Results
2013-15-11: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the left-side chord of the fin closure rib on the vertical stabilizer. This AD requires repetitive inspections of the left and right side chords of the fin closure rib for cracking and corrosion, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking and corrosion in the left- and right-side chords of the fin closure rib, which could lead to widespread cracking in the chords that might weaken the fin closure rib structure and result in loss of airplane control due to lack of horizontal stabilizer support.
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.
2000-12-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney PW4000 Series Turbofan Engines, that currently requires revisions to the Time Limits Section of the manufacturer s Engine Manuals (EM s) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. 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.
2003-11-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas airplanes, that requires inspections of the linear variable differential transducers (LVDTs) of the autopilot for discrepancies, and follow-on actions if necessary. This amendment is prompted by information from the manufacturer advising that certain LVDTs were delivered with an undersize nylok element on the threaded extension. The actions specified by this AD are intended to prevent failure of the LVDTs, which could result in an automatic pitch trim malfunction or an autopilot disconnect, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2025-05-06: The FAA is superseding Airworthiness Directive (AD) 2022-01-02, which applied to certain De Havilland Aircraft of Canada Limited Model DHC-8-400, -401, and -402 airplanes. AD 2022-01-02 required inspecting for corrosion of the nacelle to wing rear spar attachment pins, and the nacelle to landing gear attachment pins, and doing all applicable corrective actions. This AD was prompted by a determination that some operators were unable to identify the airplanes subject to each requirement. This AD continues to require the actions specified in AD 2022-01-02, clarifies the affected airplanes for each required action, and revises the applicability by removing Model DHC-8-400 airplanes; as specified in Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-08: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PW118A, PW118B, PW119B, PW119C, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD was prompted by reports of fractures of the first-stage power turbine (PT) blade. This AD requires inspection of the first-stage PT blades and the removal from service of those blades that fail the inspection or their replacement with blades eligible for installation. We are issuing this AD to prevent fracture of the first-stage PT blade, possible engine fire, and damage to the airplane.
97-03-17: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 and 757 series airplanes, that requires repetitive visual inspections to detect discrepancies of the wire terminal assembly, electrical connector, and wire insulation on the fuel pump; and replacement of the fuel pump with a new fuel pump, if necessary. This amendment also requires repetitive insulation resistance tests of the fuel pump wiring. This amendment is prompted by reports of fuel leaks at the fuel boost and override/jettison pumps due to corrosion. The actions specified by this AD are intended to prevent such a fuel leakage, which could result in a fire at the location of the affected fuel pump.
73-24-02: 73-24-02 SEMCO: Amendment 39-1746 is further amended by Amendment 39-2741. Applies to Model 30-AL, Serial Numbers SEM C1, SEM C2, SEM 11 to SEM 118 inclusive, Model TC-4A, Serial Numbers SEM 81 to SEM 118 inclusive, and Model "Model T," Serial Numbers SEM 28, SEM 60, SEM 61, SEM 62, SEM 64 through SEM 73, SEM 76, SEM 77 and SEM 78 to SEM 118 inclusive balloons certificated in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent inadvertent fuel leakage accomplish either 1 or 2 below: 1. (a) Remove the Amflo quick change female coupler part number C-2 from the lower end of the Imperial fuel hose Part Number Y905. NOTE: This is the vertical fuel hose connecting the tank to the burner valve. (b) Install an Amflo quick change male plug Part Number CP-2 or an equivalent part approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, on the lower end of the Imperial fuel hose Part Number Y905. (c) Remove the Amflo quick change male plugs Part Number CP-1 from the fuel tank 1/4" brass tee. (d) Install an Amflo quick change female coupler Part Number C-1 or an equivalent part approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, into the fuel tank 1/4" brass tee. 2. (a) Remove the Amflo quick change female coupler Part Number C-2 from the lower end of the Imperial fuel hose part number Y905. NOTE: This is the vertical fuel hose connecting the tank to the burner valve. (b) Remove the Amflo quick change male plug, Part Number CP-1, from the fuel tank 1/4" brass tee. (c) Install an AN 901-2 coupling and the Amflo quick change male plug part number CP-1 which was removed in step (b) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, onto the lower end of the Imperial fuel hose Part Number Y905. (d) Install an AN 911-2 nipple and the Amflo quick change female coupling Part Number C-2 which was removed in step (a) or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, into the 1/4" brass tee at the fuel tank. Amendment 39-1746 became effective November 26, 1973. This amendment 39-2741 becomes effective October 20, 1976.
2025-05-04: The FAA is superseding Airworthiness Directive (AD) 2019-05- 02, which applied to certain Rolls-Royce Deutschland Ltd & Co KG (RRD) (type certificate previously held by Rolls-Royce plc) Model RB211-Trent 970-84 and RB211-Trent 972-84 engines. AD 2019-05-02 required repetitive inspections of the drains mast for any crack and replacement or repair of the drains mast if necessary. Since the FAA issued AD 2019-05-02, the manufacturer has developed a modification (improved drains mast and drains support bracket), which the FAA has determined mitigates the unsafe condition. This AD was prompted by cracks found in the transition duct area of the drains mast. This AD requires modification with improved drains mast and drains support bracket. The FAA is issuing this AD to address the unsafe condition on these products.
2013-16-06: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model BO-105A, BO-105C, BO- 105LS A-1, BO-105LS A-3, and BO-105S helicopters. This AD requires inspecting for debonding of the erosion protective shell (abrasion strip) on the leading edge of each main rotor blade. This AD was prompted by the discovery of abrasion strip debonding during an inspection on one Model BO-105 helicopter and also by an incident on a second Model BO-105 helicopter that lost its abrasion strip in-flight. The actions of this AD are intended to detect debonding of the main rotor blade abrasion strip, which could lead to an unbalanced main rotor, high vibrations, damage to the tail boom or tail rotor, and loss of control of the helicopter.
73-16-03: 73-16-03 BELL: Amdt. 39-1695. Applies to Model 205A-1 helicopters certificated in all categories equipped with float landing gear kit, P/N 205-706-050-1, with 200 hours or more total service time on the float gear. Compliance required as indicated: To detect possible cracks in the forward and aft cross tubes of the float landing gear, accomplish the following inspections specified in Bell Helicopter Company Service Bulletin 205- 02-73-1 dated February 16, 1973 or later approved revision or in accordance with an equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. (a) Within the next 10 hours time in service after the effective date of this A.D., unless already accomplished, conduct the inspections specified in Part I, paragraphs 3 and 4 of Bell Service Bulletin 205-02-73-1. (b) At each 25 hours interval after the initial inspection, conduct the inspection specified in Part I, paragraph 6 of Bell Service Bulletin 205-02-73-1. (c) At each 100 hours interval after the initial inspection, conduct the inspection specified in Part I, paragraph 7 of Bell Service Bulletin 205-02-73-1. (d) The repetitive inspections specified herein, with the exception of the one-time inspection in (e), are no longer required after friction dampers, P/N 205-050-127-3 and 205-050- 127-5 have been installed. (e) If friction dampers have been installed on helicopters with float kit, P/N 205- 706-050-1, with cross tubes which had 200 hours or more service time at the time of damper installation, conduct the inspections specified in Part II, paragraph 1 of Bell Service Bulletin 205- 02-73-1 within 10 hours time in service, after the effective date of this A.D., unless already accomplished. (f) If a crack is found in a cross tube, replace the cross tube prior to next flight. This amendment becomes effective August 13, 1973.
2013-13-16: We are superseding airworthiness directive (AD) 2005-07-04 for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2005-07-04 required repetitive inspections to detect discrepancies of the transfer tubes and the collar of the ball nut of the trimmable horizontal stabilizer actuator (THSA), and corrective action if necessary; repetitive inspections for discrepancies of the ball screw assembly, and corrective action if necessary; repetitive greasing of the THSA ball nut, and replacement of the THSA if necessary; and modification or replacement (as applicable) of the ball nut assembly, which ends certain repetitive inspections. This new AD removes certain inspections, revises certain actions, and adds airplanes to the applicability. This AD was prompted by several reports of [[Page 47538]] disconnection of the transfer tube from the ball nut of the THSA. We are issuing this AD to prevent degraded operation of the THSA, which could result in reduced controllability of the airplane.
2013-16-02: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD requires incorporation of a new procedure into the airplane flight manual (AFM). This AD was prompted by a report of a runway excursion caused by failure of the nose landing gear position feed-back assembly. We are issuing this AD to detect and correct an incorrect angle signal causing an un-commanded nose wheel deflection, which could result in reduced controllability of the airplane.
2013-13-12: We are superseding airworthiness directive (AD) 2000-06-13 R1, which applied to certain The Boeing Company Model 737-200, -200C, -300, and -400 series airplanes. AD 2000-06-13 R1 required repetitively inspecting for cracking of the corners of the door frame and the cross beams of the aft cargo door, and corrective actions if necessary. AD 2000-06-13 R1 also required modifying the aft cargo door, which terminates the repetitive inspections. This new AD adds airplanes to the applicability, adds inspections and related investigative and corrective actions, revises certain inspection types, and reduces a certain compliance time for modifying the doors. This AD was prompted by reports of cracking in the forward and aft corner frames of the aft cargo door and in the lower cross beam. We are issuing this AD to prevent fatigue cracking of the corners of the door frame and the cross beams of the aft cargo door, which could result in rapid depressurization of the airplane.
2024-06-12: The FAA is superseding Airworthiness Directive (AD) 2021-24- 20, which applied to all Airbus SAS Model A350-941 and -1041 airplanes, and AD 2023-03-05, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-24-20 required repetitive water drainage and plug cleaning of the left- and right-hand slat geared rotary actuators (SGRAs) having a certain part number installed on slat 5 track 12 with certain functional item numbers. AD 2023-03-05 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2021-24-20 and AD 2023-03-05 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2013-14-06: We are adopting a new airworthiness directive (AD) for certain CFM International, S. A. (CFM) model CFM56-5 and CFM56-5B series turbofan engines. This AD was prompted by corrosion of the delta-P valve in the hydro-mechanical unit (HMU) fuel control caused by exposure to type TS-1 fuel. This AD requires cleaning, inspection, and repair of affected HMUs. We are issuing this AD to prevent seizure of the HMU, leading to failure of one or more engines and damage to the airplane.