Results
2020-20-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, AS350B3, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This AD requires inspecting the main rotor (M/R) servo actuators, and depending on the inspection results, replacing the affected part, applying a slippage mark, and reporting information. This AD was prompted by an incident of a sudden, strong nose-up attitude followed by intensive vibrations and increased loads on the flight controls during a cruise flight. The actions of this AD are intended to address an unsafe condition on these products.
2003-21-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 airplanes, that currently requires a one-time detailed visual inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; and corrective action, if necessary. This amendment requires a new inspection of the wire bundle installation behind the first observer's station to detect damaged or chafed wires; repair if necessary; installation of a grommet around the lower edge of the feed-through; replacement of the support bracket with a new bracket; and relocation of the support clamp of the wire bundle; as applicable. The actions specified by this AD are intended to prevent the wire bundle contained in the feed-through from contacting the bottom of the feed-through, which could cause cable chafing, electrical arcing, and smoke or fire in the cockpit. This action is intended to address the identified unsafe condition.
80-21-01: 80-21-01 MCDONNELL DOUGLAS: Amendment 39-3933. Applies to DC-10 Series Airplanes fuselage numbers 1 through 243. \n\n\tCompliance required as indicated, unless already accomplished. To prevent restriction of travel of the wing and tail engine fuel shutoff valve, thereby adversely affecting operation of the engine emergency fire shutoff handles and loss of associated fire fighting safeguards, accomplish the following: \n\n\t(a)\tWithin 300 hours additional time in service after the effective date of this AD replace P/N AA 2603 type cable guard pins in accordance with McDonnell Douglas Alert Service Bulletin A76-28 as dated September 8, 1980. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. \n\n\t(c)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective October 13, 1980.
94-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 series airplanes, KC-10A (military) airplanes, and Model MD-11 series airplanes, that requires the installation of retainers and supports at the lateral control mixer bracket on the center of the wing rear spar of the airplane. This amendment is prompted by an analysis conducted by the manufacturer, which revealed that failure of a lateral control mixer bracket could result in uncommanded deployment of the spoiler. The actions specified by this AD are intended to prevent inadvertent asymmetric deployment of the spoiler, which may lead to reduced controllability of the airplane.
2021-10-17: The FAA is adopting a new airworthiness directive (AD) for certain Mooney International Corporation (Mooney) Model M20V airplanes. This AD was prompted by reports of short circuit and arcing of the alternator main power cable in the engine compartment. This condition, if unaddressed, could result in a fire hazard, loss of engine thrust control, and reduced control of the airplane. This AD requires inspecting the alternator main power cable and the exhaust crossover tube for damage, replacing damaged parts as necessary, and installing an additional alternator cable clamp. The FAA is issuing this AD to address the unsafe condition on these products.
80-13-51: 80-13-51 GROUPEMENT d'INTERET ECONOMIQUE AIRBUS INDUSTRIE (AIRBUS): Amendment 39-4010. Applies to Model A300B4-103 airplanes modified in accordance with Airbus Mod. 2150, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible operation at degraded performance levels due to inaccurate performance data presented in the airplane flight manual (AFM), accomplish the following: (a) Prior to further flight, except that the airplane can be ferried in accordance with FAR Sections 21.197 and 21.199 to a place where replacement can be made, if CF-6-50C or CF- 6-50C1 engines are installed, replace with serviceable CF6-50C2 engines, and (b) Within 20 hours time in service after the effective date of this AD, incorporate Airbus Industrie A300B4-103 AFM, Revision 6, dated May 28, 1980, or an FAA-approved equivalent, into the airplane flight manual and operate the airplane accordingly. (c) If an equivalent meansof compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. This amendment becomes effective January 2, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-13-51, issued June 18, 1980, which contained this amendment.
2003-21-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes. This action requires modifying the rear fuselage to reinforce a certain frame segment. This action is necessary to prevent fatigue cracking of the rear fuselage, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
94-22-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-8-70 series airplanes, that currently requires replacement of all attachment screws at the exhaust nozzle plug splice, and a check of nut plates for running torque and replacement of nut plates, if necessary. This amendment requires modification of the engine exhaust plug assemblies as terminating action for the currently required replacement and check. This amendment is prompted by reports of loose or missing attachments at the splice joint of the engine forward and aft exhaust plugs, and loss of the rear exhaust plug following an engine bird strike. The actions specified by this AD are intended to prevent reduced integrity of the engine exhaust plug installation, which may lead to separation of exhaust plugs from the airplane, and create a hazard to persons and property on the ground.
81-18-06: 81-18-06 FAIRCHILD: Amendment 39-4202. Applies to Model C-119 series airplanes certificated in all categories under various type certificates including, but not limited to Pacific International Foods, Inc., A6NW, William Waara, A32CE, Starbird, Inc., A5NW, Aero Union Corporation, A21WE, Hawkins and Powers, Inc., A24WE. Compliance required as indicated, unless already accomplished. To prevent possible wing failure due to loads induced by a free aileron, accomplish the following: (a) Within 100 hours' time in service or within 60 days from the effective date of this AD, whichever occurs earlier, conduct inspections of the inboard and outboard aileron, aileron control system, and all aileron attachment fittings of the outer wing panel using the applicable inspection instructions of Section III Wing Group and Section X Control Systems Group of USAF Technical Order T.O. 1C-119G-36 and additional inspection procedures given below. (b) Remove the left and right handinboard and outboard ailerons and inspect for evidence of cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear and elongated holes in accordance with the visual, dye penetrant and X-ray procedures of TO.O 1C-119G-36, paragraphs 3-25 through 3-36. (c) Inspect the aileron flight control linkage in the left and right hand wing outer panel for evidence of cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear and elongated holes in accordance with visual, magnetic and dye penetrant procedures of T.O. 1C-119G-36, paragraphs 10-11 through 10-14, with the following exceptions for the bellcrank item C-30 of T.O. 1C-119G-36. (1) Remove the left and right hand inboard aileron bellcrank assembly, P/N 110-727202-21 and P/N 110-727202-22, indicated as item C-30 in T.O. 1C-119G-36, Figure 10-3, page 10-25. (2) Conduct a dye penetrant inspection in accordance with T.O. 1C-119G-36, paragraph 10-14(c)(2), after removal ofthe bushings and bearings. Particular attention should be directed to the exterior and interior surfaces of the central hub of the bellcrank. (d) Using a 10X magnifier, inspect the truss support assembly which is attached to the upper and lower rear wing spar cap and inner aileron bellcrank inter-rib support bracket in left and right outer wing panels for evidence of corrosion, cracks or loss of structural integrity caused by erosion of tubular wall thickness. NOTE: Part numbers found on some C-119 model aircraft are P/N 78-135106-0005R and P/N 78-135106-0008L. (e) If any cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear or elongated holes are detected during the inspections, repair in accordance with T.O. 1C-119B-3 or replace with like serviceable part in accordance with the procedures of the applicable paragraphs in T.O. 1C-119G-36, prior to further flight. (f) Prior to return to service, after accomplishing other inspectionsrequired by this AD, conduct a balance inspection of all four ailerons per procedures specified in the applicable maintenance instructions. Any out-of-limit condition must be corrected prior to further flight. (g) Repeat the inspections required by paragraph (c), (d) and (f) of this AD at intervals not to exceed 3000 hours' time in service or one (1) year from the last such inspection, whichever occurs earlier. (h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (i) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (j) The specifications and procedures identified and described in this directive 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 these documents may obtain copies upon request to FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office. This amendment becomes effective September 10, 1981.
88-12-07: 88-12-07 BOEING: Amendment 39-5937. Applies to Model 757 series airplanes, listed in Boeing Service Bulletin 757-27-0079, Revision 1, dated June 25, 1987, certificated in any category. \n\n\tCompliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent binding in the aileron control system, accomplish the following: \n\n\tA.\tModify the aileron control system in accordance with Boeing Service Bulletin 757-27-0079, Revision 1, dated June 25, 1987. \n\n\tB.\tAn alternate means 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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-5937, becomes effective July 1, 1988.