Results
97-03-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires, among other things, repetitive visual inspections to detect discrepancies of the fuel pipe of the fuel transfer system of the tail tank and associated mounting bracket located in the aft fuselage compartment. That AD was prompted by reports of cracking or bending of the fuel pipe mounting support and/or attaching bracket in the aft fuselage compartment due to a fuel pressure surge that caused repetitive loading of this area. This amendment adds a requirement to install a restraint on the tail tank fuel pipe, which would terminate the repetitive visual inspections. The actions specified by this AD are intended to prevent such cracking/bending, which could expose the fuel pipe coupling O-ring. An exposed O-ring could lose its sealing effect and could allow a fuel leak in the aft fuselage compartment, which would present a fire hazard.
63-22-04: 63-22-04 PIAGGIO: Amdt. 635 Part 507 Federal Register October 30, 1963. Applies to All Model P.166 Aircraft. Compliance required within 50 hours' time in service after the effective date of this AD. As a result of failures of the main landing gear shock absorber the following modifications must be accomplished in the manner specified in Piaggio Service Bulletin 166- 25A. (a) Install Teflon sealing gasket P/N 4/22015.52 on inner ring nut of shock absorber casing. (b) Replace light alloy piston bottom with steel P/N 4/22015.55. (c) Replace the present ring nut with P/N 4/22015.56. (d) Shock absorbers modified as specified herein shall have a letter "D" placed on the nameplate. (e) Shock absorbers modified as specified herein shall be overhauled every 1,200 hours' time in service or every 2 years, whichever occurs first. This directive effective December 2, 1963
2005-01-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 series airplanes. This AD requires a one-time inspection for discrepancies of the frame web and inner chords on the forward edge frame of the number 5 main entry door cutout, and related corrective action. This AD is prompted by a report of cracking of the frame web and inner chords on the forward edge frame of the number 5 main entry door. We are issuing this AD to find and fix discrepancies of the frame web and inner chords, which could result in cracking, subsequent severing of the frame, and consequent rapid depressurization of the airplane.
80-17-07: 80-17-07 SIKORSKY AIRCRAFT: Amendment 39-3877. Applies to S-61 series helicopters certificated in all categories, including military counterparts. Compliance required as indicated. To prevent fatigue failures of the horizontal hinge pins: Replace the Rotary Wing Horizontal Hinge Pin P/N S6110-23020 and S6110-23320 prior to 4000 and 5300 hours time in service, respectively, or within 25 hours time in service after the effective date of this AD, whichever occurs later. This amendment is effective August 15, 1980.
97-03-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300 series airplanes, that requires an inspection to detect fatigue cracking, base trim, and upper flange over-trim of the pulley brackets of the aileron control cables. This amendment also requires, if necessary, replacement of the pulley brackets with new pulley brackets, and replacement of the two button-head rivets with flush-head rivets. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent fatigue cracking or fracturing of the pulley brackets, which could result in slack in the cables and consequent reduced ability of the flightcrew to control the aileron.
62-03-01: 62-03-01 HILLER: Amdt. 395 Part 507 Federal Register January 30, 1962. Applies to All UH-12A and UH-12B Helicopters. Compliance required within the next 150 hours' time in service after the effective date of this AD. To preclude additional failures of the tail rotor drive slip joints which can result in loss of power to the tail rotor, replace CR-10 or CR-10T type rollers of both fore and aft slip joints UH-12A Assembly Nos. 24500-9 and -10 and UH-12B Assembly Nos. 24565 and 24544, with the improved Torrington CR-10U type rollers. (Hiller Service Bulletin No. 44, Revision A covers this same subject.) This supersedes AD 55-08-03. This directive effective January 30, 1962.
83-14-01: 83-14-01 SHORT BROTHERS LTD.: Amendment 39-4681. Applies to SC7 Skyvan Series 3 airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the flaps, accomplish the following: (a) For all affected aircraft, except SNs SH1845 and SH1883, within the next 50 flights after the effective date of this AD or upon accumulating 7,000 flights, whichever occurs later, and thereafter at each subsequent 7,000 flights: (1) Inspect the inboard flap outer hinge arm and operating arm attachment ribs and replace the outer hinge arm in accordance with Part 1 of the Accomplishment Instructions Section of Short Brothers Service Bulletin No. 57-A61, Rev. 5, dated October 28, 1980, or an FAA approved equivalent. (b) Within the next 250 flights after the effective date of this AD or upon accumulating 7,000 flights, whichever occurs later: (1) Modify the outboard flap attachment ribs at the inboard hinge arm and operating arm in accordance with Part 1 of the Accomplishment Instructions Section of Short Brothers Service Bulletin No. 57-62, Rev. 1, dated September 9, 1980, or an FAA approved equivalent. (c) For S/Ns SH1845 and SH1883 only: (1) Accomplish the initial inspection and outer hinge arm replacement described in paragraph (a) (1) of this AD within the next 250 flights after the effective date of this AD. (2) Accomplish the modification described in paragraph (b)(1) of this AD within the next 250 flights after the effective date of this AD. (d) For all affected aircraft, including S/Ns SH1845 and SH1883, replace the outboard flap inner hinge arm, P/N SC7-25-39, operating arm, P/N SC7-25-107/8, inboard flap inner hinge arm, P/N SC7-25-39, operating arm P/N SC7-25-109/110, and their associated attachment ribs at 20,000 flights or 18,000 flights, as defined by Short Brothers Life Extension Service Bulletin No. 51-51, Rev. 1, dated October 19, 1978, in accordance with Short Brothers ServiceBulletin No. 57-A61, Rev. 5, dated October 28, 1980, or an FAA approved equivalent. (e) For purposes of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of flights may be determined by multiplying each airplane's hours time-in-service by 2. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on August 19, 1983.
2005-01-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100 and -200B series airplanes. This AD requires installing bonding clips and bonding jumpers from the housing of each fuel pump to airplane structure outside the fuel tanks. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure adequate electrical bonding between the housing of each fuel pump and airplane structure outside the fuel tanks. Inadequate electrical bonding, in the event of a lightning strike or pump electrical fault, could cause electrical arcing and ignition of fuel vapor in the wing fuel tank, which could result in a fuel tank explosion.
2000-11-22: This amendment adopts a new airworthiness directive (AD), applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines. This AD requires revisions to the Airworthiness Limitations Section of the Allison Engine Company AE 3007A and AE 3007C Engine Manuals to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. Air carriers with an approved continuous airworthiness maintenance program will be allowed to either maintain the records showing the current status of the inspections using the record keeping system specified in the air carrier's maintenance manual or establish an acceptable alternate method of record keeping. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that, if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2023-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by a report that an incorrect wiring arrangement was detected around the weather radar system. This AD requires modifying the weather radar redundant wiring, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.