Results
77-16-12: 77-16-12 PRATT & WHITNEY AIRCRAFT: Amendment 39-3008. Applies to Pratt and Whitney Aircraft JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, and -17 turbofan engine models containing Number 4-1/2 bearing, P/N 707007, bearing Serial Numbers 800 through 999, and Serial Numbers 100A through 214A. Compliance required as indicated. To preclude possible low turbine shaft failure, resulting from failure of the Number 4-1/2 bearing, remove from service, prior to March 31, 1978, Number 4-1/2 bearings, P/N 707007, Serial Numbers 800 through 999, and Serial Numbers 100A through 214A. Replace with an FAA approved, serviceable 4-1/2 bearing. Affected bearings shipped in engines and shipped as spares are identified by serial number in Tables I and II of Pratt and Whitney Aircraft Alert Service Bulletin Number 4639, dated August 12, 1976, or later revision approved by the Chief, Engineering and Manufacturing Branch, New England Region. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date specified in this A.D. to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. The manufacturer's service bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Pratt and Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. This amendment becomes effective August 31, 1977.
2003-26-04: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires certain inspections of the rod-end of the main rotor head damper for freedom of movement, and depending on the torque required to move the rod-end, either further inspection for a crack or replacing the rod-end. This amendment is prompted by reports of rod-end fractures due to fatigue failure resulting in increased helicopter vibrations. This condition, if not corrected, could result in failure of the rod-end, extreme vibrations, and a subsequent forced landing or loss of control of the helicopter.
2008-04-11 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Model 707 airplanes, and Model 720 and 720B series airplanes. That AD currently requires revising the FAA-approved maintenance program by incorporating new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
94-23-09: This amendment supersedes telegraphic airworthiness directive (AD) T89-02-52, which superseded Telegraphic AD T88-22-51 (AD), applicable to Rolls-Royce, plc (R-R) Spey series turbofan engines. Telegraphic AD T88-22-51 reduced cyclic life limits for seventh stage high pressure compressor (HPC) disks from 40,000 total part cycles in service (TPC) to 35,000 TPC for the R-R Spey Model 506-14 and -14D engines. Telegraphic AD T89-02-52 currently requires repetitive inspections or further reduced cyclic life limits for seventh stage HPC disks. This amendment increases the AD's effectivity to include additional R-R Spey engine models, eliminates the option for repetitive inspections, and further reduces the cyclic life limits. This amendment is prompted by further investigation into disk bore cracking that was caused by corrosion. The actions specified by this AD are intended to prevent a seventh stage HPC disk burst due to cracking attributed to corrosion, which may result in an uncontained engine failure. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 6, 1995.
2020-26-17: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport Regional Model ATR42-500 and ATR72 airplanes. This AD was prompted by a report of damage found on a wire bundle connecting an angle-of-attack (AOA) probe and a multi-function computer (MFC), which can inhibit activation of the stick pusher without any indication to the flight crew by the stall warning system. This AD requires a repetitive operational test for discrepancies of the stall warning system and stick pusher in the flight configuration, an inspection for discrepancies in the wiring bundles between AOA probes and MFCs, and corrective action 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.
78-03-02: 78-03-02 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 3134. Applies to Grumman American Aviation Corporation Model G-1159 airplanes, all serial numbers certificated in all categories. COMPLIANCE: Compliance is required as indicated. To prevent possible main landing gear failures, accomplish the following: (A) Inspect the main landing gear prior to the next flight after the effective date of this A.D. to determine if part number 1159SC-L202-11 or 1159SC-L202-13 side brace/actuating cylinders are installed. (B) Within the next ten landing gear operating cycles after the effective date of this A.D., replace all P/N 1159SC-L202-13 actuators with modified units identified as 1159SC-L202- 13A in accordance with Grumman American Aviation Corporation Mandatory Customer Bulletin #261 dated January 27, 1978. (C) Within the next 100 landing gear operating cycles after the effective date of this A.D., inspect all P/N 1159SC-L202-11 actuators in accordance with Grumman American Mandatory Customer Bulletin #261 dated January 27, 1978, and if found defective, replace with modified units identified as 1159SC-L202-11A or -13A. (D) Remove from the aircraft any 1159SC-L202-11A or 1159SC-L202-13A actuator upon accumulating more than 500 actuator cycles and replace with an allowable actuator having less than 500 cycles. (E) An alternate method of compliance with paragraphs (B), (C), or (D) of this A.D. may be used if approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment becomes effective February 3, 1978.
2003-24-12R1: The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. That AD currently requires a one-time visual inspection of the gearbox pressure tube and No. 4 bearing front pressure manifold and the attaching clamp assemblies for correct positioning and for wear and damage, and replacement if necessary. This ad requires the same actions. This AD results from the need to correct errors in depicted clamping to ensure that AD compliance can be achieved, and to relax the level of maintenance required, as an optional method, when inspecting the affected tubing for dents. We are issuing this AD to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds.
94-22-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections of the strut skin in the area of the precooler exhaust vent for cracks on the inboard and outboard struts, and repair, if necessary. This amendment requires inspections of an expanded area for certain airplanes, and inspections of airplanes on which a skin doubler has been installed as terminating action for the existing AD. This amendment is prompted by reports of strut skin fatigue cracks and heat damage found aft of the edges of skin doublers installed on certain Model 747 series airplanes. The actions specified by this AD are intended to prevent separation of an engine due to overheating and subsequent cracking of the engine strut.
67-21-01: 67-21-01 HUGHES: Amdt. No. 39-440, Part 39, Federal Register June 28, 1967, Applies to Hughes Model 269 Series Helicopters. Compliance required within the next 25 hours' time in service following the effective date of this AD unless already accomplished. To prevent concentration of carbon monoxide gas in the cabin in excess of the amounts allowable under applicable airworthiness rules, accomplish the following: Install air scoop, restrict positioning of the upper and lower air vents on the left and right hand door panels to face forward and upward, and seal cabin in accordance with Hughes Service Information Notice No. N-33 dated May 12, 1967, or later approved revision or by a method approved by the Aircraft Engineering Division, FAA Western Region, Los Angeles, California. This amendment effective July 3, 1967.
2020-25-08: The FAA is adopting a new airworthiness directive (AD) for certain Yabora Industria Aeronautica S.A. Model ERJ 170 airplanes and Model ERJ 190-100 STD, -100 LR, -100 ECJ, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of installation of inverted poles of the horizontal stabilizer pitch trim switches on the control yokes, which causes opposite commands for the horizontal stabilizer. This AD requires installing supports for the horizontal stabilizer control yoke pitch trim switches and re-identifying the control yokes, as specified in two Agencia Nacional de Aviacao Civil (ANAC) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.