Results
2017-06-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. This AD requires identification of the potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. We are issuing this AD to address the unsafe condition on these products.
73-11-04: 73-11-04 SIAI-MARCHETTI: Amdt. 39-1644. Applies to SIAI Marchetti Models S.205-18R, -20R, and -22R airplanes. Serial Numbers 001 through 003, and 101 through 399. Compliance is required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. To provide a means for periodic lubrication to prevent seizing of the eye bolts, P/N 205- 9-047-11, connecting the articulated drag braces to the main landing gear cross members, install grease fittings and washers, P/N MS15720-1 and P/N 205-9-012-15, respectively, in the attachments for the eye bolts, P/N 205-9-047-11, to the main landing gear cross members in accordance with SIAI Marchetti Service Bulletin No. 205B32 dated November 19, 1971, or an FAA-approved equivalent. This amendment becomes effective June 20, 1973.
2017-07-09: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires removing from service the tail gearbox center housing (housing) when it has 12,200 or more hours time-in-service (TIS). This AD was prompted by fatigue analysis conducted by Sikorsky that determined the housing required a retirement life. The actions are intended to prevent an unsafe condition on these products.
2017-07-04: We are superseding Airworthiness Directive (AD) 2013-24-17 for General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with certain high-pressure compressor (HPC) rotor stage 2-5 spools installed. AD 2013-24-17 required removing these spools from service at times determined by a drawdown plan. This AD retains the same requirements as AD 2013-24-17. This AD also adds additional part number (P/N) HPC spools to the applicability. This AD was prompted by reports of cracking on these additional spools. We are issuing this AD to correct the unsafe condition on these products.
2024-16-03: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400F series airplanes. This AD was prompted by a report that cap seals were not applied to certain fasteners in the fuel tanks during production. This AD requires applying cap seals to certain fastener collars inside the fuel tanks. The FAA is issuing this AD to address the unsafe condition on these products.
2017-07-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by reports of cracks in main landing gear (MLG) leg components. This AD requires detailed visual inspections of these MLG leg components and replacement of the MLG leg if cracked components are found. We are issuing this AD to address the unsafe condition on these products.
2024-15-10: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 505 helicopters. This AD was prompted by a fuel leakage discovered during fuel system crash impact testing activity. This AD requires installing a grommet around the sump drain port fitting airframe hole, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-06-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319 and A320 series airplanes. This AD was prompted by a report that fatigue cracking could appear at certain fastener locations in the longeron area below the emergency exit cut-outs. This AD requires the modification of certain fastener locations in the longeron area below the emergency exit cut-outs. We are issuing this AD to address the unsafe condition on these products.
2017-07-02: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D Configuration A helicopters. This AD requires reducing the life limit of and inspecting certain drive shafts. This AD is prompted by four incidents involving failure of a drive shaft. The actions specified by this AD are intended to prevent the unsafe condition on these products.
75-27-06: 75-27-06 PILATUS AIRCRAFT LTD: Amendment 39-2478. Applies To Pilatus Model PC-6 airplanes, serial numbers 685 and below (all variants) manufactured by Pilatus Aircraft Ltd., powered by Lycoming GSO-480-B1A6 engines. NOTE: This AD does not apply to Pilatus PC-6 airplanes manufactured by Fairchild Hiller. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent hazardous fuel leaks from developing at the elbow fittings connecting the fuel line to the fuel pump and carburetor and to prevent a broken fuel line, accomplish the following: (a) Replace aluminum fittings (AN 822-8D and AN 823-8D) with stainless steel fittings (MS 20822-8C and MS 20823-8C), or FAA-approved equivalents. (b) Replace aluminum fuel line P/N 6238.0094.80 with a stainless steel fuel line P/N 6238.0094.80C, or an FAA-approved equivalent. This amendment becomes effective on January 19, 1976.
58-22-01: 58-22-01 HAMILTON STANDARD: Applies to All 6800, 6900, and 7000 Series Externally Surface-Treated Aluminum Alloy Blades (Airfoil Shotpeened and/or Shank Rolled, Including Nickel-Plated Blades). Compliance required at first blade overhaul after January 1, 1959, and at every overhaul thereafter. Two surface-treated aluminum alloy blades have fractured during operation. Blade bending may have, depending on the circumstances surrounding the incident, a serious detrimental effect on the fatigue strength of a blade. Therefore, it is considered necessary to establish a means to detect and evaluate instances of unrecognized blade bending by systematically comparing at overhaul measured face alinement values with previously established values. To establish such a means, follow the detailed instructions contained in Hamilton Standard Service Bulletin No. 546. This procedure requires that face alinement measurements be made prior to any overhaul, and then again following all operationsthat would affect face alinement. (Hamilton Standard Service Bulletins Nos. 546 and 546A cover this same subject.)
53-09-02: 53-09-02\tde HAVILLAND: Applies to All Model DHC-2 Beaver Aircraft. \n\n\tCompliance required as indicated. \n\n\tInspect as soon as practical but not later than the next 100-hour flying time and at 100- hour intervals thereafter for skin cracks on the fuselage side panel at front door step. (See Figure 2 for typical cracks and methods of repairing.) Any cracks found should be stop drilled at each end and repaired in accordance with directions in sketch. 100-hour inspection may be discontinued upon incorporation of recommended repair. \n\n\n\n\n\n\t(de Havilland Technical News Sheet, Series B, No. 59 - Issue 2, dated January 15, 1953, covers this same subject.)
2017-06-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4- 605R and A300 B4-622R airplanes; and Model A300 C4-605R Variant F airplanes. This AD was prompted by an in-service detection of cracks in the fuselage skin lap joints. This AD requires an ultrasonic inspection of certain skin lap joints, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2024-16-02: The FAA is superseding Airworthiness Directive (AD) 2018-01- 07, AD 2018-19-33, AD 2019-21-01, AD 2021-26-20, AD 2022-13-09, AD 2022-14-06, AD 2023-09-05, and AD 2023-26-06, which applied to all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and AD 2020-23-11, which applied to all Airbus SAS Model A300 and A300-600 series airplanes. AD 2018-01-07, AD 2018-19-33, AD 2019-21-01, AD 2021-26-20, AD 2022-13-09, AD 2022-14-06, AD 2023-09-05, and AD 2023-26-06 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. AD 2020-23-11 required repetitive inspections for discrepancies of certain areas in and around the fuselage and repair if necessary. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions specified in the superseded ADs, 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. This AD also removes the Model A300 series airplanes from the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
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.)
75-05-05: 75-05-05 GOODYEAR AEROSPACE CORPORATION: Amendment 39-2101. Applies to main wheel assemblies P/N's 5000757-1 and -2 typically used on, but their use is not limited to, McDonnell-Douglas DC-10-30 and DC-10-40 series aircraft. \n\n\tCompliance is required at the next tire change or wheel re-assembly after the effective date of this Airworthiness Directive, unless already accomplished, and thereafter at each tire change or wheel re-assembly or during replacement of any wheel half attaching bolts in a tire/wheel assembly. New wheels or spare wheel assemblies with previously magnetic-particle inspected bolts are exempt only from the initial inspection. \n\n\tTo prevent failures of the MS 21250-10060 bolts attaching the wheel halves, accomplish the following: \n\n\t(a)\tPerform magnetic-particle inspection for cracks of all wheel-half attaching bolts, paying particular attention to the radius under the bolt head and to the threads. Replace cracked bolts and those having stripped, crossed ordamaged threads. No reworking of wheel bolts is permitted. Defective bolts shall be scrapped. \n\n\tThis amendment becomes effective March 26, 1975.