Results
2025-10-06: The FAA is superseding Airworthiness Directive (AD) 2023-10- 08, which applied to all ATR--GIE Avions de Transport R[eacute]gional Model ATR42-200, -300, and -320 airplanes. AD 2023-10-08 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2023-10-08, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023-10-08 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.
2002-12-06: This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney (PW) PW2000 series turbofan engines. That AD currently requires revisions to the engine manufacturer's Time Limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts that has indicated the need for mandatory inspections. 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.
2002-12-08: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc. (formerly AlliedSignal Inc., and Textron Lycoming) ALF502 and LF507 series turbofan engines. This amendment requires removal from service of certain gas producer turbine (GPT) components prior to reaching new, lower cyclic life limits using drawdown plans and replacing with serviceable parts. This amendment is prompted by continuous analysis of field-returned hardware indicating smaller service life margins than originally expected. The actions specified by this AD are intended to prevent GPT component failure, which could result in an uncontained engine failure and damage to the airplane.
2023-13-12: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500, 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER, 757- 200, 757-200PF, 757-200CB, 757-300, 767-200, 767-300, 767-300F, and 767-400ER series airplanes. This AD was prompted by reports indicating premature aging of certain passenger chemical oxygen generators. This AD requires repetitively replacing affected chemical oxygen generators with serviceable parts. This AD also limits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2011-03-01: We are superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life- limited parts at each piece-part opportunity. This AD modifies the TLS of the manufacturer's engine manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements and reduce the model applicability. This AD was prompted by PW developing, and the FAA approving, improved inspection procedures for the critical life-limited parts. The mandatory inspections are needed to identify those critical rotating parts with conditions which, if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life- limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2002-12-03: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332L2 helicopters. This action requires removing the main rotor shaft non-rotating scissors (non-rotating scissors) from the swashplate balljoint and inspecting for friction or play in the hinges between the two links of the non-rotating scissors, or between the non-rotating scissors link and the flared housing, and replacing the non-rotating scissors, if necessary. This amendment is prompted by the discovery of in-service damage to main rotor shaft non-rotating scissors attachment hinges. The actions specified in this AD are intended to prevent friction on non-rotating scissors, failure of the swashplate, loss of main rotor pitch control, and subsequent loss of control of the helicopter. Comments for inclusion in the Rules Docket must be received on or before August 12, 2002.
2023-13-06: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by an in-service event where the nose gear door amber caution message displayed on the crew alerting system during the initial climb after gear retraction. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
94-04-14: This amendment supersedes Airworthiness Directive (AD) 91-08-09, which currently requires the following on certain Twin Commander Aircraft Corporation (Twin Commander) 500, 680, 681, 685, and 690 series airplanes: repetitively inspecting the wing front spar lower cap (spar cap) for corrosion; and replacing the spar cap if corrosion exceeds certain limits. This action incorporates updated and more detailed inspection procedures, extends the repetitive inspection intervals, and provides the option of incorporating one of three modifications as terminating action for the repetitive inspections. The actions specified by the AD are intended to prevent wing structural damage that, if not detected, could progress to the point of failure.
2023-13-51: The FAA is superseding Airworthiness Directive (AD) 2022-19-08 which applied to all Airbus Helicopters Model SA341G and SA342J helicopters. AD 2022-19-08 was prompted by a report of manufacturing defects on multiple tail rotor blades (TRBs) and required visually inspecting certain part-numbered TRBs for the presence of a linear indication, and, depending on the inspection results, fluorescent penetrant inspecting the TRB and further corrective actions if necessary. AD 2022-19-08 also prohibited installing an affected TRB unless certain requirements had been met. This AD was prompted by the determination that parts that have accumulated more than 500 flight hours (FH) since new are also affected by the unsafe condition. In addition, the defined compliance time for the visual inspection of the root area of each affected part was determined to be too strict. This AD retains certain requirements of AD 2022-19-08, includes all TRBs in the inspection requirements, and increases a compliance time as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. The FAA is issuing this AD to address the unsafe condition on these products.
2002-11-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires an inspection of visually accessible areas for indications of overheating of the heater tape attached to the potable water fill and drain lines in the forward and aft cargo compartments, exposed foam insulation or missing or damaged protective tape around the potable water fill and drain lines, and debris or contaminants on or near the potable water fill and drain lines. It also requires corrective action, as necessary. This action is necessary to prevent overheating of the heater tape on potable water fill and drain lines, which may ignite accumulated debris or contaminants on or near the potable water fill and drain lines, resulting in a fire in the airplane. This action is intended to address the identified unsafe condition.
2023-13-08: The FAA is superseding Airworthiness Directive (AD) 2021-05-03 for certain Airbus Helicopters Model EC225LP helicopters. AD 2021-05-03 required various inspections of a certain part-numbered left-hand (LH) engine fuel supply (fuel supply) hose and depending on the inspection results, reinstalling or removing the fuel supply hose from service. AD 2021-05-03 also required installing an improved part and prohibited installing an affected fuel supply hose on any helicopter unless it was installed by following certain procedures. Since the FAA issued AD 2021-05-03, there were reports of difficulties using an adjusting tool to install the improved fuel supply hose. This AD continues to require the actions of AD 2021-05-03, expands the applicability, expands the parts installation limitations, and requires using an improved adjusting tool and updated procedures. This AD also updates certain compliance times and clarifies certain requirements. The FAA is issuing this AD to address the unsafe condition on these products.
2002-11-10: This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Model S-70A and S-70C helicopters. That AD currently requires inspecting a certain part-numbered main landing gear drag beam (beam) for a crack, removing any cracked beam before further flight, and reducing the torque of the jackpad mounting bolt retention nut (nut) of each beam. This amendment contains the same actions but requires those actions for another beam part number (P/N). This amendment is prompted by the inadvertent omission in the current AD of the additional beam that is susceptible to failure due to stress corrosion resulting from sustained excessive tensile stress due to excessive torque of the nut. The actions specified by this AD are intended to prevent excessive torque of the nut, failure of a beam, and subsequent loss of control of the helicopter during takeoff or landing.
2002-11-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models E55, E55A, A56TC, 58, 58A, 58P, 58PA, 58TC, and 58TCA airplanes. This AD requires you to inspect the Instrument Subpanel electroluminescent panel retaining screw for proper length and the rotating beacon circuit breaker switch (or any other switch in the same location) for damage and replace any screw or circuit breaker switch as necessary. This AD is the result of a report that an improper length electroluminescent panel retaining screw damaged the rotating beacon circuit breaker switch, which resulted in damaged wiring. The actions specified by this AD are intended to prevent damage to the rotating beacon circuit breaker switch or any other switch in the same location because of an incorrect length electroluminescent panel retaining screw. This condition could result in failure of the circuit breaker and lead to smoke and/or fire in the cockpit.
94-05-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model L-1011 series airplanes, that currently requires certain structural modifications and inspections. This amendment revises certain inspections required by the existing AD, and requires additional inspections and structural modifications. This amendment is prompted by reports of recent incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This action also reflects the FAA's determination that long term continued operational safety should be assured by actual modification of the airframe rather than repetitive inspections. The incorporation by reference of Lockheed Service Bulletin 093-51-035, Revision 1, dated December 16, 1991, as revised by L-1011Service Bulletin Change Notification 093-51-035, R1-CN1, dated October 27, 1992, as listed in the regulations, is approved by the Director of the Federal Register as of April 4, 1994. The incorporation by reference of Lockheed Service Bulletin 093-51-035, dated June 28, 1990, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 22, 1991 (56 FR 6556, February 19, 1991).
2023-14-08: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVII-G600 airplanes. This AD was prompted by an addition of a life limit in the Airworthiness Limitations Section (ALS) for GVII-G600 flap yokes. The life limit for the GVII-G600 flap yokes was informed by a GVII-G500 flap yoke failure that occurred during flight testing and, ultimately, resulted in additional test and analysis to establish more accurate life limits reflective of each model's design features and stress levels. The FAA is issuing this AD to require revising the existing ALS to prevent the GVII-G600 inboard flap yoke from remaining in service beyond its life limit. The FAA is issuing this AD to address the unsafe condition on these products.
2023-13-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by reports of inoperative manual and alternate horizontal stabilizer trim switches. This AD requires repetitive inspections for immersion of each limit switch and position transmitter module (LSPTM) and of the LSPTM electrical wiring, repetitive inspections for blockage of the drain holes and cleaning of each drain hole, repetitive inspections for loose or cracked leveling compound, and applicable on-condition actions. For certain airplanes, this AD also requires installing two new drain holes, performing repetitive inspections for blockage of the drain holes and cleaning each drain hole, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-20: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by reports of oxygen leaks caused by cracked, brittle, or broken oxygen hoses that were found during scheduled maintenance tests of the airplane oxygen system. This AD requires replacing oxygen system hoses having any part number in the O2C20T1 and O2C20T14 series. This AD also prohibits installation of affected oxygen hoses. The FAA is issuing this AD to address the unsafe condition on these products.
2002-11-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that currently requires repetitive inspections to detect cracking of the cove skin on the outboard leading edge slats, and corrective actions, if necessary. The existing AD also provides for an optional modification that significantly increases the repetitive inspection interval. This amendment expands the applicability of the existing AD by mandating the currently required inspections, and corrective actions, if necessary, for additional airplanes. Also, for airplanes on which the optional modification has been accomplished, this action requires a new one-time inspection for undersized seal inserts in the spanwise bulb seals on certain slats, and replacement of seal assemblies with new assemblies, if necessary. The actions specified by this AD are intended to detect and correct cracking or missing pieces of the cove skin, or undersized seal inserts installed in the spanwise bulb seals, on the outboard leading edge slats on the wings, which could result in skin separation or structural damage to the leading edge slats and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 10, 2000 (65 FR 57282, September 22, 2000).\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 777-57A0034, Revision 2, dated November 19, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 8, 1999 (64 FR 8230, February 19, 1999).
2023-12-19: The FAA is superseding Airworthiness Directive (AD) 2013-07- 03, which applied to all Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. AD 2013-07-03 required repetitive inspections for degradation of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main and central landing gear; an inspection of the affected bogie pivot pins for corrosion and base metal cracks; and repairing or replacing bogie pivot pins and pivot pin bushes, if necessary. This AD was prompted by development of a modification that address the unsafe condition and a determination that a parts installation prohibition is necessary. This AD continues to require certain actions in AD 2013-07-03, add an optional modification that would terminate the repetitive inspections, and add a parts installation prohibition, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-17-05: The FAA is adopting a new airworthiness directive (AD) for certain GE CF6-80C2 and CF6-80E1 turbofan engines. This AD requires you to inspect the high pressure compressor rotor (HPCR) stage 11-14 spool shaft for circumferential repair cuts, and to repair or replace the spool shaft if you find certain circumferential cuts. This AD results from an updated stress analysis. We are issuing this AD to prevent failure of the HPCR stage 11-14 spool shaft due to low-cycle fatigue that could result in an uncontained engine failure.
2002-11-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-502, AT-502A, AT-502B, and AT-503A airplanes. This AD lowers the safe life for the wing lower spar cap established in AD 2001-10-04 R1 and further reduces the safe life for airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets. This AD also requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification to detect and correct any crack in a bolthole before it extends to the modified center section of the wing and report the results of this inspection to the Federal Aviation Administration (FAA). This AD is the result of reports of several cracks originating in the outboard 3/8-inch hole of the main spar lower cap on Air Tractor Models AT-502, AT-502A, AT-502B, and AT-503A airplanes at times lower than the established safe life. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight. \n\n\tThe Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulation as of June 8, 2001 (66 FR 27014, May 16, 2001). \n\n\tThe FAA must receive any comments on this rule on or before July 5, 2002.
94-03-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires inspections of the brake rod inner cylinder bolts on the main landing gear (MLG) wheels and brakes; inspections of certain MLG bushings; installation of retainer plates at each MLG brake disconnect; inspection and modification of the brake rod pin assembly at each MLG wheel; repair or replacement of discrepant parts; and revision of the Airplane Flight Manual (AFM), as necessary. This amendment is prompted by numerous reports of brake failure during landing and during a low energy rejected takeoff. The actions specified in this AD are intended to prevent failure of two or more MLG brakes, which could adversely affect the stopping performance of the airplane.
2023-13-04: The FAA is superseding Airworthiness Directive (AD) 2021-16- 18, which applied to all Airbus SAS Model A330-200 Freighter, A330-200, A330-300, A330-800, A330-900, A340-200, A340-300, A340-500, and A340- 600 series airplanes. AD 2021-16-18 required repetitive inspections of certain fuel pumps for cavitation erosion, replacement if necessary, revision of the operator's existing minimum equipment list (MEL), and accomplishment of certain maintenance actions related to defueling and ground fuel transfer operations. This AD was prompted by reports of a fuel pump showing cavitation erosion that exposed the fuel pump power supply wires, and a determination that affected fuel pumps must be replaced with new, more erosion resistant pumps. This AD continues to require the actions in AD 2021-16-18, and also requires replacement of affected parts, which would terminate the repetitive inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of certain affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
94-04-01: This amendment supersedes two existing airworthiness directives (AD's) that currently require repetitively inspecting the wing attachment fittings and the wing front fittings for cracks on certain de Havilland DHC-6 series airplanes, and replacing any cracked part. The Federal Aviation Administration's policy on aging commuter class aircraft is to eliminate or, in certain instances, reduce the number of repetitions of certain short-interval inspections when improved parts or modifications are available. This action requires incorporating a modification that would eliminate the need for the repetitive inspections currently required by the two existing AD's. The actions specified by this AD are intended to prevent loss of control of the airplane caused by cracked wing attachment fittings.
93-05-10: 93-05-10 PIPER AIRCRAFT CORPORATION: Amendment 39-8514; Docket No. 92- CE-37-AD. Applicability: The following model and serial number airplanes, certificated in any category: Model Serial Numbers PA-32R-300 32R-7680001 through 32R-7880068 PA-32RT-300 32R-7885001 through 32R-7985105 PA-32RT-300T 32R-7887001 through 32R-7987126 PA-32R-301 32R-8013001 through 32R-8613005 and 3213001 through 3213037 PA-32R-301T 32R-8029001 through 32R-8629006 and 3229001 through 3229003 Compliance: Required within the next 100 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information. To prevent the inability to retract or extend the nose landing gear, which could result in substantial damage to or loss of control of the airplane, accomplish the following: (a) Inspect the engine mount as specified in and in accordance with the INSTRUCTIONS: PART I section of Piper Service Bulletin (SB) No. 955, dated March 3, 1992. Prior to further flight, repair any cracks in accordance with Piper SB No. 955. (b) Modify the airframe structure and strengthen the landing gear and engine mount attach areas in accordance with the instructions contained in either Engine Mount Drag Link Installation Kit, Piper Part No. 766-252 (for turbocharged models); or Engine Mount Drag Link Installation Kit, Piper Part No. 766-253 (for normally aspirated models). These kits are referenced in Piper SB No. 955, dated March 3, 1992. (c) Inspect the nose gear actuator attachment bracket for correct rivet dimensions in accordance with the INSTRUCTIONS: PART III section of Piper SB No. 955, dated March 3, 1992. If any rivets are found that are not of the dimensions referenced in Piper SB No. 955, prior to further flight, reinforce the nose gear actuator attachment bracket in accordance with the referenced service information. (d) If the parts that are required to accomplish the modification specified in paragraph (b) of this AD have been ordered, but are not available from the manufacturer, reinspect the engine mount as required by paragraph (a) of this AD at intervals not to exceed 100 hours TIS until parts become available. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (g) The inspections required by this AD shall be done in accordance with Piper Service Bulletin No. 955, dated March 3, 1992. The modification required by this AD shall be done in accordance with the instructions to Engine Mount Drag Link Installation Kit, Piper Part No. 766-252 (for turbocharged models); or Engine Mount Drag Link Installation Kit, Piper Part No. 766-253 (for normally aspirated models), which are referenced in Piper Service Bulletin No. 955. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on April 30, 1993.