Results
73-12-06: 73-12-06 GRUMMAN: Amdt. 39-1657. Applies to Grumman Models G-21 and G-21A Type Airplanes (Army OA-9, Navy, JRF-1 through JRF-6B under TC654) certificated in all categories. Compliance required as indicated: 1. To prevent hazards in flight associated with the failure of the elevator torque tube assembly P/N 12755, rudder torque tube assembly P/N 12756, L.H. and R.H. rudder pedal torque tube assemblies P/N's 12757, 12758 and hinge support assembly P/N 12725, located below the cockpit floor, visually inspect these assemblies for cracks and corrosion within one month after the effective date of this A.D. unless already accomplished within the last eleven months and thereafter at intervals not to exceed twelve months in service from the last inspection. 2. On assemblies having 3000 hours or more time in service or exceeding 36 months in service, within one month's time in service after the effective date of this A.D. unless already accomplished within the last 23 monthsand thereafter at intervals of 2000 hours in service but not exceeding 24 months in service, remove and disassemble the elevator torque tube assembly P/N 12755, rudder torque tube assembly P/N 12756, the L.H. and R.H. rudder pedal torque tube assembly P/N's 12757 and 12758, and hinge support assembly P/N 12725. Inspect all parts for corrosion or cracks, using visual and dye penetrant or magnaflux inspection methods. 3. Before further flight, repair or replace corroded parts and replace cracked parts with new parts or with a used part inspected in accordance with this AD or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, except that the aircraft may be flown in accordance with FAR 21.197. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, may adjust the repetitive inspection interval specified in this AD. This AD supersedes AD 72-13-05. This amendment is effective June 14, 1973.
2021-11-51: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527- A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 model turbofan engines. This AD was prompted by a review of investigative findings from an event involving an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. This AD requires an ultrasonic inspection (USI) of affected HPT 1st-stage disks and HPT 2nd-stage disks and, depending on the results of the USI, removal of the affected HPT 1st-stage and HPT 2nd-stage disks from service. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and is now issuing this AD to address the unsafe condition on these products.
2004-06-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of the existing main landing gear (MLG) leg assembly with a modified assembly. This action is necessary to prevent fatigue damage of the MLG leg, which could result in collapse of the MLG. This action is intended to address the identified unsafe condition.
2021-12-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a report that the auxiliary power unit (APU) aft fuel pump printed circuit board (PCB) varnish had deteriorated; the varnish is one of the layers of protection against development of an ignition source. This AD requires replacing each affected APU aft fuel pump, 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.
68-10-02: 68-10-02\tBOEING: Amendment 39-595. Applies to Model 707 and 727 Series airplanes equipped with G. E. cargo door and escape hatch heater blankets P/N 8921165G1 through G7, Boeing P/N 10-60911-9 through -15, which have not been modified in accordance with General Electric Service Bulletin No. SB-2 dated October 4, 1967, including Modification No. 2 dated December 11, 1967. \n\n\tCompliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent fires in the cargo door and escape hatch heater blankets, accomplish the following: \n\n\t1.\tDeactivate the "Passenger Cabin Blanket Heater" switch on the flight engineer's panel and placard switch "Inoperative", and deactivate the "Main Cargo Door Heater" circuit breaker or breakers on the pilot's overhead circuit breaker panel. Secure the circuit breaker(s) in the "OFF" position to prevent inadvertent activation, and placard the breaker(s) "Inoperative". \n\n\t2.\tDeactivate the "Passenger Cabin Blanket Heater" switch on the flight engineer's panel and placard it "Inoperative" and deactivate the "Escape Hatch Heater" circuit breaker or breakers on the pilot's overhead circuit breaker panel. Secure the circuit breaker(s) in the "OFF" position to prevent inadvertent activation, and placard the circuit breaker(s) "Inoperative". \n\n\t3.\tThe heater blankets may be re-activated upon accomplishment of G.E. Service Bulletin No. SB-2 dated October 4, 1967, including Modification No. 2 dated December 11, 1967, or an equivalent approved by the Chief, Aircraft Engineering Division, Western Region. \n\n\tThis amendment becomes effective May 11, 1968.
69-08-05: 69-08-05 BRITISH AIRCRAFT CORPORATION: Amdt. 39-749. Applies to Model BAC 1-11, 200 and 400 Series airplanes. Compliance required within the next 1500 hours' time in service after the effective date of this AD, unless already accomplished. To ensure that the shear pin which is installed within the Elevator Centralizing Spring Pots, Part Numbers AB34-A881, A3003, A3017, A3019, and A3021 remains effective, remove and disassemble the spring pots from the right and left elevators and modify in Accordance with BAC 1-11 Service Bulletin No. 27-A-PM 3536 or later ARB-approved issue, or FAA-approved equivalent. This amendment becomes effective May 11, 1969.
2004-06-02: This amendment adopts a new airworthiness directive (AD); applicable to certain Airbus Model A319, A320, and A321 series airplanes; that requires replacing the lower guide rod fittings at the rear passenger doors with improved fittings. This action is necessary to prevent failure of a lower guide rod fitting, which could cause a rear passenger door to jam during opening, delaying an emergency evacuation and resulting in injury to passengers or crew members. This action is intended to address the identified unsafe condition.
2021-12-17: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport Regional Model ATR42-300, - 320, and -500 airplanes; and all Model ATR72-101, -102, -201, -202, - 211, -212, and -212A airplanes. This AD was prompted by reports of defective seat tracks. This AD requires a detailed visual inspection of each affected part for deficiencies (sealant blockage and out of tolerance ligaments), 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.
71-16-02: 71-16-02 HAWKER-SIDDELEY AVIATION, LTD.: Amdt. 39-1251 as amended by Amendment 39-1329. Applies to Hawker-Siddeley Model DH-125 series 1A serial numbers 25013, 25104, 25016, 25018, 25021, 25022, 25026, 25027, 25030, 25031, 25034 through 25039, 25042, 25051 through 25053, 25057, and 25058; and series 1A-522 serial numbers 25017, 25020, 25023, 25029, 25032, 25033, 25043, 25046, 25047, 25060, 25064, 25065, 25066, 25068, 25070, 25073 through 25075, 25078, 25079, 25082 through 25084, 25086 through 25088, 25091, 25093, and 25095 airplanes. To prevent a hazardous drift in the Rotax voltage sensing unit, within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, incorporate Rotax Modification No. SP.7172 by replacing the transistor T.1 in the Rotax Voltage Sensing Unit Type U.3624 or U.3624/1 with a new transistor in accordance with Hawker Siddeley Aviation, Ltd., 125 Series Aircraft Service Bulletin 24/124 (7355), dated July 9, 1970, or later ARB-approved issue or FAA-approved equivalent. Amendment 39-1251 became effective August 23, 1971. This Amendment 39-1329 becomes effective November 5, 1971.
2021-12-16: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (AHD) Model MBB-BK117 C-2 and MBB- BK117 D-2 helicopters. This AD was prompted by a report of increased control force in the collective axis. This AD requires repetitive visual inspections of the main rotor actuator (MRA), 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.