Results
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.