Results
77-02-07: 77-02-07 BEECH: Amendment 39-2817. Applies to Model 200 (Serial Numbers BB-2, BB-6 thru BB-18 and BB-20 thru BB-50) airplanes. Compliance: Required within 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent unintentional feathering of a propeller due to failure of the secondary low pitch stop amplifier, accomplish either Paragraph A or B: A) Replace both P/N 101-364171-1 and P/N 101-364171-9 printed circuit board assemblies with P/N 101-364170-15 printed circuit board assemblies in accordance with Beechcraft Service Instruction No. 0745-354, notwithstanding its supersedence by Beechcraft Service Instruction No. 0808-247. B) Remove secondary low pitch stop system in accordance with Beechcraft Service Instruction No. 0808-247, or later approved revisions. C) Airplanes which have accumulated 100 hours' time in service after the effective date of this AD may be flown in accordance with FAR 21.197 to a place where a replacement or removal can be performed, providing the existing amplifiers have not malfunctioned. D) Any equivalent method of compliance with this AD, must be approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. NOTE: The manufacturer has advised the FAA that sufficient replacement parts are available to accomplish Paragraph A of this AD. This amendment becomes effective March 1, 1977.
2008-04-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Bombardier Aerospace has completed a system safety review of the CL-600-2B19 aircraft fuel system against new fuel tank safety standards, introduced in Chapter 525 of the Airworthiness Manual through Notice of Proposed Amendment (NPA) 2002-043. The identified non-compliances were assessed using Transport Canada Policy Letter No. 525-001 to determine if mandatory corrective action is required. The assessment and lightning tests showed that certain fuel tube self-bonded couplings do not provide sufficient lightning current capability. The assessment also showed that single failure of the integral bonding wire of the self-bonded couplings or excessive axial clearance at the reducer ferrules of certain self-bonded couplings could affect electrical bonding between fuel tubes. Insufficient electrical bonding between fuel tubes or insufficient current capability of fuel tube couplings, if not corrected, could result in arcing and potential ignition source inside the fuel tank during lightning strikes and consequent fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-04-14: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD requires inspecting the wheel speed transducer (WST) wiring harness, replacing the wiring harness if necessary, installing wiring hardware, and rerouting the WST wiring harness on both the left and right brake assemblies. This AD also requires revising the Abnormal Procedures section of the airplane flight manual (AFM) and quick reference handbook (QRH). This AD was prompted by reports of damage to the wiring harness due to excessive slack in the wiring harness assembly that allows contact with the main landing gear tire and by the determination that the AFMs and QRHs contain incorrect procedures for anti-skid braking system failures. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-06: 78-12-06 PIPER: Amendment 39-3242 as amended by amendment 39-3461. Applies to Piper Aircraft Corporation Model PA-31T aircraft, S/N 31-7620012 and up, certificated in all categories, equipped with nose landing gear wheel assembly, Piper P/N 551-778, Cleveland P/N 40-120A. To detect cracks in the nose landing gear wheel, accomplish the following: (a) Prior to next flight visually check the nose wheel cup and flange area for cracks. If a crack is found, replace the wheel with an airworthy part of the same P/N or Piper P/N 551- 758, B. F. Goodrich P/N 3-1331, equipped with a tubeless tire, size 18 x 4.4, 6 ply rating or Piper P/N 551-782, B. F. Goodrich P/N 3-1076. Check may be accomplished by pilot. (b) Repeat paragraph (a) prior to each flight. (c) When wheel of Piper P/N 551-758, B. F. Goodrich P/N 3-1331 or Piper P/N 551- 782, B. F. Goodrich P/N 3-1076 is installed, repeat inspections of paragraph (b) may be discontinued. (d) Record results of each check in aircraft log or continuous inspection manual. Amendment 39-3242 was effective June 22, 1978. This amendment 39-3461 is effective May 9, 1979.
2020-06-02: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines, LLC (IAE) PW1122G-JM, PW1124G1-JM, PW1124G- JM, PW1127GA-JM, PW1127G1-JM, PW1127G-JM, PW1133G-JM, PW1133GA-JM, PW1130G-JM, and PW1129G-JM model turbofan engines with a certain low- pressure turbine (LPT) 3rd-stage blade installed. This AD requires initial and repetitive borescope inspections (BSI) of the turbine stator intermediate outer rear air seal (turbine piston seal) and, depending on the results of the inspection, replacement with a part eligible for installation. This AD was prompted by reports of failure of turbine piston seals leading to fracture of the LPT 3rd-stage blades. The FAA is issuing this AD to address the unsafe condition on these products.
76-09-04: 76-09-04 HAMBURGER FLUGZEUGBAU GmbH: Amendment 39-2594. Applies to Model HFB-320 Hansa airplanes, S/N 1021 thru 1023, 1026 thru 1028, 1030 thru 1040, 1045, and 1049 thru 1055, certificated in all categories. Compliance is required as indicated. To prevent possible abrupt unwanted deflection of nose wheel steering, caused by a disengaged torque coupling, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished - (1) Inspect the nose landing gear steering torque coupling to ensure that it is in the proper engaged position; (2) Apply paint markings to the shaft (screw head and nut) and housing of the nose landing gear steering torque coupling in accordance with Figure 1 of HFB 320 Hansa Alert Service Bulletin 32-24A dated September 26, 1975, or an FAA-approved equivalent; and (3) Install an operating limitations placard in full view of the pilot that reads - "Prior to each takeoff, check for proper nose wheel marking alignment" NOTE: It is possible that the nose landing gear torque coupling may become overloaded and disengaged if the maximum steering angle is exceeded in maintenance or taxiing. This condition can be detected by an increased resistance felt at the control wheel. (b) Prior to each takeoff after the paint markings have been applied in accordance with paragraph (a) of this AD, check the markings for proper alignment. This check may be carried out by the pilot. (c) If improper alignment is detected during a check required by paragraph (b) of this AD, before further flight, repair the nose wheel steering unit. This amendment becomes effective, May 10, 1976.
92-10-11: 92-10-11 BOEING: Amendment 39-8245. Docket No. 91-NM-192-AD.\n\n\tApplicability: Model 757 series airplanes, listed in Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991, certificated in any category.\n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless previously accomplished.\n\n\tTo prevent damage to the floor beam at body station (BS) 1640, hydraulic system components, and flight control functions in the event of a sudden decrease in air pressure aft of the bulkhead lining, accomplish the following:\n\n\t(a)\tModify the soft bulkhead support structure at BS 1640 and replace the bulkhead lining in accordance with Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991.\n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO.\n\n\t(c)\tSpecial 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.\n\n\t(d)\tThe modification shall be done in accordance with Boeing Alert Service Bulletin 757-25A0112, dated July 18, 1991. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e)\tThis amendment becomes effective on June 1, 1992.
2020-05-20: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, and AS332L2 helicopters. This AD requires removing the drain plugs from the fuel tank compartments located under the bottom structure. This AD was prompted by the discovery that a modification to the fuel tank could lead to fuel accumulating in an area containing electrical equipment and subsequent ignition of fuel vapors. The actions of this AD are intended to address an unsafe condition on these products.
78-02-01: 78-02-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3124 as amended by amendment 39-3460. Applies to model PA-31T airplanes, serial numbers 31T-7400002 through 31T-7820077, and Model PA-31T1 airplanes, serial numbers 31T-7804001 through 31T-780-4006, certificated in all categories. Compliance required within the next fifty hours in service after the effective date of this AD, unless already accomplished. (a) To preclude possible failure of the main landing gear actuating cylinder rod end bearing assemblies, accomplish the inspection and replacement where required, described in the "Instruction" portion of Piper Aircraft Corporation Service Bulletin No. 57A, dated August 30, 1978. (b) Equivalent alterations or methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-3124 was effective January 18, 1978. This amendment 39-3460 is effective May 9, 1979.
84-12-51: 84-12-51 WESTLAND HELICOPTERS LIMITED: Amendment 39-4904. Applies to Westland Model 30 Series 100 helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent possible hazards in flight associated with cracking of the main rotor blades, accomplish the following: (a) Before the next flight and thereafter before the first flight of each day, visually inspect the main rotor blades in accordance with Westland Service Bulletin W30-05-23 dated July 16, 1984, or FAA-approved equivalent. (b) Within 15 hours after the effective date of this AD, unless already accomplished, conduct an eddy current inspection of the main rotor blade and thereafter at intervals not to exceed every 15 hours time in service since the last inspection in accordance with Westland Service Bulletin W30-05-23, or FAA-approved equivalent. (c) Remove from service any main rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with the AD may be used when approved by the Manager, Brussels Aircraft Certification Office, Federal Aviation Administration, c/o American Embassy, APO New York 09667. This amendment becomes effective September 11, 1984, as to all persons except those person to whom it was made immediately effective by telegraphic AD T84-12-51, issued June 5, 1984, which contained this amendment.