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2004-11-04: The FAA is adopting a new airworthiness directive (AD) for all Eagle Aircraft (Malaysia) Sdn. Bhd (Eagle Aircraft) Model Eagle 150B airplanes. This AD requires you to inspect certain canard inboard flap hinge support brackets (initially prior to further flight and repetitively before the first flight of each day) and perform any necessary follow-up action. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authorities for Australia and Malaysia. We are issuing this AD to prevent failure of the canard inboard flap hinge support brackets caused by undetected cracks. This failure could result in asymmetric flap deployment and the inability to lower or raise the flaps with consequent loss of control of the airplane.
70-08-02: 70-08-02 BELL: Amendment 39-968 as amended by Amendment 39-1137 Applies to all Bell Model 47 Series Helicopters and all other helicopters incorporating any of the following tail rotor drive shaft assemblies: 47-644-172-3 47-644-180-1 47-644-186-1 47-644-180-5 47-644-187-5 47-644-214-1 47-644-187-11 Compliance required no later than March 1, 1971; however, replacement is recommended at the next 1200-hour overhaul. To prevent failure from internal corrosion, remove and replace all tail rotor drive shaft assemblies installed on applicable helicopters as indicated below in accordance with the applicable maintenance and overhaul manual: Remove Replace With 47-644-172-3 47-644-172-9 47-644-180-1 47-644-180-9 47-644-180-5 47-644-180-11 47-644-214-1 47-644-214-9 47-644-186-1 47-644-186-5 47-644-187-5 47-644-187-17 47-644-187-11 47-644-187-19 (Bell Service Bulletin No. 47-145, Rev. B, dated March 26, 1970, pertains to this matter) Amendment 39-968 effective May 9, 1970. This amendment, 39-1137, becomes effective January 1, 1971.
90-21-20: 90-21-20 AIRBUS INDUSTRIE: Amendment 39-6770. Docket No. 90-NM-91-AD. Applicability: All Model A320-111, A320-211, and A320-231 series airplanes, certificated in any category. Compliance: Required within the next 350 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent the simultaneous activation in flight of two angle of attack sensors and subsequent incorrect pitch-down command to the elevator, accomplish the following: A. Perform one of the following: 1. Disconnect and modify the wiring in the relay box 103VU, in Zone 127, and in Zone 232, in accordance with Airbus Industrie Service Bulletin A320-34-1012, Revision 1, dated April 10, 1990; or Revision 2, dated June 8, 1990; or 2. Accomplish Modification No. 21824P1953, which consists of moving the test control wires of the angle of attack sensors, in accordance with Airbus Industrie Service Bulletin A320-34-1013, dated June 1, 1990. B. An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6770, AD 90-21-20) becomes effective November 19, 1990.
2016-24-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by a report that static strength analysis has shown that the aluminum transmission aft bearing plate assemblies have inadequate structural strength for one or more of the required load cases. This AD requires removing aluminum transmission aft bearing plate assemblies from the flap track and installing titanium transmission aft bearing plate assemblies to the flap track. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 85119))
2024-19-17: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. Model 204B, 205A, 205A-1, 205B, 210, and 212 helicopters and various restricted category helicopters with certain part-numbered tension torsion (TT) straps installed by supplemental type certificate (STC) No. SR03408CH. This AD was prompted by an accident involving failure of a TT strap. This AD requires removing the specified part-numbered TT straps from service and prohibits installing those TT straps. The FAA is issuing this AD to address the unsafe condition on these products.
75-25-03: 75-25-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2448. Applies to PA- 34-200T airplanes, serial numbers 34-7570001 through 34-7670077 certificated in all categories. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent loss of engine oil, accomplish the following: Replace the existing engine oil pressure hose assemblies with a tube assembly and a new hose assembly in accordance with Piper Service Bulletin Number 483 or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective December 10, 1975.
2016-22-04: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. This AD was prompted by a new revision to the Airworthiness Limitations Section (ALS) of the Aircraft Maintenance Manual (AMM) based on fatigue and damage tolerance testing, and updated analysis. This AD requires revising the maintenance or inspection program to incorporate updated inspection requirements and life limits that address fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of PSEs is detected and corrected; such fatigue cracking could result in reduced structural integrity of the PSEs and critical components.
92-10-01: 92-10-01 BOEING: Amendment 39-8234. Docket No. 91-NM-240-AD. Supersedes AD 91-15-13, Amendment 39-7077.\n\n\tApplicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-27-0104, Revision 2, dated September 12, 1991; certificated in any category.\n\n\tCompliance: Required as indicated, unless previously accomplished.\n\n\tTo prevent the overwing escape slide from being damaged by sharp edges of the rub strip on the inboard spoilers, accomplish the following:\n\n\t(a)\tExcept as provided by paragraph (b) of this AD, within the next 9 months after August 29, 1991 (the effective date of amendment 39-7077), modify the inboard edges of the rub strip on the inboard spoilers in accordance with Boeing Service Bulletin 767-27-0104, dated November 15, 1990, or Revision 1, dated May 30, 1991.\n\n\t(b)\tFor airplanes equipped with inboard spoiler assemblies, part numbers 113T4100-37, -38, -41, -42, -45, and -46: Within the next 9 months after the effective date of this AD, modify the inboard edges of the rub strip on the inboard spoilers in accordance with Boeing Service Bulletin 767-27-0104, Revision 2, dated September 12, 1991.\n\n\t(c)\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. The request shall 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(d)\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(e)\tThe modification shall be done in accordance with Boeing Service Bulletin 767-27-0104, dated November 15, 1990; or Revision 1, dated May 30, 1991; or Revision 2, dated September 12, 1991; as applicable. This incorporation by reference was approved by theDirector of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. (The incorporation by reference of Boeing Service Bulletin 767-27-0104, dated November 15, 1990, and Revision 1, dated May 30, 1991, was previously approved by the Director of the Federal Register as of August 29, 1991 (56 FR 34019, July 25, 1991).) 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(f)\tThis amendment becomes effective on June 11, 1992.
2022-13-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report of inadvertent auto flight system (AFS) altitude changes on the flight control unit (FCU). This AD requires revising the existing airplane flight manual (AFM) to include a procedure on the use of the AFS control panel ALT knob and replacing any affected FCU with a serviceable FCU, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-15: The FAA is adopting a new airworthiness directive (AD) for various airplanes modified with certain configurations of Garmin G3X Touch Electronic Flight Instrument System installed per Supplemental Type Certificate (STC) No. SA01899WI or Garmin GI 275 Multi-Function Display (MFD) installed per STC No. SA02658SE. This AD was prompted by a report of a fuel quantity disparity between the amount of fuel indicated and the actual amount of fuel. This AD requires modifying the resistive fuel probe interface. The FAA is issuing this AD to address the unsafe condition on these products.