Results
75-21-01: 75-21-01 SIAI-MARCHETTI: Amendment 39-2378. Applies to Models F.260 and 260B airplanes, Serial Numbers 101 thru 125, 2-26 thru 2-56, 3-76, 3-77, 3-80, and 502, except Serial Numbers 112, 2-33, 2-37, 2-43, 2-47, 2-53, and 2-54, certificated in all categories. Compliance is required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of the landing gear actuator relay and subsequent inability to extend the landing gear by normal electrical means, replace the landing gear actuator relay, P/N 3311- 2(10A), with new relay, P/N MS 24166-D1(50A), and add a circuit breaker, P/N MS 3320-10, in accordance with the accomplishment instructions of SIAI-Marchetti Service Bulletin, S.B. No. 260B5B, dated December 22, 1973, or an FAA-approved equivalent. This amendment becomes effective October 13, 1975.
2005-12-03: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This action requires replacing the main gearbox (MGB) lubrication/scavenge pump vespel spline adapters (vespel spline adapters) before further flight, and thereafter, replacing them at certain intervals. This amendment is prompted by a reported incident of an in-flight loss of oil pressure. The actions specified in this AD are intended to prevent loss of lubrication to the MGB, which could cause failure of one or both engine input drives, or planetary gear to sun gear tooth mesh failure, resulting in loss of power to the rotor system and subsequent loss of control of the helicopter.
75-26-14: 75-26-14 SCHEIBE FLUGZEUGBAU GmbH: Amendment 39-2463. Applies to Model Bergfalke II/55 and III gliders, certificated in all categories, equipped with loose connecting bolt between the elevator push-pull rod and elevator control lever. Compliance is required as indicated, unless already accomplished. To ensure a reliable elevator control connection, within the next 10 hours' time in service after the effective date of this AD, replace the safety pin (Fokker needle) at the connecting bolt between the elevator push-pull rod and the elevator control lever with an aviation quality washer and cotter pin. This supersedes Amendment 39-2334 (49 FR 33008), AD 75-17-29. This amendment becomes effective December 29, 1975.
2001-15-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes powered by Pratt & Whitney JT9D-7 series engines, that currently requires detailed visual inspections of the lugs on the bulkhead fitting of the rear engine mount, and corrective action, if necessary. The existing AD also specifies optional ultrasonic inspections, which, if accomplished, extend the repetitive interval for the required detailed visual inspections. This amendment requires accomplishment of the previously optional ultrasonic inspections and, for certain airplanes, rework of the bulkhead fitting of the rear engine mount. The actions specified by this AD are intended to detect and correct bushing migration, corrosion, or cracking of the lugs on the bulkhead fitting of the rear engine mount, which could result in fracture of the lugs and separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
64-13-01: 64-13-01 de HAVILLAND: Amdt. 739, Part 507, Federal Register May 27, 1964. Applies to All Model 104 "Dove" Aircraft. Compliance required as indicated. To prevent overheating of the electric cables in the cockpit and fuselage nose areas caused by a high resistance ground at the main ground post, accomplish either (a) or (b) as follows: (a) If the main ground (earth) has not been removed and inspected within 12 months prior to January 8, 1964, accomplish the provisions of paragraph (c) within the next 200 hours' time in service after the effective date of this AD unless already accomplished. (b) If the main ground (earth) has been removed and inspected within the 12 months prior to January 8, 1964, accomplish the provisions of paragraph (c) within the next 300 hours' time in service after the effective date of this AD unless already accomplished. (c) Dismantle, clean, inspect, and reassemble the main ground (earth) assembly in the forward fuselage in accordance with the method described in Hawker Siddeley Aviation, de Havilland Division, T.N.S. CT (104) No. 186, or an equivalent method approved by the Chief, Aircraft Certification Division, Europe, Africa, and Middle East. This directive effective June 26, 1964.
2001-15-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to include procedures that will ensure that the center tank fuel pumps are not operated with less than 1,000 pounds of fuel in the center tank. This amendment requires a further revision of the AFM to specify conditions for minimum fuel weight requirements and procedures for ground transfer of fuel for certain airplanes, repetitive inspections to detect discrepancies of the center tank override or override/jettison fuel pump, as applicable, and replacement of any discrepant pump with a new or serviceable pump. This amendment also requires that any override or override/jettison fuel pump without a diffuser be restored to a configuration that incorporates a diffuser. Additionally, this amendment requires installation of a new configuration center tank override or override/jettison fuel pump witha cast-in diffuser, which terminates the AFM revisions and repetitive inspections. The actions specified by this AD are intended to prevent ignition of fuel vapors due to the generation of sparks, to prevent a potential ignition source inside the fuel tank caused by steel-to-steel contact during dry fuel pump operation, and to ensure satisfactory fuel pump and fuel system operation.
64-09-05: 64-09-05 PIPER: Amdt. 721 Part 507 Federal Register April 25, 1964. Applies to Model PA-30 Aircraft Serial Numbers 30-1 to 30-321 Inclusive. Compliance required as indicated. (a) Within the next 10 hours' time in service after the effective date of this AD, and within every 10 hours' time in service thereafter until a new alternate air door is installed per (b): (1) Inspect each engine induction system air takeoff assembly, P/N 23810- 00, for signs of hinge wear at the alternate air door P/N 23809-00. (2) Replace worn or loose alternate air doors before further flight. (b) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, replace the P/N 23809-00 alternate air door with a new door P/N 23809-07 in accordance with Piper Kit Instructions 756794. After the new part is installed, the repetitive inspections in paragraph (a) are no longer required. (Piper Service Bulletin No. 220 covers this samesubject.) This directive effective April 29, 1964.
2005-12-08: The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A-1, and 2 B2 turboshaft engines. This AD requires replacing the software in the Engine Electronic Control Unit (EECU). This AD results from a report of simultaneous loss of automatic control of both engines of a Eurocopter Deutschland EC 135 helicopter, during flight. We are issuing this AD to prevent simultaneous loss of automatic control of both engines and subsequent loss of control of the helicopter.
2016-04-13: We are superseding airworthiness directive (AD) 2015-04-03 that applies to certain Rolls-Royce plc (RR) RB211 Trent 768-60, 772- 60, and 772B-60 turbofan engines. AD 2015-04-03 required inspection of the sealing sleeve on the high-pressure/intermediate-pressure (HP/IP) turbine support internal oil feed tube and removal of those sealing sleeves affected by AD 2015-04-03. This AD requires removal of either the affected sealing sleeve only or both the affected sealing sleeve and the oil feed tube. This AD was prompted by fractures of the HP/IP turbine support internal oil feed tube. We are issuing this AD to prevent failure of the HP/IP turbine support internal oil feed tube, uncontained engine failure, and damage to the airplane.
2010-21-06: 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: Within the framework of the A300-600 aircraft Service Life Extension programme (42,500 FC [flight cycles]), it has been concluded that a reinforcement of the junction of frame bases at FR48, FR49 and FR51 to FR53 is necessary to enable the aircraft to reach the Extended Service Goal (ESG). * * * [Failure of the frame base], if not corrected, could affect the structural integrity of the fuselage. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.