane with a full tank, which self provides such protection. altitude. The time interval during ever is greater. (b) Spaces adjacent to the surfaces which take-off power is used shall not (2) Integral tanks shall be submitted of the tank shall be ventilated consistent exceed the take-off time limitation. ' to a minimum pressure of 3.5 p. s. i. un with the size of the compartment to avoid (2) The weight shall be with full fuel less the pressure developed during the fume accumulation in the case of minor tanks, minimum crew, and such ballast maximum limit acceleration of the air leakage. If the tank is in a sealed com as is required to maintain the center of partment it shall be acceptable to limit plane with a full tank exceeds this value, the ventilation to that provided by drain gravity within allowable limits. in which case a hydrostatic head', or holes of sufficient size to prevent exces (3) The speed of climb shall not ex equivalent test, shall be applied to du sive pressure resulting from altitude ceed that which will permit compliance plicate the acceleration loads in so far as changes. with the climb requirement specified in possible, except that the pressure need (c) Location of fuel tanks shall com § 4b.ll9 (b). not exceed 3.5 p. s. i. on surfaces not exposed to the acceleration loading. ply with the provisions of § 4b.481 (a). (4) A fuel temperature not less than (3) Nonmetallic tanks the walls of (d) No portion of engine nacelle skin 110° P. which are supported by the airplane which lies immediately behind a major (b) The test prescribed in paragraph structure shall be submitted to a pres air egress opening from the engine com (a) of this section shall be conducted sure of 3.5 p. s. i. when mounted in the partment shall act as the wall of an in either in flight or on the ground closely airplane structure, tegral tank. simulating flight conditions. Where the ,(b) Tanks with large unsupported or (e) Fuel tanks shall be isolated from flight test is conducted in cold weather, unstiffened flat areas shall be capable of personnel compartments by means of it may be required that fuel tank sur withstanding the following tests, or fume and fuel proof enclosures. faces, fuel lines, and other fuel system other equivalent tests, without leakage § 4b.423 Fuel tank expansion space. parts subjected to cooling action from or failure. (a) Fuel tanks shall be provided with cold air be suitably insulated to simulate, (1) The complete tank assembly to an expansion space of not less than 2 in so far as practicable, flight in hot gether With its supports shall be sub percent of the tank capacity. weather. jected to a vibration test when mounted (b) It shall not be possible to fill the in a manner simulating t h e actual fuel tank expansion space inadvertently § 4b.418 Flow between interconnected installation. when the airplane is in the normal tanks. In fuel systems with tanks the (2) The tank assembly shall be vi ground attitude. outlets of which are interconnected, it brated for 25 hours at an amplitude of § 4b.424 Fuel tank sump, (a) Each shall not be possible for fuel to flow be not less than %2 inch while filled two- fuel tank shall be provided with a sump tween tanks in quantities sufficient to thirds full of water. having a capacity of not less than either cause an overflow of fuel from the tank (3) The frequency of vibration shall 0.25 percent of the tank capacity or 1.16 vent when the airplane is operated as be 90 percent of the maximum Continu of a gallon, whichever is greater. specified in § 4b.416 (b) and the tanks ous rated speed of the engine unless (b) The fuel tank sump capacity are full. some other frequency within the normal specified in paragraph (a) of this section 432 PROPOSED RULE MAKING shall be effective with the airplane in (a) The clear area of the fuel tank which relative motion may exist shall the normal ground attitude. The fuel outlet strainer shall not be less than 5 incorporate provisions for flexibility. tank shall be constructed to permit times the area of the fuel tank outlet (c) Flexible connections in lines drainage of any hazardous quantity of line. which may be under pressure and sub water from all portions of the tank to (b) The diameter of the strainer shall jected to axial loading shall employ flex the sump when the airplane is in the not be less than the diameter of the fuel ible hose assemblies rather than hose ground attitude. tank outlet. clamp connections. (c) Fuel tank sumps shall be provided (c) Finger strainers shall be accessible (d) Flexible hose shall be of an accept with a drain to permit complete drainage for inspection and cleaning. able type or shall be shown to be suitable of the sump on the ground. The drain Fuel System Components for the particular application. shall discharge clear of all portions of § 4b.433 Lines and fittings in desig the airplane and shall be provided with § 4b.430 Fuel pumps, (a) If the en nated fire zones. Fuel lines and fittings means fdr positively or automatically gine fuel supply is maintained by means in all designated fire zones (see § 4b.480) locking the drain in the closed position. of pumps, one fuel pump for each engine shall comply with the provisions of The drain shall be accessible. shall be engine driven. § 4b.483. (b) Fuel pumps shall meet the perti § 4b.425 Fuel tank filler connection. nent flow requirements of § 4b.413. § 4b.434 Fuel valves. In addition to (a) The fuel tank filler connections shall (c) Unless equivalent provisions are the requirements of § 4b.482 for shut-off be marked as prescribed in § 4b.738 (b). available for the continuous supply of means, all fuel valves shall be provided (b) Provision shall be made to pre fuel to all engines in case of the failure with positive stops or suitable index pro vent the entrance of fuel into the fuel of any positive displacement fuel system visions in the “on” and “off” positions tank compartment or any portions of the pump, the pump itself shall incorporate and shall be supported so that loads re airplane other than the tank itself. an integral bypass. Engine fuel injec sulting from their operation or from (c) Recessed fuel filler connections tion pumps which are certificated as an accelerated flight conditions are not which retain any appreciable quantity integral part of the engine need not in transmitted to the lines attached to the of fuel shall incorporate a drain, and corporate a bypass. valve. the drain shall discharge clear of all (d) Emergency fuel pumps shall be portions of the airplane. § 4b.435 Fuel strainer. A fuel strainer provided to permit supplying all engines complying with the following paragraphs (d) The filler cap shall provide a fuel- with fuel in case of the failure of any one tight seal. shall be provided between the fuel tank fuel system pump, unless the engine- outlet and the carburetor inlet. § 4b.426 Fuel tank vents and car driven pump has been approved with the (a) If an engine-driven fuel pump is buretor vapor vents, (a) Fuel tanks engine and suitable precautions are provided, the strainer shall be located shall be vented from the top portion of taken to avoid vapor lock and pump between the tank outlet and the engine- the expansion space in such a manner cavitation. If the only pump used in the driven pump inlet. that the tank is vented under all normal system is an engine fuel-injection pump (b) The strainer shall be accessible flight conditions. The following shall which has been certificated as an inte for drainage and cleaning, and the be applicable. gral part of the engine, an emergency strainer screen shall be easily remov (1) Vent outlets shall be so located pump need not be provided. able. and constructed as to prevent the pos (e) Emergency pumps shall be capable (c) The strainer shall be mounted in sibility of being obstructed by ice or other of complying with the same flow require a manner not to cause its weight to be foreign matter. ments as are prescribed for the main supported by the connecting lines or by (2) The vent shall be constructed to pumps. the inlet or outlet connections of the preclude the possibility of siphoning fuel (f) Hand emergency pumps shall not strainer itself. during normal operation. require excessive effort for their con (3) The vent shall be of sufficient size tinued operation at the rate of 60 com § 4b.436 Fuel system drains. Drain to permit the rapid relief of excessive plete cycles (120 single strokes) per age of the system shall be accomplished differences of pressure between the in minute. by fuel strainer drains and other drains terior and exterior of the tank. (g) Emergency pumps shall be avail as provided in § 4b.424. The following (4) Air spaces of tanks the outlets of able for immediate use in case of failure shall apply. which are interconnected shall also be of any other pump. (a) Drains shall discharge clear of all interconnected. (h) If engine-driven pumps are ca portions of the airplane and shall incor (5) There shall be no points in the pable of maintaining flight up to 6,000 porate means for positive or automatic vent line where moisture may accumu feet altitude and with 110° F. fuel with locking of the drain in the closed posi late with the airplane in either the out the aid of auxiliary pumps, the tion. ground or the level flight attitudes un auxiliary pump may be considered as (b) All fuel system drains shall be less drainage is provided. emergency pumps. accessible. (6) Vents and drainage shall not ter (c) If drainage of the strainer per minate at points where the discharge of § 4b.431 Fuel pump installation. mits compliance with paragraphs (a) fuel from the vent outlet will constitute (a) Provision shall be made to maintain and (b) of this section, no additional a fire hazard or from which fumes may the fuel pressure at the inlet to the car drains need be provided unless it is pos enter personnel compartments. buretor within the range of limits estab sible for a hazardous quantity of water (b) Carburetors which are provided lished for proper engine operation. or sediment to be trapped therein. (See (b) When necessary for the mainte also § 4b.483 (c).) with vapor elimination connections shall nance of the proper fuel delivery pres be provided with a vent line which will sure, a connection shall be provided to § 4b.437 Fuel jettisoning system, (a) lead vapors back to one of the fuel tanks. transmit the carburetor air intake static If the maximum take-off weight for The vents shall comply with the follow which the airplane is certificated ex ing. pressure to the proper fuel pump relief valve connection. In such cases, to ceeds 105 percent of its maximum land (1) Satisfactory provisions shall be avoid erroneous fuel pressure reading, ing weight, provision shall be made to incorporated in the vent system to avoid the gauge balance lines shall be inde permit the jettisoning of fuel from the stoppage by ice. pendently connected to the carburetor maximum take-off to the maximum (2) If more than one fuel tank is pro inlet pressure. landing weight at an average rate of 1 vided and it is necessary to use the tanks percent of the maximum take-off weight in a definite sequence, the vapor vent re § 4b.432 Fuel system lines and fit per minute, except that the time required turn line shall lead back to the fuel tank tings. (a) Fuel lines shall be installed to jettison the fuel need not in any case used for take-off and landing. and supported to prevent excessive vi be less than 10 minutes when the air § 4b.427 Fuel tank outlet. A fuel bration and to withstand loads due to plane is flown in the following conditions. strainer, of 8 to 16 meshes per inch, shall fuel pressure and accelerated flight The fuel jettisoning system shall permit be provided either for the fuel tank out conditions. the safe discharge of fuel clear of all let or for the booster pump. Strainers (b) Lines which are connected to portions of the airplane under the fol shall comply with the following. components of the airplane between lowing conditions at the maximum take- Wednesday, January 25,1950 FEDERAL REGISTER 433 off weight and with flaps and landing (a) Oil tank expansion space. (1) Oil (3) The breather shall not discharge gear up: tanks shall have an expansion space of into the engine air induction system. (1) Power-off glide at a speed of 1.4 not less than either 10 percent of the (See also § 4b.483 (c).) tank capacity or 0.5 gallon, whichever § 4b.445 Oil valves, (a) The re (2) Climb at the one-engine-inopera Is greater. quirements of § 4b.482 for shut-off means tive speed with the critical engine in (2) Reserve oil tanks which have.no shall be complied with. Closing of oil operative, the other engines at maximum direct connection to any engine shall shut-off means shall not prevent feath continuous power; have an expansion space which is not ering the propeller. (3) Level flight at a speed of 1.4 V$v less than 2 percent of the tank capacity. (b) All oil valves shall be provided if found critical as a result of tests speci (3) It shall not be possible to fill the with positive stops or suitable index fied in subparagraphs (1) and (2) of this oil tank expansion space inadvertently provisions in the “on” and “off” positions, paragraph. when the airplane is in the normal and shall be supported so that loads re (b) Unless it is demonstrated that the ground attitude. sulting from their operation or from ac flap position does not adversely affect (b) Oil tank filler connection. (1) Oil celerated flight conditions are not trans fuel jettisoning, a placard shall be pro tank filler connections shall be marked mitted to the lines attached to the valve. vided adjacent to the jettisoning control as prescribed in § 4b.738 (b). to warn flight personnel against jettison (2) Recessed oil filler connections § 4b.446 Oil radiators, (a) Oil radi ing fuel while the flaps are lowered. A which retain any appreciable quantity ators shall be capable of withstanding notation to this effect shall also be in of oil shall incorporate a drain, and the without failure all vibration, inertia, and cluded in the Airplane Flight Manual drain shall discharge clear of all por oil pressure loads to which they may be (§ 4b.740). tions of the airplane. subjected in operation. (c) The fuel jettisoning system and its (3) The filler cap shall provide an oil- (b> Oil radiator air ducts shall be lo operation shall be free of fire hazard. tight seal. cated so that flames issuing from normal (d) Neither fumes nor fuel shall enter (c) Oil tank vent. (1) Oil tanks shall openings of the engine nacelle in case of any portion of the airplane. be vented from the top portion of the fire shall not impinge directly upon the (e) The jettisoning operation shall not expansion space in such a manner that radiator. adversely affect the controllability of the the tank is vented under all normal flight § 4b.447 Oil filters. ■ If the airplane airplane. conditions. is equipped with an oil filter, the filter (f) Compliance with the provisions (2) Oil tank vents shall be arranged shall be constructed or installed in such of paragraphs (c), (d), and (e) of this so that condensation of water vapor a manner that complete blocking of the section shall be demonstrated in flight. which may freeze and obstruct the line flow through the filter element will not (g) It shall not be possible to jettison cannot accumulate at any point. (See ' prevent the safe operation of the engine fuel in the tanks used for take-off and also § 4b.483 (c).) oil supply system. landing below the level providing 45 (d) Oil tank outlet. The oil tank out minutes flight at 75 percent maximum let shall not be enclosed or covered by § 4b.448 Oil system drains. Aces- continuous power, except that all fuel any screen or other guard which may sible drains shall be provided to permit may be Jettisoned where an auxiliary impede the flow of oil. (See also safe drainage of the entire oil system control is provided independent of the 9 4b.449.) and shall incorporate means for positive main jettisoning control. (e) Flexible oil tank liners. Flexible or automatic locking of the drain in the (h) The fuel jettisoning valve shall oil tank liners shall be of an acceptable closed position. (See also § 4b.483 (c).) permit the flight personnel to close the type or shall be shown to be suitable for § 4b.449 Propeller feathering system. valve during any portion of the jettison the particular application. (a) If the propeller feathering system is ing operation. (See § 4b.475 for fuel § 4b.442 Oil tank tests, (a) Oil tanks dependent upon the use of the engine oil jettisoning system controls.) shall be capable of withstanding without supply, provision shall be made to trap a Oil System failure all vibration, inertia, and fluid quantity of oil in the tank in case the loads to which they may be subjected in supply becomes depleted due to failure of § 4b.440 General, (a) Each engine operation. any portion of the lubricating system shall be provided with an independent oil (b) Oil tank tests shall be the same as other than the tank itself. system capable of supplying the engine fuel tank tests (see § 4b.421), except as (b) The quantity of trapped oil shall with an appropriate quantity of oil at a follows: be sufficient to accomplish the feather temperature not exceeding the maximum (1) The test pressure specified in ing operation and shall be available only which has been established as safe for § 4b.421 (a) shall be 5 p. s. i. to the feathering pump. continuous operation. (For oil system (c) The ability of the system to ac instruments see §§4b.604 and 4b.735.) (2) The test fluid specified in § 4b.421 complish feathering with the trapped (b) The oil capacity of the system (c) shall be oil at a temperature of supply of oil shall be demonstrated. It shall not be less than one gallon for 250° F. shall be acceptable to make this demon every 30 gallons of fuel capacity, unless § 4b.443 Oil tank installation. Oil stration on the ground. provisions are made for transferring oil tank installation shall comply with the Cooling System between tanks in flight or unless a re provisions of § 4b.422, except that oil serve oil supply which can be fed to any tanks may be located on the engine side § 4b.450 General. The powerplant tank during flight is provided. cooling provisions shall be capable of (c) If either a reserve oil system or an of the fire wall. maintaining the temperatures of major oil transfer system is provided, the total § 4b.444 Oil lines and fittings—(a) powerplant components, engine fluids, oil capacity need not exceed one gallon General. Oil lines shall comply with the and the carburetor intake air within the for each 40 gallons of fuel capacity. provisions of § 4b.432. established safe values under all condi (d) Oil-fuel ratios lower than those (b) Lines and fittings in designated tions of ground and flight operation. prescribed in paragraphs (b) and (c) of fire zones. Oil lines and fittings in all (For cooling system instruments see this section shall be acceptable if sub §§ 4b.604 and 4b.734.) stantiated by data indicating unusually designated fire zones (see § 4b. 480) shall low oil consumption of the engine. comply with the provisions of § 4b.483. § 4b.451 Cooling tests—(a) General. (e) The ability of the oil cooling pro (c) Engine breather lines. (1) En Compliance with the provisions of visions to maintain the oil inlet tem gine breather lines shall be arranged so § 4b.450 shall be demonstrated under that condensation of water vapor which critical ground, water, and flight operat perature to the engine at or below the ing conditions. If the tests are con maximum established value shall be may freeze and obstruct the line cannot ducted under conditions which deviate demonstrated in accordance with perti accumulate at any point. from the maximum anticipated air tem nent provisions of § § 4b.450 through (2) Breathers shall discharge in a perature (see paragraph (b) of this sec 4b.454. location which will not constitute a fire tion) , the recorded powerplant tempera § 4b.441 Oil tank construction. The hazard in case foaming occurs and so tures shall be corrected in accordance following requirements shall apply to the that the emitted oil will not impinge with the provisions of paragraphs (b) construction of the oil tank. upon the pilot windshield. and (c) of this section. The corrected 434 PROPOSED RULE MAKING temperatures determined in this manner (a) The take-off cooling test shall be (2) Pads shall be provided to prevent shall not exceed the maximum estab commenced by stabilizing temperatures chafing between the tank and the sup-' lished safe values. The fuel used during during level flight at 75 percent of maxi port. Material used for padding shall be the cooling tests shall be of the minimum mum continuous power (all engines op nonabsorbent or shall be treated to pre octane number approved for the engines erating) with the appropriate cowl flap vent the absorption of flammable fluids. involved, and the mixture settings shall and shutter settings. (d) Coolant tank filler connection. be those used in normal operation. The (b) After all temperatures have sta (1) Coolant tank filler connections shall test procedures shall be as outlined in bilized, the climb shall be started at the be marked as specified in § 4b.738 (b). § § 4b.452 through 4b.454. lowest practicable altitude and shall be (2) Recessed coolant filler connections (b) Maximum - anticipated air tem conducted with one engine inoperative which retain any appreciable quantity of perature. The maximum anticipated air and its propeller feathered. coolant shall incorporate a drain, and temperature (hot day condition) shall be (c) The remaining engines shall be the drain shall discharge clear of , all por 100° F. at sea level, decreasing from this operated at take-off rpm and power (or tions of the airplane. value at the rate of 3.6° F. per thousand full throttle when above the take-off § 4b. 457 Coolant system installation. feet of altitude above sea level until a critical altitude) for the same time inter The following requirements shall apply temperature of —67° F. is reached above val as take-off power is used during de to the installation of the coolant system which altitude the temperature shall be termination of the take-off flight path components. constant at —67° F. (see § 4b.ll6). (a) Fire-resistant coolant lines and (c) Correction factor for cylinder (d) At the end of the time interval fittings. If the coolant used will ignite head, oil inlet, carburetor air, and engine prescribed in paragraph (c) of this sec and burn under the conditions of power- coolant outlet temperatures. The cylin tion the power shall be reduced to the plant fires, all lines and fittings located der head, oil inlet, carburetor air, and maximum continuous power and the within designated fire zones shall comply engine coolant outlet temperatures shall climb continued until at least 5 minutes with the provisions of § 4b.483. be corrected by adding the difference after the occurrence of the highest (b) Coolant radiators. (1) Coolant between the maximum anticipated air temperature recorded. radiators shall be capable of withstand temperature and the temperature of the (e) The speed used during take-off ing without failure all vibration, inertia, ambient air at the time of the first oc power operation (paragraph (c) of this and coolant pressure loads to which they currence of maximum head, air, oil, or section) shall not exceed the speed used may be subjected in operation. coolant temperature recorded during the during determination of the take-off (2) Radiators shall be supported in a cooling test, unless a more rational cor flight path. manner which will permit expansion due rection is shown to be applicable. § 4b.454 Cooling test procedure for to operating temperatures and which will (d) Correction factors for cylinder flying boat operation. In the case of prevent the transmittal of harmful vi barrel temperatures. Cylinder barrel flying boats, cooling shall be demon bration to the radiator. temperatures shall be corrected by add strated during taxying down wind for (3) The air intake duct to the coolant ing 0.7 of the difference between the 10 minutes at 5 m. p. h. above the step radiator shall be so located that in case maximum anticipated air temperature speed. of fire, flames issuing from normal open and the temperature of the ambient air ings of the engine nacelle cannot impinge at the time of the first occurrence of the § 4b.455 Liquid cooling systems. Each directly upon the radiator. maximum cylinder barrel temperature liquid-cooled engine shall be provided (c) Coolant system drains. (1) One recorded during the cooling test, unless with an independent cooling system. or more drains'shall be provided to per a more rational correction is shown to be The coolant system shall be so arranged mit drainage of the coolant system, in applicable. that no air or vapor can be trapped in cluding the coolant tank, radiator, and § 4b.452 Climb cooling test procedure. any portion of the system, other than the engine, when the airplane is in the (a) The climb cooling test shall be con the expansion tank, either during filling normal ground attitude. ducted with the critical engine inoper or during operation. No flammable (2) Drains shall discharge clear of all ative and its propeller feathered. coolant shall be used. portions of the airplane and shall in (b) All remaining engines shall be § 4b.456- Coolant tank—(a) General. corporate means for positive locking of operated at their maximum continuous The tank shall have a usable coolant the drain in the closed position. power or at full throttle when above the capacity of not less than one gallon and (3) Coolant system drains shall be ac critical altitude. shall be capable of withstanding without cessible. (c) After stabilizing temperatures in failure all vibration, inertia, and fluid Induction and Exhaust Systems flight, the climb shall be started at or be loads to which it may be subjected in § 4b.460 General, (a) The engine air low the lower of the two following alti operation. Coolant tanks shall be pro induction system shall permit supplying tudes and shall be continued until at vided with an expansion space of not less an adequate quantity of air to the engine least 5 minutes after the occurrence of than 10 percent of the total coolant the highest temperature recorded, or system capacity. It shall not be possible under all conditions of operation. until the maximum altitude is reached (b) The induction system shall pro inadvertently to fill the expansion space vide air to permit acceptable fuel meter for which certification is desired: with the airplane in the normal ground (1) 1,000 feet below the engine criti attitude. ing and mixture distribution with the cal altitude, induction system valves in any position. (b) Coolant tank tests. Coolant tank (c) Each engine shall be provided with (2) 1,000 feet below the maximum al tests shall be the same as fuel tank tests titude at which the rate of climb is an alternate air source unless equivalent (see § 4b.421), except as follows: safety is demonstrated by other means. equal to that established in accordance (1) The 3.5 p. s. i. pressure test of (d) Air intakes shall not open within with § 4b.120 (c). § 4b.421 (a) shall be replaced by either the cowling, unless that portion of the (d) The climb shall be conducted at the sum of the pressure developed during cowling is isolated from the engine ac an air speed which does not exceed the the maximum ultimate acceleration with speed used in establishing the rate of cessory section by means of a fire-resist climb required in § 4b.l20 (c). It shall a full tank plus the maximum working ant diaphragm, or unless provision is be acceptable to conduct the climb cool pressure of the system, or 1.25 times the made to prevent the emergence of back ing test in conjunction with the take-off maximum working pressure of the sys- fire flames. cooling test of § 4b.453. , tern, whichever is greater. (e) Alternate air intakes shall be (2) In the case of tanks with non- located in a sheltered position. § 4b.453 Take-off cooling test proce dure. If the time for which take-off metallic liners, the test fluid shall be a § 4b.461 Induction system de-icing power is used in establishing the take coolant at operating temperature rather and anti-icing provisions. The engine air off path of the airplane exceeds two than fuel as specified in § 4b.421 (c). induction system shall incorporate means minutes, a take-off cooling test shall be (c) Coolant tank installation. (1) for the prevention and elimination of ice conducted to demonstrate cooling during Coolant tanks shall be supported in such accumulations in accordance with the take-off and during subsequent climb a manner that the tank loads will be dis following provisions, unless it is demon with one engine inoperative. The fol tributed over a large portion of the tank strated that equivalent safety can be ob lowing procedure shall be applicable. surface. tained by a lower heat rise or by other Wednesday, January 25, 1950 FEDERAL REGISTER 435 means. It shall be demonstrated that § 4b.467 Exhaust system and instal proven suitable for the particular ap compliance with the following provisions lation components—(a) General. Cl) plication. They shall be installed and can be accomplished when the airplane The exhaust system shall be constructed supported to assure their safe operation is operating in air at a temperature of 30° and arranged to assure the safe disposal between normal inspection and overhaul P. when the air is free of visible moisture. of exhaust gases without the existence of periods. (a) Airplanes equipped with altitude a fire hazard or carbon monoxide con (2) Provision for expansion and flexi engines employing conventional venturi tamination of air in personnel compart bility shall be made between exhaust carburetors shall be provided with a pre ments. conduits and the turbine. heater capable of providing a heat rise (2) Unless suitable precautions are (3) Provision shall be made for lubri of 120° F. when the engine is operating taken, exhaust system parts shall not be cation of the turbine and for cooling of at 60 percent of its maximum continuous located in hazardous proximity to por those turbine parts where the tempera power. tions of any systems carrying flammable tures are critical. (b) Airplanes equipped with altitude fluids or vapors nor shall they be located (4) Means shall be provided for auto engines employing carburetors which under portions of such systems where matically limiting the turbine speed to embody features tending to reduce the the latter may be subject to leakage. its maximum allowable overspeed value. possibility of ice formation shall be pro (3) All airplane components upon Power-Plant Controls and Accessories vided with a preheater capable of pro which hot exhaust gases may impinge, or viding a heat rise of 100° P. when the which may be subjected to high temper § 4b.470 Power-plant controls. All engine is operating- at 60 percent of its atures due to proximity to exhaust sys power-plant controls shall comply with maximum continuous power. tem parts, shall be constructed of the provisions of § 4b.353 with respect to fireproof material. All exhaust system location, grouping, and direction of mo § 4b.462 Carburetor air preheater de components shall be separated by means tion, and shall comply with the provi sign. (a) Means shall be provided to* of fireproof shields from adjacent por sions of § 4b.737 with respect to marking. assure ventilation of the carburetor air tions of the airplane which are outside In addition they shall comply with the preheater when the engine is being op the engine compartment. following. erated with cold air. (4) Exhaust gases shall not discharge (a) Controls shall be so located that (b) The preheater shall be constructed within dangerous proximity of any fuel they cannot be inadvertently operated to permit inspection of exhaust manifold or oil system drains. by personnel entering or -leaving the air parts which it surrounds and also to (5) Exhaust gases shall not discharge plane, or while flight personnel are mak permit inspection of critical portions of at a location which will cause a glare ing normal movements in the cockpit. the preheater itself. seriously affecting pilot visibility at night. (b) Controls shall maintain any set § 4b.463 Induction system ducts, (a) (6) All exhaust system components position without constant attention by Induction system ducts ahead of the first shall be ventilated to prevent the exist flight personnel. They shall not tend stage of the supercharger shall be pro ence of points of excessively high tem to creep due to control loads or vibration. vided with drains to prevent the haz perature. (c) Flexible controls shall be of an ardous accumulation of fuel and mois (b) Exhaust piping. (1) Exhaust pip approved type or shall be proven suitable ture in the ground attitude. ing shall be constructed of material suit for the particular application. (b) Sufficient strength shall be incor ably resistant to heat and corrosion, and (d) Controls shall have strength and porated in the ducts to prevent induction shall incorporate provisions to prevent rigidity to withstand operating loads system failures resulting from normal failure due to expansion When heated to without failure and without excessive backfire conditions. operating temperatures. deflection. (c) Drains shall not discharge in lo (2) Exhaust pipes shall be supported § 4b.471 Throttle controls, (a) A cations which might cause a fire hazard. to withstand all vibration and inertia separate throttle control shall be pro (d) Ducts which are connected to loads to which they may be subjected in operation. vided for each engine. components of the airplane between (b) Throttle controls shall afford a which relative motion may exist shall (3) Portions of the exhaust piping positive and immediately responsive incorporate provisions for flexibility. which are connected to components be tween which relative motion may exist means of controlling the engines. § 4b.464 Induction system screens. shall incorporate provisions for flexi (c) Throttle controls shall be grouped (a) If induction system screens are em bility. and arranged to permit separate control ployed, they shall be located upstream (c) Exhaust heat exchangers. (1) of each engine and also simultaneous from the carburetor. Exhaust heat exchangers shall be con control of all engines. (b) It shall not be possible for fuel to structed and installed to assure their § 4b.472 Ignition switches, (a) Igni impinge upon induction system screens. ability to withstand without failure all tion switches shall provide control for (c) Screens shall not be located in vibration, inertia, and other loads to each ignition circuit on each engine. portions of the induction system which which they may be subjected in opera (b) Means shall be provided for quickly constitute the wily 'passage through tion. shutting off all ignition by the grouping which air may reach the engine, unless (2) Heat exchangers shall be con of switches or by providing a master the screen is so located that it can be structed of materials which are suitable ignition control. de-iced by heated air. for continued operation at high temper (c) If a master ignition control is pro (d) De-icing of induction system atures and which are resistant to corro vided, a guard shall be incorporated to screens by means of alcohol alone shall sion due to products contained in exhaust prevent inadvertent operation of the not be acceptable. gases. control. § 4b.465 Carburetor air cooling, (a) (3) Provision shall be made for the § 4b.473 Mixture controls, (a) If Installations employing two-stage super inspection of all critical portions of ex mixture controls are provided, a separate chargers shall be provided with means to haust heat exchangers. control shall be provided for each en maintain the air temperature at the inlet (4) Heat exchangers shall be cooled gine. to the carburetor at or below the maxi whenever they are subject to contact (b) The mixture controls shall be mum established value. with exhaust gases. grouped and arranged to permit sepa (b) Demonstration of compliance (d) Exhaust heating of ventilating air. rate control of each engine and also with the provision of paragraph (a) If an exhaust heat exhanger is used for simultaneous control of all engines. shall be accomplished in accordance with heating ventilating air, a secondary heat § 4b.451. exchanger shall be provided between the § 4b.474 Propeller controls—(a) Pro primary exhaust gas heat exchanger and peller speed and pitch controls. (See § 4b.466 Inter-coolers and after-cool the ventilating air system, unless it is also § 4b.404.) The propeller speed and ers. Inter-coolers and after-coolers demonstrated that sufficient safety can pitch controls shall be grouped and ar shall be capable of withstanding without be obtained by other means. ranged to permit control of the propel failure all vibration, inertia, and air (e) Exhaust driven turbo-supercharg lers separately and together. The pressure loads to which they may be ers. (1) Exhaust driven turbines shall controls shall provide for synchroniza subjected in operation. be of an approved type or shall be tion of all propellers. 436 PROPOSED RULE MAKING (b) Propeller feathering controls. (1) Powerplant Fire Protection (c) Vent and drain lines and fittings A separate feathering control shall be § 4b.480 Designated fire zones, (a) located in designated fire zones and provided for each propeller. Designated fire zones-shall comprise the which carry flammable fluids or gases (2) Propeller feathering controls shall following regions: shall comply with the provisions of para be provided with means to prevent in (1) Engine power section; graph (a) of this section, if it is found advertent operation. (2) Engine accessory section; that rupture or breakage of a particular (3) If feathering is accomplished by (3) Complete powerplant compart drain or vent line may result in a fire movement of the propeller pitch or speed ments in which no isolation is provided hazard. control lever, provision shall be made to between the engine power section and § 4b.484 Fire extinguisher systems— prevent the movement of this control to the engine accessory section; (a) General. (1) Unless it is demon the feathering position during normal (4) Auxiliary power unit compart strated that equivalent protection against operation. ments; destruction of the airplane in case of (c) Propeller reversing controls. If (5) Fuel-burning heaters, regions sur fire is provided by the use of fireproof the propeller blades can be placed in a rounding them, and other combustion materials in the nacelle and other com pitch position which produces negative equipment installations. ponents which would be subjected to thrust, propeller reversing controls shall (b) Designated fire zones shall be flame, fire extinguishing systems shall be arranged to prevent inadvertent oper protected from fire by compliance with be provided to serve all designated fire ation. §§ 4b.481 through 4b.489. zones, except in the case of an engine § 4b.475 Fuel system control. (See § 4b.481 Flammable fluids, (a) No power section which is completely iso § 4b.434): tanks or reservoirs which are a part of lated from the engine accessory section (a) Fuel jettisoning system controls a system containing flammable fluids or by a fireproof diaphragm complying with shall be provided with guards to prevent gases shall be located in designated fire the provisions of § 4b.486. their inadvertent operation. zones, except where the fluid contained, (2) The fire extinguishing system, the (b) Fuel jettisoning system controls the design of the system, the materials quantity of extinguishing agent, and the shall not be located in close proximity used in the tank, the shut-off means, all rate of discharge shall be such as to pro to fire extinguisher controls nor to any connections, lines, and controls are such vide two adequate discharges. It shall other controls intended for operation to as to provide equivalent safety. be possible to direct both discharges to combat fire. (b) Not less than % inch of clear air any main engine installation. Indi § 4b.476 Carburetor air preheat con space shall be provided between any tank vidual “one-shot” systems shall be ac trols. Separate carburetor air preheat or reservoir and a fire wall or shroud ceptable in the case of auxiliary power controls shall be provided to regulate the isolating a designated fire zone. units, fuel-burning heaters, and other combustion equipment. temperature of the carburetor air for § 4b.482 Shut-off means, (a) Means each engine. (3) Materials in the fire extinguishing for each individual engine and for each system shall not react chemically with § 4b.477 Powerplant accessories, (a) individual fire zone specified under sub- the extinguishing agent so as to consti Engine mounted accessories shall be of paragraphs (4) and (5) of § 4b.480 (a) tute a hazard. a type approved for installation on the shall be provided for shutting off or (b) Fire extinguishing agents. (1) engine involved, and shall utilize the pro otherwise preventing hazardous quanti Extinguishing agents employed shall be visions made on the engine for mount ties of fuel, oil, de-icer, and other flam methyl bromide, carbon dioxide, or any ing. - mable fluids from flowing into, within, other agent which has been shown to (b) Items of electrical equipment sub or through any designated fire zone, ex provide equivalent extinguishing action. ject to arcing or sparking shall be in cept that means need not be provided to (2) If methyl bromide, carbon dioxide, stalled to minimize the possibility of their shut off flow in lines forming an integral or any other toxic extinguishing agent contact with any flammable fluids or part of an engine. is employed, provision shall be made to vapors which may be present in a free (b) In order to facilitate rapid and prevent the entrance of harmful concen state. effective control of fires, shut-off means tration of fluid or fluid vapors into any § 4b.478 Engine ignition systems. shall permit an emergency operating se personnel compartments either due to (a) Battery ignition systems shall be quence which is compatible with the leakage during normal operation of the supplemented with a generator which is emergency operation of other equip airplane or as a result of discharging the automatically made available as an al ment, such as feathering the propeller. fire extenguisher on the ground or in ternate source of electrical energy to (c) Shut-off means shall be located flight. Compliance with this require permit continued engine operation in the outside of designated fire zones, unless ment shall be demonstrated by appro event of the depletion of any battery. equivalent safety is provided (see priate tests. (b) The capacity of batteries and gen §4b.481). It shall he shown that no (3) If a methyl bromide system is pro erators shall be sufficient to meet the hazardous quantity of flammable fluid vided, the containers shall be charged simultaneous demands of the engine igni will drain into any designated fire zone with a dry agent and shall be sealed by tion system and the greatest demands of after shutting-off has been accomplished. the fire extinguisher manufacturer or by any airplane electrical system compon (d) Provisions shall be made to guard any other party employing satisfactory ents which may draw electrical energy against inadvertent operation of the recharging equipment. from the same source. shut-off means and to make it possible (4) If carbon dioxide is used, it shall (1) The design of the engine ignition for the crew to reopen the shut-off not be possible to discharge sufficient gas system shall take into consideration the means after it has once been closed. into personnel compartments to consti condition of an inoperative generator § 4b.483 Lines and fittings, (a) All tute a hazard from the standpoint of and the condition of a completely de lines and fittings located in designated suffocation of the occupants. pleted battery when the generator is fire zones which carry flammable fluids (c) Extinguishing agent container running at its normal operating speed. or gases and which are under pressure, or pressure relief. Extinguisher agent con (2) If only one battery is provided the which attach directly to the engine, or tainers shall be provided with a pressure design of the engine ignition system shall are subject to relative motion between relief to prevent bursting of the con take into consideration the condition in components, exclusive of those lines and tainer due to excessive internal pressures. which the battery is completely depleted fittings forming an integral part of the The following shall apply: and the generator is operating at idling engine, shall be flexible, fire-resistant (1) The discharge line from the relief speed. lines with fire-resistant end fittings of connection shall terminate outside the (c) Means shall be provided to warn the permanently attached, detachable, or airplane in a location convenient for in flight personnel if malfunctioning of any other approved types. spection on the ground. part of the electrical system is causing (b) Lines and fittings which are not (2) An indicator shall be provided at the continuous discharging of a battery subject to pressure or to relative motion the discharge end of the line to provide which is necessary for engine ignition. between components shall be of fire-re a visual indication when the container (See § 4b.472 for ignition switches.) sistant materials. has discharged. Wednesday, January 25, 1950 FEDERAL REGISTER 437 (d) Extinguishing agent container ment. This diaphragm shall comply with (f) Fuel quantity indicator for each compartment temperature. Precautions the provisions of § 4b.486. fuel tank (see § 4b.613 (c)), (g) Manifold pressure indicator for shall be taken to assure that the extin § 4b.489 Protection of other airplane guishing agent containers are installed components against lire. AH airplane each engine, in a location where reasonable tempera (h) Oil pressure indicator for each surfaces aft of the nacelles, in the region engine, tures can be maintained for effective use of one nacelle diameter on both sides of of the extinguisher system. . (i) Oil quantity indicator for each oil the nacelle center line, shall be con-* tank when a transfer or oil reserve sup (e) Fire extinguishing system mate structed of fire-resistant material. This rials. All components of fire extin ply system is used (see § 4b.613 (e)), provision need not be applied to tail sur (j) Oil temperature indicator for each guishing systems located in designated faces lying behind nacelles, unless the fire zones shall be constructed of fire engine, dimensional configuration of the aircraft (k) Tachometer for each engine, proof materials, except for connections is such that the tail surfaces could be which are subject to relative motion be (l) Fire warning indicators (see affected readily by heat, flames, or sparks § 4b.485). tween components of the airplane, in emanating from a designated fire zone or which case they shall be of flexible fire- engine compartment of any nacelle. § 4b.605 Miscellaneous equipment. resistant construction and so located as (a) Approved seats for all occupants (see to minimize the possibility of failure. SUBPART F— EQUIPMENT § 4b.358). § 4b.485 Fire detector systems, (a) General (b) Approved safety belts for all occu Quick acting fire detectors shall be pro pants (see § 4b.643), § 4b.600 Scope. The required equip (c) A master switch arrangement for vided in all designated fire zones and ment as prescribed in this subpart is the shall be sufficient in number and loca electrical circuits other than ignition, minimum which shall be installed in the (d) Adequate source (s) of electrical tion to assure the detection of fire in airplane for certification. Such addi such zones. tional equipment as is necessary for a energy, (b) Fire detectors shall be constructed (e) Electrical protective*devices, specific type of operation is prescribed (f) Radio communication system and installed to assure their ability to in the operating parts of the Civil Air resist without failure all vibration, in Regulations. (two-way), ertia, and other loads to which they may (g) Radio navigation system, be subjected in operation. § 4b.601 Functional and installational (h) Windshield wiper or equivalent (c) Detectors shall be unaffected by requirements. Each item of equipment for each pilot, exposure to oil, water, or other fluids or shall be: (i) Ignition switch, for each and all fumes which may be present. (a) Of a type and design satisfactory engines (see4b.472), to perform its intended function, (j) Approved portable fire extin § 4b.486 Fire walls. All engines, (b) Adequately labeled as to its iden guisher (see §4b.641). auxiliary power units, fuel-burning heat tification, function, or operational limi I nstruments—Installation ers, and other combustion equipment tations, or any combination of these, which are intended for operation in flight whichever is applicable, § 4b.610 General. The provisions of shall be isolated from the remainder of (c) Properly installed in accordance §§ 4b.611 through 4b.613 shall establish the airplane by means of fire walls, with specified limitations of the equip the installation requirements for aircraft shrouds, or other equivalent means. The ment, and powerplant instruments. following shall apply: (d) Demonstrated to function satis § 4b.611 Arrangement and visability (a) Fire walls and shrouds shall be factorily in the airplane. of instrument installations, (a) Flight, constructed in such a manner that no navigation, and powerplant instruments hazardous quantity of air, fluids, or § 4b.602 • Required basic equipment. for use by each pilot shall be easily visible flame can pass from the engine com The basic equipment listed in §§ 4b.603 to him from his station With the mini partment to Other portions of the air through §4b.605 shall be required for cer mum practicable deviation from his nor plane. tification of the airplane. mal position and line of vision when he is (b) All openings in the fire wall or § 4b.603 Flight navigation instruments. looking out and forward along the flight shroud shall be sealed with close-fitting (a) Air-speed indicating system with path. fireproof grommets, bushings, or fire heated pitot tube or equivalent means of (b) All of the required flight instru wall fittings. preventing malfunctioning due to icing ments shall be conveniently grouped and (c) Fire walls and shrouds shall be (see paragraphs 4b.612 (a) and (b)), as nearly as practicable centered about constructed of fireproof material and (b) Altimeter (sensitive) (see §4b.612 the vertical plane of the pilot’s forward shall be protected against corrosion. (b) ), vision. § 4b.487 Cowling, (a) Cowling shall (c) Clock (sweep-second), (c) All the required powerplant in be constructed and supported so as to (d) Free air temperature indicator, struments shall be closely grouped on make it capable of resisting all vibra (a) Gyroscopic bank and pitch indica the instrument panel. tion, inertia, and air loads to which it tor (see § 4b.612 (e)), (d) Identical powerplant instruments may be subjected in operation. (f) Gyroscopic rate-of-turn indicator for the several engines shall be located (b) Provision shall be made to permit (with bank indicator) (see § 4b.612 (e)), to prevent any misleading impression as rapid and complete drainage of all por (g) Gyroscopic direction indicator to the engines to which they relate. tions of the cowling in all normal ground (see § 4b.612 (e)), (e) Important powerplant instruments and flight attitudes. Drains shall not (h) Magnetic direction indicator (see shall be easily visible to the appropriate discharge in locations which might cause § 4b.612 (c)), crew members. a fire hazard. (i) Rate-of-climb indicator (vertical (f) The vibration characteristics of (c) Cowling, unless otherwise specified speed) (see § 4b.612 (b)). the instrument panel shall be such as by these regulations, shall be constructed § 4b.604 Powerplant instruments, (a) not to impair seriously the accuracy of of fire-resistant material; Carburetor air temperature indicator for the instruments or to damage them. (d) Those portions of the cowling each engine, § 4b.612 Flight and navigation which are subjected to high tempera (b) Coolant indicator for each liquid- instruments—(a) Air-speed indicating tures due to their proximity to exhaust cooled engine, systems. (1) Air-speed indicating in system parts or exhaust gas impinge (c) Cylinder head temperature indi struments shall be calibrated to indicate ment shall be constructed of fireproof cator for each air-cooled engine (see true air speed at sea level in the standard material. § 4b.613 (f)), atmosphere with a minimum practicable § 4b.488 Engine accessory section dia (d) Fuel pressure indicator for each instrument calibration error when the phragm. Unless equivalent protection pump-fed engine, corresponding pitot and static pressures can be shown by other means, a dia (e) For each engine not equipped with are applied to the instrument. phragm shall be provided on air-cooled an automatic altitude mixture control: (2) The air-speed indicating system engines to isolate the engine power sec (1) Fuel flowmeter indicator (see shall be calibrated in flight to determine tion and all portions of the exhaust sys 9 4b.613 (d)), or the system error, i. e, the relation be tem from the engine accessory compart- (2) Fuel mixture indicator, tween IAS and CAS. 438 PROPOSED *ULE MAKING (3) The air-speed error of the instal (2) A suitable means shall be provided Electrical Systems and Equipment lation, excluding the air-speed indicator in the suction air pump installation, § 4b.620 Installation, (a) Electrical instrument calibration error, shall not where the lines from the individual systems and equipment shall . be free exceed 3 percent or 5 m. p. h., whichever pumps connect into a common line, to from hazards in themselves, in their is greater, throughout the speed range select either pump in case of failure of method of operation, and in their ef from VN0 to 1.3 VSl with flaps retracted, one pump source. v fects on other parts of the airplane. and at 1.3 Vi0 with flaps in landing posi (3) When an automatic means to per They shall be protected from fuel, oil, tion. mit simultaneous air flow is provided in water, other detrimental substances, (4) The air-speed indicating system the system, a suitable method for indi and from mechanical damage. shall be arranged in so far as practicable cating any interrupted air flow in the (b) For substantiation of the electri to preclude malfunctioning or serious suction air pump lines shall be incor cal system the data required under error due to the entry of moisture, dirt, porated in the system. In order to in § 4b. 13 shall include: or other detrimental substances. dicate which source has failed, a visual (1) Wiring diagrams, including a (5) The air-speed indicating system means shall be provided to indicate this schematic power supply diagram, shall be provided with a heated pitot condition to the flight crew. (2) Installation data, Including the tube or equivalent means of ice protec (4) A suction gauge shall be installed manufacturer’s name, type of all elec tion. to indicate readily to the flight crew trical items, and reference to pertinent (b) Static air vent system. (1) All while in flight the suction in inches of specifications. instruments provided with static air case mercury which is being applied to the (3) An electrical load analysis. connections shall be vented to the outside air-driven types of gyroscopic instru atmosphere through a suitable piping ments. § 4b.621 Batteries, (a) The battery system. capacity shall be that determined nec § 4b.613 Power plant instruments— essary from an electrical load analysis. (2) The vent(s) shall be so located on (a) Operational markings. Instruments thé airplane that its orifices will be least (b) Means shall be provided to pre shall be marked as specified in §§ 4b.734 vent corrosive battery substance from affected by air flow variation, moisture, through 4b. 738. or other foreign matter. coming in contact with other parts of (b) Instrument lines. (1) Instrument the airplane during servicing or in flight. (3) The installation shall be such that lines carrying flammable fluids or gases the system will be air-tight, except for (c) Batteries shall be completely en under pressure shall be provided with re closed in a container or compartment the vent into the atmosphere. stricted orifices or equivalent safety de (c) Magnetic direction indicator. (1) and shall be easily accessible for servic vices at the source of the pressure to ing and inspection on the ground. The magnetic direction indicator shall prevent escape of excessive fluid or gas in be installed so that its accuracy will not (d) The battery container or compart case of line failure. ment shall be vented so that gases re be excessively affected by the airplane’s (2) Power plant instrument lines shall vibration or magnetic fields of a perma leased by the battery are carried outside comply with the provisions of § 4b.432. the airplane. nent or transient nature. (For fire-resistant power plant instru (2) After the magnetic direction in (e) Battery cooling shall be provided, ment lines see § 4b.483.) if found necessary to keep the battery dicator has been compensated, the cali (c) Fuel quantity indicator. Means bration shall be such that the deviation temperature within the limits specified shall be provided to indicate to the flight by the battery manufacturer. in level flight does not exceed ±10° on crew the quantity in gallons or equiva any heading. lent units of usable fuel in each tank § 4b.622 Generator system—(a) Gen (3) A calibration placard shall be pro during flight. The following shall apply: erator. The generator capacity neces vided as specified in § 4b.733. (1) Tanks, the outlets and air spaces sary shall be determined initially from (d) Automatic pilot system. If an of which are interconnected, shall be an electrical load analysis, and its ade automatic pilot'system is installed, the considered as one tank for the purpose quacy shall be demonstrated during following shall be applicable: of providing separate indicators. flight test. A switch shall be provided (1) The actuating (servo) devices shall (2) Exposed sight gauges shall be pro for each generator to permit its output be of such design that they can, when tected against damage. to be interrupted. Individual genera necessary, either be disengaged posi (3) Fuel quantity indicators shall be tors shall be capable of delivering their tively or be overpowered by the pilot to calibrated to read zero during level flight continuous rated power. enable him to maintain satisfactory con when the quantity of fuel remaining in (b) Generator controls. Generator trol of the airplane. the tank is equal to the unusable fuel voltage control equipment shall be ca (2) A satisfactory means shall be pro supply as defined by § 4b.416 (see pable of regulating the generator output vided to indicate readily to the pilot the § 4b.736). within rated limits. alignment of the actuating device in re (d) Fuel flowmeter system. When a (c) Reverse current cutout. ,A gen lation to the control system which it flowmeter system is installed, the meter erator reverse current cutout shall dis operates, except when automatic syn ing component shall include a suitable connect the generator from the battery chronization is provided. means for bypassing the fuel supply in and from other generators when the (3) The manually operated control(s) the event that malfunctioning of the generator is developing a voltage of such for the system’s operation shall be read metering component results in a severe value that current sufficient to cause ily accessible to the pilot. restriction to fuel flow. malfunctioning can flow into the gener (4) The automatic pilot system shall (e) Oil quantity indicator. (1) A stick ator. be of such design and so adjusted that, gauge or other equivalent means shall § 4b.623 Master switch. A master iWithin the range of adjustment available be provided to indicate the quantity of switch arrangement shall be provided to the human pilot, it cannot produce oil in each tank (see § 4b.735). which will disconnect all sources of elec loads in the control system and surfaces (2) If an oil transfer system or a re trical power from the main distribution greater than those for which the system serve oil supply system is installed, system at a point adjacent to the power- and surfaces were designed. means shall be provided to indicate to sources. (e) Gyroscopic indicators (air-driven the crew during flight the quantity of oil § 4b.624 Master switch installation. type). All air-driven gyroscopic instru in each tank. ments shall derive their energy from a The master switch and its controls shall suction air pump driven either by an en (f) Cylinder head temperature indi be so installed that is easily discernible gine or by an auxiliary power unit. The cating system for air-cooled engines. and accessible to a member of the crew following shall be applicable. A cylinder head temperature indicator in flight. (1) Two suction air pumps actuated shall be provided for each air-cooled en § 4b.625 Protective devices. Protec by separate power means shall be pro gine on airplanes equipped with cowl tive devices (fuses or circuit breakers) vided, either one of which shall be of suf flaps. In the case of airplanes without shall be installed in the circuits to all ficient capacity to operate all of the cowl flaps, an indicator shall be provided electrical equipment, except that such air-driven gyroscopic instruments at the if compliance with the provisions of items need not be installed in the main service ceiling of the airplane in normal § 4b.450 is demonstrated at a speed in circuits of starter motors or in other cir cruising condition. excess of the speed of best rate of climb. cuits where no hazard is presented by Wednesday, January 25, 1950 FEDERAL REGISTER 439 their omission. If fuses are used, one directed symmetrically aft from each § 4b.605 (j) shall be installed primarily spare of each rating or 50 percent spare light with the axis of the maximum cone for the use of the pilot and copilot. fuses of each rating, whichever is greater, of illumination parallel to the flight (b) When the operating rules require shall be provided. path. additional fire-extinguishing equipment, § 4b.626 Protective devices installa (2) The intersection of the two planes the installation of such equipment shall tion. Protective devices in circuits used forming the dihedral angle A prescribed depend upon the size and compartmen- in flight shall be located conveniently in Part 15 shall be vertical. tation of the aircraft and on the number and properly to facilitate replacement of (3) If separate red and white lights and distribution of the crew and pas fuses or resetting of circuit breakers in are used, they shall be located as close sengers. Such fire extinguishers shall flight. together as practicable. be placed in approved locations. (d) Top and bottom fuselage lights. § 4b.627 Electric cables. The elec (1) The top and bottom fuselage lights § 4b.642 Flare installation, (a) Para tric cables used shall be in accordance shall each furnish illumination of an chute flares shall be releasable from the with approved standards for aircraft intensity equivalent to a 32-candlepower pilot compartment and installed to mini electric cable of a slow-burning type. lamp installed in a reflector of high re mize the danger of accidental discharge. They shall have current-carrying ca flective properties and shall have a clear (b) It shall be demonstrated in flight pacity sufficient to deliver the necessary cover glass. that the flare installation is such that power to the items of equipment to which (2) The top and bottom fuselage lights ejection can be accomplished without they are connected. hazard to the airplane and its occupants. shall show through approximately a (c) If the flares are ejected so that § 4b.628 Switches. Switches shall be hemisphere. recoil loads are involved, the structure of capable of carrying their rated current. (3) The top fuselage light shall be in the airplane shall withstand such loads. They shall be accessible to the crew and stalled approximately in line with the shall be labeled as to operation and the forward position lights. § 4b.643 Safety belts. Airplanes circuit controlled. (4) The bottom fuselage light on manufactured on or after January 1, landplanes shall be installed approxi 1951, shall be equipped with safety belts Lights mately in line with the forward position approved in accordance with § 4b. 18. In § 4b.630 Instrument lights—(a) Il lights. In the case of seaplanes the lo no case shall the rated strength of the lumination. Instrument lights shall pro cation of the bottom light will be sub safety belt be less than that correspond vide sufficient illumination to make all ject to specific approval on each model ing with the ultimate load factors speci instruments, switches, etc., easily read airplane. fied in § 4b.260 (a), taking due account able. (e) Position light flasher. (1) The of the dimensional characteristics of the (b) Instrument light installation. In position light flasher shall incorporate safety belt installation for the specific strument lights shall be installed in a two flashing circuits which are ener seat or berth arrangement. Safety belts manner so that their direct rays are gized alternately to provide a flashing shall be attached so that no part of the shielded from the pilot’s eyes and so that of the position and fuselage lights in the anchorage will fail at a load lower than no objectional reflections are visible to manner indicated in paragraph (f). that corresponding with the ultimate him. (2) The flasher shall be of an ap load factors specified in § 4b.260 (a). (c) Light dimming. A means of con proved type. § 4b.644 Safety belt signal. When a trolling the intensity of illumination (f) Flashing light sequence. (1) The means is provided to indicate to the pas shall be provided, unless it is shown that forward position lights and the rear sengers when seat belts should be nondimmed instrument lights are satis white position light shall be on one of the fastened, the device shall be so installed factory under all expected conditions of flasher circuits, and the top and bottom flight. fuselage lights and the rear red posi that it can be operated from the seat of tion light shall be on the other circuit. either pilot or copilot. § 4b.631 Landing lights—(a) Type. (2) The flashing sequence shall be re § 4b.645 Emergency flotation and Landing lights shall be of an approved peated automatically when the position signaling equipment, (a) Rafts and life type. light switch is in the “flash” position. preservers shall be installed so as to be (b) Landing light installation. (1) (g) Flashing light cutout switch. A readily available to the crew and Landing lights shall be installed so that switch shall be provided to eliminate passengers. there is no objectionable glare visible to the flasher from the position light cir (b) Rafts released automatically or re , the pilot and so that the pilot is not ad cuit so that continuous light may be leased by the pilot shall be attached to versely affected by halation. provided by the forward position lights the airplane by means of a line to keep (2) Landing lights shall be installed in and the rear white position light, while them adjacent to the airplane. a location where they provide the neces the top and bottom fuselage lights are (c) Signaling devices shall be accessi sary illumination for night landing. not lighted. ble, shall function satisfactorily, and (c) Landing light switch. A switch shall be free from any hazard in their for each light shall be provided, except § 4b.633 Riding light. When a rid operation. that where multiple lights are installed ing (anchor) light is required for a sea at one location a single switch for the plane, flying boat, or amphibian, it shall Miscellaneous Equipment multiple lights shall be acceptable. be capable of showing a white light for at least two miles at night under clear § 4b.650 Radio installation. Radio § 4b.632 Position lights—(a) Type. atmospheric conditions. • equipment installations in the airplane Forward and rear position lights shall be shall be free from hazards in themselves, of a type certificated in accordance with § 4b. 634 Riding light—installation. in their method of operation, and in their Part 15. The riding light specified in § 4b.633 shall effects on other components of' the (b) Forward position light installa be installed to show the maximum airplane. / tion. (1) Forward position lights shall unbroken light practicable when the air be installed so that, with the airplane in plane is moored or drifting on the water. § 4b.651 Oxygen equipment and sup normal flying position, the red light is Externally hung lights shall be accept ply. When required by the operating displayed on the left side and the green able. parts of the Civil Air Regulations, the light on the right side, each showing Safety Equipment supplemental and protective breathing unbroken light between two vertical equipment and its installation shall meet planes the dihedral angle of which is 110° § 4b.640 De-icers. When an ice pro the following requirements. when measured to the left and to the tection system is installed, it shall be of (a) General. The oxygen system in right of the airplane from dead ahead. an approved type. If pneumatic boots stalled shall be free from hazards in it (2) The lights shall be spaced lat are used, at least two independent sources self, in its method of operation, and in its erally as far apart as practicable. of power and a positive means for the effect on other components of the air (c) Rear position light installation. deflation of the boots shall be provided. plane. A means shall be provided to en ^ rec* anc* w^ite position lights § 4b.641 Fire extinguishers; number able the crew to determine the quantity shall be mounted as far aft as practicable and installation, (a) The approved of oxygen available in each source of and installed so that unbroken light is portable fire extinguisher required in supply. 440 PROPOSED RULE MAKING (b) Required minimum mass flow sup enable the crew to determine whether an integral1 part of the engine or plemental oxygen. The minimum mass oxygen is being delivered to each user. propeller. flow of supplemental oxygen required § 4b.652 Engine - driven accessories. SUBPART G— OPERATING LIMITATIONS AND per person at various cabin pressure alti Engine-driven accessories essential to INFORMATION tudes shall be at least that indicated by safe operation of the airplane shall be General figure 4b-18. so distributed among two or more engines (c) Equipment standards for distribu that the failure of any one engine will § 4b.700 Scope, (a) The operating tion system. Where oxygen is to be sup not impair the safe operation of the limitations listed in §§ 4b.710 through plied to both crew and passengers, the airplane. 4b.723 shall be established as prescribed distribution system shall be designed to in this part. provide either: § 4b.653 Hydraulic systems—(a) De (b) The operating limitations, to (1) A source of supply for the flight sign. Hydraulic systems and elements gether with any other information con crew on duty and a separate source for shall withstand, without exceeding the cerning the airplane found necessary for the passengers and other crew members, yield point, all structural loads wich may safety during operation, shall be made Or be imposed in addition to the hydraulic available to appropriate members of the (2) A common source of supply with loads. flight crew by means of the Airplane means provided so that the minimum (b) Tests. Hydraulic systems shall be Flight Manual, as prescribed in § 4b.740, supply required by the flight crew on substantiated by proof pressure tests. by means of the markings and placards duty can be separately reserved. When proof tested, no part of the hy as prescribed in § 4b.730, and by such (d) Equipment standards for dispens draulic systems shall fail, malfunction, additional means as may be found nec ing units. An individual dispensing unit or experience a permanent set. The essary to accomplish this purpose. shall be provided for each crew member proof load of any system shall be 1.5 and passenger for whom supplemental times the maximum operating pressure Operating Limitations oxygen is required to be furnished. All of that system. § 4b.710 Air-speed limitations; gen units shall be designed to cover the nose, (c) Lines and fittings. Hydraulic lines eral. When air-speed limitations are a and at least 25 percent of the units re and fittings in all designated fire zones function of weight, weight distribution, quired to be furnished shall, in addition, (see § 4b.480) shall comply with the pro cover the mouth. (For crew masks to be altitude, or Mach number, the values used for protective breathing purposes visions of § 4b.483. corresponding with all critical combina see the pertinent air carrier operating (d) Reservoirs and accumulators. Lo tions of these values shall be established. rules.) cation of hydraulic reservoirs and These air speeds shall be expressed in (e) Means for determining use of accumulators shall comply with the pro IAS. oxygen. A means shall be provided to visions of § 4b.481, except when they are § 4b.711 Never-exceed speed, VNE. (a) To allow for possible variations in the airplane characteristics and to minimize the possibility of inadvertently exceed ing safe speeds, the never-exceed speed 250 VNE shall be a speed established suffi ciently below the lesser of: (1) The design dive speed VD chosen in accordance with § 4b.210 (b) (5), or (2) The maximum speed demonstrated in flight in accordance with § 4b. 190. 200 (b) In the absence of a rational in vestigation, the value of VNE shall not exceed 0.9 times the lesser of the two speeds referred to in paragraph (a). § 4b.712 Normal operating limit speed, 150 VN0. (a) The normal operating limit speed VN0 shall be established not to exceed the design cruising speed Va chosen in accordance with § 4b.210 (b) (4) and sufficiently below the never- exceed speed VNE to make it unlikely 100 that VSE would be exceeded in a mod * erate upset occurring at VN0. o (b) In the absence of a rational in E vestigation, the value of VN0 shall not » exceed 0.9 times VNE. to 50 O' S 4b.713 Maneuvering speed. The 2 maneuvering speed shall not exceed the c design maneuvering speed VA determined 0 in accordance with § 4b.210 (b) (2). 1 § 4b.714 Flaps extended speed, VFE. O (a) The flaps extended speed VFE shall be established not to exceed the lesser of: 10 20 30 4 0 (1) The design flap speed VF chosen in accordance with § 4b.210 (b) (1), or Cabin Pressure Altitude ( thousand* of (set ) (2) The design speed for slipstream N otes effects with flaps in the landing position, 1. Data based on: chosen in accordance with § 4b.221. a. System 100 percent efficient. (b) The value of VFE established in b. Respiratory m inute volume equals 15 liters (915 cubic Inches) per minute. accordance with paragraph (a) shall not c. 100 percent oxygen above 30,000 feet. be less than a value which provides a 2. For dilutor-demand regulators use flow characteristics supplied by manufacturer to safe speed margin above the stall during calculate required supply. Such flows m ust not be less than those Indicated on this graph approach and landing. of delivery rate of 15 liters per m inute. (c) It shall be acceptable to establish Figure 4b-18—Minimum flow of oxygen for operation at various altitudes. supplementary values of VFE for other Wednesday, January 25, 1950 FEDERAL REGISTER 441 combinations of flap setting, air speed, § 4b.72I Types of operation. The (b) The calibration readings shall be and engine power, if the structure and types of operation to which the airplane in terms of magnetic headings in not the flight characteristics of the airplane is limited shall be established by the greater than 45° increments. have been shown to be satisfactory for category in which it has been found eligi such combinations. § 4b.734 Powerplant instruments; gen ble for certification and by the equip eral. All required powerplant instru § 4b.715 Landing gear operating ment installed. (See the operating parts ments shall be marked as follows: speed, VL0. The landing gear operating of the Civil Air Regulations.) (a) The maximum and the minimum speed VL0 shall be established not to ex § 4b.722 Maximum operating altitude. (if applicable) safe operational limits ceed a speed at which it is safe to ex A maximum altitude shall be established shall be marked with red radial lines. tend or retract the landing gear as up to which operation is permitted, as (b) The normal operating ranges shall ^ limited by design in accordance with limited by flight, structural, powerplant, be marked with a green arc not extend § 4b.334 or by flight characteristics. functional, or equipment characteristics. ing beyond the maximum and minimum safe operational limits. § 4b.716 Landing gear extended speed, § 4b.723 Maneuvering flight load fac (c) The take-off and precautionary VjjE‘. The landing gear extended speed tors. Load factor limitations shall be ranges shall be marked with a yellow arc. Vle shall be established not to exceed a established not to exceed the limit posi speed at which it has been shown that tive load factors determined from the § 4b.735 Oil quantity indicators. In the airplane can be safely flown with the maneuvering diagram, figure 4-2. (See dicators shall be marked in sufficient landing gear secured in the fully ex § 4b.211 (a).) increments so that they will indicate tended position, and for which the struc Markings and Placards readily and accurately the quantity of ture has been proven in accordance with oil. § 4b.334. § 4b.730 General, (a) Markings and § 4b.736 Fuel quantity indicator. placards shall be displayed in a conspic § 4b.717 Minimum control speed, When the unusable fuel supply for any uous plape and shall be such that they tank exceeds I gallon or 5 percent of the VM0. (See § 4b.l33.) cannot be easily erased, disfigured, or obscured. tank capacity, whichever is greater, a § 4b.718 P ower plant limitations. red arc shall be marked on the indicator The following powerplant limitations (b) Additional information, placards, extending from the calibrated zero read shall be established for the airplane. and instrument markings having a di ing to the lowest reading obtainable in They shall not exceed the corresponding rect and important bearing on safe op the level flight attitude. A suitable no limits established as a part of the type eration shall be required when unusual tation in the Airplane Flight Manual certification of the engine and propeller design, operating, or handling charac shall be made to indicate that the fuel installed in the airplane. teristics so warrant. remaining in the tank when the quan (a) Take-off operation. (1) Maxi § 4b. 731 Instrument markings; gen tity indicator reaches zero is not usable mum rotational speed (rpm), eral. (a) When markings are placed on inflight. (See § 4b.613 (c).) (2) Maximum permissible manifold the cover glags of the instrument, provi § 4b.737 Control markings; general. pressure, sion shall be made to maintain the cor All cockpit controls, with the exception (3) The time limit for use of the power rect alignment of the glass cover with of the primary flight controls and other which corresponds with the values estab the face of the dial. controls the function of which is obvious, lished in subparagraphs (1) and (2), of (b) All arcs and lines shall be of suffi shall be plainly marked and/or identi this paragraph, cient width and so located that they are fied as to their function and method of (4) Where the time limit established clearly visible to the pilot. operation. in subparagraph (3) of this paragraph § 4b. 732 Air-speed indicator. The (a) Aerodynamic controls. The sec exceeds two minutes, the maximum al following markings shall be placed on ondary controls shall be marked to com lowable cylinder head or coolant outlet, the air-speed indicator. If speeds vary ply with §§ 4b.322 and 4b.323. and oil temperatures. with altitude, means shall be provided (b) Powerplant fuel controls. (1) (b) Maximum continuous operation. to indicate the appropriate limitation to Controls for fuel tank selector valves (1) Maximum rotational speed (rpm), the pilot throughout the operating alti shall be marked to indicate the position (2) Maximum permissible manifold corresponding with each tank and with pressure, tude range. (a) A radial red line shall indicate the all possible cross-feed positions. (3) Maximum allowable cylinder head never-exceed speed V$E (see § 4b.711). (2) When more than one fuel tank is or coolant outlet, and oil temperatures. provided, and if safe operation depends (c) Fuel octane rating. The mini (b) A yellow arc extending from the red line specified in paragraph (a) of upon the use of tanks in a specific se mum octane rating of fuel required for quence, the fuel tank selector controls satisfactory operation of the powerplant this section to the upper limit of the green arc specified In paragraph (c) of shall be marked adjacent to or on the at the limits specified in paragraphs (a) control itself to indicate .the order in and (b) of this section. this section shall indicate the caution range. which the tanks should be used. § 4b.719 Airplane weight and center (c) A green arc with the lower limit at (3) Controls for engine selector valves of gravity limitations. The airplane VSl as determined in § 4b.ll2 (b) with shall be marked to indicate the position weight and center of gravity limitations maximum take-off weight, landing gear corresponding with each engine. shall be those determined in accordance and wing flaps retracted, and the upper (c) Accessory and auxiliary controls. with §§ 4b.l01 and 4b.l02. Where the limit at the normal operating limit (1) When a retractable landing gear is airplane is certificated for more than one speed VN0 established in § 4b.712 shall used, the visual indicator required in center of gravity range, the appropriate indicate the normal operating range. §4b.334 (e) shall be marked so that the limitations with regard to weight and (d) A white arc with the lower limit at pilot can ascertain at all times when loading procedures shall be set forth in the wheels are locked in either extreme Vs0 as determined in § 4b.ll2 (a) at the position. the Airplane Flight Manual for each maximum landing weight, and the upper separate center of gravity range. limit at the flaps-extended speed VFE as (2) Emergency controls shall be col ored red and shall be marked to indicate § 4b.720 Minimum flight crew. The established in § 4b.714‘shall indicate the their method of operation. minimum flight crew shall be established flap operating range. by the Administrator as that number of § 4b.733 Magnetic direction indicator. § 4b.738 Miscellaneous markings and persons which he finds necessary for (a) A placard shall be installed on or placards—(a) Baggage compartments safety in the operations authorized under in close proximity to the magnetic direc and ballast location. Each baggage and § 4b.721. This finding shall be based tion indicator which contains the cali cargo compartment as well as the ballast upon the work load imposed upon indi bration of the instrument in a level flight location shall bear a placard stating the vidual crew members with due considera attitude with engine (s) operating. The maximum allowable weight of contents tion given to the accessibility and the placard shall state whether the calibra and, if applicable, any other limitation ease of operation of all necessary con tion was made with radio receiver (s) on on contents .found necessary due to trols by the appropriate crew members. or off. loading requirements. 442 PROPOSED RULE MAKING (b) Fuel, oil, and coolant filler open (2) The normal operating limit speed (f) Type of operation. The type(s) ings. The following information shall (see § 4b.712) together with a statement of operation (s) shall be listed for which be marked on or adjacent to the appro to the effect that normal flight opera the airplane and its equipment installa priate filler cover: tions should be confined to speeds below tions have been approved. (1) The word “fuel”, the minimum this value, and a further statement to (g) Maximum operating altitude. The permissible fuel octane number for the the effect that the range of speeds be altitude established under § 4b.722 shall engines installed, and the usable fuel tween the normal operating limit speed be included, together with an explana tank capacity (see § 4b.416); and the never-exceed speed should be tion of the limiting factors. (2) The word “oil” and the oil tank entered with caution and with due re § 4b.742 Operating procedures—(a) capacity; gard to the prevailing flight and atmos Normal. Information and instructions (3) The name of the proper coolant pheric conditions; shall be included regarding any peculi fluid and the capacity of the coolant (3) When an air-speed limitation is arities of starting and warming the en system. based upon compressibility effects, a gines, taxying, operation of wing flaps, (c) Emergency exit placards. (1) statement to this effect, together with landing gear, automatic pilot, etc. Emergency exits shall be marked as such information as to any symptoms, the (b) One engine inoperative. The rec with luminous paint in letters not less probable behavior of the airplane, and ommended procedure shall be described than % inch high. The markings shall recommended recovery procedures; to be followed in the event of engine be located either on or immediately adja (4) The maneuvering speed (see failure, including minimum speeds, trim, cent to the exit and shall be conspicuous § 4b.210 (b) (2)), together with a state operation of remaining engine(s), opera to the passengers. ment to the effect that full application tion of flaps, etc. (2) The location and method of opera of rudder and aileron controls as%ell. as (c) Propeller feathering. The recom tion of the emergency exit handles those maneuvers which involve angles of mended procedure shall be described to shall be marked with luminous paint. attack near the stall should be confined be followed in stopping the rotation of (See § 4b.362 (c).) to speeds below this value; propellers in flight. (d) Operating limitation placard. A (5) The flaps extended speed (see (d) Other emergency procedures. placard shall be provided in front of and § 4b.714), together with a description of Recommended procedures shall be de in clear view of the pilots stating: “This the pertinent flap positions and engine scribed to be followed in the event of fire, airplane must be operated in compli powers; decompression, etc. ance with the operating limitations spe (6) The landing gear operating speed cified in CAA approved Airplane Plight (see § 4b.715), together with a statement § 4b.743 Performance information— Manual.” to the effect that this is the maximum (a) Performance data. A summary of all (e) Safety equipment. (1) Safety speed at which it is safe to extend or re pertinent performance data shall be equipment controls which the crew is tract the landing gear; given, including the performance data expected to operate in time of emergency (7) The landing gear extended speed necessary for the application of the op such as flares, automatic life raft re (see § 4b.716), if greater than the landing erating rules of the Civil Air Regulations, leases, etc., shall be easily accessible and gear operating speed, together with a tbgether with descriptions of the condi plainly marked as to their method of statement to the effect that this is the tions, air speeds, etc., under which these operation. maximum speed at which the airplane data were determined. (2) When fire extinguishers and sig can be flown saf ely with the landing gear (b) Flap controls. Instructions shall naling and other life-saving equipment in the extended position. be included describing the use and ad are carried in lockers, compartments, (b) Powerplant limitations. Informa justment of the flap controls necessary etc., these locations shall be marked ac tion shall be included to outline and to to obtain the performance listed accord cordingly. explain all powerplant limitations (see ing to paragraph (a) of this section. Airplane Flight Manual § 4b.718) and to permit marking the in (c) Air speeds. The indicated air struments as required in §§ 4b.734 speeds corresponding with those deter § 4b.740 General. . (a) An Airplane through 4b.736. mined for take-off shall be listed together Plight Manual shall be furnished with (c) Weight and loading distribution. with the procedures to be followed in thç each airplane. The airplane weights and c. g. limits event the critical engine becomes inop (b) The portions of the manual listed required by §§ 4b.l01 and 4b.l02, shall be erative during take-off (see § 4b.742 (b) ). in §§4b.741 through 4b.743 as are included together with the items of (d) Miscellaneous. An explanation appropriate to the airplane shall be equipment on which the empty weight is shall be included of any significant or verified and approved and shall be based. Where the variety of possible unusual flight or ground handling char segregated, identified, and clearly dis loading conditions warrants, instructions acteristics. tinguished from portions not so ap shall be included to facilitate observance Airplane Identification Data proved. of the limitations. (c) Additional items of information (d) Flight load acceleration limits. § 4b.750 Identification plate. A fire having a direct and important bearing The positive maneuvering limit load proof identification plate shall be secure on safe operation shall be required when factors for which the airplane structure ly attached to the structure in an unusual design, operating, or handling has been proven shall be described in accessible location where it will not likely characteristics so warrant. terms of accelerations, together with a be defaced during normal service. Thé § 4b.741 Operating limitations—(a) statement to the effect that these accel identification plate shall not be placed Air-speed limitations. The following erations limit the angle of bank in in a location where it might be expected air-speed limitations shall be included turns and limit the severity of pull-up to be destroyed or lost in the event of an together with sufficient information to maneuvers. accident. The identification plate shall permit marking the air-speed indicator (e) Flight crew. The number and contain the identification data required in accordance with § 4b.732: functions yof the minimum flight crew by § 2.36 of this chapter. (1) The never-exceed speed (see determined in accordance with § 4b.720 [F. R. Doc. 50-723; Piled, Jan. 24, 1950; § 4b.711); shall be described. 8:59 a. m.] Wednesday, January 25, 1950 fed er a l' r eg ist er 443
NOTICES
IV. Payment. 1. Payment at par for CIVIL AERONAUTICS BOARD DEPARTMENT OF THE TREASURY notes allotted hereunder must be made Fiscal Service, Bureau of the on or before February 1,1950, or on later [Docket No. 4150] Public Debt allotment, and may be made only in G olden N orth Airways, I nc. Treasury Certificates of Indebtedness of [1950 Dept. Circular 856] Series B-1950, maturing February 1, NOTICE OF HEARING 1950, which will be accepted at par, and In the matter of the suspension and iy 4 P ercent T reasury N otes of S eries should accompany the subscription. revocation of Letter of Registration No. A-1951 V. General Provisions. 1. As fiscal 666 issued to Golden North Airways, Inc. OFFERING OF NOTES ' agents of the United States, Federal Notice is hereby given that hearing in Reserve Banks are authorized and re the above-entitled proceeding postponed J anuary 20, 1950. quested to receive subscriptions, to make from January 19, 1950, to a time and 1. Offering of notes. 1. The Secretary allotments on the basis and up to the place to be fixed, is assigned to be held of the Treasury, pursuant to the author amounts indicated by the Secretary of on February 2,1950, at 10:00 a. m., e. s. t., ity of the Second Liberty Bond Act, as the Treasury to the Federal Reserve in Room 116, Wing “C”, Temporary amended, invites subscriptions, at par, Banks of the respective Districts, to issue Building No. 5, Sixteenth Street and Con from the people of the United States for allotment notices, to receive payment for stitution Avenue NW., Washington, D. C., notes of the United States, designated notes allotted, to make delivery of notes before Examiner Curtis C. Henderson. li/4 percent Treasury Notes of Series on full-paid subscriptions allotted, and Dated at Washington, D. C., January A-1951, in exchange for Treasury Cer they may issue interim receipts pending tificates of Indebtedness of Series B- delivery of the definitive notes. 19, 1950. 1950, maturing February 1, 1950. 2. The Secretary of the Treasury may By the Civil Aeronautics Board. II. Description of notes. 1. The notes at any time, or from time to time, pre [seal] M. C. M ulligan, will be dated February 1, 1950, and will scribe supplemental or amendatory rules Secretary. bear interest from that date at the rate and regulations governing the offering, of IV4 percent per annum, payable on which will be communicated promptly to [F. R. Doc. 50-673; Filed, Jan. 24, 1950; a semiannual basis on October 1, 1950, the Federal Reserve Banks. 8:46 a. m.] and April 1 and October 1, 1951. They will mature October 1,1951, and will not [seal] J ohn W. S nyder, be subject to call for redemption prior Secretary of the Treasury. FEDERAL COMMUNICATIONS to maturity. [F. R. Doc. 50-690; Filed, Jan. 24, 1950; COMMISSION 2. The income derived from the notes 8:50 a. m.j shall be subject to all taxes, now or here D elegations of Authority after imposed under the Internal Rev In the matter of amendment of sec enue Code, or laws amendatory or DEPARTMENT OF AGRICULTURE tion 0.145 of the Commission’s statement supplementary thereto. The notes shall of delegations of authority. be subject to estate, inheritance, gift or Forest Service At a meeting of the Federal Commu other excise taxes, whether Federal or [Memorandum No. 1249] nications Commission held at its offices State, but shall be exempt from all taxa in Washington, D. C. on the 18th day tion now or hereafter imposed on the National F orest Advisory Board of of January 1950; principal or interest thereof by any Appeals 1 The Commission having under con State, or any of the possessions of the sideration a delegation to the Secretary United States, or by any local taxing There is hereby established the Na of the Commission upon securing the authority. tional Forest Advisory Board of Appeals approval of the Bureaus of Law, Engi 3. The notes will be acceptable to se to advise the Secretary on any appeals to neering and Accounting, to act on ap cure deposits of public moneys. They him from the decisions of the Chief of plications for construction permits for will not be acceptable in payment of the Forest Service involving any public noncommercial educational FM broad taxes. use of the national forests and other cast stations; and 4. Bearer notes will be issued in de lands under the administration or con It appearing, that such delegation nominations of $1,000, $5,000, $10,000, trol of the Forest Service. The Board would expedite Commission action on $100,000 and $1,000,000. The notes will shall be comprised of five employees of the above authorizations and would be not be issued in registered form. the Department of Agriculture, to be se in the public interest; and 5. The notes will be subject to the gen lected from any agencies within the De It further appearing, that the amend eral regulations of the Treasury Depart partment except the Forest Service. A ment of the Commission’s rules and ment, now or hereafter prescribed, gov majority of the members of the Board regulations to effectuate the above pro erning United States notes. shall constitute a quorum. Upon re posal is procedural in nature and that III. Subscription and allotment. 1. ceipt of a written request to the Secre the public notice and procedure pro tary from the appellant, the Secretary vided for in section 4 of the Adminis Subscriptions will be received at the Fed trative Procedure Act is not required eral Reserve Banks and Branches and at shall refer the appeal to the Board be fore which the appellant may appear if herein; the Treasury Department, Washington. It is ordered, That, effective immedi Banking institutions generally may sub he so desires and the Board shall con ately, section 0.145 of the Commission’s mit subscriptions for account of custom sider the appeal on its merits and furnish rules and regulations is amended by the ers, but only the Federal Reserve Banks its advice and recommendations to the addition of new paragraph (g), reading and the Treasury Department are- au Secretary. as follows: thorized to act as official agencies. 2. The Secretary of the Treasury re Done at Washington, D. C., this 17th (g) Applications for construction per serves the right to reject any subscrip day of January 1950. Witness my hand mits for new noncommercial educa tion, in whole or in part, to allot less than and the seal of the Department of Agri tional FM broadcast stations. the amount of notes applied for, and to culture. Released: January 18, 1950. close the books as to any or all subscrip tions at any time without notice; and any [seal] Charles F. B rannan, F ederal Communications action he may take in these respects shall Secretary of Agriculture. Commission, be final. Subject to these reservations, all [F. R. Doc. 50-699; Filed, Jan. 24, 1950; [seal] T. J. S low ie, subscriptions will be allotted in full. Al 8:49 a. m.] Secretary. lotment notices will be sent out promptly [F. R. Doc. 50-687; Filed, Jan. 24, 1950; upon allotment. 1 See Title 36, Chapter n , Part 211, supra. 8:52 a. m.] 444 NOTICES
INTERSTATE COMMERCE From: To and between points in the [4th Sec. Application 24811] south. COMMISSION W oodpulp F rom the S outh to M enom Grounds for relief : Circuitous routes. in e e , M ich., and M arinette, W is . (Rev. S. O. 562, King’s Rev. L C . C . Order 9] Any interested person desiring the Commission to hold a hearing upon such application for relief R erouting or D iversion of T raffic application shall request the Commission J anuary 20,1950. In the opinion of Homer C. King, in writing so to do within 15 days from Agent, the railroads, because of high the date of this notice. As provided by The Commission is in receipt of the water of the Ohio and the Wabash rivers the general rules of practice of the Com above-entitled and numbered applica and their tributaries in the states of mission, Rule 73, persons other than tion for relief from the long-and-short- Illinois, Indiana, and Kentucky, are un applicants should fairly disclose their in haul provision of section 4 (1) of the able to transport traffic routed over their terest, and the position they intend to Interstate Commerce Act. lines in that territory: It is ordered, that: take at the hearing with respect to the Filed by: R. E. Boyle, Jr., Agent, for (a) Rerouting traffic. Raijroads un application. Otherwise the Commission, and on behalf of carriers parties to Agent able to transport traffic to or through in its discretion, may proceed to investi C. A. Spaninger’s tariff I. C. C. No. 1051. points in the states of Illinois, Indiana, gate and determine the matters involved Commodities involved: Woodpulp, car and Kentucky because of high waters of in such application without further or loads. the Ohio and the Wabash rivers and formal hearing. If because of an emer From: Points in the south. their tributaries, are hereby authorized gency a grant of temporary relief is found To: Menominee, Mich., and Marinette, and directed to reroute or divert such to be necessary before the expiration of Wis. traffic over any available route to expe the 15-day period, a hearing, upon a Grounds for relief: Circuitous routes. dite the movement; the billing covering request filed within that period, may be Schedules filed containing proposed all such cars rerouted shall carry a ref held subsequently. rates: C. A. Spaninger’s tariff I. C. C. No. erence to this order as authority for the 1051, Supplement 79. By the Commission, Division 2. Any interested person desiring the rerouting. Cofaimission to hold a hearing upon such (b) Concurrence of receiving roads to [seal] W. P. B artel, application shall request the Commission be obtained. The railroad desiring to Secretary. divert or reroute traffic under this order in writing so to do within 15 days from shall confer with the proper transporta [F. R. Doc. 50-675; Filed, Jan. 24, 1950; the date of this notice. As provided by tion officer of the railroad or railroads to, 8:46 a. m.] the general rules of practice of the Com Which such traffic is to be diverted or mission, Rule 73, persons other than rerouted, and shall receive the concur applicants should fairly disclose their rence of such other railroads before the interest, and the position they intend [4th Sec. Application 24810] to take at the hearing with respect to rerouting of diversion is ordered. the application. Otherwise the Com (c) Notification to shippers. The M otor-R ail R ates; N ew Y ork, N ew carrier rerouting cars in accordance with mission, in its discretion, may proceed this order shall notify each shipper at the H aven and H artford R ailroad Co. to investigate and determine the matters APPLICATION FOR RELIEF involved in such application without fur time each car is rerouted or diverted and ther or formal hearing. If because of shall furnish to such shipper the new J anuary 20, 1950. routing provided under this order. an emergency a grant of temporary re (d) Effective date. This order shall The Commission is in receipt of the lief is found to be necessary before the become effective 12:01 a. m., January 18, above-entitled and numbered applica expiration of the 15-day period, a hear 1950. tion for relief from the long-and-short- ing, upon a request filed within that pe (e) Expiration date. This order shall haul provision of section 4 (1) of the riod, may be held subsequently. expire at 11:59 p. m., January 31, 1950, Interstate Commerce Act. By the Commission, Division 2. unless otherwise modified, changed, Filed by: The New York, New Haven and Hartford Railroad Company and [ seal] W. P. B artel, suspended or annulled. Secretary. It is further ordered, that this order Rand Express Freight Lines, Inc. shall be served upon the Association of Commodities involved: All commodi [F. R. Doc. 50-677; Filed, Jan. 24, 1950; American Railroads, Car Service Divi ties. 8:47 a. m.] sion, as agent of all railroads subscribing Between; Harlem River, N. Y., and to the car service and per diem agree Providence, R. I., or Boston, Mass., or ment under the terms of that agreement. Springfield, Mass. Grounds for relief: Competition with [4th Sec. Application 24812] Issued at Washington, D. C., January motor carriers. 18, 1950. Any interested person desiring the G rain F rom T exas to S t. Lo u is, M o., and East S t. Lo u is, II I. Interstate Commerce Commission to hold a hearing upon such application shall request the Commis APPLICATION FOR RELIEF Com m ission, sion in writing so to do within 15 days H omer C. K ing, J anuary 20, 1950. Agent. from the date of this notice. As provided by the general rules of practice of the The Commission is in receipt of the [P. R. Doc. 50-679; Piled, Jan. 24, 1950; Commission, Rule 73, persons other than above-entitled and numbered applica 8:47 a. m.] applicants should fairly disclose their tion for relief from the long-and-short- interest, and the position they intend to haul provision of section (4) (1) of the take at the hearing with respect to the Interstate Commerce Act. [4th Sec. Application 24809] application. Otherwise the Commission, Filed by: D. Q. Marsh, Agent, for and in its discretion, may proceed to investi on behalf of carriers parties to his tariff Various Commodities F rom , T o and gate and determine the matters involved I. C. C. No. 3831. B etween P oints in the S outh in such application without further or Commodities involved: Grain, grain formal hearing. If because of an emer products and related articles, also seeds, APPLICATION FOR RELIEF gency a grant of temporary relief is found carloads. J anuary 20, 1950. to be necessary before the expiration of From: Points in Texas. The Commission is in receipt of the the 15-day period, a hearing upon a re To: St. Louis, Mo., and East St. Louis, above-entitled and numbered application quest filed within that period, may be 111. for relief from the long-and-short-haul held subsequently. Grounds for relief: Circuitous routes. provision of section 4 (1) of the Inter By the Commission, Division 2. Schedules filed containing, proposed state Commerce Act. rates: D. Q. Marsh’s tariff I. C. C. No. Filed by: R. E. Boyle, Jr., Agent, pur [ seal] W. P. B artel, 3831, Supplement 14. suant to fourth-section order No. 9800. Secretary. Any interested person desiring the Commodities involved: Various com [F. R. Doc. 50-676; Filed, Jan. 24, 1950; Commission to hold a hearing upon such modities. 8:47 a. m.] application shall request the Commis- Wednesday, January 25, 1950 FEDERAL REGISTER 445 sion in writing so to do within 15 days companies concerned have been engaged Appropriate documents and papers from the date of this notice. As pro in negotiations looking toward the sale effectuating this order will issue. vided by the general rules of practice of of the gas properties; and the Commission, Rule 73, persons other It appearing to the Commission that Executed at Washington, D. C., on than applicants should fairly disclose it is appropriate to grant the application January 18, 1950. ■their interest, and the position they in in view of all the circumstances of this For the Attorney General. tend to take at the hearing with respect case: to the application. Otherwise the Com It is ordered, That the period for [seal] H arold I. Baynton, mission, in its discretion, may proceed to American Gas and Indiana & Michigan Acting Director, investigate and determine the matters to dispose of the gas properties of Indi Office of Alien Property. involved in such application without ana & Michigan be, and the same hereby further or formal hearing. If because is, extended to June 30, 1950. [F. R. Doc. 50-692; Filed, Jan. 24, 1950; of an emergency a grant of temporary 8:51 a. m.] relief is found to be necessary before the By the Commission. expiration of the 15-day period, a hear [seal] Orval L. DuB ois, ing, upon a request filed within that Secretary. [Return Order 532] period, may be held subsequently. [P. R. Doc. 50—672; Piled, Jan. 24, 1950; Unita B alducci By the Commission, Division 2. 8:46 a. m.] Having considered the claim set forth [seal] W. P. B artel, below and having issued a determina Secretary. DEPARTMENT OF JUSTICE tion allowing the claim, which is incor [F. R. Doc. 50-678; Piled, Jan. 24, 1950; Office of Alien Property porated by reference herein and filed 8:47 a. m.] herewith, Au th o rity : 40 Stat. 411, 55 Stat. 839, Pub. It is ord,ered, That the claimed prop Laws 322, 671, 79th Cong., 60 Stat. 50, 925; 50 erty, described below and in the deter SECURITIES AND EXCHANGE U. S. C. and Supp. App. 1, 616; E. O. 9193, July 6, 1942, 3 CFR, Cum. Supp., E. O. 9567, mination, be returned, subject to any COMMISSION June 8, 1945, 3 CFR, 1945 Supp., E. O. 9788, increase or decrease resulting from the administration thereof prior to return, [File Nos. 70-1178, 70-1852] Oct. 14, 1946, 11 F. R. 11981. [Vesting Order 14049, Amdt.] and after adequate provision for taxes I ndiana Service Corp. et al. and conservatory expenses: M ary H opff SUPPLEMENTAL ORDER APPROVING Claimant, Claim No., Notice of Intention EXTENSION OF TIME In re: Debt owing to Mary Hopff, also To Return Published, and Property known as Caecilie Hopff. At a regular session of the Securities Unita Balducci, Vicopisano, Pisa, Italy; and Exchange Commission held at its Vesting Order 14049, dated November Claim No. 7136; December 2, 1949 (14 F. R. office in the city of Washington, D. C., on 17, 1949, is hereby amended as follows 7261); $4,602.07 in the Treasury of the United and not otherwise; ■ States and an undivided one-half interest the 19th day of January A. D. 1950. By deleting from subparagraph 2 of in each of two pieces of real property, de In the matter of Indiana Service Cor said Vesting Order 14049 the date “De scribed as. follows: poration, Indiana & Michigan Electric cember 31, 1945” and substituting there (1) All that certain lot, piece or parcel Company, American Gas and Electric for the date “July 18,1948”. of land, lying and being in the City of Company, Pile No. 70-1852; American Richmond, Virginia, at the northwest cor Gas and Electric Company, File No. 70- All other provisions of said Vesting ner of Kensington and Belmont Avenues, 1178. Order 14049 and all actions taken by or and more fully described as follows: Begin on behalf of the Attorney General of the ning at the northwest intersection of Ken American Gas and Electric Company United States in reliance thereon, pur sington and Belmont Avenues, thence (“American Gas") having on June 30, suant thereto and under the authority running westwardly along and fronting on 1947, acquired all the common stock of thereof are hereby ratified and con the north line of Kensington Avenue Fifty Indiana Service Corporation (“Indiana firmed. ( 5 0 ) Feet, thence back northw ard.1 v from Service”) in accordance with the Com said front and between parallel li t (the mission’s order of December 18, 1946, Executed at Washington, D. C.f on eastern line of which is the western line of subject to the condition that the non January 6, 1950. Belmont Avenue) One hundred and Twenty ( 1 2 0 ) Feet to an alley in the rear Fifteen electric properties of Indiana Service be For the Attorney General. disposed of within one year from the date ( 1 5 ) feet wide, being lots 3 2 and 3 3 in [seal! H arold I. B aynton, Block 5 in the Plan of Lee Annex. of acquisition, provided, however, that (2) All that certain lot, piece or parcel application might be made for an ex Acting Director, of land, lying and being in the City of tension or extensions of such period for Office of Alien Property. Richmond, Virginia, and more fully de good cause shown; and [F. R. Doc. 50-691; Filed, Jan. 24, 1950; scribed as follows, to-wit: Beginning at a . The Commission by order dated June 8:50 a. m.] point on the West Line of Belmont Avenue distant One Hundred (100) Feet North of 30,1948, having (1) approved the merger the intersection of the Northern line of of Indiana Service into Indiana & Mich Kensington Avenue with the Western line igan Electric Company (“Indiana & of Belmont Avenue, thence running North Michigan”), also a subsidiary of Ameri [Return Order 529] wardly along the said Western line of Bel can Gas, and (2) extended the period for G isela B oesl mont Avenue Twenty (20) Feet to the South the disposition of the gas properties by ern line of a fifteen (15) Foot alley, thence the merged company; and the Commis Having considered the claim set forth back Westwardly between parallel lines sion by orders dated January 6,1949, and below and having issued a determination Thirty (30) Feet, (the Northern line of allowing the claim, which is incorporated which is the Southern line of said Fifteen July 6, 1949, having granted further (15) Foot alley. extensions of time for such dispositions; by reference herein and filed herewith, and It is ordered, That the claimed prop Appropriate documents and papers American Gas and Indiana & Michigan erty, described below and in the deter effectuating this order will issue. having filed an application for a further mination, be returned, subject to any increase or decrease resulting from the Executed at Washington, D. C., on extension of the period for the disposi January 18, 1950. tion of the gas properties to June 30, administration thereof prior to return, 1950, said application indicating that and after adequate provision for taxes For the Attorney General. American Gas and Indiana & Michigan and conservatory expenses: have heretofore disposed of the trans Claimant, Claim No., Notice of Intention To [seal] H arold I. B aynton, portation and water properties of Indi Return Published, and Property Acting Director, Office of Alien Property. ana & Michigan, that the only remaining Gisela Boesl, Vienna, Austria; Claim No. properties of the company to be disposed 39913; December 2, 1949 (14 F. R. 7261); [F. R. Doc. 50-693; Filed, Jan. 24, .1950; of are the gas properties, and that the $990.51 in the Treasury of the United States. 8:51 a. m.] 446 RULES AND REGULATIONS
[Return Order 536] City, New York, together with the cash vision for taxes and conservatory ex B ertha G rumbach dividends accrued thereon be returned, penses. The claimants, the number of subject to any increase or decrease re shares claimed, the stock certificate Having considered the claim set forth sulting from the administration thereof numbers and the amount of the dividends below and having issued a determination prior to return and after adequate pro- are identified below: allowing the claim, which is incorporated by reference herein and filed herewith, Shares Certif It is ordered, That the claimed prop Claim Claimant icate Amount erty, described below and in the deter No. numbers mination, be returned, subject to any Common Preferred increase or decrease resulting from the Giuseppina Azzolini, Sarzana, Italy______f 51 32 administration thereof prior to return, 39579 \ ...... — 30 86 $218.02 and after adequate provision for taxes 39600 Alfonso Bruzzo, Lorenzo Bruzzo, Benedetto Bruzzo, Matteo and conservatory expenses: Bruzzo, a/k/a Fratelli Bruzzo, Genoa, Italy...... 210 105 1,074.30 39614 Maria Barbano ved. Ceci, a/k/a Maria Ceci, Rome, Italy__ / 25 64 236.27 Claimant, Claim No., Notice of Intention To \...... — 40 119 39616 Bianca Boccardo, Paolina Boccardo ved. Cerone, Eugenia f 20 66 Return Published, and Property Boccardo, as heirs of Domenico Boccardo Genoa, Italy. l ...... —- 39 121 224.83 Bertha Grumbach, Freiburg, Germany; 39626 Ida Novaresio ved. de Ferrari, Giovanna De Ferrari, Nico / 215 74 } 1, 499.96 letta De Ferrari, as heirs of Angelo De Ferrari, Pavia, Italy. \ ...... — - 240 131 Claim No. 29438; December 14, 1949 (14 F. R. / 25 92 7496) ; $4,192.45 in the Treasury of the United 39643 Angelo Galletto as sole heir of G. B. Galletto, Genoa, Iatly. 32 147 195.35 States. All right, title and interest of Bertha 39647 Giuseppe Gambaro, as sole heir of Maria Gambaro, Genoa, f 220 96 Italy. \ __ 166 151 } 1,127.66 Grumbach in and to the Estate of Emil Weil, f 18 122 deceased, and in and to the trusts created 39673 Giuseppe Orlando, Florence, Italy______\ ...... 34 175 196.72 under the Will of Emil Well. 39677 Enrica Basevi ved. Levi, Gabriella Basevi in Zamorani, Rome, Italy,...... 25 126 31.64 39693 Lina Poggiolini, Anna Poggiolini, Florence, Italy______36 147 45.57 Appropriate documents and papers ef / 20 153 fectuating this order will issue. 39699 Enrichetta Capurro, Genoa, Italy______l ...... — 20 203 127.63 39702 Olga Queirolo, Anna Benvenuto, as heirs of Giovanni 156 Executed at Washington, D. C., on Jan Queirolo, Genoa, Italy. 1...... - 30 206 166.13 39709 Ing. Riccardo Salvadon, Rome, Italy...... 106 213 542.26 uary 18, 1950. 39712 Maria Scartezzini, Giorgina Scartezzini, Maria Scartezzini, as the heirs of Giovanna Bassi ved. Scartezzini, Genoa, 1 18 165 534.35 For the Attorney General. Italy. f...... -...... 100 216 [ seal] H arold I. B aynton, 39719 Enrico Sermarini, as the sole heir of Andreina Vignolo ved. / 6 172 Sermarini, Genoa, Italy. l...... — 70 222 365.69 Acting Director, 39732 Clemente Aldobrandini, Ferdinando Aldobrandini, as heirs / 25 185 Office of Alien Property. of Giuseppe Aldobrandini, Rome, Italy. \ ...... 20 233 133.96 39741 Gemma Apricale, Angelita Apricale, as heirs of Placida 190 [F. R. Doc. 50-694; Filed, Jan 24, 1950; Erminia Apricale, Genoa, Italy. { 4 7 237 40.88 8:52 a. m.] 39779 Adelaide Marmi Reale, a/k/a Adelaide Marmi di Attilio, / 6 225 Rome, Italy. 1...... 2 268 24.07 39780 Carlo Miragoli, Maria Grazia De Angelis, as heirs of Gio vanni Miragoli, Rome, Italy...... 0 226 9.84 39786 Cesare Cavalleroni, Leopolda Pizzomo Cavalleroni, Elena Cavalleroni, Adele Bignone ved. Cavalleroni, as heirs of D u sine M arie F rimer Riccardo Cavalleroni, Genoa, Italy...... 10 232 18.66 39795 Eugenia Tornati, Maria Tornati, as heirs of Mario Daglio, / 3 240 Genoa, Italy. \ ...... 23 27? 121.46 NOTICE OF INTENTION TO RETURN VESTED 39839 Angelita Apricale, Gemma Apricale, Lorenzo Rubatto, PROPERTY Genoa, Italy...... —...... 86 312 184.17 39847 William Thomas Dowland Robson, as sole heir of Jole 4 318 Pursuant to section 32 (f ) of the Trad Robson, Apuania, Italy. j 10 282 33.13 ing With the Enemy Act, as amended, 40644 Francesco Perotto, Giovanni Perotto, as heirs of Umberto r 40 142 306.41 notice is hereby given of intention to re Perotto, Spezia, Italy. l ...... 50 194 40645 Giovanna Saudino, Giuseppe Saudino, Pier Luigi Snudino, 143 turn, on or after 30 days from the date of Giovanni Ferrarini, as heirs of Leopoldo Ferrarini, Naples, 1 61 42 195 279.41 the publication hereof, the following Italy. i ...... property, subject to any increase or de crease resulting from the administration Appropriate documents and papers Claim No. 37365; property to the extent effectuating this order will issue. owned by the claimant immediately prior to thereof prior to return, and after ade the vesting thereof, described in Vesting quate provision for taxes and conserva Executed at Washington, D. C., on Order No. 4033 (9 F. R. 13269, November 8, tory expenses : January 17, 1950. 1944) relating to certain copyrights identi Claimant, Claim No., Property, and Location fied by assignments in the United States For the Attorney General. Copyright Office (listed in Exhibit A of said Dusine Marie Frimer, Veslos, Denmark; [seal] H arold I. B aynton, vesting order), including royalties pertain Claim No. 4734; $1,122.83 in the Treasury of ing thereto in the amount of $1,631.65. the United States. Acting Director, Office of Alien Property. Executed at Washington, D. C., on Executed at Washington, D. C., on January 19, 1950. January 19,1950. [F. R. Doc. 50-665; Filed, Jan. 23, 1950; 8:49 a. m.] For the Attorney General. For the Attorney General. [ seal] H arold L B aynton, [seal] H arold I. B aynton, Acting Director, Acting Director, Office of Alien Property. Office of Alien Property. F eliks G rabczewski [P. R. Doc. 50-696; Filed, Jan. 24, 1950; [F. R. Doc. 50-695; Filed, Jan. 24, 1950; notice of intention to return vested 8:52 a. m.] 8:52 a. m.] PROPERTY Pursuant to section 32 (f) of the Trad ing With the Enemy Act, as amended, notice is hereby given of intention to re [Return Order 519] turn, on or after 30 days from the date H erman R ottenberg et al. NOTICE OF INTENTION TO RETURN VESTED G iuseppina Azzolini et al. of publication hereof, the following prop erty located in Washington, D, C., includ PROPERTY Having considered the claims set forth ing all royalties accrued thereunder and below and having issued a determination Pursuant to section 32 (f) of the Trad all damages and profits recoverable for ing With the Enemy Act, as amended, allowing the claims, which is incor past infringement thereof, after ade porated by reference herein and filed notice is hereby given of intention to re quate provision for taxes and conserva turn, on or after 30 days from the date herewith, tory expenses: It is ordered, That the claimed prop of the publication hereof, the following erty, consisting of shares of the common Claimant and Property property, subject to any increase or de and third preferred capital stock of the Feliks Grabczewski; d/b/a F. Grabczewski; crease resulting from the administration De Nobili Cigar Company, Long Island Lodz, Cegielniana 82/8, Warsaw, Poland; thereof prior to return, and after ade- Wednesday, January 25, 1950 FEDERAL REGISTER 447 quate provision for taxes and conserva Property Custodian, Account No. 28-12305, It is ordered, That the claimed prop tory expenses: Washington, D. C. erty, described below and in the deter United States Savings Bond No. 3667947, mination, be returned, subject to any Claimant, Property, and Location Series G, 2 V2 % , in the face amount of increase or decrease resulting from the Herman Rottenberg, Brooklyn, N. Y.J $1,000.00, dated September 1, 1943, due Sep administration thereof prior to return, Emanuel David Rothenberg, Waco, Tex.; tember 1, 1955, registered in the name of Alien Property Custodian, Account No. 28- and after adequate provision for taxes Ruth Dina Rottenberg, New York, N. Y.; and conservatory expenses: Gusti Rottenberg, New York, N. Y.; Regina 12305, Washington, D. C. Rottenberg, Brooklyn, N. Y.; Claim No. 24741; Executed at Washington, D. C., on Claimant, Claim No., Notice of Intention To All right, title, interest and claim of any January 19, 1950. Return Published, and Property kind or character of Mina Rottenberg in Hans Strauss, New York, N. Y.; Claim No. and to the trust created under the will of For the Attorney General. 7778; Dec. 2, 1949 (14 F. R. 7261); all right, Aaron Hanauer, deceased, in equal shares to title, interest and claim of any kind or char [seal] H arold I. B aynton, the claimants; $1,019.40 in the Treasury of acter whatsoever of Bertha Lion Strauss in the United States in equal shares to the Acting Director, and to the trust estate of Meier Katten, claimants. Office of Alien Property. deceased; $3,881.46 in the Treasury of the To each of the claimants a one-fifth (%) [F. R. Doc. 50-697; Filed, Jan. 24, 1950; United States. interest in and to the following securities 8:52 a. m.] in the custody of the Safekeeping Depart Appropriate documents and papers ef ment of the Federal Reserve Bank of New fectuating this order will issue. York: United States Savings Bond No. 565515, Executed at Washington, D. C., on Series G, 2 y2%, in the face amount of [Return Qrder 526] January 17, 1950. $5,000.00, dated October 1, 1942, due Octo H ans S trauss For the Attorney General. ber 1, 1954, registered in the name of the Alien Property Custodian, Account No. 28- Having considered the claim set forth [seal] H arold I. B aynton, 12305, Washington, D. C. below and having issued a determina Acting Director, United States Savings Bond No. 3667977, Office of Alien Property. Series G, 2%%, in the face amount of tion allowing the claim, which is incor $1,000.00, dated October 1, 1942, due Octo porated by reference herein and filed [F. R. Doc. 50-666; Filed, Jan. 23, 1950; ber 1, 1954, registered in the name of Alien herewith, 8:50 a. m.]