Results
2005-02-06: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model MD-11 and MD-11F airplanes equipped with Pratt & Whitney PW4000 series engines. This AD requires, for each engine, replacing, with a tube assembly, the existing hose assembly that connects the oil pressure transmitter to the main oil circuit. This AD is prompted by a report indicating that, for each engine, the existing hose assembly does not meet zero-flow fireproof capability requirements. We are issuing this AD to prevent, if there is an engine fire, failure of the oil pressure indicator and the low-oil pressure warning, which could result in an unannounced shutdown of that engine; and oil leakage, which may feed the engine fire.
2023-13-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of a non-full life clearance in the low-pressure hydraulic pipes of the nose landing gear return line, due to two quality escapes. This AD requires replacing the affected aluminum pipes with titanium pipes, 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.
79-13-06: 79-13-06 DORNIER GmbH: Amendment 39-3489. Applies to Model Do 28 D-2 Skyservant airplanes, serial numbers 4050 and 4301 through 4307, certificated in all categories. Compliance required as indicated, unless already accomplished. To detect and eliminate corrosion and chafing of the engine fire extinguishing system pipelines, accomplish the following in accordance with Dornier Service Bulletin No. 2062-2828, dated April 1, 1977, or an FAA-approved equivalent: (a) Within the next 25 hours time in service after the effective date of this AD, inspect the engine fire extinghishing system for corrosion, accumulation of water, and pipeline chafing. (b) If corrosion or water accumulation is found during the inspection required by paragraph (a), before further flight, except as provided in paragraph (d) of this AD, modify the system by - (1) Installing a pipeline seal; (2) Incorporating pipeline water drainage holes; (3) Installing a drain valve; and(4) Replacing corrosion-prone pipelines with stainless steel pipelines between the engine fire extinghisher bottle and frame 6020. (c) If pipeline chafing is found during the inspection required by paragraph (a), before further flight, except as provided in paragraph (d), modify the system by - (1) Incorporating anti-abrasive protection; and (2) Installing a pipeline securing clamp. (d) Airplanes may be flown in accordance with FAR 21.197 and 21.199 to a base where the modifications required by paragraphs (b) and (c) of this can be performed. This amendment becomes effective July 11, 1979.
2005-02-07: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135BJ series airplanes. This AD requires modifying the electrical wiring for the "stick pusher" system. This AD is prompted by a report that the stick pushers are not being inhibited when the AP/PUSH/TRIM switches are activated, which can result in reduced controllability of the airplane if there is a system malfunction. We are issuing this AD to prevent reduced controllability of the airplane if the stick pusher system malfunctions.
2014-22-02: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) Trent 1000-A, 1000-C, 1000-D, 1000-E, 1000-G, and 1000-H turbofan engines. This AD requires removing engine electronic controller (EEC) software earlier than standard MB6.15 and replacing with a software standard eligible for installation. This AD was prompted by a finding that an intermediate pressure [[Page 64505]] (IP) shaft failure may not be detected by EEC software earlier than standard MB6.15. We are issuing this AD to detect IP shaft failure and prevent IP compressor turbine burst, uncontained engine failure, and damage to the airplane.
2023-13-02: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 airplanes. This AD was prompted by reports indicating that certain flight control electrical harnesses were routed incorrectly, providing inadequate separation from other electrical harness installations. This AD requires an inspection of certain flight control electrical harnesses for incorrect routing, and modifying any incorrect electrical harness installations, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
62-22-01: 62-22-01 CESSNA: Amdt. 494 Part 507 Federal Register October 16, 1962. Applies to All Models 150, 175, 175A, 175B, and 175C Aircraft Equipped with Continental Engines O-200-A, GO-300-A and GO-300-C Modified to Incorporate Airborne Mechanisms Model 113A5 Vacuum Pumps (Supplemental Type Certificates Nos. SA1-630 and SA1-610 Amended March 13, 1962, Issued to Airborne Mechanisms Division of Randolph Manufacturing Co.). Compliance required within the next 10 hours' time in service after the effective date of this AD. In order to prevent failure of the Airborne Mechanisms Model 113A5 vacuum pump because of improper installation, remove and reinstall the pump as follows: Mount the pump and then remove it from the engine drive pad. The coupling will remain in the engine spline and the separation will occur between the pump shaft and the coupling. The coupling must then be pressed 1/16 inch further into the engine spline. Reinstall the pump, and insure that the steel cross vanes protrude approximately 1/16 inch from the hub of the coupling. (Airborne Mechanisms Service Letter No. 4 dated May 15, 1962, entitled "Installation Interference of Model 113A5 Drive Splines" covers this same subject.) This directive effective October 31, 1962.
79-25-02 R1: 79-25-02 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3629 as amended by amendment 39-4098. Applies to Lockheed-California Company L-1011-385 series airplanes certificated in all categories. To preclude possible failure of the main landing gear pistons P/N 1523009 (-109, -113, - 117, -121), perform the following: Compliance required as indicated. (a) Within the next 48 hours after the effective date of the AD, unless already accomplished, conduct a visual inspection of the main landing gear piston clevis lugs including the web area directly above the lugs. If a crack is found, the piston must be replaced prior to further revenue flight. (b) Repeat the visual inspection of paragraph (a), above, once per each day in which the aircraft is operated. NOTE: The visual inspection of paragraphs (a) and (b), above, should be conducted with the piston clevis lugs and the web area directly above the lugs thoroughly cleaned of all accumulated dirt and grease. The conductof this visual inspection is considered to constitute an interim safety action. (c) Installation and/or modification of the main landing gear uplock snubber, truck pivot pin and bushings using Kits 1630462-101, -103, -105, and -107 or alternate Kits 1630462- 109, -111, -113, and -115 per Lockheed Service Bulletin 093-32-154 Revision #2 dated January 5, 1981, constitutes terminating action for this AD. (d) 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 replacements required by this AD. (e) Alternative inspections or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. The manufacturer's 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 from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 92520, Attention: Commercial Support Contracts, Department 63-11, 033, B- 1. These documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. Amendment 39-3629 became effective December 11, 1979. This amendment 39-4098 becomes effective May 22, 1981.
2005-02-09: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319, A320, and A321 series airplanes, that requires operators to revise the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness to incorporate new and more restrictive service life limits for certain items, and new and more restrictive inspections to detect fatigue cracking, accidental damage, or corrosion in certain structures. The actions specified by this AD are intended to ensure the continued structural integrity of these airplanes. This action is intended to address the identified unsafe condition.
2023-14-11: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of unexpected pitch upset upon autopilot disconnect. This AD requires revising the Non-Normal Procedures section of the existing airplane flight manual (AFM) associated with Auto Flight. The FAA is issuing this AD to address the unsafe condition on these products.