Results
2013-08-02: We are superseding an existing airworthiness directive (AD) that applies to all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. That AD currently requires repetitive inspections for cracking of the elevator actuator fittings. This new AD requires, for previously modified airplanes, repetitive inspections for movement of the fittings or fastener heads, and eventual replacement of certain bolts (including related investigative and corrective actions if necessary). For all airplanes, this replacement, with corrected torque values, would terminate the requirements of the existing AD. This new AD also removes certain airplanes from the applicability. This AD was prompted by the manufacturer's development of a modification that was approved as an optional terminating action to the existing AD's required repetitive inspections. We have been advised that the modification procedures include certain incorrect torque values. We are issuing this AD to detect and correct a cracked actuator fitting or incorrectly installed bolts to the actuator fitting, which could lead to the elevator becoming detached and unrestrained, and a consequent unacceptable flutter condition and loss of control of the airplane.
47-14-02: 47-14-02\tBOEING: (Was Mandatory Note 3 of AD-719-1 and Mandatory Note 3 of AD-726- 1.) Applies to 307 Series Aircraft. \n\tCompliance required prior to May 15, 1947. \n\tInspect the attachment of the main landing gear motors to the retracting unit. Determine, by testing, that the keys in these locations have been heat treated to 200,000-220,000 pounds per square inch. All keys that do not meet this strength specification should be replaced. Aircraft which have had this attachment revised to include an additional gearbox for the hand retracting drive are not subject to this inspection. \n\t(TWA E.O. No 3489 covers this same subject.)
2013-07-13: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD requires revising the aircraft flight manual (AFM); performing operational tests of the oxygen mask oxygen assembly; and replacing affected stowage boxes, which terminates the AFM revision and operational tests. This AD was prompted by failure of the flight crew oxygen supply due to a potentially defective flight crew mask oxygen assembly. We are issuing this AD to prevent failure to supply oxygen upon demand to the flight crew in flight in ``100%'' and ``Emergency'' modes, which, in an emergency, may result in incapacitation of the flight crew.
2000-05-25: This amendment supersedes an existing airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires installation of a placard prescribing special procedures to be followed when operating at certain flight levels with the engine and airframe anti-ice switch ON; modification of the air brake auto-retract function; and a revision to the Airplane Flight Manual (AFM) relative to altitude and operating limitations associated with flight in icing conditions above 26,000 feet. This amendment requires installation/replacement of new placards. This amendment also provides for a terminating modification for the AFM revision and installation/replacement of placards. This amendment is prompted by reports of uncommanded engine thrust reductions (rollback) when operating in certain icing conditions that exist in the vicinity of thunderstorms. The actions specified by this AD are intended to prevent enginepower rollback during flight in icing conditions, a condition that could result in insufficient power to sustain flight.
93-24-08: 93-24-08 CORPORATE JETS LIMITED (FORMERLY DE HAVILLAND, HAWKER SIDDELEY, BEECHCRAFT HAWKER, AND BRITISH AEROSPACE): Amendment 39-8757. Docket 93-NM-52-AD. Applicability: Model DH/HS/BH/BAe 125 series airplanes, excluding Model BAe 125-1000A series airplanes; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the engine fire extinguisher systems, accomplish the following: (a) Within 90 days after the effective date of this AD, conduct a one-time functional test of the diodes located in each engine fire extinguisher system to verify proper operation of the diodes, in accordance with Corporate Jets, Limited, Service Bulletin S.B. 26-33, dated December 8, 1992. (b) If any diode is found to be defective, prior to further flight, replace the defective diode in accordance with Corporate Jets Limited Service Bulletin S.B. 26-33, dated December 8, 1992. (c) Within 10 days after accomplishingthe functional test required by paragraph (a) of this AD, report all test findings, positive or negative, by mail or fax message to the following address: Service Support Manager, Corporate Jets Limited, 3 Bishop Square, St. Albans Road West, Hatfield, Hertfordshire AL10 9NE, England; fax 011-44-707 253959, or 011-44-707 252367. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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) The functional test and replacement shall be done in accordance with Corporate Jets Limited Service Bulletin S.B. 26-33, dated December 8, 1992. 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 Corporate Jets, Inc., 22070 Broderick Drive, Sterling, Virginia 20166. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on January 18, 1994.
2013-07-06: We are adopting an airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, AS332L, and AS332L1 helicopters and superseding an AD for Model AS332L2 and EC225LP helicopters. This AD requires inspecting the chip detector and modifying the chip collector, both installed on the main gearbox (MGB). This AD is prompted by an investigation which showed a failure within the epicyclic reduction gear module (epicyclic module) resulted in the rupture of the MGB case and separation of the main rotor head of a Model AS332L2 helicopter. These actions are intended to prevent failure of the MGB and subsequent loss of control of the helicopter.
2013-08-04: We are adopting a new airworthiness directive (AD) for Grob- Werke Model G115EG 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 cracks in the elevator trim tab arms on several Grob G 115 airplanes, which could result in failure of the part and consequent loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
92-12-04: 92-12-04 DE HAVILLAND, INC.: Amendment 39-8264. Docket No. 91-NM-267-AD. Applicability: de Havilland Model DHC-7 series airplanes; serial numbers 1 through 23; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of flap track no. 1, accomplish the following: (a) Within 6 months after the effective date of this AD, perform a one-time dye penetrant inspection to detect cracks in flap track no. 1, in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. (b) If cracks are evident or suspected as a result of the inspection required by paragraph (a) of this AD, prior to further flight, replace the flap track in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. (c) If no cracks are evident or suspected as a result of the inspection required by paragraph (a) of this AD, within 6 months after theeffective date of this AD, modify the lower surface of flap track no. 1 in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. (d) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, Engine and Propeller Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (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) The inspections and repairs shall be done in accordance with de Havilland Service Bulletin 7-53-15, Revision A, dated November 27, 1981. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment becomes effective on July 24, 1992.
2003-10-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections for cracking of the skin, bear strap, and sill chord of the lower lobe cargo door cutout, and repair, if necessary. For certain airplanes, the AD also provides an optional modification of the lower lobe cargo door cutout, which ends the pre-modification repetitive inspections, but necessitates new post-modification repetitive inspections after a certain time. The actions specified by this AD are intended to find and fix cracking of the skin, bear strap, and sill chord of the lower lobe cargo door cutout, which could lead to reduced structural integrity of the lower lobe cargo door cutout, and result in rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
69-08-11: 69-08-11 CESSNA: Amdt. 39-755. Applies to Models 210-5 (205), Serial Numbers 205-0001 through 205-0577; Models 206, U206 and P206, Serial Numbers 206-0001 through U206-1284 and P206-0001 through P206-0566; Models 210 and T210, Serial Numbers 21058221 through 21059111 and T210-0001 through T210-0424 series airplanes. Compliances: Within 50 hours' time-in-service after the effective date of this airworthiness directive, unless already accomplished: To prevent complete loss of engine power when using the fuel boost pump, accomplish the following: Modify the fuel boost pump electrical circuit by installing a resistor in accordance with Cessna Service Letter No. SE 69-9, dated April 11, 1969, or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. This amendment becomes effective April 22, 1969.
2021-06-10: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747 series airplanes and Model 767 series airplanes. This AD was prompted by a report of an un-commanded fuel transfer between the main and center fuel tanks. This AD prohibits operation of an airplane with any inoperative refuel valve (fueling shut-off valve) failed in the open position. The FAA is issuing this AD to address the unsafe condition on these products.
2003-10-14: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-231 series airplanes; equipped with International Aero Engines (IAE) V2500-A5 series engines. This action requires revising the airplane flight manual to incorporate new procedures to follow in the event of an oil filter clog message. This action is necessary to require the flightcrew to follow the procedures necessary to prevent smoke caused by an oil filter clog from entering the cabin during flight. This action is intended to address the identified unsafe condition.
2000-05-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS355N helicopters. This action requires inspecting the: 4 engine exhaust pipe ejector attachment lugs (lugs) for cracks; starter-generator (S-G) shaft for radial play; S-G attachment flange for cracks; and S-G attachment half- clamps for cracks. This amendment is prompted by 9 reports of S-G damage; 3 reports of the discovery of cracks in the lugs; and 1 report of an in-flight loss of the exhaust pipe ejector. The actions specified in this AD are intended to prevent separation of an engine exhaust pipe ejector from the helicopter, which could result in a tail rotor strike and subsequent loss of control of the helicopter.
2021-05-07: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model BO-105A, BO-105C, BO-105S, 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, and MBB-BK 117 C-1 helicopters. This AD was prompted by a report of a loss of electrical ground between the starter-generator and the generator voltage regulator (regulator). This AD requires inspecting the starter-generator electrical ground connection, retrofitting the starter-generator wire harness, and depending on model, revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2003-10-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Mystere-Falcon 50 series airplanes. This action requires a detailed inspection for clearance and chafing of the entire length of the hydraulic lines located within the engine pylons, and follow-on/corrective actions, as applicable. This action also requires a revision of the maintenance manual to ensure that the clamps that hold the hydraulic lines are in their initial position during normal maintenance, and that the position is identified with a yellow paint line. This action is necessary to prevent chafing and consequent leakage of the hydraulic lines located within the No. 1 and No. 3 engine pylons, which can result in failure of the No. 1 and No. 2 hydraulic systems, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2000-05-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Fan Jet Falcon series airplanes; Model Mystere-Falcon 20, 50, 200, and 900 series airplanes; and Model Falcon 10, 900EX, and 2000 series airplanes, that requires a functional test of the passenger oxygen masks, determination of the part number of the installed oxygen mask bags; 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 by this AD are intended to ensure that proper plastic bags of the passenger oxygen masks are installed, and that the masks are functioning properly. Improper plastic bags that have cracks or improperly functioning masks could result in insufficient oxygen to passengers in the event of rapid depressurization of the airplane.
2003-08-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2003-08-52 that was sent previously to all known U.S. owners and operators of GE Aircraft Engines (GEAE) CT7-9B turboprop engines. This AD requires rigging the compressor variable geometry (VG) to VG schedule N. This AD is prompted by reports of 12 compressor stall events that occurred over a six-month period. The actions specified in this AD are intended to prevent a dual-engine in-flight shutdown or power loss due to a compressor stall during deceleration from takeoff power to climb power.
2013-08-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200 and A340-300 series airplanes. This AD was prompted by a report that revealed the wheel axles of the main landing gear (MLG) were machined with a radius as small as 0.4 millimeters. This AD requires replacing the wheel axle of the MLG with a serviceable part. We are issuing this AD to prevent fatigue of the wheel axle of the MLG, which could adversely affect the structural integrity of the airplane.
74-26-06: 74-26-06 LOCKHEED-CALIFORNIA: Amendment 39-2049 as amended by Amendment 39-2104. Applies to all L-1011-385-1 Series Airplanes certificated in all categories, incorporating Engine Shutoff Control Panel Assemblies, P/N 1520324 or P/N 1580810, all configurations. Compliance required as indicated, unless already accomplished. To provide protection in the event of an unknown incipient failure condition in the housing of the fire pull handle assembly, P/N 1520324 or P/N 1580810, accomplish the following: (1) Within 600 hours time in service after the effective date of this AD, as amended, (a) Modify the Control Panel Assembly, P/N 1520324 or P/N 1580810, in accordance with Part 2 of Lockheed Service Bulletin 093-26-010, dated November 21, 1974, revised February 11, 1975 or later FAA-approved revisions. (b) Re-identify all modified Control Panel Assemblies in accordance with Part 3B of Lockheed Service Bulletin 093-26-010, dated November 21, 1974, revised February 11,1975, or later FAA-approved revisions. (2) Equivalent repairs or modifications may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. Note: Those engine shutoff control panel assemblies marked as P/N 1604009 or P/N 1605009 are in compliance with this AD. Amendment 39-2049 was effective December 23, 1974. This amendment 39-2104 to AD 74-26-06 becomes effective March 4, 1975.
2013-08-06: We are adopting a new airworthiness directive (AD) for Bell Model 430 helicopters, which requires replacing certain components of the air data system. This AD was prompted by the discovery of incorrect indicated airspeed when the helicopter was tested to the cold temperature limits (-40 degrees centigrade) required for Category A operations. The actions of this AD are intended to correct the published Vne and to correct the indicated airspeed.
93-02-12: 93-02-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8495. Docket 92-NM-183-AD. Applicability: Model 400A airplanes; serial numbers RK-2 through RK-29, inclusive, RK-31, and RK-32; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of standby power and the possibility of an electrical fire, accomplish the following: (a) Within 100 hours time-in-service after the effective date of this AD, inspect the left-hand interstage turbine temperature (LH ITT) circuit breaker wiring, in accordance with Beechcraft Service Bulletin No. 2458 (ATA Code 39-10), dated August 1992. Prior to further flight, correct any discrepancies found, in accordance with the service bulletin. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) 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. (d) The inspection shall be done in accordance with Beechcraft Service Bulletin No. 2458 (ATA Code 39-10), dated August 1992. (NOTE: The issue date of Beechcraft Service Bulletin No. 2458 is indicated only on "page 1 of 5"; no other page is dated.) 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085.Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 26, 1993.
74-25-05: 74-25-05 SIKORSKY: Amendment 39-2030. Applies to S-61L, S-61N, S-61NM and S- 61R helicopters certificated in all categories including Military Type CH-3C helicopters equipped with S6115-20501 series, S6115-20601 series, S6117-20101 series, and S6188-15001 series main rotor blades except for blades with serial numbers subsequent to 61M-6350-6105 and blades which have had all main rotor blade pockets replaced by Sikorsky Aircraft after October 30, 1972. Compliance required within 5 hours time in service after the effective date of this AD. The maximum never exceed speed is hereby reduced to 110 knots. Install placards as close as practicable to the airspeed indicators reading as follows: "Never exceed speed 110 knots." This supersedes telegram dated October 8, 1974 and supersedes the maximum never exceed speed established by Airworthiness Directive 74-20-7, Amendment 39-1989. This amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated November 6, 1974.
2025-06-08: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH (Type Certificate previously held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and Model 328-300 airplanes. This AD was prompted by a report of a nose landing gear (NLG) uplock bracket assembly cracking. This AD requires an inspection of the affected part and applicable on-condition actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2013-07-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700, -700C, -800, and -900ER series airplanes, Model 747-400F series airplanes, and Model 767-200 and -300 series airplanes. This AD was prompted by reports indicating that certain crew oxygen mask stowage box units were possibly delivered with a burr in the inlet fitting. The burr might break loose during test or operation, and might pose an ignition source or cause an inlet valve to jam. This final rule adds a step to identify and label certain crew oxygen mask stowage box units that have already been inspected and reworked by the supplier, and allows operators to install new or serviceable crew oxygen mask stowage box units, and requires a general visual inspection for affected serial numbers of the crew oxygen mask stowage box units, and replacement or re-identification as necessary. We are issuing this AD to prevent an ignition source, which could result in an oxygen-fed fire; or an inlet valve jam in a crew oxygen mask stowage box unit, which could result in restricted flow of oxygen.
2000-05-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A and 400T series airplanes, that requires a one-time inspection to detect incorrect wiring of the engine fire extinguisher bottle squibs, and corrective action, if necessary. It also requires a modification to the wiring and the addition of wire harness and bottle labeling for future reference. This amendment is prompted by reports of incorrect wiring of the engine fire extinguisher bottle squibs. The actions specified by this AD are intended to prevent failure of the engine fire extinguisher bottle to discharge, or discharge of the wrong engine fire extinguisher bottle.