37020 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Rules and Regulations

(e) A coolant temperature indicator. 11. Powerplant—Fuel system—Fuel- considered possible in engine designs (f) An indicating means for the fuel Freezing: with removable cylinders or other non- strainer or filter required by § 23.997 to If the fuel in the tanks cannot be integral block designs. The following is indicate the occurrence of shown to flow suitably under all required: contamination of the strainer or filter possible temperature conditions, then a. It must be shown that the engine before it reaches the capacity fuel temperature limitations are construction type (massive or integral established in accordance with required. These will be considered as block with non-removable cylinders) is § 23.997(d). part of the essential operating inherently resistant to liberating high 1. No indicator is required if the parameters for the aircraft and must be energy fragments in the event of a engine can operate normally for a limitations. catastrophic engine failure; or, specified period with the fuel strainer a. The takeoff temperature limitation b. It must be shown by the design of exposed to the maximum fuel must be determined by testing or the engine, that engine cylinders, other contamination as specified in MIL– analysis to define the minimum cold- engine components or portions thereof 5007D and provisions for replacing the soaked temperature of the fuel that the (fragments) cannot be shed or blown off fuel filter at this specified period (or a airplane can operate on. the engine in the event of a catastrophic shorter period) are included in the b. The minimum operating engine failure; or maintenance schedule for the engine temperature limitation must be c. It must be shown that all possible installation. determined by testing to define the liberated engine parts or components do (g) Power setting, in percentage. minimum operating temperature not have adequate energy to penetrate (h) Fuel temperature. acceptable after takeoff (with minimum engine cowlings; or (i) Fuel flow (engine fuel takeoff temperature established in (1) d. Assuming infinite fragment energy, consumption). above). and analyzing the trajectory of the b. In place of compliance with 12. Powerplant Installation— probable fragments and components, § 91.205, the following will be complied Vibration levels: any hazard due to liberated engine parts with: The diesel engine has no manifold a. Vibration levels throughout the or components will be minimized and pressure gauge as required by § 91.205, engine operating range must be the possibility of crew injury is in its place, the engine instrumentation evaluated and: eliminated. Minimization must be as installed is to be approved as (1) Vibration levels imposed on the considered during initial design and not equivalent. TCDS is to be modified to airframe must be less than or equivalent presented as an analysis after design show power indication will be accepted to those of the gasoline engine; or completion. to be equivalent to the manifold (2) Any vibration level that is higher pressure indication. than that imposed on the airframe by Issued in Kansas City, Missouri on June 22, 2005. 9. Operating Limitations and the replaced gasoline engine must be Information—Powerplant limitations— considered in the modification and the John Colomy, Fuel grade or designation (Compliance effects on the technical areas covered by Acting Manager, Small Airplane Directorate, with § 23.1521(d) requirements): the following paragraphs must be Aircraft Certification Service. Instead of compliance with investigated: 14 CFR part 23, 23.251; [FR Doc. 05–12720 Filed 6–27–05; 8:45 am] § 23.1521(d), the applicant must comply 23.613; 23.627; 23.629 (or CAR 3.159, as BILLING CODE 4910–13–P with the following: applicable to various models); 23.572; The minimum fuel designation (for 23.573; 23.574 and 23.901. diesel engines) must be established so it b. Vibration levels imposed on the DEPARTMENT OF TRANSPORTATION is not less than that required for the airframe can be mitigated to an Federal Aviation Administration operation of the engines within the acceptable level by use of isolators, limitations in paragraphs (b) and (c) of dampers clutches, and similar 14 CFR Part 39 § 23.1521. provisions, so unacceptable vibration 10. Markings And Placards— levels are not imposed on the previously [Docket No. 2003–NM–127–AD; Amendment Miscellaneous markings and placards— certificated structure. 39–14168; AD 2005–13–31] 13. Powerplant Installation—One Fuel, oil, and coolant filler openings RIN 2120–AA64 (Compliance with § 23.1557(c)(1) cylinder inoperative: requirements): It must be shown by test or analysis, Airworthiness Directives; Short Instead of compliance with or by a combination of methods, that the Brothers Model SD3–60 Airplanes § 23.1557(c)(1), the applicant must airframe can withstand the shaking or comply with the following: vibratory forces imposed by the engine AGENCY: Federal Aviation a. Fuel filler openings must be marked if a cylinder becomes inoperative. Diesel Administration, Department of at or near the filler cover with— engines of conventional design typically Transportation. (1) For diesel engine-powered have extremely high levels of vibration ACTION: Final rule. airplanes— when a cylinder becomes inoperative. (a) The words ‘‘Jet Fuel’’; and Data must be provided to the airframe SUMMARY: This amendment adopts a (b) The permissible fuel designations, installer/modifier so either appropriate new airworthiness directive (AD), or references to the Airplane Flight design considerations or operating applicable to all Short Brothers Model Manual (AFM) for permissible fuel procedures, or both, can be developed to SD3–60 airplanes, that requires designations. prevent airframe and propeller damage. performing repetitive inspections of the (c) A warning placard or note that 14. Powerplant Installation—High shear attachment fittings of the vertical states the following or similar: Energy Engine Fragments: stabilizer for corrosion, and performing ‘‘Warning—this airplane equipped It may be possible for diesel engine corrective actions if necessary. The with an aircraft diesel engine, service cylinders (or portions thereof) to fail actions specified by this AD are with approved fuels only.’’ and physically separate from the engine intended to detect and correct corrosion The colors of this warning placard at high velocity (due to the high internal in the area of the main spar web fittings should be black and white. pressures). This failure mode will be of the vertical stabilizer, which could

VerDate jul<14>2003 15:51 Jun 27, 2005 Jkt 205001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\28JNR1.SGM 28JNR1 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Rules and Regulations 37021

result in reduced structural integrity of SUPPLEMENTARY INFORMATION: A Explanation of Change to Applicability the vertical stabilizer. This action is proposal to amend part 39 of the Federal We have revised the applicability of intended to address the identified Aviation Regulations (14 CFR part 39) to the proposed AD to identify model unsafe condition. include an airworthiness directive (AD) designations as published in the most that is applicable to all Short Brothers DATES: Effective August 2, 2005. recent type certificate data sheet for the Model SD3–60 airplanes was published The incorporation by reference of a affected models. certain publication listed in the as a supplemental notice of proposed regulations is approved by the Director rulemaking (NPRM) in the Federal Explanation of Change to Final Rule of the Federal Register as of August 2, Register on April 1, 2005 (70 FR 16764). The proposed AD had an incorrectly 2005. That action proposed to require numbered ‘‘Note’’ paragraph. We have ADDRESSES: The service information performing repetitive inspections of the corrected the number of that Note in the referenced in this AD may be obtained shear attachment fittings of the vertical final rule. from Short Brothers, Airworthiness & stabilizer for corrosion, and performing Engineering Quality, P.O. Box 241, corrective actions if necessary. The Conclusion Airport Road, Belfast BT3 9DZ, actions specified by this AD are We have carefully reviewed the Northern Ireland. This information may intended to detect and correct corrosion available data and determined that air be examined at the Federal Aviation in the area of the main spar web fittings safety and the public interest require Administration (FAA), Transport of the vertical stabilizer, which could adopting the AD with the changes Airplane Directorate, Rules Docket, result in reduced structural integrity of described previously. We have 1601 Lind Avenue, SW., Renton, the vertical stabilizer. determined that these changes will Washington. Comments neither increase the economic burden FOR FURTHER INFORMATION CONTACT: on any operator nor increase the scope Todd Thompson, Aerospace Engineer, We provided the public the of the AD. International Branch, ANM–116, FAA, opportunity to participate in the Cost Impact Transport Airplane Directorate, 1601 development of this AD. No comments Lind Avenue, SW., Renton, Washington have been submitted on the proposed The following table provides the 98055–4056; telephone (425) 227–1175; AD or on the determination of the cost estimated costs for U.S. operators to fax (425) 227–1149. to the public. comply with this AD.

ESTIMATED COSTS

Number of Action Work hours Average labor Parts Cost per U.S.-registered Fleet cost rate per hour airplane airplanes

Inspection, per inspec- 4 $65 None ...... $260 46 $11,960, per inspection cycle. tion cycle.

The cost impact figure discussed ‘‘General requirements.’’ Under that Regulatory Policies and Procedures (44 above is based on assumptions that no section, Congress charges the FAA with FR 11034, February 26, 1979); and (3) operator has yet accomplished any of promoting safe flight of civil aircraft in will not have a significant economic the requirements of this AD action, and air commerce by prescribing regulations impact, positive or negative, on a that no operator would accomplish for practices, methods, and procedures substantial number of small entities those actions in the future if this AD the Administrator finds necessary for under the criteria of the Regulatory were not adopted. The cost impact safety in air commerce. This regulation Flexibility Act. A final evaluation has figures discussed in AD rulemaking is within the scope of that authority been prepared for this action and it is actions represent only the time because it addresses an unsafe condition contained in the Rules Docket. A copy necessary to perform the specific actions that is likely to exist or develop on of it may be obtained from the Rules actually required by the AD. These products identified in this rulemaking Docket at the location provided under figures typically do not include action. the caption ADDRESSES. incidental costs, such as the time Regulatory Impact List of Subjects in 14 CFR Part 39 required to gain access and close up, planning time, or time necessitated by The regulations adopted herein will Air transportation, Aircraft, Aviation other administrative actions. not have a substantial direct effect on safety, Incorporation by reference, Safety. Authority for This Rulemaking the States, on the relationship between the National Government and the States, Adoption of the Amendment Title 49 of the United States Code or on the distribution of power and specifies the FAA’s authority to issue responsibilities among the various I Accordingly, pursuant to the authority rules on aviation safety. Subtitle I, levels of government. Therefore, it is delegated to me by the Administrator, Section 106, describes the authority of determined that this final rule does not the Federal Aviation Administration the FAA Administrator. Subtitle VII, have federalism implications under amends part 39 of the Federal Aviation Aviation Programs, describes in more Executive Order 13132. Regulations (14 CFR part 39) as follows: detail the scope of the Agency’s For the reasons discussed above, I authority. PART 39—AIRWORTHINESS certify that this action (1) is not a DIRECTIVES We are issuing this rulemaking under ‘‘significant regulatory action’’ under the authority described in Subtitle VII, Executive Order 12866; (2) is not a I 1. The authority citation for part 39 Part A, Subpart III, Section 44701, ‘‘significant rule’’ under DOT continues to read as follows:

VerDate jul<14>2003 15:51 Jun 27, 2005 Jkt 205001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\28JNR1.SGM 28JNR1 37022 Federal Register / Vol. 70, No. 123 / Tuesday, June 28, 2005 / Rules and Regulations

Authority: 49 U.S.C. 106(g), 40113, 44701. (2) If any corrosion is outside the limits BT3 9DZ, Northern Ireland. To inspect copies specified in the Accomplishment of this service information, go to the FAA, § 39.13 [Amended] Instructions of Short Brothers Service Transport Airplane Directorate, 1601 Lind I 2. Section 39.13 is amended by adding Bulletin SD360–53–45, dated December Avenue, SW., Renton, Washington; or to the the following new airworthiness 2003, before further flight, replace the National Archives and Records Administration (NARA). For information on directive: corroded fitting with a new fitting, in accordance with the Accomplishment the availability of this material at the NARA, 2005–13–31 Short Brothers PLC: Instructions of the service bulletin. call (202) 741–6030, or go to http:// Amendment 39–14168. Docket 2003– (c) If no corrosion is found during the www.archives.gov/federal_register/code_of_ NM–127–AD. inspection required by paragraph (a) or if the federal_regulations/ibr_locations.html. Applicability: All Model SD3–60 airplanes, fitting was replaced with a new fitting in Effective Date certificated in any category. accordance with Short Brothers Service Compliance: Required as indicated, unless Bulletin SD360–53–45, dated December (h) This amendment becomes effective on accomplished previously. 2003, do the actions in paragraphs (c)(1) and August 2, 2005. To detect and correct corrosion in the area (c)(2) of this AD. Issued in Renton, Washington, on June 14, of the main spar web fittings of the vertical (1) Within 24 months after the initial 2005. stabilizer, which could result in reduced inspection required by paragraph (a) of this Kevin M. Mullin, structural integrity of the vertical stabilizer, AD or within 24 months after replacement of Acting Manager, Transport Airplane accomplish the following: the fitting with a new one, whichever occurs later, do a borescope (intrascope) detailed Directorate, Aircraft Certification Service. Inspection and Previous Actions inspection for corrosion, in accordance with [FR Doc. 05–12508 Filed 6–27–05; 8:45 am] (a) Except as provided by paragraphs (a)(1) Part A of the Accomplishment Instructions of BILLING CODE 4910–13–P and (a)(2) of this AD, within 4,800 flight Short Brothers Service Bulletin SD360–53– hours or 90 days after the effective date of 45, dated December 2003. Repeat this this AD, whichever occurs first, do a inspection thereafter at intervals not to DEPARTMENT OF TRANSPORTATION borescope inspection to detect corrosion of exceed 24 months. Do corrective actions in the shear attachment fittings of the vertical accordance with paragraph (b) of this AD. Federal Aviation Administration stabilizer, in accordance with the (2) Thereafter, except as provided in Accomplishment Instructions of Short paragraph (f) of this AD, no alternative 14 CFR Part 39 Brothers Service Bulletin SD360–53–45, borescope inspections may be approved. [Docket No. FAA–2004–18716; Directorate dated December 2003. Previous Repetitive Inspections (1) If an airplane (the shear attachment Identifier 2003–NM–240–AD; Amendment fitting) has been inspected in accordance (d) Borescope (intrascope) detailed 39–14156; AD 2005–13–19] with the Accomplishment Instructions of inspections done before the effective date of RIN 2120–AA64 Short Brothers Service Bulletin SD360–53– this AD in accordance with Bombardier Temporary Revisions (TR) TR360–MPSUPP– 44, Revision 1, dated January 24, 2003, before Airworthiness Directives; BAE the effective date of this AD, and was found 04 and TR360–MPSUPP–03, both dated to have no corrosion on the fittings, then the August 20, 2003, are acceptable for Systems (Operations) Limited Model initial inspection specified in paragraph (a) compliance with the requirements of BAe 146 and Avro 146–RJ Series of this AD is not required. paragraph (c)(1) of this AD. Airplanes (2) If the shear attachment fitting has been Disposition of Repairs for Corroded/ AGENCY: Federal Aviation inspected in accordance with the Oversized Holes Accomplishment Instructions of Short Administration (FAA), Department of Brothers Service Bulletin SD360–53–44, (e) Where Short Brothers Service Bulletin Transportation (DOT). Revision 1, dated January 24, 2003, and was SD360–53–45, dated December 2003, says to ACTION: Final rule. found to have corrosion, but the corroded contact the manufacturer for action on any fitting is not yet replaced, then a review of corroded or oversized hole found during the SUMMARY: The FAA is adopting a new the inspection results is required to inspection required by paragraph (a) or (c) of airworthiness directive (AD) for all BAE determine if the corrosion was within the this AD, before further flight, repair in Systems (Operations) Limited Model acceptable limits specified in Short Brothers accordance with a method approved by BAe 146 and Avro 146–RJ series either the Manager, International Branch, Service Bulletin SD360–53–45, dated airplanes. This AD requires repetitive December 2003. ANM–116, FAA, Transport Airplane Directorate; or the Civil Aviation Authority external eddy current inspections of the Corrective Actions and Repetitive (or its delegated agent). forward fuselage skin to detect cracking Inspections due to fatigue, and repair if necessary. Alternative Methods of Compliance (b) If any corrosion is found during the This AD is prompted by evidence of inspection required by paragraph (a) of this (f) In accordance with 14 CFR 39.19, the cracking due to fatigue along the edges AD, do the applicable actions required by Manager, International Branch, ANM–116, is of the chemi-etched pockets in certain paragraph (b)(1) or (b)(2) of this AD. authorized to approve alternative methods of front fuselage canopy skin panels. We compliance for this AD. (1) If any corrosion is within the limits are issuing this AD to detect and correct specified in the Accomplishment Note 1: The subject of this AD is addressed this cracking, which could result in in British airworthiness directive G–2004– Instructions of Short Brothers Service reduced structural integrity of the Bulletin SD360–53–45, dated December 0005, effective March 16, 2004. 2003, do the actions required by paragraphs airplane fuselage. (b)(1)(i) and (b)(1)(ii) of this AD. Incorporation by Reference DATES: This AD becomes effective (i) Repeat the inspection required by the (g) You must use Short Brothers Service August 2, 2005. service bulletin at intervals not to exceed 6 Bulletin SD360–53–45, dated December The incorporation by reference of a months. 2003, to perform the actions that are required certain publication listed in the AD is (ii) Within 18 months after the initial by this AD, unless the AD specifies approved by the Director of the Federal inspection required by paragraph (a) of this otherwise. The Director of the Federal Register as of August 2, 2005. AD, replace all corroded shear attachment Register approves the incorporation by ADDRESSES: fittings in accordance with the reference of this document in accordance For service information Accomplishment Instructions of the service with 5 U.S.C. 552(a) and 1 CFR part 51. To identified in this AD, contact British bulletin. Accomplishing the replacement get copies of the service information, contact Aerospace Regional Aircraft American ends the repetitive inspections required by Short Brothers, Airworthiness & Engineering Support, 13850 Mclearen Road, paragraph (b)(1)(i) of this AD. Quality, P.O. Box 241, Airport Road, Belfast Herndon, Virginia 20171.

VerDate jul<14>2003 15:51 Jun 27, 2005 Jkt 205001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\28JNR1.SGM 28JNR1