Results
2004-09-18: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires repetitively inspecting the seat rails located in the passenger cabin for evidence of damage and corrosion, repairing any damage or corrosion, and replacing any floor panels found to be "soft" due to ingress of moisture. This action is necessary to detect and correct corrosion on the seat rails for the passenger seats, which could result in the reduced structural integrity of the passenger seats, detachment of the seats from the seat rails, and injury to passengers. This action is intended to address the identified unsafe condition.
69-23-05: 69-23-05 MESSERSCHMITT-BOLKOW Gmb.H.: Amdt. 39-873. Applies to Bolkow Model Bolkow Junior Aircraft, Serial Numbers 505 through 684. Compliance is required as indicated unless already accomplished. To prevent failures of the lower engine-mounting bolts within the next 100 hours' time in service after the effective date of this AD, replace the lower engine-mounting bolts P/N 298-21093.22 with new bolts P/N 208- 21093.22 in accordance with Messerschmitt-Bolkow Mounting Instructions No. 04/68, dated October, 1968, or an FAA-approved equivalent (Messerschmitt-Bolkow Service Bulletin No. 208-1/68, dated November 14, 1968, covers this same subject). This amendment becomes effective December 11, 1969.
2021-19-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC130B4 and EC130T2 helicopters. This AD was prompted by a report of a jammed pilot collective pitch lever (collective). This AD requires inspecting the collective for proper engagement of the locking pin. The FAA is issuing this AD to address the unsafe condition on these products.
58-02-03: 58-02-03 HILLER: Applies to UH-12 Series Helicopters Equipped With Marvel- Schebler Automatic Altitude Compensating Carburetor Model MA-4-5AA (Aircooled P/N 19588). Compliance required by June 1, 1958. With a Marvel-Schebler Model MA-4-5AA carburetor installed, it is possible to start and run the engine with the carburetor mixture control in the idle cutoff position if the throttle is partially or fully opened. However, as soon as the throttle is fully closed, the idle cutoff will operate and shut off the engine. Therefore, it would be possible to start the engine, take off, and fly with the mixture in idle cutoff, as long as the throttle is never closed. The first time the throttle is closed, however, as in autorotation, an immediate engine stoppage would occur. To prevent inadvertent engine stoppage in flight due to failure to place the carburetor mixture control in the "ALT.COMP" position before takeoff, the following measure is necessary: Delete the carburetor mixture control from the cockpit and secure the carburetor setting at "ALT.COMP" at the carburetor. Hiller will issue a service bulletin covering this subject. Appropriate FAA approved Helicopter Flight Manual revision required.
2021-19-16: The FAA is superseding Airworthiness Directive (AD) 2021-16- 02, which applied to certain Airbus Helicopters Model SA330J, AS332C, AS332L, AS332L1, AS332L2, and EC225LP helicopters. AD 2021-16-02 required inspecting the locking safety mechanism of the left-hand (LH) side stairway door handle and depending on the results, corrective action. AD 2021-16-02 also required modifying that locking safety mechanism. This AD retains the requirements in AD 2021-16-02, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference, and clarifies a certain exception. This AD was prompted by the need to clarify that exception. The FAA is issuing this AD to address the unsafe condition on these products.
98-12-07: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D series engines, that currently requires a determination of the utilization rate and coating type of the 7th, 8th, 9th, 10th, 11th, and 12th stage high pressure compressor (HPC) disks, and removal, inspection for corrosion, and recoating of those HPC disks based on utilization rate. This amendment shortens the inspection interval for certain low utilization disks. This amendment is prompted by reports of an additional uncontained 9th stage HPC disk failure due to corrosion pitting. The actions specified by this AD are intended to prevent fracture of the HPC disks, which can result in uncontained release of engine fragments, inflight engine shutdown, and airframe damage. The incorporation by reference of Pratt & Whitney Alert Service Bulletin No. 6038, Revision 5, dated August 17, 1994, as listed in the regulations, was approved previously by the Director of the Federal Register as of November 28, 1994 (59 FR 49175, September 27, 1994).
2021-19-05: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by a report of a cracked hoist support assembly having a certain part number. This AD requires a one-time inspection of the hoist support assembly and, depending on the findings, replacement with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA) Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
72-06-03: 72-06-03 HAWKER SIDDELEY: Amdt. 39-1404. Applies to Hawker Siddeley Model DH-114 "Heron" Airplanes. Compliance is required as indicated. To prevent hazardous internal corrosion of the tubular structure of engine mounting frames, P/N's 14EM11A and 12A, accomplish the following: (a) For airplanes with engine mounting frames with serial numbers DHB/1 and subsequent, or with serial numbers prefixed by "DH/...", that do not incorporate Modification No. 1529, within four years after the effective date of this AD, unless already accomplished within the last four years, and thereafter at intervals not to exceed four years from the last inspection, conduct an x-ray inspection of the tubular structure of the engine mounting frame, P/N's 14EM11A and 12A, for internal corrosion in accordance with Hawker Siddeley Aviation Ltd. Technical News Sheet Series: Heron (114) No. E.3, Issue 1, dated August 24, 1964, or Issue 3, dated September 14, 1970, or later ARB-approved issue or FAA-approved equivalent. (b) For airplanes with engine mounting frames with serial numbers DHB/1 and subsequent, or with serial numbers prefixed by "DH/...", that incorporate Modification No. 1529, within four years after the date of incorporation of the modification, or within one year after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed four years from the last inspection, conduct an x-ray inspection of the tubular structure of the engine mounting frames, P/N's 14EM11A and 12A, for internal corrosion in accordance with Hawker Siddeley Aviation Ltd. Technical Sheet Series: Heron (114) No. E.3, Issue 3, dated September 14, 1970, or later ARB-approved issue or FAA-approved equivalent. (c) For airplanes with engine mounting frames with serial numbers prefixed by "S4/DHB..." or "BGB/DHB..." (manufactured to the standards of Modification No. 1529), within 10 years from the date of manufacture, and thereafter at intervals not to exceedfour years from the last inspection, conduct an x-ray inspection of the tubular structure of the engine mounting frames, P/N's 14EM11A and 12A, for internal corrosion in accordance with Hawker Siddeley Aviation Ltd. Technical News Sheet Series: Heron (114) No. E.3, Issue 3, dated September 14, 1970, or later ARB-approved issue or FAA-approved equivalent. NOTE: See Hawker Siddeley Technical News Sheet Series: Heron (114), No. E.3, Issue 3, dated September 14, 1970, for dates of engine mount manufacture. (d) If internal corrosion is found during an inspection required by paragraph (a), (b), or (c), before further flight replace or repair the engine mounting frame in accordance with Hawker Siddeley factory approved instructions or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, and continue to inspect in accordance with paragraph (a), (b), or (c) whichever is applicable. This supersedes Amendment 39-128 (30 F.R. 11030), AD 65-20-03. This amendment becomes effective April 6, 1972.
2004-09-23: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires repetitive inspections of the control panel of the direct current (DC) generator for discrepancies, and replacement of any discrepant part. This action is necessary to prevent loss of both DC generator systems and loss of several other airplane systems, which could lead to the pilot's inability to maintain controlled flight. This action is intended to address the identified unsafe condition.
2011-25-10: We are adopting a new airworthiness directive (AD) for all PW JT9D-7R4H1 turbofan engines. This AD was prompted by reports of cracks in five high-pressure compressor (HPC) shafts. This AD requires removing certain HPC shafts before their certified life limits and establishes a new, lower life-limit for these parts. We are issuing this AD to correct the unsafe condition on these products.