Results
2003-26-09: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW4090-3, and PW4098 turbofan engines. That AD requires initial and repetitive visual and borescope inspections of the No. 3 bearing weep tube and turbine exhaust case (TEC), and removal of the high pressure turbine (HPT) assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found. This ad requires the same actions. This AD results from the finding of a significant reference error in one of the borescope inspection compliance paragraphs. We are issuing this AD to prevent thermal distressed HPT assembly hardware from remaining in service, which could result in a cracked HPT stage 1 disk or HPT stage 1-2 air seal and an uncontained engine failure.
95-12-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires a revision to the input wiring for the flap control unit (FCU). This amendment requires a new systems test for the wiring of the trailing edge flap, and also expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by a report indicating that a wiring error was not detected by the system test required by the existing AD. The actions specified by this AD are intended to prevent the possibility of an all-flaps-up landing due to the loss of control of all flap operations.
2003-26-06: The FAA adopts a new airworthiness directive (AD) for certain Anjou Aeronautique (ANJOU) (formerly TRW Repa S.A., formerly L'AIGLON) safety belts and restraint systems that are installed in aircraft. This AD requires you to inspect safety belts and restraint systems for defects and service life limits, and, if necessary, repair safety belts and restraint systems that have not reached service life limits; and replace safety belts and restraint systems that have reached service life limits. This AD is the result of reports of inadvertent unbuckling of the ANJOU seat belts and two safety recommendations to take AD action. We are issuing this AD to detect and correct defective safety belts and restraint systems, which could result in failure of the safety belts and restraint systems. This failure could lead to lack of occupant restraint during normal or crash loads.
76-12-09: 76-12-09 ROCKWELL INTERNATIONAL: Amendment 39-2645. Applies to Model NA-265-70 airplanes, serial numbers 370-1 through 370-9, and Model NA-265-80 airplanes, serial numbers 380-1 through 380-42 and 380-44. Compliance required as indicated, unless already accomplished. To prevent possible in flight flutter due to an improper static balance of the rudder, accomplish the following: (A) Immediately upon receipt of this AD, notify the flight crewmembers by the most practicable means, of the maximum operating limit speed: 250K/0.8M. (B) Within the next 10 hours' time in service after receipt of this AD, effect the following operating limitations and install the following placards and markings in clear view of the pilots: (1) Install a placard adjacent to each airspeed indicator that reads: "MAXIMUM OPERATING LIMIT SPEED: 250/K0.8M" (2) Mark the face of each airspeed indicator with a red radial line at 250 knots. (C) Within 60 days after receiptof this AD accomplish the following: (1) Remove the rudder from the airplane and measure the rudder's static unbalance about the hinge line using a balance measuring procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region, and (2) If the static unbalance measured exceeds the limits of 0 to 5 inch-lbs leading edge heavy, before further flight adjust the static balance to be within these limits by a modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. NOTE: Rockwell International intends to issue Sabreliner Service Bulletin No. 17 to provide the necessary instructions on rebalance. (D) The operating limitations, placards, and markings required by paragraph (B) may be removed after accomplishment of paragraph (C). (E) The airplane may be flown in accordance with FAR 21.197 to a base where the placards and markings required by paragraph (B) can be installed or the balance inspection and rebalance procedure of paragraph (C) can be accomplished, provided the operating limitations of paragraph (B) are not exceeded. This amendment is effective June 23, 1976 for all persons except those to whom it was made effective by airmail letter dated May 21, 1976, which contained this amendment.
2009-26-14: 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: * * * As a consequence of cracks [that were originally] detected on some CN-235 aircraft, in flap fittings P/N 35-15501-0101, -0102, -0201 and -0202, attaching the structure of the outer flaps to their rear supports and, in the adjacent structure, DGAC Spain issued AD Nr. 01/97[.] * * * Since AD 1/97 Rev.1 was published, similar cracks have been detected in flaps longerons. * * * * * * * * Fatigue cracking of the rear internal support fittings and longerons of the outer flap structure could result in failure of the outer flaps, and consequent reduced controllability of the airplane. We are issuing this AD to require actions to correctthe unsafe condition on these products.
2009-26-12: The FAA is superseding an existing airworthiness directive (AD) for Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, "Parallel Valve" reciprocating engines, with certain Engine Components, Inc. (ECi) cylinder assemblies, part number (P/N) AEL65102 series "Titan," installed. That AD currently requires initial and repetitive visual inspections and compression tests to detect cracks at the head-to-barrel interface, replacement of cylinder assemblies found cracked, and replacement of certain cylinder assemblies at new, reduced times-in-service. This AD requires the same actions, but for an expanded population of cylinder assemblies. This AD results from reports of 10 additional cylinder head separations since issuing AD 2008-19-05, on cylinder serial numbers not listed in that AD. We are issuing this AD to prevent loss of engine power due to cracks at the head-to-barrel interface and possible engine failure caused by separation of a cylinder head, which could result in loss of control of the aircraft.
96-12-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires installation of reinforcement plates under each hook latch fitting on the frame of each large cargo door. For some airplanes, this amendment requires inspections to detect cracking in the area around each hook latch fitting, and repair, if necessary. This amendment is prompted by the results of stress analyses and destructive tests which revealed that fatigue-related cracking may develop in the vicinity of the hook latch fittings on the frame of the large cargo doors. The actions specified by this AD are intended to prevent reduced structural integrity of the frames of the cargo door due to fatigue cracking, which may lead to the cargo door(s) opening while the airplane is in flight.
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.