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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.
2023-12-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
97-02-13: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JFTD12A series and T73 series turboshaft engines, that requires initial and repetitive fluorescent penetrant inspections (FPI) of compressor hubs, disks, spacers, and bolted on (rotating) airseals for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of extensive compressor rotor part cracking. The actions specified by this AD are intended to prevent disk rupture, an uncontained engine failure, and possible damage to the aircraft.
80-02-05: 80-02-05 ROLLS ROYCE LIMITED: Amendment 39-3655. Applies to Viper MK 601-22 model engine as installed in, but not limited to, Hawker Siddeley HS 125 series 600A and Beechcraft Hawker Siddeley BH 125 series 600A aircraft. Compliance is required as indicated unless already accomplished. To prevent possible failure of the flexible fuel hose, accomplish the following: (a) Within 250 hours engine time in service after the effective date of this AD, remove the flexible fuel hose assembly, Rolls Royce P/N DX 33-180-300 and install a new flexible fuel hose assembly, Rolls Royce P/N V 103813, in accordance with paragraph 2.A., "Accomplishment Instructions," of Rolls Royce Service Bulletin No. 73-A17, dated June 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Region, Brussels, Belgium. (b) Upon request of an operator, an FAA Maintenance Inspector may adjust the compliance time specified in paragraph (a) of this ADto be compatible with that operator's maintenance schedule. This amendment becomes effective January 24, 1980.
2005-01-11: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to check the airplane logbook to determine whether any main landing gear (MLG) actuator (part number (P/N) 960.30.01.103) with serial numbers (SNs) 830E through 881E is installed. If any MLG actuator with one of these SNs is installed, you are required to replace the MLG actuator with a P/N 960.30.01.103 actuator that has a SN other than 830E through 881E. The pilot is allowed to do the logbook check. If the pilot can positively determine that no MLG actuator with one of these SNs is installed, then no further action is required. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to prevent failure of the MLG actuator caused by an incorrect heat treating process, which could result in loss of hydraulic extension/retraction of the MLG. This failure could lead to loss of control during ground operations.
2023-12-01: The FAA is superseding Airworthiness Directive (AD) 2006-10- 13, which applied to all Airbus SAS Model A330-223, -321, -322, and - 323 airplanes. AD 2006-10-13 required repetitive inspections of the firewall of the lower aft pylon fairing (LAPF), and corrective actions if necessary. AD 2006-10-13 also provided an optional terminating action for the repetitive inspections. This AD was prompted by the design of an updated LAPF, the installation of which constitutes terminating action for the repetitive inspection required by AD 2006- 10-13. This AD continues to require the actions specified in AD 2006- 10-13, provides new optional terminating actions, and changes the applicability to exclude certain airplanes; 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.