Results
2001-17-28 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that currently requires a one-time inspection to detect abrasion damage and installation discrepancies of the wire bundles located below the P37 panel, corrective action if necessary, relocating the wire support standoff, and installing protective sleeving over the wire bundles. This amendment removes the requirements to relocate the wire support standoff and install the protective sleeving, and revises the applicability by removing certain airplanes. The actions specified in this AD are intended to detect and correct such abrasion damage and installation discrepancies, which could result in arcing to structure and consequent fire or loss of function of affected systems. \n\n\tThe incorporation by reference of certain publications listed in the regulations, is approved by the Director of the Federal Register as of December 11, 2001.\n\n\tThe incorporation by reference of certain other publications listed in the regulations was approved previously by the Director of the Federal Register as of September 13, 2001 (66 FR 45579, August 29, 2001).\n\n\tComments for inclusion in the Rules Docket must be received on or before January 25, 2002.
2001-23-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Aeromot-Industria Mecanico Metalurgica Itda. (Aeromot) Models AMT-100 and AMT-200 powered sailplanes. This AD requires you to inspect (one-time) the main landing gear lever and elevator control rod for interference, warping, or incorrect gaps; and requires you to reconfigure or replace discrepant parts. This AD also requires you to report to the Federal Aviation Administration (FAA) any instances of interference, warping, or incorrect gaps. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Brazil. The actions specified by this AD are intended to detect and correct bending or warping in the main landing gear lever before it interferes with the elevator control rod. Such interference could result in the elevator control becoming jammed with consequent loss of control of the powered sailplane.
2017-11-09: We are superseding Airworthiness Directive (AD) 2017-08-07 for certain Learjet, Inc., Model 60 airplanes. AD 2017-08-07 required a one-time inspection of the fuselage skin for corrosion, and related investigative and corrective actions if necessary. This new AD retains the actions of AD 2017-08-07 and removes certain airplanes from the applicability. This AD was prompted by a determination that only certain airplanes are affected by the unsafe condition. We are issuing this AD to address the unsafe condition on these products.
2025-10-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B2, AS350B3, and EC130B4 helicopters. This AD was prompted by reports of broken cargo swing frames and the determination to change an existing repetitive inspection threshold. This AD requires repetitively inspecting the cargo swing installation and frame and, depending on the results, performing corrective action, 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.
2005-15-08: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100B SUD, -200B, -300, -400, and -400D series airplanes. This AD requires repetitive inspections for cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 460, 480, and 500 frame locations; and repair if necessary. This AD is prompted by findings of cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 460, 480, and 500 frame locations. We are issuing this AD to detect and correct fatigue cracking in certain fuselage stringers, which, if left undetected, could result in fuselage skin cracking that reduces the structural integrity of the skin panel, and consequent rapid depressurization of the airplane.
90-20-13: 90-20-13 CFM INTERNATIONAL: Amendment 39-6679. Docket No. 90-ANE-16. Applicability: CFM56-3B-2 and CFM56-3C-1 series turbofan engines equipped with fan blade Part Numbers (P/N's) 9527N99P08, 9527M99P09, 9527M99P10, 9527M99P11, and 1285M39P01. The above noted engine models are installed in, but not limited to, the Boeing 737-300/400/500 series aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent fan blade failure, inflight shutdown, and severe engine damage, accomplish the following: (a) Modify the fan module assembly by installing fan blade dampers P/N 335-105-305-0, axial stops P/N 335-105-201-0, and bolts P/N J815PO56A, in accordance with the accomplishment instructions contained in CFM56 Service Bulletin 72-494, Revision 2, dated June 18, 1990, within 60 days from the effective date of this AD. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, and alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The installation of fan blade friction dampers and associated hardware into the fan module assembly shall be done in accordance with the following CFMI document: DOCUMENT PAGE REVISION DATE CFMI SB 72-494 ALL 2 June 18, 1990 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 CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Council, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, D.C. 20591. Amendment (39-6679, AD 90-20-13) became effective on October 14, 1990.
98-07-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection for discrepancies of certain engine control cables, and replacement of the cables with new or serviceable control cables, if necessary. It also requires modification of the cable fairleads on the nose rib firewall. Additionally, this amendment requires modification of the mounting brackets of the control cable pulleys in the pulley box. 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 prevent chafing of engine control cables, which could cause the cables to break and result in loss of engine control and consequent reduced controllability of the airplane.
2023-02-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by reports of main landing gear (MLG) bogie pivot pins with damaged high velocity oxygen fuel (HVOF) coating, which resulted from heating caused by friction between the MLG bogie pivot pin and the bushes. This AD requires repetitively greasing the MLG bogie pivot pins, 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.
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.)