Results
2007-20-04: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A300 and A310 airplanes, and certain Model A300-600 series airplanes. That AD currently requires an inspection of the wing and center fuel tanks to determine if certain P- clips are installed and corrective action if necessary. That AD also requires an inspection of electrical bonding points of certain equipment in the center fuel tank for the presence of a blue coat and related investigative and corrective actions if necessary. That AD also requires installation of new bonding leads and electrical bonding points on certain equipment in the wing, center, and trim fuel tanks, as necessary. This new AD requires, for certain airplanes, installation of bonding on an additional bracket and modification of the fuel/defuel valves on the left-hand wing. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure continuous electrical bonding protection of equipment in the wing, center, and trim fuel tanks and to prevent damage to wiring in the wing and center fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the fuel tanks.
2019-20-08: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model G-IV and Model GIV-X airplanes. This AD was prompted by a revision to the airworthiness limitations section (ALS) of the aircraft maintenance manual (AMM) based on fatigue and damage tolerance testing and updated analysis. This AD requires revising the maintenance or inspection program to incorporate updated inspection requirements and life limits that address fatigue cracking of principal structural elements. The FAA is issuing this AD to address the unsafe condition on these products.
2010-04-11: We are adopting a new airworthiness directive (AD) for the products listed above. 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: The manufacturer has advised that the combination of a redesigned tail spring support with a stiffer tail spring and rough field operations has led to cracks in the tail spring support mounting base. Cracks have also been reported on aeroplanes already compliant with Part II of Extra Service Bulletin No. SB-300-2-97 issue A, as mandated by the LBA AD D-1998-001, dated 15 January 1998. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-01-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech ) Models B300 and B300C airplanes that do not have all cabin seats modified through the incorporation of Beech Kit No. 303-307. This action requires inspecting the cabin seat frames for cracks, repairing any cracks, and modifying the cabin seat frames by incorporating the kit referenced above. Inspection of affected in-service airplanes reveals cracking of these cabin seats around the welded-in bushings. The bearing shafts, which retain the seat frame and belted occupant, are bolted to the frame through these bushings. The actions specified by this AD are intended to prevent separation of the seat from its base caused by cracks around the welded-in bushings, which, in the event of an accident, could result in occupant injury.
2007-20-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: It has been revealed that the control surface balancing procedure in the * * * SAAB 2000 SRM (structural repair manual) * * * is incorrect. Incorrect balance, outside the tolerance of the aileron control surface, may lead to vibrations that in [the] worst case can result in flutter. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-08-02: This amendment supersedes two existing airworthiness directives (AD), applicable to all Boeing Model 707 and 720 series airplanes, that currently require inspections of the upper chords of the wing front and rear spars, repair, if necessary, and application of corrosion inhibitor to the inspected areas. This amendment requires repetitive inspections of the upper and lower chords on the wing front and rear spars, repair, if necessary, and application of corrosion inhibitor to the inspected areas. These actions are necessary to find and fix stress corrosion cracking of the upper and lower chords on the wing front and rear spars, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of May 8, 2001. \nThe incorporation by reference of Boeing Service Bulletin3240, Revision 3, dated October 18, 1985, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 10, 1992 (57 FR 4153, February 4, 1992). \n\n\tComments for inclusion in the Rules Docket must be received on or before June 22, 2001.
2001-08-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive inspections of the upper housing assembly of the forward trunnion of the main landing gear (MLG) for discrepancies (migrated or missing wearplates, loose or fractured attachment screws); and corrective action, if necessary. This action also provides for an optional modification of the upper housing assembly for airplanes without discrepant wearplates, which would end the repetitive inspections. This action is necessary to prevent migration or loss of the upper housing wearplate, which could result in loss of the MLG during the takeoff roll; consequent damage to the airplane structure; and injury to flight crew, passengers, or ground personnel. This action is intended to address the identified unsafe condition.
94-01-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell International, Collins Air Transport Division (Collins), Traffic Alert and Collision Avoidance System (TCAS) II processors that are installed on aircraft. This action requires replacing the existing TCAS II processor with a new processor that incorporates updated computer logic or reprogramming certain processors while they are still on board the aircraft. The development of candidate enhancements to TCAS II logic that improves its utility and increases its overall operational acceptance prompted the proposed action. The actions specified by this AD are intended to prevent collisions or near misses caused by incompatibility between the TCAS II processors and the current air traffic control system.
2007-13-11: The FAA is adopting a new airworthiness directive (AD) for all Eclipse Aviation Corporation (Eclipse) Model EA500 airplanes. This AD requires you to incorporate information into the Limitations section of the airplane flight manual (AFM) that will require operation only in day visual flight rules (VFR), allow only a VFR flight plan, and maintain operation with two pilots. This AD is being issued because of three instances of loss of primary airspeed indication due to freezing condensation within the pitot system. The loss of air pressure in the pitot system could cause the stall warning to become unreliable and the stick pusher, overspeed warning, and autopilot to not function. The concern is heightened by the aerodynamic characteristics of the Eclipse Model EA500 airplane, which relies on the stall warning and the stick pusher to alert the pilot prior to the loss of aircraft control. The standby airspeed is reliable and not affected by this failure mode. A temporary AFM revision prohibits operation in instrument meteorological conditions (IMC), requires two pilots, and limits the airspeed and altitude envelope if the event occurs in flight. The AFM limitations and FAA operational rules allow Model EA500 flight crews to file an instrument flight rule (IFR) flight plan even though the airplane is not approved for flight in IMC. This potentially causes an undue workload burden and confusion when the pilot has to refuse any instructions that take them into IMC. We are issuing this AD to prevent an unsafe condition when Air Traffic Control's (ATC's) ability to maintain traffic separation is compromised because an airplane on an IFR flight plan cannot accept a flight plan into IMC.
2001-08-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-7-100, -101, -102, and -103 series airplanes, that requires inspecting the endcaps of the main landing gear selector valve for leaks of hydraulic oil and, if leaks are detected, replacing the leaking endcaps or the entire selector valve. This amendment also requires eventual replacement or rework of certain selector valves, which would terminate the repetitive inspections. This amendment is prompted by a report of the collapse of the main landing gear due to an external leak of hydraulic oil in the landing gear selector valve, resulting from a fracture of the endcap. The actions specified by this AD are intended to prevent leaks of hydraulic oil from the main landing gear selector valve, which could result in the collapse of the main landing gear.
2019-21-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340- 200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by reports that non-approved passenger oxygen containers (POCs) may have been installed on the affected airplanes. This AD requires a one-time special detailed inspection (SDI) of each POC, and replacement if necessary, 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.
92-25-03: 92-25-03 AEROSPATIALE: Amendment 39-8418. Docket No. 91-NM-99-AD. Applicability: Model SN 601 Corvette series airplanes on which Modifications 1291 and 1368 have not been incorporated, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent damage to the fuselage passenger door frame skins at the hinge axis, accomplish the following: (a) Prior to the accumulation of 8,100 landings, or within 100 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current inspection of the skins on the upper and lower frames at the level of the passenger door hinge pins to detect cracks, in accordance with Aerospatiale Corvette Service Bulletin 53-21, dated June 25, 1990. (1) If no crack is found as a result of the inspection required by paragraph (a) of this AD, repeat the inspection at intervals not to exceed 3,300 landings. (2) If any crack is found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, accomplish Modification 1291, in accordance with Aerospatiale Corvette Service Bulletin 53-22, dated July 20, 1990. Accomplishment of this modification constitutes terminating action for the inspections required by paragraph (a) of this AD. (b) Prior to the accumulation of 9,100 landings or within 100 landings after incorporation of Modification 1291, whichever occurs later, perform a low frequency eddy current inspection of the upper door frame, and a high frequency eddy current inspection of the lower door frame, to detect damage to the fuselage passenger door frame skins at the hinge axis between Frames 11 and 12, in accordance with Aerospatiale Corvette Service Bulletin 53-23, Revision 2, dated November 6, 1991. (1) If no damage is found as a result of the inspections required by paragraph (b) of this AD, repeat the inspections at intervals not to exceed 3,600 landings. (2) If any damage is found as a result of the inspections required by paragraph (b) of this AD, prior to further flight, accomplish Modification 1368, in accordance with Aerospatiale Corvette Service Bulletin 53-8, Revision 1, dated August 20, 1990. Accomplishment of this modification constitutes terminating action for the low frequency eddy current inspection of the upper door frame required by paragraph (b) of this AD; however, the high frequency eddy current inspection of the lower door frame required by paragraph (b) of this AD must continue to be performed at intervals not to exceed 3,600 landings. (c) 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. (d) 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. (e) The inspections and modifications shall be done in accordance with the following Aerospatiale Corvette service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page Service Bulletin 53-21, June 25, 1990 1-9 Original June 25, 1990 Service Bulletin 53-22, July 20, 1990 1-13 Original July 20, 1990 Service Bulletin 53-23, Revision 2, November 6, 1991 1-5, 12-31 6-11 2 1 November 6, 1991 March 29, 1991 Service Bulletin 53-8, Revision 1, August 20, 19901-11 1 August 20, 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, 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. (f) This amendment becomes effective on December 23, 1992.
2007-19-14: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede existing ADs. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC-6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could lead to failure on the upper attachment fitting. This could result in the failure of the wing structure with subsequent loss of control of the aircraft. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2001-08-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-620, A310-203, A310-221, and A310-222 series airplanes, that requires repetitive inspections of fuselage frame 07 in the upper frame section assemblies of the lateral cockpit windows, and corrective action, if necessary. Accomplishment of certain corrective actions extends the repetitive inspection interval. The actions specified by this AD are intended to detect and correct fatigue cracking in that area, which could result in reduced structural integrity of the airplane.
2017-17-15: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of failures of the landing gear alternate-extension system. This AD requires replacement of certain nose landing gear and main landing gear electro-mechanical actuators. We are issuing this AD to address the unsafe condition on these products.
2001-08-08: This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 35-C33A, E33A, E33C, F33A, F33C, S35, V35, V35A, V35B, 36, and A36 airplanes that incorporate a certain Teledyne Continental engine configuration. This AD requires you to repetitively replace the existing Aeroquip V-band exhaust clamp. The actions specified by this AD are intended to prevent the tailpipe from detaching from the turbocharger due to failure of the V-band exhaust clamp. Clamp failure could result in the release of high temperature gases inside the engine compartment with the potential for a consequent fire in the engine compartment.
2019-19-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and 747-400F series airplanes. This AD was prompted by an evaluation that determined fatigue cracks could develop in the underwing longerons. This AD requires repetitive inspections of the underwing longerons and certain fuselage skins for any crack, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2017-17-14: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) airplanes. This AD was prompted by the discovery of circuit breakers of unsuitable strength that fail to protect the system from an overcurrent. This AD requires replacing certain circuit breakers. We are issuing this AD to address the unsafe condition on these products.
2001-08-04: This amendment supersedes an existing airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. That AD currently requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of that AD. This amendment requires the same actions as the existing AD but adds the BHTI Model 412EP helicopters to the applicability. This amendment is prompted by the discovery that the BHTI Model 412EP helicopter was inadvertently omitted from the existing AD. The actions specified by this AD are intended to prevent an actuator piston from unthreading from its rod end, loss of control of the mainrotor, and subsequent loss of control of the helicopter.
2018-10-03: We are adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as abrasion damage to the wing leading edge that could result in a fuel leak. We are issuing this AD to require actions to address the unsafe condition on these products.
94-03-09: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires inspection, modification, and replacement, if necessary, of the flap vane lugs. This amendment is prompted by reports of failure of flap vane lugs due to stress corrosion. The actions specified by this AD are intended to prevent failure of the flap vane lugs, which could lead to separation of flap vane from the airplane and cause injury to people or damage to property on the ground.
2007-19-19: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 747 series airplanes. The existing AD currently requires repetitive inspections and torque checks of the hanger fittings and strut forward bulkhead of the forward engine mount and adjacent support structure, and corrective actions if necessary. The existing AD also currently requires a terminating action for the repetitive inspections and checks. This new AD requires, among other actions, new repetitive inspections in the existing area and new areas. This new AD also provides for an optional inspection and no longer allows the existing fastener replacement to terminate repetitive inspections. This AD results from new reports of under-torqued or loose fasteners, a cracked bulkhead chord, and a fractured back-up angle after operators accomplished the terminating action required by the existing AD. We are issuing this AD to detect and correct loose fasteners and/or damaged or cracked hanger fittings, back-up angles, and bulkhead of the forward engine mount, which could lead to failure of the hanger fitting and bulkhead and consequent separation of the engine from the airplane. \n\nDATES: This AD becomes effective October 9, 2007. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 9, 2007. \n\tOn December 6, 2000 (65 FR 69862, November 21, 2000), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-54A2203, dated August 31, 2000. \n\n\tWe must receive any comments on this AD by November 20, 2007.
2001-08-01: This amendment adopts a new airworthiness directive (AD) that applies to certain JanAero Devices (JanAero) fuel regulator and shutoff valves used with JanAero combustion heaters that are installed on airplanes. This AD requires you to visually inspect and pressure test for leaks, and, if leaks are found, replace the fuel regulator and shutoff valve used with JanAero combustion heaters. This AD is the result of numerous reports of fuel regulator and shutoff valves leaking fuel. The actions specified by this AD are intended to prevent fuel leakage in airplanes with these combustion heaters with a consequent hazardous fire.
2019-20-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-09: 91-21-09 PIPER AIRCRAFT CORPORATION: Amendment 39-8056. Docket No. 91- CE-41-AD. Supersedes AD 91-02-06. Applicability: Model PA-24-260 airplanes (serial number (S/N) 24-3642, S/N 24-4000 through 24-4255, S/N 24-4257 through 24-4782, and S/N 24-4784 through 24-4803) that are equipped with nonturbocharged fuel-injected engines, certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent inadvertent engine stoppage while flying in weather conditions conducive to induction system icing, accomplish the following: (a) Modify the airplane by installing a manually controlled heated alternate air induction system in accordance with the instructions in either Piper Service Bulletin No. 861, dated May 4, 1987, or Supplemental Type Certificate SA2694CE. (b) The installation of a manually controlled heated alternate air induction system does not constituteapproval for flight in icing conditions. (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) An alternative method of compliance that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. (e) The modification required by this AD shall be done in accordance with Piper Service Bulletin No. 861, dated May 4, 1987. 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 of Piper Service Bulletin No. 861, dated May 4, 1987, may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies of the service bulletin may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. Airworthiness Directive 91-21-09 supersedes Amendment 39-6849, AD 91-02-06. This amendment (39-8056, AD 91-21-09) becomes effective on November 29, 1991.