Results
47-21-04: 47-21-04 NAVION: (Was Mandatory Note 3 of AD-782-3.) Applies to Serial Numbers NAV-4-2 Through 21, 24 Through 29, 32, 35, 36, 40, 42 Through 47, 57, 192, 199, 251. To be accomplished not later than August 1, 1947. The original fuel filler scupper will collect spilled gasoline since no drain line is provided. In addition, the thickness of material is insufficient to prevent damaging by the filler hose nozzle. To eliminate these conditions, a redesigned scupper with drain line is to be installed per NAA Drawing 145-89010. (NAA Field Service Bulletin No. 2 covers this same subject.)
2016-07-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of cracking of the aft fixed fairing (AFF) of the pylons due to fatigue damage of the structure. This AD requires repetitive inspections for damage and cracking of the AFF of the pylons, and repair if necessary. We are issuing this AD to detect and correct damage and cracking of the AFF of the pylons, which could result in detachment of a pylon and consequent reduced structural integrity of the airplane.
2024-22-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model Airbus A350-941 and -1041 airplanes. This AD was prompted by a determination that the lower attachment studs on the aft galley complex may be installed incorrectly due to a missing instruction in the maintenance procedure task. This AD requires a one- time inspection of the lower attachment studs on the aft galley complex, and depending on findings, accomplishment of applicable corrective actions, 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.
47-10-05: 47-10-05 LOCKHEED: (Was Mandatory Note 6 of AD-763-3.) Applies Only to Model 49 Serial Numbers 2021 to 2088, Inclusive. Compliance required prior to March 15, 1947. Inspect landing gear selector valve (Bendix P/N 403875-0-1) installed in forward cargo compartment. Those valves bearing Serial Numbers 1 through 120 and identified by letter "R: following the serial number have been reworked to incorporate a new type poppet. All unreworked valves should be replaced with reworked valves. (LAC Service Instruction 049/SI-34 covers this same subject.)
51-10-06: 51-10-06 CURTISS-WRIGHT Applies to all model C-46 Series aircraft. Compliance required at next periodic inspection, not to exceed 100 hours, and each 200 hours or nearest regular inspection period thereafter. Inspect all aileron, rudder and elevator hinge fittings and adjacent structure for cracks, loose rivets, worn bolts and condition of bearings. If defects are found, the part should be replaced by an undamaged part or repaired. This supersedes AD 50-14-1.
73-12-05: 73-12-05 FAIRCHILD: Amendment 39-1656 as amended by Amendment 39-2078 is further amended by Amendment 39-3543. Applies to all Fairchild F-27 and FH-227 Type Aircraft Certificated in all categories. Compliance required as indicated: 1. As to the vertical stabilizer attachment fitting assemblies for both front and rear spars, P/N's 27-233000-11, -12, -31, -32, -41 and -42 which have accumulated 2500 hours or more in service. a. Within the next 30 days, unless accomplished within the last 11 months, inspect all surfaces of the lugs of the fittings for cracks using an ultrasonic method in accordance with paragraph 2, Accomplishment Instructions, Part I, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent inspection. Inspect other areas of the fittings for cracks using a dye penetrant and a 10-power glass or an approved equivalent inspection. b. Within the next 60 days, unless accomplished within the last 10 months, inspect the fittings around the flanges and inner cavity for corrosion in accordance with paragraph 2, Accomplishment Instructions, Part II, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or in accordance with an approved equivalent procedure. c. The inspection specified in "a" above shall be repeated at intervals not to exceed 12 calendar months or 2500 hours in service from the last inspection, whichever occurs first. d. The inspection specified in "b" above shall be repeated at intervals not to exceed 12 calendar months from the last inspection. 2. Cracked parts shall be replaced and corroded parts shall be replaced or repaired prior to further flight. a. Parts replacement shall be in accordance with paragraph 2 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, and they shall be the same part number or approved equivalent parts. b. Parts repair shall be in accordancewith paragraph 2 and Figures 2 and 3 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent repair. 3. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspection or repairs can be performed. 4. 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 interval specified in this AD. Equivalent inspections, parts or repair must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-1656 was effective June 14, 1973. Amendment 39-2078 was effective January 28, 1975. This Amendment 39-3543 is effective August 29, 1979.
2016-07-08: We are adopting a new airworthiness directive (AD) for a certain The Boeing Company Model DC-9-83 (MD-83) airplane. This AD requires installing fuel level float and pressure switch in-line fuses, and doing applicable wiring changes, on the left, right, and center wing forward spars, forward auxiliary fuel tank, and aft auxiliary fuel tank. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
66-16-02: 66-16-02 BRITISH AIRCRAFT CORPORATION: Amdt. 39-254 Federal Register July 1, 1966. Applies to Model BAC 1-11 200 Series Airplanes. Compliance required before the accumulation of 3,000 hours' time in service for airplanes with less than 2,900 hours' time in service on the effective date of this AD and within the next 100 hours' time in service after the effective date of this AD for airplanes with 2,900 or more hours' time in service on the effective date of this AD unless already accomplished. To prevent chafing of the fuselage frame forward flange by the aft end of the headliner, rework the headliner, P/N AB77 A1605, and inspect the flange of fuselage frame, P/N AB29 A501, and rework as necessary in accordance with British Aircraft Corporation (BAC) One- Eleven Alert Service Bulletin 53-A-PM 2107, dated February 1, 1966, or later ARB-approved issue. This directive effective July 31, 1966.
73-16-05: 73-16-05 PRATT & WHITNEY: Amdt. 39-1698. Applies to all Pratt and Whitney Aircraft JT9D turbofan engines containing fourth and fifth stage turbine discs, P/N 646304, 694804, 618305, and 705905. Compliance required as indicated. To prevent possible failure of fourth and fifth stage turbine discs, the life limits on these parts have been reduced below the figures currently approved. Unless already accomplished, remove from service fourth and fifth stage turbine discs prior to reaching the revised life limit listed below or within the next 25 cycles in service after the effective date of this airworthiness directive whichever comes later. Disc Part Number Previous Life Limit Cycles Revised Life Limit Cycles 646304 8000 4000 694804 8000 4000 618305 8000 4000 705905 8000 4000 (Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time). NOTE: (Pratt and Whitney Service Bulletin No. 3785 pertains to this subject). This amendment becomes effective August 15, 1973.
2016-07-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that, during the assembly process, several gaps between the two parts of the girt bar fittings for the aft passenger doors were found to exceed tolerances. This AD requires an inspection of the gap between the two parts of the girt bar fittings on left-hand (LH) and right-hand (RH) aft passenger doors, and corrective actions if necessary. We are issuing this AD to detect and correct incorrect gaps between the girt bar fittings. Detachment of a girt bar could lead to the separation of the slide or slide-raft from the fuselage, making the emergency exit inoperative, which could impede an emergency evacuation.