Results
2024-19-03: The FAA is superseding Airworthiness Directive (AD) 2023-12-03 and AD 2023-04-05, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2023-12-03 and AD 2023-04-05 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 all actions in AD 2023-12-03 and certain actions in AD 2023-04-05, 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. The FAA is issuing this AD to address the unsafe condition on these products.
2016-16-14: We are superseding Airworthiness Directive (AD) 2013-20-11, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-20-11 required modifying the passenger emergency oxygen container assembly. This new AD expands the affected group of oxygen containers to include those labeled ``DAe Systems.'' This AD was prompted by a determination that the unsafe condition also affects oxygen containers labeled ``DAe Systems.'' We are issuing this AD to prevent a high temperature oxygen generator and mask from falling down and possibly resulting in an ignition source in the passenger compartment, injury to passengers, and reduced availability of supplemental oxygen.
2024-19-02: The FAA is superseding Airworthiness Directive (AD) 2023-02- 08, which applied to certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes. AD 2023-02-08 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 2023-02-08, 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. The FAA is issuing this AD to address the unsafe condition on these products.
51-10-05: 51-10-05 TEMCO: Applies to Models GC-1A and GC-1B Aircraft, Serial Numbers 3711 and Below. Compliance required at next periodic inspection but not later than May 1, 1951. (This Airworthiness Directive supplements AD48-28-01.) The two most forward AN 3-4 bolts in each flange of reinforcement P/N 11-213-5074 (4 bolts in all), installed to comply with AD 48-28-01, interfere with the tailwheel shock strut cylinder at the upper extreme of its travel. The tailwheel shock strut should be removed from the airplane and the shock strut and the tailwheel support channel, P/N 11-212-1484, carefully inspected for damage. Any damaged part should be replaced or repaired. Reexamination of this reinforcement P/N 11-213-5074, shows that the two forward AN 3-4 bolts in each flange (4 bolts in all), are not necessary to achieve the required strength. Therefore, remove these bolts, leaving the two most rear AN 3-4 bolts in each flange of the reinforcement (4 bolts in all). The flanges of the P/N 11-213-5074 reinforcement may be cut off along a line located 3/8-inch forward of the centerline of the two rear 3/16-inch bolt holes in each flange, if necessary to accommodate a pair of the tailwheel shock strut support channel. Reinstall the tailwheel shock strut.
2016-17-03: We are superseding Airworthiness Directive (AD) 2003-25-07 for certain Airbus Model A319 and A320 series airplanes, and AD 2005-13-39 for certain Airbus Model A321 series airplanes. AD 2003-25-07 required a revision to the airplane flight manual (AFM) and replacement of both elevator aileron computers (ELACs) having L80 standards with new ELACs having L81 standards. AD 2005-13-39 required a revision to the AFM, replacement of existing ELACs with ELACs having L83 or L91 standards, as applicable; and a concurrent action. Since we issued AD 2003-25-07 and AD 2005-13-39, we have determined that new ELAC standards must be incorporated. The ELAC standards have been upgraded to version L97+, which implements enhanced angle-of-attack (AOA) monitoring to better detect AOA blockage, including multiple AOA blockages. This AD requires replacing existing ELACs with new ELACs having L97+ standards or revising the software in an existing ELAC to the L97+ standards, as applicable, which terminates the requirements of AD 2003-25-07 and AD 2005-13-39. This AD also expands the applicability to include all Airbus Model A318, A319, A320, and A321 series airplanes. We are issuing this AD to prevent inadvertent activation of the AOA protections. Inadvertent activation of the AOA protections could result in a continuous nose-down pitch rate that could result in reduced controllability of the airplane.
82-25-05: 82-25-05 NIHON AEROPLANE MANUFACTURING COMPANY: Amendment 39- 4504. Applies to Model YS-11/11A series airplanes, certificated in all categories. Compliance required within the next 250 hours time in service or 90 days, whichever occurs first, after the effective date of this AD, unless previously accomplished. To prevent the loss of both D.C. generator outputs: 1. Modify the terminal wiring on the D.C. generators in accordance with the Accomplishment Instructions of Lear Siegler, Inc., Service Bulletin No. 30029-02 dated November 16, 1980. 2. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. The manufacturer's specifications and proceduresidentified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective December 6, 1982.
2016-16-09: We are superseding Airworthiness Directive (AD) 2011-10-01 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011-10-01 required repetitive functional tests of the ram air turbine (RAT) heater, and repair if necessary. This new AD requires revision of the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by the need for new and more restrictive maintenance requirements and airworthiness limitations for airplane structures and systems. We are issuing this AD to prevent reduced structural integrity and reduced control of these airplanes due to the failure of system components.
69-08-06: 69-08-06 FAIRCHILD: Amdt. 39-750. Applies to All Model F-27 Series and FH-227 Series Airplanes. Compliance required within the next 500 hours time in service after the effective date of this AD unless already accomplished. To prevent hazards associated with an unselected landing gear retraction on the ground, accomplish the following: (a) Rewire the landing gear retraction system in accordance with Fairchild Hiller Service Bulletin 32-64 dated June 12, 1967, for F-27 aircraft and Fairchild Hiller Service Bulletin 32-5 dated March 13, 1967, for FH-227 aircraft or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, or equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.This amendment is effective April 23, 1969.
83-01-02: 83-01-02 GENERAL DYNAMICS (Convair): Amendment 39-4536. Applies to Models 340/440, and military models eligible or to be made eligible for civil use under Type Certificate 6A6, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent fracture of the nose landing gear (NLG) axle caused by fatigue cracks, accomplish the following. NOTE: All references to hours of time in service apply to nose landing gear axle and not to the aircraft. (A) Within 150 hours time in service after the effective date of this AD, or prior to the accumulation of 10,150 hours time in service, whichever occurs later, unless accomplished within the last 1050 hours time in service, conduct an ultrasonic inspection of each NLG axle (P/N 240- 5217002 or P/N 340-7310205) in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions," of GeneralDynamics Convair Division Service Bulletin 640 (340D) 32-13 dated August 7, 1978. If cracks are found, replace with a like serviceable part prior to return of aircraft to service. (B) Repeat the ultrasonic inspection specified in paragraph (A) or perform the magnetic particle inspection specified in paragraph (C) of this AD at intervals not to exceed 1200 hours time in service. (C) Within 12,000 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 12,000 hours time in service, conduct a magnetic particle inspection of the NLG axle (P/N 240-5217002 or P/N 340-7310205) in accordance with the applicable provisions of paragraph 2, entitled "Accomplishment Instructions" of Service Bulletin 640(340D) 32-13. If cracks are found, replace NLG axle with a like serviceable part prior to return of aircraft to service. (D) Prior to issuance of a Certificate of Airworthiness for military aircraft being converted for civil certification the airplane must be inspected in accordance with paragraph (A) or (C) of this AD. (E) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (F) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region, Hawthorne, California. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Dynamics, Convair Division, P.O. Box 80877, San Diego, California 92138. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California. This amendment becomes effective January 19, 1983.
2024-18-08: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -800 series airplanes. This AD was prompted by a report that the protective spiral wrap used on certain galley wire bundles does not have the correct flammability properties. This AD requires inspecting certain galleys to determine part numbers, inspecting for an existing galley modification placard and marking on galleys with affected part numbers, and replacing wire bundle spiral wrap sleeving as applicable. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.