Results
94-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes, that requires inspections to detect cracking in the No. 2 engine pylon lower spar forward mount and thrust link fitting attach bolts, replacement of cracked bolts, and the eventual replacement of all bolts made of H-11 material with bolts made of Inconel. This amendment is prompted by reports of failures of these attach bolts due to stress corrosion. The actions specified by this AD are intended to prevent failure of the attach bolts, which could reduce the fail-safe capability of the attachment assembly.
2005-23-04: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB 2000 airplanes. This AD requires modifying the manual feather-and-unfeather system for the propellers to make the design of the system more robust. This AD results from reports of in- flight engine shutdown caused by uncommanded operation of the feather pump of the propeller. We are issuing this AD to prevent uncommanded feathering of the propeller, which could result in the shutdown of an engine during flight and consequent reduced controllability of the airplane.
68-02-01: 68-02-01 BRISTOL SIDDELEY: Amendment 39-542. Applies to deHavilland Model Gipsy Queen Series 70 Engines with Crankshafts with Modifications 1399 (R.155), 1609 (R.259), 2289 (R.155 and R.259), 2931 (R.563 and R.564), or Repair Schemes R.155 and R.259 incorporated. Compliance required as indicated, unless already accomplished. To prevent failure of the crankshaft front end that could result in loss of the propeller, accomplish the following: (a) Within the next 400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, visually inspect the crankshaft for cracks, in accordance with Bristol Siddeley Technical News Sheet (TNS) G.Q. 70 No. 105, dated August 14, 1967, or later ARB-approved issue, or an FAA-approved equivalent. (b) If cracks are found during the inspections required by paragraph (a), replace cracked crankshaft before further flight with an uncracked crankshaft, or incorporate Gipsy Modification 2925 (R.550). If Gipsy Modification 2925 (R.550) is not incorporated, inspect the replacement crankshaft in accordance with paragraph (a). (c) If no cracks are found during the inspections required by paragraph (a), incorporate Modification 2925 (R.550), or an FAA-approved equivalent, at next overhaul. (d) The repetitive inspections required by paragraph (a) may be discontinued after the incorporation of Gipsy Modification 2925 (R.550). This amendment becomes effective February 16, 1968.
2002-19-52: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-600, -700, -700C, -800, and - 900 series airplanes; Model 747 series airplanes; and Model 757 series airplanes, that currently requires revision of the FAA-approved airplane flight manual (AFM) to advise the flight crew of certain operating restrictions for maintaining minimum fuel levels; prohibits use of the horizontal stabilizer tank on certain airplanes, and prohibits the installation of certain fuel pumps. This amendment requires concurrent removal of the currently required AFM revisions and insertion of new AFM revisions; requires installation of placards to alert the flightcrew to the operating restrictions; and prohibits installation of any uninspected pumps. This amendment permits the AFM revision and placard to be removed under certain conditions. The actions specified in this AD are intended to prevent fuel vapors from coming into contact with an ignition source inthe center wing fuel tank, horizontal stabilizer fuel tank, center auxiliary fuel tank (body tank), or auxiliary fuel tanks 1 and 4, which could result in fire/ explosion.
2018-20-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-300 series airplanes. This AD was prompted by reports indicating that a certain emergency exit door could not be opened during maintenance. This AD requires a detailed inspection of the ball bearings of an emergency exit, replacement of bearings if necessary, application of corrosion inhibiting compound (CIC), and revision of the maintenance or inspection program, as applicable. We are issuing this AD to address the unsafe condition on these products.
2005-23-03: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F airplanes. This AD requires replacement of the spherical accumulator for the main hydraulic system with a new cylindrical accumulator. For certain airplanes, this AD also requires modification of the accumulator pressure gauge. This AD results from reports of the failure of two thrust reverser accumulators (which are similar to the main hydraulic system's spherical accumulator) and fatigue cracks found on four thrust reverser accumulators. We are issuing this AD to prevent failure of the spherical accumulator for the main hydraulic system, due to fatigue cracking on the threads, which could result in the loss of hydraulic power, damage to the surrounding airplane structure, and loss of airplane control. The failure of the accumulator could also result in injury to any persons in the surrounding area. The loss of hydraulic fluid could also leak onto a potential source of ignition and result in a consequent fire.
81-13-51: 81-13-51 CANADAIR: Amendment 39-4268. Applies to all Canadair CL-600 series airplanes certified in all categories. To detect dragging wheel brakes, unless already accomplished, accomplish the following prior to further flight. A. Inspect and replace, if necessary, wheel brake assembly P/N 600-85083-55 with wheel brake assembly P/N 600-85083-57 in accordance with Canadair Alert Service Bulletin A600-0045, Revision 1, dated June 15, 1981. B. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197. C. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain 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 the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective December 7, 1981 and was effective earlier to those recipients of Telegraphic AD T81-13-51 dated June 19, 1981.
2018-23-11: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214, - 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, - 212, -213, -231, and -232 airplanes. This AD was prompted by investigations that revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. This AD requires identifying the BDDV part number installed on the airplane, and modifying or replacing BDDVs having certain part numbers. We are issuing this AD to address the unsafe condition on these products.
98-18-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -15, and -30 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the upper cargo doorjamb have been previously modified; various follow-on repetitive inspections; and modification, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners of the upper cargo doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
2018-22-05: We are adopting a new airworthiness directive (AD) for all Engine Alliance (EA) GP7270, GP7272, and GP7277 turbofan engines with a certain high-pressure turbine (HPT) case installed. This AD requires removal of affected HPT stator cases (HPT cases) from service and their replacement with a part eligible for installation. This AD was prompted by the discovery of a quality escape at a manufacturing facility involving unapproved welds on HPT cases. We are issuing this AD to address the unsafe condition on these products.