Results
2013-15-14: We are superseding airworthiness directive (AD) 2008-06-29, which applied to all The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2008-06-29 required repetitive inspections of the downstop assemblies on the main tracks of the No. 2, 3, 4, and No. 5 slats and the inboard track of the No. 1 and 6 slats to verify if any parts are missing, damaged, or in the wrong order; other specified actions; and related investigative and corrective actions if necessary. This new AD retains these requirements and adds an inspection of the slat can interior for foreign object debris (FOD), and removal of any FOD found; modification of the slat track hardware; an inspection for FOD and for damage to the interior surface of the slat cans; and related investigative and corrective actions, if necessary. This AD was prompted by development of a modification by the manufacturer, which, when installed, would terminate the repetitive inspections. We are issuing this AD to prevent loose or missing parts in the main slat track downstop assemblies, which could puncture the slat track housing and result in a fuel leak and consequent fire.
75-17-10: 75-17-10 SLINGSBY SAILPLANES: Amendment 39-2312. Applies to T59D Kestrel gliders certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent structural failure of the elevator actuator bracket, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 5 hours' time in service, visually inspect the elevator actuator bracket P/N 59A-30-11 for cracks in the inside welded corners. (b) If cracks are found, prior to further flight, replace the elevator actuator bracket, P/N 59A-30-11, with a machined aluminum bracket, P/N 59A-03-8A/B/C, in accordance with Slingsby Sailplanes Technical Instruction No. 65, Issue 2, dated May 23, 1974, or an FAA- approved equivalent. (c) The inspections required by paragraph (a) of this AD may be discontinued after a machined aluminum elevator actuator bracket, P/N 59A-03-8A/B/C, has been installed in place of P/N 59A-30-11 in accordance with Slingsby Sailplanes Technical Instruction No. 65, Issue 2, dated May 23, 1974, or an FAA-approved equivalent. This amendment becomes effective August 18, 1974.
97-17-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly known as Beech Aircraft Corporation Model 1900D airplanes) that have not had the propeller removed and re-installed since factory installation. This action requires inspecting the propeller mounting bolts for the proper torque and replacing or re-torquing any propeller bolt with the wrong torque level. The manufacturer discovered some under-torqued propeller mounting bolts during factory installation of the propeller. The actions specified by this AD are intended to prevent fatigue cracking and failure of the propeller mounting bolts, which if not detected and corrected, could result in loss of the propeller. Comments for inclusion in the Rules Docket must be received on or before October 30, 1997.
2013-16-04: We are adopting a new airworthiness directive (AD) for all Eclipse Aerospace, Inc. Model EA500 airplanes equipped with Avio, Avio with ETT, or Avio NG 1.0 avionics suites. This AD was prompted by a report of potential aircraft hardware failure in the autopilot control panel and the center switch panel. This AD requires either incorporating updates to the aircraft computer system software or incorporating a temporary revision to the aircraft flight manual. We are issuing this AD to correct the unsafe condition on these products.
2025-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) Model PW535E and PW535E1 engines. This AD was prompted by a manufacturer design review that indicated certain flange bolts securing the gas generator case and turbine support case are susceptible to cracking at their current low- cycle fatigue (LCF) life. This AD requires repetitive borescope inspections (BSI) of the gas generator case to turbine support case retaining bolts for evidence of bolt cracks, bolt fracture, missing bolts, or loose bolts and replacement, if necessary, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-12: We are superseding airworthiness directive (AD) 2004-15-07, for certain Airbus Model A310 series airplanes. AD 2004-15-07 required repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. AD 2004- 15-07 also provided for an optional terminating action to end the repetitive inspections. This new AD reduces the initial inspection compliance time and intervals, and provides additional terminating action options. This AD was prompted by a reassessment of a previous fatigue threshold and inspection interval, which resulted in a determination that reduced inspection thresholds and intervals for accomplishment of the tasks are necessary. We are issuing this AD to detect and correct fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reducedstructural integrity of the wings.
97-26-05: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model HS 748 series airplanes. This action requires inspections of the inspection holes in all engine W frame socket fittings to determine if certain fasteners have been installed, or if the inspection holes have been reworked; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent fatigue cracking at the inspection hole locations, due to the installation of certain fasteners or hole enlargement, which could result in failure of the engine mount structure and consequent separation of the engine from the airplane.
2021-17-10: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model A109A, A109A II, A109C, A109E, A109K2, A109S, and AW109SP helicopters, having a certain rotor brake kit installed. This AD was \n\n((Page 46763)) \n\nprompted by a report of un-commanded activation of the rotor brake system before take-off due to a jammed rotor brake control cable and subsequent partially open brake control valve. This AD requires repetitive inspections of the rotor brake control cable and replacement of the rotor brake control cable, if necessary, 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.
2013-15-09: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) turbofan engine model PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 with a certain second- stage high-pressure turbine (HPT) air seal part number installed. This AD was prompted by discovery of cracks in second-stage HPT air seals. This AD requires inspection and removal from service of HPT air seals that fail inspection. We are issuing this AD to prevent failure of the second-stage HPT air seal, which could lead to an uncontained engine failure and damage to the airplane.
70-25-05: 70-25-05 AMERICAN AVIATION: Model AA-1. Amdt. 39-1118. Applies to American Aviation Model AA-1, Serial Number AA1-0001 through AA1-0125 airplanes certificated in all categories. Unless already accomplished, compliance required within the next 25 hours in service or within three (3) weeks from the effective date of this AD, whichever occurs first. To preclude binding of the trim actuator and elevator centering bungee in the existing bearing, comply with Item 1, "Bungee Mounting Plate Replacement," of American Aviation Service Letter No. 69-1A, dated July 10, 1969, or later revision or equivalent modification, either of which must be approved by the Chief, Engineering and Manufacturing Branch, FAA - Eastern Region. This amendment is effective December 8, 1970.