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75-08-17: 75-08-17 LOCKHEED AIRCRAFT SERVICE COMPANY: Amendment 39-2169 as amended by Amendment 39-2459. Applies to Lockheed Aircraft Service Company Model 209 Digital Flight Data Recorders installed in, but not limited to Boeing 727, 737 and 747, Douglas DC-8, DC-9, and DC-10, Lockheed L-1011, Dassault/Sud Fan Jet Falcon, Hawker-Siddeley DH-125 and 748, and Fokker F-28 airplanes, and Boeing-Vertol 114A (U.S. Army CH-47A) helicopters, certificated in all categories. \n\n\tCompliance required on or before January 1, 1976, unless already accomplished, except for Boeing 727 and 737 airplanes for which compliance is required on or before June 30, 1976, unless already accomplished. \n\n\tTo provide satisfactory recording of the required flight data parameters, install four identical vibration isolators under the ARINC 1/2 ATR rack supporting the Model 209 Digital Flight Data Recorder in accordance with Lockheed Aircraft Service Company Drawing No. 10077J500, Revision F, dated March 14, 1975, or later FAA-approved revisions. \n\n\tEquivalent vibration isolators and/or installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-2169 was effective May 20, 1975. \n\n\tThis amendment 39-2459 becomes effective December 19, 1975.
2016-25-25: We are superseding Airworthiness Directive (AD) 2012-11-15 for all BAE Systems (Operations) Limited Model 4101 airplanes. AD 2012-11- 15 required a one-time detailed inspection for cracks, corrosion, and other defects of the rear face of the wing rear spar, and repair if necessary. This new AD requires repetitive detailed inspections, and repair if necessary. This AD was prompted by new reports of cracking found in the wing rear spar and technical analysis results, which confirmed that the crack initiation and propagation are due to fatigue, with no indication of any other crack initiation mechanism (e.g., stress corrosion). We are issuing this AD to address the unsafe condition on these products.
2017-04-51: We are adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A., Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. Emergency AD 2017-04-51 was sent previously to all known U.S. owners and operators of these engines. This AD requires inspecting, wrapping, and replacing the affected drain valve assembly (DV) installed on these Arriel 1 engines. This AD was prompted by reports of fuel leaks originating from the DV on certain Arriel engines. We are issuing this AD to correct the unsafe condition on these products.
2024-15-11: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A109C, A109E, A109K2, A109S, and AW109SP helicopters. This AD was prompted by reports of loose tail rotor duplex bearing locking nuts, possibly caused by improper installation. This AD requires disassembling certain tail rotor duplex bearings and reassembling them in accordance with updated procedures. This AD also prohibits installing certain tail rotor duplex bearing housings and pitch change slider assemblies. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-05-05: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines. This AD was prompted by an uncontained failure of a high-pressure turbine (HPT) hub during takeoff. This AD requires an inspection to measure the surface condition of the aft side web/rim fillet of HPT 1st stage hubs and removal from service of hubs that fail inspection. We are issuing this AD to correct the unsafe condition on these products.
58-22-04: 58-22-04 SUD AVIATION: Applies to All Alouette II SE 3130 Helicopters Except Serial Numbers 1168, 1169, 1170, 1175, 1176 and 1177. Compliance required (1) inspection prior to next flight and (2) rivet replacement by November 15, 1958. Due to sudden engine and rotor synchronization which may result upon completion of clutch engagement, stresses applied to the overall drive may be considerably increased. This can cause the shearing of rivets which hold the tail rotor inclined drive shaft tube to the yokes of the universal joints. Sud Aviation issued the following corrective measures which French SGACC considers mandatory: A. Prior to Next Flight: (1) Remove the tail rotor inclined drive shaft assembly as directed in instruction sheet P.I. 4404 of periodic inspection manual; (2) Check that the center lines of the bores in the yokes at each end of the shaft are parallel and lie in the same plane; (3) If drive shaft assembly is satisfactory, index the relative positions of the tube and yoke by means of a line of paint; (4) Repeat inspection after any sudden clutch engagement until compliance is shown with B. B. Prior to November 15, 1958: Replace the two diametrically opposite rivets on both ends of the tail rotor inclined drive shaft assembly. Sud Aviation P/N 67.20.000 which attaches to the universal joint fork with bolt, Sud Aviation P/N 67.21.103. (Sud Aviation Service Bulletin AL 67.11.140 and Modification Proposal V-42 cover this same subject.) (CAA telegraphic instructions of October 20, 1958, contained this information.)
2024-15-04: The FAA is superseding Airworthiness Directive (AD) 2023-22- 13, which applied to certain Dassault Aviation Model FALCON 7X airplanes. AD 2023-22-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023- 22-13 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2017-05-01: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates that a section of the wing and aft fuselage is subject to widespread fatigue damage (WFD). This AD requires an inspection to determine if certain modifications have been done. We are issuing this AD to address the unsafe condition on these products.
2017-04-06: We are adopting a new airworthiness directive (AD) for certain United Instruments, Inc. 5934 series altimeters that were manufactured between January 2015 and February 2016 and installed in airplanes and helicopters. This AD was prompted by reports of certain altimeters displaying higher than actual altitude due to a slow diaphragm leak, which would affect the accuracy of the altimeters. This AD requires replacing the affected altimeters. We are issuing this AD to correct the unsafe condition on these products.
57-13-01: 57-13-01 COLONIAL: Applies to All Model C-1 Aircraft. Compliance required within next 10 hours of operation or July 15, 1957, whichever occurs first unless already accomplished, and every 100 hours' operation thereafter. Inspect with 10-power glass the engine pylon side strut attaching fittings (P/N 3208-10) for cracks in the weld areas. (Inspection may be readily accomplished after removal of the fairing cuff, P/N 5400-33.) Fittings with cracks originating across the edge may be salvaged for use if the crack can be removed by grinding to a maximum depth of 1/16 inch measured in from the edge. Fittings with cracks located in areas other than the edge or in excess of the salvage limits must be replaced. (Colonial Service Bulletin No. 4 revision 1 dated May 22, 1957, covers this same subject.)