Results
2023-09-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes, and certain Model 737-8 and -9 airplanes. This AD was prompted by reports of uncommanded escape slide deployments in the passenger compartment, caused by too much tension in the inflation cable and the movement of the escape slide assembly in the escape slide compartment. This AD requires inspecting all escape slide assemblies to identify affected parts, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-09-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series 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 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.
2000-08-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections or checks to detect broken H-11 steel bolts at the wing rear spar side-of-body on the lower chord splice plate and kick fitting; and corrective actions, if necessary. This AD also requires eventual replacement of the existing bolts with new Inconel bolts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report of broken bolts at the wing rear spar side-of-body on the lower chord splice plate. The actions specified by this AD are intended to prevent cracking of the bolts due to stress corrosion, which could result in reduced structural integrity of the wing-to-body joint structure.
2000-08-16: This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters. This AD requires modifying the engine and transmission cowling doors (cowling doors). This amendment is prompted by an emergency landing of an ECD Model MBB-BK 117 helicopter after the No. 1 engine cowling opened, separated from the helicopter, and struck the main and tail rotor blades resulting in a tail rotor imbalance and subsequent departure of the tail rotor gear box from the helicopter. The actions specified by this AD are intended to prevent the cowling doors opening during flight, separating from the helicopter and impacting the main or tail rotor blades, and subsequent loss of control of the helicopter.
83-07-02: 83-07-02 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, "PZL MIELEC": Amendment 39-4601. Applies to Model PZL M18 Serial Nos. 1Z003-01 through 1Z003-010, 1Z004-05 through 1Z004-010, 1Z005-01 through 1Z005-15 airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent flutter and buffeting which could cause structural damage to the airplane, accomplish the following: a) Within the next 50 hours time-in-service after the effective date of the AD, reinforce all counterweights (elevator and rudder) as prescribed in Mandatory Bulletin Nos. I/010/81 dated February 1981 and U/019/81 dated November 1981. b) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. c) An equivalent method of compliance with this AD if used must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. Thisamendment becomes effective on April 7, 1983.
2023-08-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters (Airbus) Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD is prompted by modifications developed by Airbus to address a report of an emergency exit window that required excessive pushing force to jettison. This AD requires removing skived polytetrafluoroethylene tape (PTFE tape) (if installed) and replacing certain polychloroprene seals with silicone seals, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits installing a jettisonable window unless the actions required by this AD have been accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
2023-07-10: The FAA is superseding Airworthiness Directive (AD) 96-12-11, which applied to all Canadair Model CL-215-1A10 airplanes. AD 96-12-11 required repetitive inspections to detect discrepancies of the microswitches fitted at the water door actuator; replacement of any discrepant microswitch; and modification of the water door actuator switches, which terminates the repetitive inspections. This AD continues to require the modification of the water door actuator switches. This AD also requires modification of the water door solenoid valve common grounds, adds airplanes to the applicability, and specifies a parts installation limitation for the water door solenoid valve. This AD was prompted by reports of uncommanded opening of the water doors during flight and water scooping. The FAA is issuing this AD to address the unsafe condition on these products.
2000-08-11: This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6-6, CF6-45, and CF6-50 series turbofan engines, that requires revisions to the Time Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action would add additional eddy current inspections (ECI) for the high pressure turbine rotor (HPTR) Stage 1 and 2 disks. This action is prompted by additional focused inspection procedures 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.
2014-12-05: We are superseding airworthiness directive (AD) 2007-10-07 for all Turbomeca S.A. Arriel 2B, 2B1, and 2B1A turboshaft engines. AD 2007-10-07 required an inspection of the splines of the coupling assembly and the hydro-mechanical metering unit (HMU) drive gear shaft for wear. This AD requires the same inspection and expands the affected population. This AD also removes Arriel 2B1A engines from the applicability. We are issuing this AD to prevent failure of the HMU drive gear shaft, which could lead to damage to the engine and damage to the airplane.
95-22-03: This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Models 60 and A60 airplanes. This action requires incorporating flight manual supplement revisions into the Airplane Flight Manual (AFM) that would specify a minimum airspeed for operating the affected airplanes in icing conditions. Reports of several incidents and accidents on the affected airplanes related to flight in icing conditions prompted the proposed action. The actions specified by the proposed AD are intended to prevent loss of control of the airplane because of the airplane traveling too slowly in icing conditions.
2023-09-13: The FAA is superseding Airworthiness Directive (AD) 2019-18- 09, which applied to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes; and Model C-130A, HP-C-130A, EC-130Q, C-130B, and C-130H airplanes. AD 2019-18-09 required a visual inspection of the center wing upper and lower rainbow fittings for cracks, an eddy current inspection of the center wing lower rainbow fittings for cracks, and replacement if necessary. This AD was prompted by an analysis of reported cracks showing repetitive inspections are needed to adequately address cracked inner tangs of the center wing lower rainbow fittings. This AD requires repetitive inspections of the center wing upper and lower rainbow fittings for cracks and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
81-14-04: 81-14-04 SHORT BROTHERS LIMITED: Amendment 39-4152. Applies to Model SD3-30 series airplanes, certificated in all categories, which have Menasco Manufacturing main landing gear actuator assembly P/N 17900, Serial numbers MMC-003 through MMC-111, installed. To prevent gear-up landing caused by the main landing gear actuator's inability to unlock, accomplish the following within 500 landings after the effective date of this AD, unless already accomplished: Rework the actuator by cutting a venting groove across the contoured face of the profiled washer in accordance with Short Brothers Limited Service Bulletin No. SD3-32-86 Rev. 2 dated March 4, 1981, or later FAA approved revisions, or in a manner acceptable to the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the addresses listed above. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective July 8, 1981.
2004-25-19: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This AD requires revising the airplane flight manual to provide the flightcrew with procedures and limitations for operating an airplane with out-of-tolerance angle of attack (AOA) transducers. This AD also requires repetitive linearity tests of the AOA transducers, and corrective action if necessary. This AD is prompted by a report of premature wear of the potentiometers in AOA transducers having a certain part number. We are issuing this AD to prevent a delay in the stall computer commands for stall warning, stick shaker, and stick pusher operation, due to premature wear of the potentiometers of the AOA transducers, which may cause the airplane to enter a stall condition, and result in loss of control of the airplane.
2023-08-03: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-1159A and G-1159B airplanes and all Model G-IV and GIV-X airplanes. This AD was prompted by a report that the ground spoiler actuator installation does not preclude improper hydraulic line connections that could result in unintended asymmetrical spoiler deployment. This AD requires incorporating corrective actions that physically prevent improper connection of the hydraulic lines to the ground spoiler actuator. The FAA is issuing this AD to address the unsafe condition on these products.
2023-09-10: The FAA is adopting a new airworthiness directive (AD) for all Saab AB, Support and Services Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of excessive wear on certain starter generator brushes installed in the starter generator. This AD requires repetitive general visual inspections of the starter generator brushes installed in the starter generator and, depending on findings, replacement of the starter generator, and limits installation of affected generators, 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.
88-19-07: 88-19-07 EMPRESA BRAZILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-6008. Applicable to all Model EMB-120 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To reduce the potential for flap asymmetry that could lead to loss of control of the airplane in a critical phase of flight, accomplish the following: A. Within 15 days after the effective date of this AD, revise the FAA-approved Airplane Flight Manual (AFM) to include Revision 9 (for EMB-120RT AFM 120/794) or Revision 14 (for EMB-120 AFM 120/624), as applicable. B. Within 90 days after the effective date of this AD accomplish the following: 1. Replace the flap actuator solenoid valves with new valves equipped with new filters, in accordance with Embraer Service Bulletin 120-027-0050, dated April 13, 1988; 2. Replace the inlet filter fitting of the flap actuators, in accordance with Embraer Service Bulletin 120-027-0042, dated February 10, 1988; and 3. Install in-line filters to the flap control hydraulic plumbing, in accordance with Embraer Service Bulletin 120-027-0038, dated November 16, 1987. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for an alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Embraer, 276 S.W. 34th Street, Fort Lauderdale,Florida 33315. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia. This amendment supersedes AD 87-11-03, Amendment 39-5663. This amendment, 39-6008, becomes effective October 7, 1988.
82-22-51: 82-22-51 FAIRCHILD REPUBLIC: Amendment 39-4543. Applies to Fairchild Republic Models F-27 and FH-227 airplanes certificated in all categories. To prevent moisture separator assembly shell failure, accomplish the following: A. Prior to accumulating 100 landings or within 20 days, whichever occurs first, unless accomplished within the last 12 months, inspect the aircraft's moisture separator assembly P/N's 890469, 890469-01, 890469-02, 891572, or 891572-01, as applicable (two per aircraft), for the following: 1) Any of the above separator assemblies having upper shell assemblies P/N 841665 or 841665-01 which have been in service for three years or 20,000 cycles, whichever occurs first, must be immediately removed from service and replaced with a serviceable shell assembly. 2) Any shell assembly P/N 841665 or 841665-01 confirmed to have been installed less than three years or 20,000 cycles accumulated service, whichever comes first, which has not had the annualfluorescent penetrant inspection of shell assembly specified by the Walter Kidde Maintenance and Overhaul Manual F-41024B must be removed from service for the inspection and overhaul specified. Strict compliance with the crack and corrosion detection criteria of the Walter Kidde Manual is mandatory. 3) Any shell assembly P/N 841665 or 841665-01 with manufacturing dates stamped on the top of the shell housing prior to September 1979 which have never been in service must be inspected in accordance with Kidde Manual F-41024B before being put in service. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective February 3, 1983, and was effective earlier to those recipients of Telegraphic AD T82-22-51 dated October 27, 1982.
2004-25-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes. This action requires various repetitive inspections for cracking of the drag and shear angles that attach the nacelle to the wing, and related corrective action. This action also requires eventual modification of the drag and shear angles, which would end the repetitive inspections. This action is necessary to prevent fatigue cracking of the drag and shear angles, which could result in reduced structural integrity of the nacelle attachment to the wing. This action is intended to address the identified unsafe condition.
2023-07-11: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1B engines. This AD was prompted by a report of multiple aborted takeoffs and air turn- backs (ATBs) caused by high-pressure compressor (HPC) stall, which was induced by high levels of non-synchronous vibration (NSV). A subsequent investigation by the manufacturer revealed that wear on the No. 3 bearing spring finger housing can lead to high levels of NSV. This AD requires repetitive calculations of the oil filter delta pressure (OFDP) data and, depending on the results of the calculation, replacement of the No. 3 bearing spring finger housing. This AD also prohibits installation of an engine with an affected No. 3 bearing spring finger housing onto an airplane that already has one engine with an affected No. 3 bearing spring finger housing installed. The FAA is issuing this AD to address the unsafe condition on these products.
2014-12-09: We are adopting a new airworthiness directive (AD) for Agusta Model AB412 helicopters. This AD requires inspecting the main transmission lubricating system oil outlet hose (hose) for damage, and, if required, replacing the hose. This AD is prompted by reports of damage found on the hose. These actions are intended to prevent loss of main gear box (MGB) lubrication, which could lead to failure of the MGB and subsequent loss of control of the helicopter.
83-14-02: 83-14-02 PILATUS BRITTEN-NORMAN, LTD.: Amendment 39-4682. Applies to BN-2A MK. III Trislander Series (S/Ns 1001 thru 1042, 1048 thru 1054, 1057 thru 1061, 350, 360, 361 and 363) airplanes certificated in any category. Compliance: Required within the next 500 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent defects in the wing attachment pins which can adversely affect the safe life of the wing-to-fuselage attachments, accomplish the following: (a) Remove the wing attachment pins, one at a time, in accordance with the instructions contained in the "ACTION" section of the Pilatus Britten-Norman, Ltd., Service Bulletin No. BN2/SB 146, Issue 1, dated December 31, 1980 (hereinafter referred to as the SB), or an FAA-approved equivalent. (b) Visually inspect the wing attachment pins for corrosion, fretmarks, file/grinding marks and thread binding of the inboard nut in accordance with the instructions contained in the "ACTION" section of the SB, and if defects are found, before further flight, replace the defective wing attachment pins with new attachment pins. NOTE: Refer to SB and Trislander Illustrated Parts Catalog (Pub. Ref. PC/2, Sec. 3.5./1). (c) Visually inspect the wing joint gaps to ensure shim washers fill the gaps, and before further flight, replace shim washers as required to fill the wing joint gaps. NOTE: Refer to SB and Trislander Maintenance Manual (Pub. Ref. MM/2). (d) Reinstall wing attachment pins in accordance with the instructions contained in the "ACTION" section of the SB. (e) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomeseffective on August 19, 1983.
2004-25-51: The FAA is adopting a new airworthiness directive (AD) for all Raytheon Aircraft Company (Raytheon) Beech Models 45 (YT-34), A45 (T- 34A, B-45), and D45 (T-34B) airplanes. This AD requires you to perform an inspection and/or modification program approved specifically for this AD by the FAA Wichita Aircraft Certification Office (ACO). This AD is the result of a total of three accidents on the affected airplanes, including a recent accident where the wing separated from the airplane in flight. We are issuing this AD to detect and correct cracking in the wing structure of the affected airplanes, which could result in the wing separating from the airplane with consequent loss of control of the airplane.
2008-21-07R1: We are revising airworthiness directive (AD) 2008-21-07 for certain Dowty Propellers model R408/6-123-F/17 propellers. AD 2008-21- 07 required initial and repetitive inspections of the blade bonded metallic leading edge (L/E) guards for correct bonding until they accumulate more than 1,200 flight hours (FH) time-in-service. This AD requires the same inspection and replacement requirements of AD 2008- 21-07. This AD also provides an optional terminating action to those requirements. This AD was prompted by updated service bulletins that identify terminating action to the requirements of AD 2008-21-07. We are issuing this AD to prevent the loss of the bonded metallic L/E guard of the propeller, which could result in damage to the propeller or to the airplane, or injury to personnel.
2023-07-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 airplanes. This AD was prompted by reports the overwing emergency exit door (OWEED) escape line may be incorrectly routed. This AD requires inspecting the OWEED escape line and correcting the routing if required, 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.
2023-07-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series 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 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.