Results
96-05-03: This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 Series Turbofan Engines, that currently requires inspection of fan rotor disks within certain schedules. This amendment requires initial and repetitive eddy current inspections using an improved, more definitive procedure for detecting fan rotor disk dovetail slot cracks. Also, this amendment adds additional engine models and fan rotor disk part numbers and disallows fluorescent penetrant inspection (FPI) as an alternative inspection method for detecting fan rotor disk dovetail slot cracks. This amendment is prompted after additional analyses revealed that stress levels in the fan rotor disk dovetail slots for the applicable engine models are higher than initially calculated. The actions specified by this AD are intended to prevent uncontained failure of fan rotor disks due to fatigue cracking in the dovetail slots, which can resultin inflight engine shutdowns, severe secondary damage, and fan rotor assembly separation from the engine.
2011-02-02: We are superseding an existing 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: Following the rupture of an alternator and vapour cycle cooling system pulley drive assembly, the AD 2008-0067-E was published to require the replacement of the pulley drive assembly by a new one of an improved design. Later on, cases of rupture of the alternator and vapour cycle cooling system compressor drive shaft and of cracks on the standby- alternator and compressor support were reportedly found. Such failures could lead to the loss of the alternator and of the vapour cycle cooling systems, and could also cause mechanical damage inside the power plant compartment. To address this condition, the AD 2008-0129-E superseded AD 2008-0067-E and mandates the removal, as a temporary measure, of the compressor drive belt and of the torque limiter, the conditional replacement of the pulley drive shear shaft, and repetitive inspections for cracks of the pulley drive assembly and of the alternator/compressor support. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-22-04: We are superseding an existing 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: Bombardier Aerospace has completed a system safety review of the aircraft fuel system against fuel tank safety standards * * *. [A]ssessment showed that supplemental maintenance tasks [for the fuel tank wiring harness installation, and the hydraulic system No. 3 temperature transducer, among other items] are required to prevent potential ignition sources inside the fuel system, which could result in a fuel tank explosion. * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 5, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 5, 2008. The Director of the Federal Register approved the incorporation by reference of Section 3, "Fuel System Limitations,'' of Part 2 of Bombardier CL-600-2C10, CL-600-2D15, and CL-600-2D24 Maintenance Requirements Manual CSP B-053, Revision 9, dated July 20, 2007, listed in this AD, as of April 16, 2008 (73 FR 13098, March 12, 2008).
76-14-01: 76-14-01 DEHAVILLAND: Amendment 39-2661. 1. DeHavilland: Applies to DeHavilland Model DHC-4 Series Airplanes, S/N 2 through 17, certificated in all categories, that have not been altered in accordance with DeHavilland Aircraft of Canada, Ltd. Engineering Bulletin Series DHC-4 No. 11. Compliance required as indicated. Within the next 50 hours' time in service after the effective date of this AD, inspect and alter the rivets attaching the hinge plates to the outboard hinge arms on the inboard trailing flap assemblies in accordance with DeHavilland Engineering Bulletin Series DHC-4 No. 11 or with an equivalent inspection and alteration. 2. DeHavilland: Applies to DeHavilland Model DHC-4 Series Airplanes, S/N 2 through 22, 24, and 25, certificated in all categories, that have not been altered in accordance with DeHavilland Aircraft of Canada, Ltd. Modification Bulletin No. 4/1101, Issue 4. Compliance required as indicated. (a) Within the next 100 hours' time in service after the effective date of this AD, inspect and alter the rudder ribs in accordance with DeHavilland Modification Bulletin No. 4/1101, Issue 4, or with an equivalent inspection and alteration. (b) Repeat the inspection noted in paragraph (a) above at intervals not to exceed 100 hours' time in service until the alteration in DeHavilland Modification Bulletin No. 4/1101, Issue 4, or an approved equivalent, has been incorporated. 3. DeHavilland: Applies to DeHavilland Model DHC-4 Series Airplanes, S/N 2 through 39, except S/N 23 and 28, certificated in all categories that have not been altered in accordance with DeHavilland Aircraft of Canada, Ltd. Modification Bulletin No. 4/1099, Issue 3. Compliance required as indicated. (a) Within the next 250 hours' time in service after the effective date of this AD, inspect all electrofilm "unibal" spherical bearings in the flap hinge arms in accordance with DeHavilland Modification Bulletin No. 4/1099, Issue 3, or with an equivalent inspection. (b) Repeat the inspection noted in paragraph (a) above at intervals not to exceed 250 hours' time in service until the replacement of all electrofilm bearings in the flap hinge arms has been accomplished with sintered bronze teflon lined unibal bearings in accordance with DeHavilland Modification Bulletin No. 4/1099, Issue 3, or with an equivalent alteration. 4. DeHavilland: Applies to DeHavilland Model DHC-4 Series Airplanes, S/N 1 through 43, 45, 46, 47, 49, 50, 51, 53, 54, 55, 57, 58, and 59, certificated in all categories, that have not been altered in accordance with DeHavilland Aircraft of Canada, Ltd. Modification Bulletin No. 4/1150, Issue 3. Compliance required as indicated. (a) Within the next 50 hours' time in service after the effective date of this AD, inspect the left and right root fore flaps for external skin cracks if the flap has accumulated 300 hours' flying time. (b) Repeat the inspection noted in paragraph (a) above at intervals not to exceed 50 hours' time in service. (c) If the inspection indicated rib damage, or if the flap has accumulated 1000 hours' time in service, remove the flap and alter, before further flight, in accordance with DeHavilland Modification Bulletin No. 4/1150, Issue 3, or with an equivalent alteration. 5. DeHavilland: Applies to DeHavilland Model DHC-4 Series Airplanes, S/N 4 through 57, except S/N 6, 13, 17, 21, 23, 26, 34, 40, 55, and 56, certificated in all categories, that have not been altered in accordance with DeHavilland Aircraft of Canada Ltd. Engineering Bulletin, Series DHC-4, No. 18. Compliance required as indicated. To preclude the possible hazard of a fire created by loose terminal lug attachment to the end of aluminum electrical cable assemblies, accomplish the following: (a) Within the next 200 hours' time in service after the effective date of this AD, inspect, test, and where necessary, replace aluminum electrical cable assembliesin accordance with DeHavilland Engineering Bulletin, Series DHC-4, No. 18 or with an equivalent inspection and test. 6. DeHavilland: Applies to DeHavilland Model DHC-4 Series Airplanes, S/N 2 through 38, except S/N 23 and 34, certificated in all categories, that have not been altered in accordance with DeHavilland Aircraft of Canada, Ltd. Modification Bulletin No. 4/1182, Issue 2. Compliance required as indicated. To prevent possible failure of the main landing gear to fully extend and lock, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, install a spacer sleeve, P/N 5735-5, into the upper end fitting, P/N 5705-5, of the main landing gear shortening mechanism assembly, P/N 5700-7, in accordance with DeHavilland Modification Bulletin No. 4/1182, Issue 2, or with an equivalent alteration. Equivalent parts, inspections, procedures, instructions, repairs and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the inspection time in this Airworthiness Directive. Compliance with the Airworthiness Directive must be noted in the log book of the aircraft by referencing the Airworthiness Directive number and the specific item complied with: i.e. AD 76 - - - (4) if item 4 is being complied with. This amendment is effective July 12, 1976.
2006-21-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A340-200, and A340-300 airplanes. This AD requires the installation of heatshields in the belly fairing of the center fuselage. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing any fuel leaked from the center fuel tank to the hot temperature areas of the air conditioning packs, which could result in a fire and consequent fuel tank explosion.
91-08-08: 91-08-08 MESSERSCHMITT-BOLKOW-BLOHM GMBH: Amendment 39-6964; Docket No. 90-CE-41-AD. Applicability: Models BO-209-150FV, BO-209-150RV, BO-209-160FV, BO-209-160RV, BO-209-150FF "Monsun" airplanes (all serial numbers), 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 failure of the elevator spar truss and mass balance attachment rib, accomplish the following: (a) Dye penetrant inspect the elevator spar truss and reinforcement angle bar for cracks in accordance with the instructions in Measure I of MBB Technical Note No. 209-1/88, dated June 22, 1988. (1) If cracks are found, prior to further flight, repair in accordance with the instructions in Measure I, paragraph b) of MBB Technical Note No. 209-1/88, dated June 22, 1988 and then install a doubler in accordance with the instructions in Measure I, paragraph a) of MBB Technical Note No.209-1/88, dated June 22, 1988. (2) If cracks are not found, prior to further flight, install a doubler in accordance with the instructions in Measure I, paragraph a) of MBB Technical Note No. 209-1/88, dated June 22, 1988. (b) Visually inspect the mass balance attachment at the elevator nose rib for cracks in accordance with the instructions in Measure II of MBB Technical Note No. 209-1/88, dated June 22, 1988, and prior to further flight, replace, repair, or modify the rib in accordance with the instructions in Coversheet to Repair Instruction Elevator 209-31014RA1 and Measure II of MBB Technical Note No. 209-1/88, both dated June 22, 1988. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (e) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Messerschmitt-Bolkow-Blohm GmbH, Post fach 801160, D-8000 Munchen 80, Federal Republic of Germany; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6964, AD 91-08-08) becomes effective on May 13, 1991.
78-23-11: 78-23-11 GRUMMAN: Amendment 39-3341 as amended by amendment 39-3420. Applies to Grumman G-164 S/N's 1 thru 400, G-164A S/N's 401 and up, G-164B S/N's 01B and up, G-164C S/N's 01C and up, certificated in all categories. Compliance is required as indicated. To detect aileron balance cables containing broken wires, P/N's A1860-101 and A1860-401 at the wing root pulley, accomplish the following: (a) Within the next 50 hours in service after the effective date of this AD, unless already accomplished within the last 550 hours, inspect the aileron cables for broken wires where they cross the pulley near the right and left wing roots. (b) Within the next 600 hours in service after the compliance with paragraph (a) of this AD, and within every 600 hours in service thereafter, repeat the inspection of paragraph (a). (c) Replace cables containing broken wires, prior to next flight, with unused cables of the same part number or with an approved equivalent. (d) Equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection intervals in this AD. (f) The aircraft may be flown in accordance with FAR 21.197 to a location where the AD can be accomplished. (Grumman American Ag-Cat Service Bulletin No. 63, dated October 6, 1978, is concerned with this subject.) Amendment 39-3341 was effective November 13, 1978. This amendment 39-3420 is effective February 28, 1979.
96-04-02: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) ALF502L series turbofan engines, that establishes reduced retirement life limits for stage 1 and stage 3-7 compressors disks, and stage 2 turbine disks, and provides a drawdown schedule for disks already beyond the reduced retirement life limits. This amendment is prompted by new life analyses of these components. The actions specified by this AD are intended to prevent disk failure, which could result in an inflight engine shutdown and extensive engine damage.
96-04-08: This amendment adopts a new airworthiness directive (AD) that applies to Air Tractor, Incorporated (Air Tractor) Models AT-802 and AT-802A airplanes. This action requires repetitively replacing the main landing gear legs. Failure of the main landing gear legs on an AT-802A prompted this action. The actions specified by this AD are intended to prevent possible failure of the main landing gear legs, which, if not detected and corrected, could result in loss of control of the airplane during landing operations.
2011-02-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a one-time inspection to detect damage of the wire assemblies of the tail tank fuel system, a wiring change, and corrective actions if necessary. This AD also requires, for certain airplanes, a general visual inspection for correct installation of the self-adhering high-temperature electrical insulation tape; installation of a wire assembly support bracket and routing wire assembly; changing wire supports; and installation of a wire protection bracket. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct a potential of ignition sources inside fuel tanks, which, in combination with flammable vapors, could result in a fuel tank fire or explosion, and consequent loss of the airplane.