Results
2017-10-08: We are superseding Airworthiness Directive (AD) 2009-21-01 for certain The Boeing Company Model 737-300 and 737-400 series airplanes. AD 2009-21-01 required repetitive inspections to detect cracking of the aft fuselage skin, and related investigative and corrective actions if necessary. This new AD adds certain inspections, repairs, replacement, related investigative and corrective actions if necessary; and removes certain airplanes from the applicability. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft fuselage skin is subject to widespread fatigue damage (WFD), and by reports of aft fuselage cracking. We are issuing this AD to address the unsafe condition on these products.
2010-24-14: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney PW4000 series turbofan engines. This AD requires initial and repetitive borescope inspections (BSI) or fluorescent penetrant inspections (FPI) for cracks in the anti-vortex tube (AVT) shelf slots on the 10th stage disk of the high-pressure compressor (HPC) drum rotor disk assembly. This AD results from 47 reports received since 2007 of HPC 10th stage disks found cracked in the AVT shelf slots during shop visit inspections. We are issuing this AD to prevent failure of the HPC 10th stage disk, uncontained engine failure, and damage to the airplane.
2001-23-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires an inspection of the flap drive transmission of the trailing edge flaps at positions 2 and 7 to determine if a discrepant torque brake is installed; and corrective action, if necessary. The action specified by this AD are intended to prevent damage to the flap system, adjacent systems, or structural components; or excessive skew of the trailing edge flap, which could result in flap asymmetry and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
90-02-15: 90-02-15 AIRBUS INDUSTRIE: Amendment 39-6477. Applicability: Model A320 series airplanes, Serial Numbers 005 through 039, and 042 through 049, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent possible false electronic centralized aircraft monitor (ECAM) messages on Auxiliary Power Unit (APU) shutdown, accomplish the following: A. Replace the standby transformer/rectifier (TR) with one identical to the main TR, and relocate it to a position with improved ventilation, in accordance with Airbus Industrie Service Bulletin No. A320-24-1028, dated July 7, 1989. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6477, AD 90-02-15) becomes effective on February 20, 1990.
2001-23-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires a review of maintenance records or an inspection to determine the serial numbers of geared rotary actuators (GRA) for the leading edge slats, and replacement of certain actuators with new or reworked actuators. This action is necessary to prevent a fractured spring washer in a GRA, which could lead to a disconnect in the GRA, and result in a slat skew condition and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2022-24-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that the thrust reverser correction factors presented in certain airplane flight manual (AFM) performance charts for landing on contaminated runways do not provide sufficient margin for stopping distances in certain conditions. This AD requires revising the existing AFM to correct the affected performance charts. The FAA is issuing this AD to address the unsafe condition on these products.
2010-24-12: We are adopting a new airworthiness directive (AD) for certain Model 777-200, -300, and -300ER series airplanes. This AD requires installing Teflon sleeving under the clamps of certain wire bundles routed along the fuel tank boundary structure, and cap sealing certain penetrating fasteners of the main and center fuel tanks. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent electrical arcing on the fuel tank boundary structure or inside the fuel tanks, which could result in a fire or explosion.
2025-06-13: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-9 and 787-10 airplanes. This AD was prompted by reports that some floor beam side-of-body fittings have been manufactured with an incorrect material type. This AD requires replacing the incorrectly manufactured floor beam side-of-body fittings, inspecting the fuselage frame and fastener holes for damage, and repairing any damage. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Dassault Model Mystere-Falcon 50 series airplanes. This action requires revising the Airplane Flight Manual to prohibit flight operation under reduced vertical separation minimum (RVSM). This action is necessary to prevent near misses or collision with other aircraft during flight, due to incorrect altitude information.
83-06-06: 83-06-06 BRITISH AEROSPACE, AIRCRAFT GROUP, SCOTTISH DIVISION: Amendment 39-4593. Applies to Model B.121, Series 1, 2, and 3 (all serial numbers) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To preclude failure of the Part Number BE.45.10193 Rudder Control Lever Assembly (or Assembly not identified by visual examination as Part Number BE.45.50107) located at Fuselage Station 217.75, within 50 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time-in-service from the last inspection, accomplish the following: (a) Visually inspect the Rudder Control Lever Assembly at Fuselage Station 217.75, to determine its part number. (b) If Part Number BE.45.50107 is determined to be installed, no further action is required. (c) If the part number cannot be determined, or is found to be number BE.45.10193, remove the Rudder Control Lever Assembly and inspect it using visual and dye penetrant procedures in accordance with Scottish Aviation Ltd., Service Bulletin No. B.121/71 dated December 29, 1976. Particular attention should be paid to areas near welds at the bases of all three levers. (d) If a crack is found in the Rudder Control Lever Assembly, replace it with a Part No. BE.45.50107 Rudder Control Lever Assembly before further flight. (e) The installation of a Part Number BE.45.50107 Rudder Control Lever Assembly constitutes terminating action for this AD. (f) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (g) Operators who have not kept records of hours time-in-service of the rudder control lever must substitute airplane hours time-in-service in lieu thereof. (h) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (i) 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 becomes effective on April 4, 1983.
98-07-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 1329-23 and -25 series airplanes, that requires replacement of a certain tailpipe V-band coupling with a new tailpipe V-band coupling. This amendment is prompted by reports indicating that the flight crew received a fire/overheat warning as a result of displacement of engine tailpipes, which allowed hot exhaust gases into the engine bypass duct. The actions specified by this AD are intended to prevent such displacement, which could result in escape of the hot exhaust gases from the engine tailpipe, and consequent damage to adjacent structure
2001-23-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 33, T-34, 35, 36, 55, 56, 58, and 95 Series airplanes. This AD requires you to inspect the left-hand and right-hand flap flex shaft assemblies to determine the manufacture date. This AD also requires you to replace any flap flex shaft assemblies manufactured from January 2000 through April 2001. This AD is the result four separate reports of flap drive cable separation. The actions specified by this AD are intended to prevent separation of the flap flex shaft assembly caused by improper heat treatment. Such a condition could lead to an asymmetric flap condition, resulting in uncommanded roll of the airplane.
2001-23-02: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc model RB211-535E4-37, RB211-535E4-B-37, RB211-535C-37, RB211-535E4-B-75 and RB211-22B-02 turbofan engines. This amendment requires inspection of certain high pressure (HP) turbine disks, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracks in two high life Trent 800 disk rim cooling air holes produced at the same manufacturing facility using the same tooling as the RB211 turbofan engine HP turbine disks. The actions specified by this AD are intended to prevent possible disk failure, which could result in an uncontained engine failure and damage to the aircraft.
2017-11-03: We are adopting a new airworthiness directive (AD) for DG Flugzeugbau GmbH Model DG-500MB gliders that are equipped with a Solo 2625 02 engine that has been modified with a fuel injection system following the instructions of Solo Kleinmotoren GmbH Service Bulletin (SB)/Technische Mitteilung (TM) 4600-3 ``Fuel Injection System'' and re-identified as Solo 2625 02i. 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 of the connecting rod bearing resulting from too much load on the rod bearings from the engine control unit. We are issuing this AD to require actions to address the unsafe condition on these products.
2017-09-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of interruptions in the airstair door operation. This AD requires repetitive inspections and modification of the handrail hardware. We are issuing this AD to address the unsafe condition on these products.
2001-23-08: This amendment supersedes priority letter AD 90-02-23, that is applicable to certain Hartzell Propeller Inc. ( )HC-( )2Y( )-( ) propellers. That priority letter currently requires repetitive visual inspections of propeller hubs for cracks using a 10X glass and, if necessary, removal of cracked hubs and replacement with serviceable parts. This amendment changes the frequency and method of inspection by requiring initial and repetitive eddy current inspections (ECI) of the propeller hub fillet radius for cracks and requires that certain model propeller hubs be removed from service. In addition, this AD allows installation of an improved design propeller hub as terminating action to the repetitive ECI. This amendment is prompted by reports of cracked propeller hubs found in service after they had been inspected in accordance with the visual inspections required by the current AD. The actions specified in this AD are intended to prevent failure of the propeller hub resulting fromcracks, that can cause blade separation and subsequent loss of aircraft control.
56-01-01: 56-01-01 BELL: Applies to Model 47G, Serial Numbers 666 Through 1411 and Model 47G2, Serial Numbers 1342 Through 1412. Compliance required as soon as possible, but not later than January 31, 1956. Ventral fin support angle braces, P/N 47-267-085-5 and -6 shafe the tail boom longeron, P/N 47-267-057-111 due to interference of these parts. The longeron must be inspected on both sides for wear and damage. Any damage of the longeron in excess of 0.008 inch, based on the diameter of the undamaged tube, must be repaired. 1/32 inch clearance must be provided between the support angle braces and the longeron. Additional rework of the 47-267-057-167 angle brace by the welding of a 1/16-inch steel plate, 3/4-inch x 3 inches, to the back of this part may be necessary to provide adequate clearance, if repair of the longeron by means of a split tube sleeve has been accomplished. (Bell Mandatory Service Bulletin No. 103 dated September 30, 1955, covers this same subject and outlines the details of the inspection and repairs.)
2001-23-05: This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes that do not have factory Modification 165, any edition, incorporated on the front seats. This AD requires you to modify the front seats that have solid metal seat pans. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to eliminate the potential for the front seats to inadvertently unlock from their fixed positions. Such uncontrolled movement could prevent the pilot from making the necessary flight maneuvers to control the airplane.
2023-02-12: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies, Inc. (Continental) GTSIO- 520, IO-470, IO-520, IO-550, IOF-550, LIO-470, LIO-520, LTSIO-520, O- 470, TSIO-470, TSIO-520, TSIO-550, TSIOF-550, and TSIOL-550 model reciprocating engines with a certain Superior Air Parts, Inc. (SAP) cylinder assembly or intake valve installed. The affected cylinder assemblies and intake valves are installed as a replacement part under parts manufacturer approval (PMA) on certain affected Continental engines. This AD was prompted by three intake valve failures on reciprocating engines that resulted in engine damage and emergency landing or aborted takeoff. This AD requires replacement of the affected engine intake valve. The FAA is issuing this AD to address the unsafe condition on these products.
2025-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A11 airplanes. This AD was prompted by an investigation of an in-service hydraulic fluid leakage event that indicated the potential use of an uncalibrated torque wrench when tightening the union fittings at the pressure and return interfaces of all three rudder hydraulic power control units (PCUs). This AD requires properly torquing the rudder PCU hydraulic fittings and applying the torque seal on the rudder PCU hydraulic fittings. The FAA is issuing this AD to address the unsafe condition on these products.
2001-23-04: This amendment adopts a new airworthiness directive (AD) that applies to all SOCATA--Groupe Aerospatiale (SOCATA) Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This AD requires you to repetitively inspect the lower rudder hinge fitting for cracks. This AD also requires you to repair any crack found in accordance with a repair scheme obtained from the manufacturer through the Federal Aviation Administration (FAA). This AD is the result mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct fatigue cracks in the lower rudder hinge fitting. This condition could cause the lower rudder to detach from the control linkage with consequent loss of control of the airplane.
88-12-11: 88-12-11 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5896. Applies to all SNIAS Alouette/Lama Model SA 315B, SE 3160, SA 316B, SA 316C, SA 3180, SA 318B, SA 318C, and SA 319B helicopters, equipped with main gearbox P/N 3160S62-00-000 or P/N 319A62-00-000; freewheel P/N 3160S60-10-000; and clutch P/N 3160S63-20-000, P/N 3180S63-10-000, or P/N 319A63-00-000, certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent failures of the main drive shaft and freewheel assemblies by ensuring proper operation of the main gearbox oil jet, P/N 3160A62-01-002, and to improve sealing at the freewheel attachment joints, accomplish the following: (a) Within the next 100 hours time in service or upon observance of a freewheel coupling and seal oil leak, whichever is earlier, comply with Alouette Service Bulletin 65-81, Issue 2, dated February 14, 1979, or Lama Service Bulletin 65-06, Issue 2, dated February 14,1979, as applicable. (b) After compliance with paragraph (a) of this AD, accomplish the following: After the first flight following the installation of a new or overhauled main gearbox, then every 100 hours time in service, comply with section 1(c) of Alouette Service Bulletin 05-65, dated February 14, 1979, or Lama Service Bulletin 05-14, dated February 14, 1979, as applicable. NOTE: Service Bulletin 05-65 supersedes Service Bulletin 05-42, dated November 10, 1971, and Service Bulletin 05-14 supersedes Service Bulletin 05-01, dated November 10, 1971. (c) An alternate method of compliance, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-0100, or by the Manager, Brussels Aircraft Certification Office, AEU-100, c/o American Embassy, Brussels, Belgium, APO NY 09667. The procedures shall be done in accordancewith Allouette Service Bulletin 65-81, Issue 2, dated February 14, 1979, or Lama Service Bulletin 65-06, Issue 2, dated February 14, 1979, as applicable. 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 Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005. Copies may be inspected in the Rules Docket, Office of Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Building 3B, Room 158, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment supersedes AD 73-13-02, Amendment 39-1666, as amended by Amendment 39-2527. This amendment, 39-5896, becomes effective May 20, 1988.
2017-10-15: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD was prompted by a reported inability to extend the external handle of the emergency door from its recess due to a jammed spring mechanism. This AD requires a one-time functional check of each emergency door handle, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2001-23-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Reims Aviation S.A. (Reims) Model F406 airplanes. This AD requires you to repetitively inspect the canted rib upper cap in the center wing carry-through area for cracks, and, if cracks are found, immediately repair the cracks or modify this area depending on the extent of any cracks found. This AD also requires you to modify the canted rib upper cap at a certain time period as terminating action for the repetitive inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct cracks in the canted rib upper cap in the center wing carry-through area, which could result in structural failure of the wing with possible loss of control of the airplane.
94-20-02: 94-20-02 AIRBUS INDUSTRIE: Amendment 39-9030. Docket 94-NM-121-AD. Applicability: All Model A320 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent severely reduced controllability of the airplane during approach under certain conditions, accomplish the following: (a) Within 10 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the information specified in Airbus A320/A321 Flight Manual Temporary Revision 9.99.99/20, dated June 14, 1994. NOTE 1: This may be accomplished by inserting a copy of Airbus A320/A321 Flight Manual Temporary Revision 9.99.99/20, dated June 14, 1994, in the AFM. When this temporary revision has been incorporated in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revisions is identical to that specified in Temporary Revision 9.99.99/20. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The revision to the AFM shall be done in accordance with Airbus A320/A321 Flight Manual TemporaryRevision 9.99.99/20, dated June 14, 1994. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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. (e) This amendment becomes effective on October 7, 1994.