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2017-24-06: We are adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) LEAP-1A turbofan engines. This AD requires removal, inspection, rework, and re-identification of the high-pressure turbine (HPT) stage 2 disk, part number (P/N) 2466M52G03. This AD was prompted by a quality escape at the manufacturer that resulted in cracks appearing during forging of the HPT stage 2 disks. We are issuing this AD to address the unsafe condition on these products.
2002-03-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, Model MD-88 airplanes, and Model MD-90-30 series airplanes, that currently requires a revision to the applicable Airplane Flight Manual (AFM) to provide the flightcrew with the appropriate landing distance and flap positions, if applicable, for wet or icy runways. That AD also provides for an optional terminating action for the applicable AFM revision. For certain airplanes, this action requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent the flightcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane overrunning the end of the runway during landing on awet or icy runway.
89-23-12: 89-23-12 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION (Allison, formerly Detroit Diesel Allison): Amendment 39-6345. Applicability: Allison Model 250-C28B and -C28C engines, with P/N 6898952 second stage turbine nozzle assembly, installed in aircraft certificated in any category except those with the following turbine assembly serial numbers: Engine Model Turbine Serial Number 250-C28B CAT 70498, CAT 70499 CAT 70502, CAT 70513 and subsequent 250-C28C CAT 28010 and subsequent Compliance: Required as indicated, unless already accomplished. To prevent failure of the second stage turbine nozzle which can lead to rubbing contact between the nozzle diaphragm and the second stage turbine wheel possibly resulting in an uncontained turbine wheel failure, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD, or at the next turbine repair or overhaul, whichever occurs first, but not later thanNovember 30, 1989, perform the following: Modify and reidentify second stage turbine nozzle, P/N 6898952, into P/N 23001942, in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989. NOTE: Existing Model 250-C28B and -28C engines which have incorporated Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989, or prior issues of CEB-72-2044, or engines which have incorporated P/N 23001942 are already in compliance with this AD. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The second stage turbine nozzle modification shall be done in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Allison Gas Turbine Division, General Motors Corporation, P.O. Box 420, Indianapolis, Indiana 46206-0420. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. 20591. This amendment (39-6345, AD 89-23-12) becomes effective on October 29, 1989.
91-15-23: 91-15-23 AEROSPATIALE: Amendment 39-7088. Docket No. 91-NM-29-AD. Applicability: Model Nord 262A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. For airplanes which are 20 years old or more since new as of the effective date of this AD: Within 2 years after the effective date of this AD, perform internal and external detailed visual inspections and a low frequency eddy current inspection of the fuselage skin panel junctions, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. B. For airplanes which are less than 20 years old since new as of the effective date of this AD: Within 4 years after the effective date of this AD, perform internal and external detailed visual inspections and a low frequency eddy current inspection of the fuselage skin panel junctions, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. C. If no corrosion is found as a result of the inspections required by paragraph A. or B. of this AD, accomplish the following: 1. At intervals not to exceed one year, perform an EXTERNAL visual inspection of the fuselage from Frame N to Frame 27, in accordance with Aerospatiale N262- Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. 2. At intervals not to exceed 2 years, perform an INTERNAL visual inspection from Frame N to Frame 27, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. 3. At intervals not to exceed 6 years, accomplish the following: a. NON-PRESSURIZED AREA: Perform internal and external detailed visual inspections of the circumferential and longitudinal skin panel junction from Frame N to Frame J and from Frame 21 to Frame 27, in accordance with the AccomplishmentInstructions, paragraph 2C(3)A of Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. b. PRESSURIZED AREA: Perform internal and external detailed visual inspections of the circumferential and longitudinal fuselage skin panel junctions in accordance with the Accomplishment Instructions, paragraph 2C(3)A of Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. D. If corrosion is found as a result of the inspections required by paragraph A., B., or C. of this AD, and the corrosion depth is equal to or less than 30 microns, accomplish one of the following: 1. Perform external visual inspections at intervals not to exceed one year, and low frequency eddy current inspections at intervals not to exceed 2 years, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991; or 2. Prior to further flight, repair in accordance with Scheme No. 1 (Preventative Measure Procedure without Removal of Panels) specified in Aerospatiale N262- Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. Thereafter, repeat the visual and low frequency eddy current inspections at intervals not to exceed 6 years, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991; or 3. Prior to further flight, repair in accordance with Scheme No. 2 (Curative Measures Procedures with Removal of Panels) specified in Aerospatiale N262-Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. This constitutes terminating action for the repetitive inspections of that area required by this AD. E. If corrosion is found as a result of the inspections required by paragraph A., B., or C. of this AD, and the corrosion depth is more than 30 microns but less than or equal to 100 microns, accomplish one of the following: 1. Prior to further flight, repair in accordance with Scheme No. 1 (Preventative Measure Procedure without Removal of Panels) specified in Aerospatiale N262- Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. Thereafter, repeat the visual and low frequency eddy current inspections at intervals not to exceed 2 years, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. 2. Prior to further flight, repair in accordance with Scheme No. 2 (Curative Measures Procedures with Removal of Panels) specified in Aerospatiale N262-Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. This constitutes terminating action for the repetitive inspections for that area required by this AD. F. If corrosion is found as a result of the inspections required by paragraph A., B., or C. of this AD, and the corrosion depth is more than 100 microns, prior to further flight, repair in accordance with Scheme No. 2 (Curative Measures Procedures with Removal of Panels) specified in Aerospatiale N262-Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. This constitutes terminating action for the repetitive inspections of that area required by this AD. G. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. H. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7088, AD 91-15-23) becomes effective on August 26, 1991.
88-06-07: 88-06-07 GENERAL ELECTRIC: Amendment 39-5866. Applies to General Electric (GE) CF34-1A and -3A turbofan engines installed in the Canadair Limited Model CL-600-2A12 and CL-600-2B16 aircraft. Compliance is required as indicated, unless already accomplished. To prevent an engine flameout or uncommanded power roll-back and subsequent inflight shutdown due to contamination of the fuel control, accomplish the following: (a) For the engines not operated in accordance with Canadair Airplane Flight Manual (AFM) Temporary Revision Numbers 601/10-1 and 601/11 for Model CL-600-2B16, or Temporary Revision Numbers 601/17-1 and 601/18 for Model CL-600-2A12, accomplish the following prior to further flight after the effective date of this AD: (1) For engines with fuel controls identified in GE Service Bulletin (SB) Number (CF34) 73-5, dated January 22, 1988, replace the fuel control with a reworked unit which has a redesigned bypass valve piston installed and cleaned internally by the improved process, in accordance with this SB. (2) For engines with fuel controls identified in GE SB Number 73-6, dated January 22, 1988, replace the bypass valve piston with redesigned hardware in accordance with this SB. (b) For the engines operated in accordance with Canadair AFM Temporary Revisions Numbers 601/10-1 and 601/11 for Model CL-600-2B16, or Temporary Revision Numbers 601/17-1 and 601/18 for Model CL-600-2A12, accomplish paragraphs (a)(1) and (a)(2) above within 500 hours in service from the effective date of this AD, or prior to September 30, 1988, whichever occurs sooner. (c) Aircraft may be ferried in accordance with the provision of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of the AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. The GE SB's identified and described in this document are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the engine manufacturer's SB's may obtain copies upon request to General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-08, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on March 23, 1988.
2017-24-04: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.27 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports indicating that certain exit signs have a hydrogen isotope that decays over time, causing the signs to lose their brightness. We are issuing this AD to address the unsafe condition on these products.
2017-23-08: We are superseding Airworthiness Directive (AD) 2014-24-02 for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. AD 2014-24-02 required repetitively inspecting the main rotor (M/R) rotating scissors, removing certain lower half scissor spherical bearings (bearings) from service, and installing a special nut. This new AD revises the inspection requirements and requires replacing the bearings. This AD is prompted by a new report of a dislodged bearing of an M/R rotating scissor. The actions of this AD are intended to correct an unsafe condition on these products.
2002-03-01: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-703 series turboshaft engines. This amendment requires initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This amendment is prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. The actions specified in this AD are intended to prevent excessive vibrations produced by the reduction gearbox assembly that could cause failure of the tachometer drive spur gear.
2017-23-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. This AD requires an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-23-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of crack indications in the right wing upper aft skin, originating from fastener holes common to the rear spar upper chord. This AD requires repetitive inspections for cracking of the wing upper aft skin, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.