Results
96-13-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Jetstream Model 4101 airplanes. This action requires a review of maintenance records to determine the time-in-service (TIS) of the bearings in the starter/generators of both engines. This action also establishes a new TIS limit for the bearings, and requires replacement of the starter/generator unit with a serviceable unit, if necessary. This amendment is prompted by reports of controlled in-flight engine shutdowns resulting from failure of the bearings in the starter/generator unit. The actions specified in this AD are intended to prevent such failure of the bearings of the starter/generator, which could cause severe vibrations and resultant in-flight shutdown of one or both engines.
2013-13-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747SP series airplanes, and certain The Boeing Company Model 747-100B SUD and 747-300 series airplanes. This AD was prompted by an evaluation by the design approval holder indicating that the fuselage skin just above certain lap splice locations is subject to widespread fatigue damage. This AD requires repetitive inspections for cracking of the fuselage skin above certain lap splice locations, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane and sudden loss of cabin pressure.
2000-08-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and 727C series airplanes, that requires one-time inspections of the exterior body skin located at the forward corners of the mid-galley door hinge cutouts to detect cracking, and corrective actions, if necessary. This AD also requires modification of the body skin of the mid-galley door hinge cutouts. This amendment is prompted by a report indicating that, during fatigue testing on a Boeing Model 727 series airplane, a crack was found in the body skin at the lower forward corners of the mid-galley door hinge cutouts due to cabin pressurization cycles. The actions specified by this AD are intended to prevent such fatigue cracking of the body skin, which could result in reduced structural integrity of the fuselage and consequent loss of cabin pressurization.
2000-08-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Learjet Model 45 airplanes. This action requires revising the Airplane Flight Manual to provide the flight crew with certain instructions associated with an exterior preflight inspection and ground operations. This amendment is prompted by a report indicating the occurrence of an uncommanded brake application condition that was not annunciated in the cockpit. The actions specified in this AD are intended to provide the flight crew with procedures to detect an uncommanded brake application condition during taxi and takeoff. Such a condition could result in a possible wheel/brake fire and/or a high-speed rejected takeoff.
2018-06-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300 and -500 series airplanes. This AD was prompted by a report indicating that fatigue cracks were found in the lower wing skin of an airplane with winglets installed. This AD requires repetitive inspections for cracking of the lower wing skin, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2013-11-11: We are superseding AD 2000-04-01 that applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes. AD 2000-04-01 currently requires an inspection of the engine oil pressure switch and, if applicable, replacement of the engine oil pressure switch. This AD increases the applicability of the AD, places a life-limit of 3,000 hours time-in- service on the engine oil pressure switch, and requires replacement when the engine oil pressure switch reaches its life limit. This AD was prompted by new reports of internal failure of the engine oil pressure switch, which could result in complete loss of engine oil with consequent partial or complete loss of engine power or fire. We are issuing this AD to correct the unsafe condition on these products.
96-09-04: This amendment supersedes Airworthiness Directive (AD) 90-12-08, which currently requires the following on de Havilland Model DHC-3 airplanes: repetitively inspecting (using dye penetrant methods) the tailplane main rib forward flanges and the main rib forward lower flanges at the tailplane front attachment fitting for cracks and repairing any cracked flange. This AD action will retain the repetitive inspections currently required by AD 90-12-08, and will allow a certain modification as terminating action for these repetitive inspections. This action is prompted by the Federal Aviation Administration's determination that installing new angles and plates on the tailplane root ribs on de Havilland Model DHC-3 airplanes provides an equivalent level of safety to the repetitive inspections required by AD 90-12-08. The actions specified by this AD are intended to prevent failure of the tailplane structure caused by cracked tailplane main rib forward flanges or main rib forwardlower flanges at the tailplane front attachment fitting, which, if not detected and corrected, could result in loss of control of the airplane.
2003-10-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and -400F series airplanes, that requires initial and, for certain airplanes, repetitive inspections of the rivets in the forward, top, and side panels of the nose wheel well (NWW) for discrepancies; and follow-on inspections and corrective action, if necessary. This amendment also provides eventual terminating action for the repetitive inspections. The actions specified by this AD are intended to find and fix discrepancies of the rivets in the NWW panels, which could result in failure of the rivets and consequent reduced structural integrity of the panels and rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
2013-12-07: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 407 helicopters with certain tailboom assemblies installed. This AD requires, at specified intervals, inspecting the tailboom assembly for a crack, loose rivet, or other damage. This AD was prompted by a stress analysis of the tailboom skin that revealed that high-stress-concentration areas are susceptible to skin cracking. This condition, if not detected, could result in a crack in the tailboom assembly, failure of the tailboom, and subsequent loss of control of the helicopter.
69-18-04: 69-18-04 ALLISON: Amdt. 39-860. Applies to Allison Models 250-C10 and 250-C18 Series Engines having Gearbox Serial Numbers CAG 20183; CAG 20185; CAG 20193 through CAG 20265; CAG 20508; CAG 21001 through CAG 21395; CAG 21600 through CAG 21706; CAG 21800 through CAG 21803 installed, except those engines modified in accordance with Allison Commercial Engine Bulletin 250 CEB-90, dated August 21, 1969, or later FAA approved revision, or having P/N 6852085 nitrided helical torquemeter shaftgears. COMPLIANCE: Amendment 39-833 effective September 10, 1969. To prevent torquemeter shaftgear failure, accomplish the following: A) Adjust the N1 speed at ground idle so that N2 speed does not exceed 71% RPM. Allison Commercial Service Letter No. 250 CSL-34, dated August 4, 1969, or later FAA approved revision relates to this subject. B) Avoid continuous operation at any flight or ground condition, other than during ground idle or practice autorotation, at engine power turbine speeds (N2) below 98% or above 102% RPM. Allison Commercial Service Letter No. 250 CSL-34, dated August 4, 1969, or later FAA approved revision relates to this subject. *See footnotes. This amendment becomes effective October 18, 1969. *As a result of these operating restrictions, the Rotorcraft Flight Manual and certain powerplant instrument markings for the Bell Model 206A and Hughes Model 369 Series Helicopters in which the affected engines are installed may require revision or modification. The necessary information for such changes is available from the manufacturers of these helicopters. Revision No. 1 dated September 24, 1969, to Allison Commercial Service Letter 250 CSL-34 and Allison Commercial Engine Bulletin 250 CEB-90 is a later FAA approved revision which relates to the subject matter of this airworthiness directive.
2000-08-05: This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109C and A109K2 helicopters, that currently requires removing the main rotor pitch control link assemblies, measuring the radial play of each upper and lower spherical rod-end bearing (bearing), and replacing any unairworthy bearing. This amendment requires replacing the pitch control link assembly with an assembly that has increased durability and wear resistance. This amendment is prompted by reports of increased helicopter vibration caused by wear of bearings on certain pitch control link assemblies. The actions specified by this AD are intended to eliminate the need for recurring bearing inspections and to prevent failure of a bearing, increased helicopter vibration, and subsequent reduced controllability of the helicopter.
75-22-20: 75-22-20 SIAI-MARCHETTI: Amendment 39-2392. Applies to Models S.205-18/R, - 20/R, and -22/R, S/N's 001 thru 003, 101 thru 399, 4-101 thru 4-282, 4-285, 4-292, 5-302, 5-303 and 5-406; and Model S.208, S/N's 001 thru 003, 1-03 thru 1-15, 2-16 thru 2-27, 2-47 thru 2-50, 4-51, 4-60, 4-61, 4-62, 369, 3-100, 4-231, 4-233, 4-256, 4-257, and 4-258 airplanes, certificated in all categories. Compliance is required as indicated. To prevent possible failure of the landing gear, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, inspect the landing gear actuator attaching fork, P/N 205-6-214-15, for cracks, failure, and fork fin distance in accordance with Instructions, paragraph A., of SIAI Marchetti Service Bulletin, S.B. No. 205B40, dated April 7, 1975, or an FAA-approved equivalent. (b) If the inspection required by paragraph (a) of this AD reveals cracks or failure of the attaching fork, orif the fork fin distance is less than the minimum specified in the service bulletin, Instructions, paragraph a.8., before further flight, replace the landing gear actuator attaching fork, P/N 205-6-214-15, with one of new design, P/N 205-6-214-07, in accordance with Instructions, paragraph b. of SIAI Marchetti S.B. No. 205B40, or an FAA-approved equivalent. (c) If the inspection required by paragraph (a) of this AD reveals no cracks or failures and the fork fin distance is within allowable limits, either - (1) Reinstall the landing gear actuator fork, P/N 205-6-214-15, in accordance with Instructions, paragraph c. of SIAI Marchetti S.B. No. 205B40, or an FAA- approved equivalent; or (2) Install a new landing gear actuator attaching fork, P/N 205-6-214-07, in accordance with Instructions, paragraph b. of SIAI Marchetti S.B. No. 205B40, or an FAA- approved equivalent. This amendment becomes effective October 30, 1975.
2025-06-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a design review that found insufficient clearance between fire extinguishing system (FIREX) lines and certain fasteners in the center mid-fuselage area. This AD requires an inspection for positioning and sufficient clearance of certain fasteners in certain fuselage and keel beam areas, an inspection for damage of the fire extinguishing lines, and applicable corrective actions, 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.
2013-11-08: We are superseding an existing airworthiness directive (AD) for Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC- 6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/ B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure to inspect and maintain stabilizer-trim attachment components and the flap actuator could result in loss of control. We are issuing this proposed AD to require actions to address the unsafe condition on these products.
76-14-04: 76-14-04 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2668. Applies to Model L-1011-385 series airplanes, certificated in all categories. Compliance required as indicated. To prevent in-flight losses of the main landing gear fixed and hinged strut doors, the requirements of paragraphs (a) and (b) must be accomplished until the modification of paragraph (c) is performed. (a) Within the next 300 hours' time in service after the effective date of this AD, unless the modification of paragraph (c) is already accomplished, accomplish the following: (1) Modify the existing landing gear maximum extend speed placard in the airplane flight station to reduce the approved landing gear maximum extend speed (VLE) from 300 KIAS/0.85M to 250 KIAS/0.73M. (2) Amend the Limitations Section of the Lockheed L-1011 FAA Approved Airplane Flight Manual, LR 25925, as follows: "Landing Gear Operating Speed, VLO: Extension, 250 KIAS/O.73M Landing Gear Extended Speeds, VLE: 250 KIAS/0.73M The Landing Gear Operating Speed, VLO, and Landing Gear Extended Speed, VLE is 300 KIAS/O.85M when FAA-approved Lockheed Service Bulletins 093-52-010, 093-52-050, 093-52- 051, 093-52-074, and 093-52-078 are accomplished, as applicable." (3) Amend the Limitations Section of Appendix 7 of the Lockheed L-1011 FAA Approved Airplane Flight Manual, LR 25925, to add the following limitations: "Flights with landing gear extended in accordance with this Appendix are prohibited unless paragraphs (i) or (ii) or (iii), below, are accomplished: (i) FAA-approved Lockheed Service Bulletins, 093-52-010, 093-52- 050, 093-52-051, 093-52-074 and 093-52-078 are accomplished, as applicable. (ii) VMO is reduced to 250 KIAS, and an FAA-approved airspeed/Mach indicator with a maximum speed pointer set at 250 KIAS is installed, and the FAA- approved aural overspeed warning is reset for 250 KIAS. (iii) All main landing gear fixed and hinged strut doors are removed prior to flight." (b) Within the next 800 hours' time in service after the effective date of this AD, and at 800 hours' time in service intervals thereafter, perform visual integrity inspections of the main landing gear fixed and hinged strut doors in accordance with instructions of the L-1011 Maintenance Manual, Sections 32-12-02 and 32-12-03 dated June 23, 1976 or later FAA- approved revisions, and accomplish repairs and replacements as necessary. (c) Within the next 9000 hours' time in service after the effective date of this AD, unless already accomplished, modify the main landing gear fixed and hinged strut doors by incorporation of the following FA-approved Lockheed-California Company Service Bulletins, as applicable, or later FAA-approved revisions or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA, Western Region. Service Bulletin Date 093-52-010 June 12, 1972 093-52-050 May 27, 1975 093-52-051 December 7, 1973 093-52-074October 7, 1975 093-52-078 June 16, 1975 (d) The requirements of paragraphs (a) and (b) may be removed after the modification of paragraph (c) has been accomplished. Equivalent modifications and replacements may be approved by the Chief, Aircraft Engineering Division, FAA, Western Region. Airplanes may be flown to a base for the accomplishment of the modifications required by this AD, per FAR's 21.197 and 21.199, provided the requirements of paragraph (a) are observed. This amendment becomes effective July 14, 1976.
90-20-22: 90-20-22 BOEING: Amendment 39-6728. Docket No. 90-NM-44-AD. \n\n\tApplicability: Model 737 series airplanes, as listed in Alert Service Bulletin 737- 57A1197, dated December 21, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fuel vapor leaks into the inboard fixed leading edge landing light cavities, resulting in fuel vapor ignition, accomplish the following: \n\n\tA.\tWithin the next 180 days after the effective date of this AD, inspect the wings' inboard leading edge landing and runway turn-off/taxi light cavities for improper fuel vapor barrier sealing, in accordance with Boeing Alert Service Bulletin 737-57A1197, dated December 21, 1989. If the sealing is found to be improperly applied, rework the vapor barrier sealing prior to further flight, in accordance with the service bulletin. \n\n\tB.\tWithin 10 days after the inspection required by paragraph A. of this AD, if configuration discrepancies are discovered, submit a report of findings to the Manager, Seattle Manufacturing District Office, FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing CommercialAirplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. \n\n\tThis amendment (39-6728, AD 90-20-22) becomes effective on October 23, 1990.
2025-06-11: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by a report of the possible use of improper material during the manufacturing of vertical stabilizer to horizontal stabilizer junction fittings. This AD requires inspections of affected parts, applicable repairs, and eventual replacement of certain affected parts, 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.
2025-06-05: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X, FALCON 900EX, and FALCON 2000EX airplanes. This AD was prompted by reported occurrences of swelling of the lithium-polymer internal and external batteries of certain electronic display units (EDUs). This AD requires modifying certain EDUs and prohibits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
75-08-07: 75-08-07 ROCKWELL INTERNATIONAL CORP., GENERAL AVIATION DIVISION: Amendment 39-2160. Applies to Model 690A airplanes, Serial Numbers 11100 through 11208. Compliance required within 25 hours' time in service after the effective date of this AD, unless otherwise accomplished. To minimize the possibility of bleed air line failure and resultant leakage, accomplish the following: Modify Model 690A airplanes in accordance with Rockwell International, General Aviation Division, Service Bulletin Number 147 dated November 27, 1974, except that the requirements of Paragraphs "s" and "u" may be ignored and the first item under "SUPPLY DATA" may be deleted, or later approved revision, or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective on April 10, 1975.
2013-11-15: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model BO-105A, BO-105C, BO- 105S, BO-105LS A-1, BO-105LS A-3, EC135 P1, EC135 P2, EC135 P2+, EC135 T1, EC135 T2, EC135 T2+, MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A- 4, MBB-BK 117 B-1, MBB-BK 117 B-2, MBB-BK 117 C-1, and MBB-BK 117 C-2 helicopters with certain part-numbered cantilever assemblies, cyclic stick locking devices, or cyclic stick holder assemblies installed. This AD requires modifying and identifying the cyclic stick cantilever or lock. This AD was prompted by pilots inadvertently taking off with the cyclic locked. The actions of this AD are intended to prevent a pilot taking off with the cyclic in the locked position, which could result in loss of control of the helicopter.
2013-11-16: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation (Type Certificate Previously Held by Raytheon Aircraft Company) Model BAe.125 Series 800A (including C-29A and U-125), and 800B airplanes; and Model Hawker 800 (including variant U-125A) and 800XP airplanes modified in accordance with a certain winglet supplemental type certificate. This AD requires revising the Limitations section of the airplane flight manual (AFM) and installing placards on the instrument panel. This AD was prompted by reports of several instances of severe vibration and wing/aileron oscillations. We are issuing this AD to prevent vibration and wing/aileron oscillations, which could cause structural damage or lead to divergent flutter, and result in loss of integrity of the wing, loss of control of the airplane, and in-flight breakup.
2013-12-02: We are adopting a new airworthiness directive (AD) for certain Engine Alliance GP7270 and GP7277 turbofan engines. This AD was prompted by damage to the high-pressure compressor (HPC) stage 7-9 spool caused by failure of the baffle plate feature on affected HPC stage 6 disks. This AD requires initial and repetitive borescope inspections of the baffle plate feature and removal from service of the HPC stage 6 disk if the plate is missing material. This AD also requires mandatory removal from service of these HPC stage 6 disks at the next HPC module exposure. We are issuing this AD to prevent failure of the HPC stage 7-9 spool, uncontained engine failure, and damage to the airplane.
2013-11-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD was prompted by reports of failure of a screw cap or end cap of the hydraulic system accumulator while on the ground, which resulted in loss of use of that hydraulic system and high-energy impact damage to adjacent systems and structures. This AD would require inspecting for the correct serial number of a certain hydraulic system accumulator, and replacing affected hydraulic system accumulators with new or serviceable accumulators. We are issuing this AD to prevent failure of a screw cap or end cap and loss of the related hydraulic system, which could result in damage to airplane structure and consequent reduced controllability of the airplane.
50-43-01: 50-43-01 DOUGLAS: Applies to All Model DC-6 Aircraft. \n\n\tTo be accomplished on or before the next major inspection where facilities are available and in any event by December 15, 1950, unless already accomplished at last previous tire change, and thereafter at the regular major inspection nearest to 330 hours. This inspection period may be extended to tire replacement periods by the assigned CAA Agent when the airline's service experience indicates that a satisfactory level of safety is being maintained. \n\n\tRemove the tires from all Goodyear main wheels, Model L20HBMF, wheel assemblies 9540049 and 9540332, and thoroughly inspect by Zyglo or equivalent methods the critical areas of the wheel, such as: \n\n\t1.\tBrake drive flange area. \n\n\t2.\tTire bead radius of the fixed flange. \n\n\t3.\tTire bead seat radius of the demountable flange. \n\n\t4.\tRadius of the demountable flange step. \n\n\t5.\tThe flange returning ring groove in the wheel. \n\n\tIf cracks are found in any of the critical areas at one of these inspections, the wheel should be retired from service.
2025-06-09: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-300 and ERJ 190-400 airplanes. This AD was prompted by a report of a MAU 3B failure which led to brake fault advisory messages followed by loss of normal braking that was undetected until the brakes were pressed by the pilots. This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures associated with the failure of certain modular avionics units (MAUs), as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.