7932 Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations

CAUTION: of the Federal Aviation Regulations (14 CFR and puncturing the APU compartment, Do not attempt to overpower the autopilot. 21.197 and 21.199) to operate the airplane to which could result in reduced fire When the autopilot is engaged, applying a location where the requirements of this AD extinguishing capability in the APU force to the column may allow the alternate can be accomplished. compartment. trim to reposition the stabilizer. If the force (f) The actions shall be done in accordance with McDonnell Douglas Service Bulletin DATES: Effective March 24, 1997. is applied long enough, it will result in an The incorporation by reference of out-of-trim condition.’’ MD80–22–122, dated August 6, 1996 (for Model DC–9–80 series airplanes and Model certain publications listed in the ‘‘AUTOTHROTTLE: MD–88 airplanes); and McDonnell Douglas regulations is approved by the Director If the Autothrottle (A/T) disconnects when Service Bulletin MD90–22–005, dated August of the Federal Register as of March 24, either throttle disconnect button is 6, 1996 (for Model MD–90 airplanes). This 1997. depressed, and re-engages when throttle incorporation by reference was approved by ADDRESSES: The service information disconnect button is released, accomplish the the Director of the Federal Register in referenced in this AD may be obtained following procedures: accordance with 5 U.S.C. 552(a) and 1 CFR from AlliedSignal Aerospace, Attn: Data part 51. Copies may be obtained from PROCEDURE: Use Autothrottle System (as Distribution, M/S 64–3/2101–201, P.O. desired) McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California Box 29003, Phoenix, AZ 85038–9003; WHEN A DISCONNECT IS NECESSARY: 90846, Attention: Technical Publications telephone (602) 365–2493, fax (602) AUTOTHROTTLE RELEASE Business Administration, Department C1– 365–5577. This information may be BUTTON PRESS AND HOLD L51 (2–60). Copies may be inspected at the examined at the Federal Aviation • Press and hold either button until FAA, Transport Airplane Directorate, 1601 Administration (FAA), New England flashing red A/T annunciation is illuminated. Lind Avenue, SW., Renton, Washington; or at Region, Office of the Assistant Chief Flashing red light indicates autothrottle is the FAA, Transport Airplane Directorate, Los Counsel, 12 New England Executive disconnected. Angeles Aircraft Certification Office, 3960 • Park, Burlington, MA 01803–5299; or at AUTOTHROTTLE RELEASE BUTTON Paramount Boulevard, Lakewood, California; the Office of the Federal Register, 800 may then be released. or at the Office of the Federal Register, 800 • The FMA A/T window will annunciate North Capitol Street, NW., suite 700, North Capitol Street, NW., suite 700, as though the A/T is engaged. Washington, DC. Washington, DC. • The flashing red A/T annunciation of the (g) This amendment becomes effective on FOR FURTHER INFORMATION CONTACT: FMA cannot be extinguished with repeated March 28, 1997. Robert Baitoo, Aerospace Engineer, Los depression of the autothrottle release button. Issued in Renton, Washington, on February Angeles Aircraft Certification Office, • If the throttle levers are retarded to the 10, 1997. FAA, Transport Airplane Directorate, idle stop, the flashing red A/T annunciation Darrell M. Pederson, 3960 Paramount Blvd., Lakewood, CA will extinguish, and the A/T system will re- engage. Acting Manager, Transport Airplane 90712–4137; telephone (310) 627–5245; • If the DFGC is selected to the IAS mode Directorate, Aircraft Certification Service. fax (310) 627–5210. and the A/T SPEED mode is selected, the A/ [FR Doc. 97–3844 Filed 2–20–97; 8:45 am] SUPPLEMENTARY INFORMATION: A T system will re-engage.’’ BILLING CODE 4910±13±U proposal to amend part 39 of the Federal (c) Within 12 months after the effective Aviation Regulations (14 CFR part 39) date of this AD, accomplish the inspection by superseding AD 93–07–13, and replacement of the autopilot and 14 CFR Part 39 Amendment 39–8545 (58 FR 21917, autothrottle engage switches in the flight guidance control panel (FGCP), in [Docket No. 96±ANE±15; Amendment 39± April 26, 1993), which is applicable to accordance with the paragraphs 3., 3.A., and 9927; AD 97±04±04] AlliedSignal Inc. (formerly Garrett 3.B. of the Accomplishment Instructions of Auxiliary Power Division) GTCP85 RIN 2120±AA64 McDonnell Douglas Service Bulletin MD80– Series auxiliary power units (APUs), 22–122, dated August 6, 1996 (for Model DC– was published in the Federal Register Airworthiness Directives; AlliedSignal 9–80 series airplanes and Model MD–88 on August 12, 1996 (61 FR 41751). That Inc. GTCP85 Series Auxiliary Power airplanes); and McDonnell Douglas Service action proposed to require installing an Units Bulletin MD90–22–005, dated August 6, 1996 improved containment augmentation (for Model MD–90 airplanes). Once these AGENCY: ring, Part Number (P/N) 3616426–1, or actions are completed, the AFM revision Federal Aviation required by paragraphs (a) and (b) of this AD Administration, DOT. P/N 3616426–3, which is a redesigned may be removed. ACTION: Final rule. containment augmentation ring to allow Note 2: The McDonnell Douglas service installation on certain APUs that cannot bulletins referenced in this paragraph refer to SUMMARY: This amendment supersedes accept the ¥1 containment Honeywell Incorporated Service Bulletin an existing airworthiness directive (AD), augmentation ring. The containment 4034242–22–13 for additional service applicable to AlliedSignal Inc. (formerly augmentation rings, P/Ns 3616426–1 instructions. Garrett Auxiliary Power Division) and 3616426-3, improve the (d) An alternative method of compliance or GTCP85 Series auxiliary power units containment capability of the APU adjustment of the compliance time that (APUs), that currently requires relative to the earlier containment provides an acceptable level of safety may be removing the existing turbine wheel augmentation ring, P/N 3612249–1, by used if approved by the Manager, Los shroud and installing one constructed of preventing turbine shroud fragments Angeles Aircraft Certification Office (ACO), Hastelloy ‘‘S’’ material, or installing a from passing around the containment FAA, Transport Airplane Directorate. containment augmentation ring. This augmentation ring. The installation Operators shall submit their requests through an appropriate FAA Principal Maintenance amendment deletes the option of must be accomplished within 24 Inspector, who may add comments and then installing a turbine shroud constructed months after the effective date of this send it to the Manager, Los Angeles ACO. of Hastelloy ‘‘S’’ material. This AD, for flight operable APUs, and Note 3: Information concerning the amendment is prompted by a report of within 36 months after the effective date existence of approved alternative methods of insufficient APU containment capability of this AD, for APUs that are operable compliance with this AD, if any, may be with the Hastelloy ‘‘S’’ shroud alone on the ground only. The actions would obtained from the Los Angeles ACO. installed. The actions specified by this be required to be accomplished in (e) Special flight permits may be issued in AD are intended to prevent turbine accordance with AlliedSignal Aerospace accordance with sections 21.197 and 21.199 shroud fragments from exiting the APU Alert Service Bulletin (ASB) No. Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations 7933

GTCP85–49–A7189, Revision 2, dated adoption of the rule with the changes § 39.13 [Amended] October 8, 1996, AlliedSignal Aerospace described previously. The FAA has 2. Section 39.13 is amended by ASB No. GTCP85–49–A7189, Revision determined that these changes will removing Amendment 39–8545 (52 FR 1, dated July 19, 1996, or AlliedSignal neither increase the economic burden 45163, November 25, 1987) and by Aerospace ASB No. GTCP85–49–A7189, on any operator nor increase the scope adding a new airworthiness directive, Original, dated March 29, 1996; and of the AD. Amendment 39–9927, to read as AlliedSignal Aerospace ASB No. There are approximately 4,100 APUs follows: GTCP85–49–A6706, Revision 2, dated of the affected design in the worldwide 97–04–04 AlliedSignal Inc.: Amendment November 28, 1994, AlliedSignal fleet. The FAA estimates that 1,300 39–9927. Docket 96–ANE–15. Aerospace ASB No. GTCP85–49–A6706, APUs installed on aircraft of U.S. Supersedes AD 93–07–13, Amendment Revision 1, dated November 12, 1993, or registry will be affected by this AD, that 39–8545. Garrett ASB No. GTCP85–49–A6706, it will take no additional work hours if Applicability: AlliedSignal Inc. (formerly Original, dated December 7, 1992. the required actions are accomplished Garrett Auxiliary Power Division) GTCP85 Interested persons have been afforded when the APU is already disassembled series auxiliary power units (APUs), an opportunity to participate in the in the shop. Required parts will cost incorporating a one-piece cast turbine wheel, making of this amendment. Due approximately $1,550 per APU. Based Part Numbers (P/Ns) 968095–X, 3604604–X, 3606982–1, or 3842072–X (where ‘‘X’’ consideration has been given to the on these figures, the total cost impact of comments received. denotes any number). These APUs are the AD on U.S. operators is estimated to installed on but not limited to the following One commenter states that the AD be $2,015,000. should apply only to APUs with one- aircraft: British Aerospace BAC 1–11 series; Boeing 707, 727, and 737 series; Lockheed piece cast turbine wheels made of The regulations adopted herein will not have substantial direct effects on the L382 series; and McDonnell Douglas DC–8– MAR–M–247 material, as only these 70, DC–9, and MD–88 series aircraft. type turbine wheels have failed in the States, on the relationship between the national government and the States, or Note 1: This airworthiness directive (AD) commenter’s experience. The FAA applies to each APU identified in the concurs in part. The proposed rule as on the distribution of power and responsibilities among the various preceding applicability provision, regardless written applies to APUs with one-piece of whether it has been modified, altered, or cast turbine wheels with the listed P/Ns, levels of government. Therefore, in repaired in the area subject to the which are made of MAR–M–247 accordance with Executive Order 12612, requirements of this AD. For APUs that have material, but also Inconel, which have it is determined that this final rule does been modified, altered, or repaired so that the failed as well. not have sufficient federalism performance of the requirements of this AD Two commenters state that the AD implications to warrant the preparation is affected, the owner/operator must request of a Federalism Assessment. approval for an alternative method of should add an additional method of compliance in accordance with paragraph (c) compliance by replacing the one-piece For the reasons discussed above, I certify that this action (1) is not a of this AD. The request should include an cast turbine wheels with two-piece assessment of the effect of the modification, wheels. The FAA does not concur. The ‘‘significant regulatory action’’ under alteration, or repair on the unsafe condition proposed AD does not apply to APUs Executive Order 12866; (2) is not a addressed by this AD; and, if the unsafe with two-piece turbine wheels. ‘‘significant rule’’ under DOT condition has not been eliminated, the One commenter (the manufacturer) Regulatory Policies and Procedures (44 request should include specific proposed states that the economic analysis FR 11034, February 26, 1979); and (3) actions to address it. provides figures for the number of APUs will not have a significant economic Compliance: Required as indicated, unless in service domestically and worldwide impact, positive or negative, on a accomplished previously. that are too low. The FAA concurs and substantial number of small entities To prevent turbine shroud fragments from revised the economic analysis of this under the criteria of the Regulatory exiting the APU and puncturing the APU compartment, which could result in reduced final rule accordingly. Flexibility Act. A final evaluation has been prepared for this action and it is fire extinguishing capability in the APU One commenter states that the compartment, accomplish the following: proposed AD should be more clear in contained in the Rules Docket. A copy (a) For flight operable APUs, within 24 stating that compliance is acceptable of it may be obtained from the Rules months after the effective date of this AD, with either ASB stated in paragraphs Docket at the location provided under accomplish either of the following: (a)(1) and (a)(2) and (b)(1) and (b)(2) of the caption ADDRESSES. (1) Install a containment augmentation ring, P/N 3616426–3, in accordance with the compliance section. The FAA List of Subjects in 14 CFR Part 39 concurs and has put the ‘‘or’’ between AlliedSignal Aerospace Alert Service the appropriate paragraphs in bold type Air Transportation, Aircraft, Aviation Bulletin (ASB) No. GTCP85–49–A7189, to highlight its significance. safety, Incorporation by reference, Revision 2, dated October 8, 1996, Revision Two commenters concur with the AD 1, dated July 19, 1996, or Original, dated Safety. March 29, 1996; or as proposed. Adoption of the Amendment (2) Install a containment augmentation Since publication of the proposed ring, P/N 3616426–1, in accordance with rule, AlliedSignal Aerospace has issued Accordingly, pursuant to the AlliedSignal Aerospace ASB No.GTCP85– Revision 2 to ASB No. GTCP85–49– authority delegated to me by the 49–A6706, Revision 2, dated November 28, A7189, dated October 8, 1996, which is Administrator, the Federal Aviation 1994, AlliedSignal Aerospace ASB No. referenced in this final rule along with Administration amends part 39 of the GTCP85–49–A6706, Revision 1, dated Revision 1, dated July 19, 1996, and Federal Aviation Regulations (14 CFR November 12, 1993, or Garrett ASB No. Original, dated March 29, 1996. These part 39) as follows: GTCP85–49–A6706, Original, dated revisions of that ASB are all approved December 7, 1992. (b) For APUs that are operable on the methods of compliance for the PART 39ÐAIRWORTHINESS DIRECTIVES ground only, within 36 months after the appropriate paragraphs of this AD. effective date of this AD, accomplish either After careful review of the available 1. The authority citation for part 39 of the following: data, including the comments noted (1) Install a containment augmentation above, the FAA has determined that air continues to read as follows: ring, P/N 3616426–3, in accordance with safety and the public interest require the Authority: 49 U.S.C. 106(g), 40113, 44701. AlliedSignal Aerospace ASB No. GTCP85– 7934 Federal Register / Vol. 62, No. 35 / Friday, February 21, 1997 / Rules and Regulations

49–A7189, Revision 2, dated October 8, 1996, (c) An alternative method of compliance or compliance with this AD, if any, may be Revision 1, dated July 19, 1996, or Original, adjustment of the compliance time that obtained from the Los Angeles Aircraft dated March 29, 1996; or provides an acceptable level of safety may be Certification Office. (2) Install a containment augmentation used if approved by the Manager, Los (d) Special flight permits may be issued in ring, P/N 3616426–1, in accordance with Angeles Aircraft Certification Office. The accordance with sections 21.197 and 21.199 AlliedSignal Aerospace ASB No. GTCP85– request should be forwarded through an of the Federal Aviation Regulations (14 CFR 49–A6706, Revision 2, dated November 28, appropriate FAA Principal Maintenance 21.197 and 21.199) to operate the aircraft to 1994, AlliedSignal Aerospace ASB No. Inspector, who may add comments and then a location where the requirements of this AD GTCP85–49–A6706, Revision 1, dated send it to the Manager, Los Angeles Aircraft can be accomplished. November 12, 1993, or Garrett ASB No. Certification Office. (e) The actions required by this AD shall GTCP85–49–A6706, Original, dated Note 2: Information concerning the be done in accordance with the following December 7, 1992. existence of approved alternative method of ASBs:

Document No. Pages Revision Date

AlliedSignal Aerospace, GTCP85±49±A7189 ...... 1±14 ...... 2 ...... Oct. 8, 1996. Total pages: 14. AlliedSignal Aerospace, GTCP85±49±A7189 ...... 1±12 ...... 1 ...... July 19, 1996. Total pages: 12. AlliedSignal Aerospace, GTCP85±49±A7189 ...... 1±10 ...... Original ...... Mar. 29, 1996. Total pages: 10. AlliedSignal Aerospace, GTCP85±49±A6706 ...... 1 ...... 2 ...... Nov. 28, 1994. 2, 3 ...... 1 ...... Nov. 12, 1993. 4 ...... 2 ...... Nov. 28, 1994. 5±8 ...... 1 ...... Nov. 12, 1993. 9, 10 ...... 2 ...... Nov. 28, 1994. Total pages: 10. AlliedSignal Aerospace GTCP85±49±A6706 1±10 ...... 1 ...... Nov. 12, 1993 Total pages: 10. Garrett GTCP85±49±A6706 ...... 1, 2 ...... Original ...... Dec. 7, 1992 4±10 ...... Original ...... Dec. 7, 1992. Total pages: 9.

This incorporation by reference was ACTION: Final rule; request for The service information referenced in approved by the Director of the Federal comments. this AD may be obtained from Register in accordance with 5 U.S.C. 552(a) Aerospatiale, 316 Route de Bayonne, and 1 CFR part 51. Copies may be obtained SUMMARY: This amendment adopts a 31060 Toulouse, Cedex 03, France. This from AlliedSignal Aerospace, Attn: Data new airworthiness directive (AD) that is information may be examined at the Distribution, M/S 64–3/2101–201, P.O. Box applicable to certain Aerospatiale Model 29003, Phoenix, AZ 85038–9003; telephone FAA, Transport Airplane Directorate, (602) 365–2493, fax (602) 365–5577. Copies ATR42–200, –300, and –320 series 1601 Lind Avenue, SW., Renton, may be inspected at the FAA, New England airplanes. This action requires Washington; or at the Office of the Region, Office of the Assistant Chief Counsel, modification of the electrical wiring of Federal Register, 800 North Capitol 12 New England Executive Park, Burlington, the stick pusher/shaker test function to Street, NW., Suite 700, Washington, DC. MA; or at the Office of the Federal Register, reinforce system protection. This 800 North Capitol Street, NW., Suite 700, amendment is prompted by a report of FOR FURTHER INFORMATION CONTACT: Gary Washington, DC. at least one occurrence when the stick Lium, Aerospace Engineer, (f) This amendment becomes effective on pusher self-activated during flight. The Standardization Branch, ANM–113, March 24, 1997. actions specified in this AD are FAA, Transport Airplane Directorate, Issued in Burlington, Massachusetts, on intended to prevent inadvertent 1601 Lind Avenue, SW., Renton, February 4, 1997. activation of the stick pusher, which Washington 98055–4056; telephone James C. Jones, could cause reduced controllability of (206) 227–1112; fax (206) 227–1149. Acting Manager, Engine and Propeller the airplane, especially during takeoff or SUPPLEMENTARY INFORMATION: The Directorate, Aircraft Certification Service. landing. [FR Doc. 97–4098 Filed 2–20–97; 8:45 am] Direction Ge´ne´rale de l’Aviation Civile DATES: Effective March 10, 1997. BILLING CODE 4910±13±U (DGAC), which is the airworthiness The incorporation by reference of authority for France, recently notified certain publications listed in the the FAA that an unsafe condition may 14 CFR Part 39 regulations is approved by the Director exist on certain Model ATR42–200, of the Federal Register as of March 10, –300, and –320 series airplanes. The 1997. [Docket No. 97±NM±30±AD; Amendment DGAC advises of at least one occurrence 39±9939; AD 97±04±14] Comments for inclusion in the Rules of the inadvertent activation of the stick Docket must be received on or before pusher test function. An electrical fault April 22, 1997. RIN 2120±AA64 could be the cause of this anomaly; ADDRESSES: Submit comments in however, at this time, the exact cause is Airworthiness Directives; Aerospatiale triplicate to the Federal Aviation not known. This condition, if not Model ATR42±200, ±300, and ±320 Administration (FAA), Transport corrected, could result in self-activation Series Airplanes Airplane Directorate, ANM–103, of the stick pusher during flight, which Attention: Rules Docket No. 97–NM– would cause reduced controllability of AGENCY: Federal Aviation 30–AD, 1601 Lind Avenue, SW., the airplane, especially during takeoff or Administration, DOT. Renton, Washington 98055–4056. landing.