Results
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.
84-13-06 R2: 84-13-06 R2 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A.: Priority letter AD 84-13-06 as amended by Amendment 39-5043 is further amended by Amendment 39- 5682. Applies to Model A109A and A109A II series helicopters certificated in any category and equipped with P/N 109-0132-02-11 or -15 tail rotor blades. Compliance is required as indicated unless already accomplished. To prevent possible hazards in flight associated with cracking of the tail rotor blade grip, accomplish the following: (a) Within the next 10 hours time in service, inspect the tail rotor blade grip in accordance with Part I of Agusta Service Bulletin (SB) 109-51, Revision A, or an FAA-approved equivalent, and at each additional 25 hours time in service, accomplish the inspection of Part III of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. (b) Prior to the first flight of each day, comply with Part II of the accomplishment instructions of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. This accomplishment may be conducted by the pilot. (c) Remove from service any tail rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office. Priority letter AD 84-13-06 was effective June 29, 1984. Amendment 39-5043 was effective May 13, 1985. This amendment, 39-5682, becomes effective August 30, 1987.
2004-26-10: The FAA is superseding an existing airworthiness directive (AD) for certain RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 650-15/10, and Tay 651-54 turbofan engines with ice-impact panels installed in the low pressure (LP) compressor case. That AD currently requires visually inspecting all ice-impact panels and fillers in the LP compressor case for certain conditions, and if necessary, replacing any ice-impact panels and fillers that have those conditions. This AD requires initial and repetitive visual inspections of all ice-impact panels and fillers in the LP compressor case for certain conditions and replacing as necessary, any or all panels. This AD also introduces a new compliance date of no later than March 1, 2005, to have all but one engine on each airplane in compliance with the polysulfide bonding of panels. This AD results from RRD issuing two service bulletins since AD 2004-05-22 was published, that required repetitive visual inspections of panels, and defines a minimum configuration and repair standard. We are issuing this AD to prevent release of ice-impact panels due to improper bonding that can result in loss of thrust in both engines.
2023-13-01: The FAA is superseding Airworthiness Directive (AD) 2008-23- 01, which applies to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2008-23-01 required inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the operator's airplane flight manual (AFM) and FAA-approved maintenance program. AD 2008-23-01 also required modifying or replacing certain fuel tank boost pumps, which terminated the AFM limitations and the maintenance program revisions. Since the FAA issued AD 2008-23-01, it has been determined that airplanes fitted with a different fuel pump can be subject to cavitation erosion on the wiring conduit. This AD requires inspecting affected fuel pumps for discrepancies and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA). This AD also requires replacing certain other fuel pumps. This AD also limits the installation of affected fuel pumps under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.