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87-16-01: 87-16-01 LOCKHEED-GEORGIA COMPANY and ISRAEL AIRCRAFT INDUSTRIES: Amendment 39-5683. Applies to Lockheed JetStar Model 1329 and Model 1329-25 series airplanes, equipped with AiResearch Aviation Company Model 30-92 APU in accordance with STC SA1043WE or STC SA3297WE; and to Israel Aircraft Aero Commander Model 1121 series airplanes, equipped with the AiResearch Aviation Company Model 30-92 APU in accordance with STC SA1356WE; certificated in any category. Compliance required as indicated, unless previously accomplished. To minimize the potential for fuel fumes entering the cockpit and passenger compartment, accomplish the following: A. Within the next 600 hours time-in-service or 12 months after the effective date of this AD, whichever occurs earlier, install fuel line shrouds and associated drains in accordance with the accomplishment instructions of AiResearch Aviation Company Service Bulletin No. 11.39, Revision A, dated November 20, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Lockheed-Georgia Company, 86 South Cobb Drive, JetStar Customer Support, Dept. 64-26, Zone 668, Marietta, Georgia 30063; or AiResearch Aviation Company, Customer Support Department, 6201 West Imperial Highway, Los Angeles, California 90045. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at4344 Donald Douglas Drive, Long Beach, California. This Amendment, 39-5683, becomes effective August 26, 1987.
94-12-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires repetitive inspections, tests, adjustments, and functional checks of the thrust reverser system and of selected engine wiring. This amendment adds a requirement for installation of a terminating modification, repetitive operational checks of that installation, and repair of any discrepancy found. This amendment is prompted by the identification of a modification that ensures that the level of safety inherent in the original type design of the thrust reverser system is further enhanced. The actions specified by this AD are intended to prevent deployment of a thrust reverser in flight and subsequent reduced controllability of the airplane.
2007-25-20: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10- 40F airplanes; and Model MD-11 and MD-11F airplanes. This AD requires, for certain airplanes, modifying the thrust reverser command wiring of the number 2 engine. For certain other airplanes, this AD requires modifying the thrust reverser system wiring from the flight compartment to engines 1, 2, and 3 thrust reversers. This AD also requires installing thrust reverser locking systems on certain airplanes. This AD results from a determination that the thrust reverser systems on these McDonnell Douglas airplanes do not adequately preclude unwanted deployment of a thrust reverser. We are issuing this AD to prevent an unwanted deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.
2001-12-06: This amendment adopts a new airworthiness directive (AD), that is applicable to GE CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines with No. 5 bearing rotating air seal part number (P/N) 4019T60G01 installed. This amendment requires initial and repetitive checks of the magnetic chip detector indicators, which are located in the lubrication system for the engine bearings, and installation of an improved No. 5 bearing rotating air seal as a terminating action. This amendment is prompted by a report of the failure of a No. 5 that led to a fire in the cavity of the low pressure turbine (LPT), overtemperature of the LPT turbine disk, and excessive turbine disk growth. The actions specified by this AD are intended to prevent No.5 bearing rotating air seal failures and possible uncontained engine failures.
2001-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 55 series airplanes and Model 60 airplanes, that requires replacement of the brake valve adjustment screw with a new improved screw, and for certain airplanes, it would also require installation of a new brake valve lever stop. The actions specified by this AD are intended to prevent bottoming of the valve components before contact of the brake valve lever with the stop, which could result in loss of all hydraulic fluid and consequent loss of normal braking. This action is intended to address the identified unsafe condition.
2001-12-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-300 series airplanes, that requires a one-time general visual inspection to find chafing and determine adequate clearance of certain wire bundles in the ceiling panel near the main passenger door, and corrective actions. The actions specified by this AD are intended to prevent damage to the wires in the bundles due to contact between the bundles and the adjacent ceiling support bracket. Such damage could result in electrical arcing, smoke, or fire in the cabin, and failure of certain systems essential to safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
2007-26-01: We are adopting a new airworthiness directive (AD) for certain Thrush Aircraft, Inc. (Thrush) Model S2R series airplanes. This AD requires you to do repetitive visual inspections of the vertical and horizontal stabilizer attach fitting, attach fitting bolts, and the vertical fin aft spar for cracks or corrosion. This AD also requires immediate replacement of the vertical and horizontal stabilizer attach fittings and attach fitting bolts if cracked or corroded parts are found, and the inspection of the vertical fin aft spar with repair or replacement if cracks or corrosion are found. This AD requires the eventual replacement of the vertical and horizontal stabilizer attach fittings and attach fitting bolts if no corrosion or cracks are found as terminating action for the repetitive inspections. This AD results from reports of cracks in the empennage of Thrush S2R series airplanes. We are issuing this AD to detect and correct these cracks, which could cause the vertical stabilizer to lose structural integrity. This failure could lead to loss of control.
94-12-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-400 series airplanes. This action requires revising the Airplane Flight Manual to include procedures that will enable the flight crew to identify fuel system leaks and to take appropriate action to prevent further fuel loss. This amendment is prompted by reports that flight crew procedures related to fuel system leaks are not defined adequately in the FAA-approved AFM for these airplanes. The actions specified in this AD are intended to ensure that the flight crew is advised of the potential hazard related to fuel exhaustion due to undetected leakage, and the procedures necessary to address it.
2001-12-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, 747-200, 747-300, and 747SR series airplanes powered by General Electric CF6-45/50 and Pratt & Whitney JT9D-70 series engines. This action requires a detailed visual inspection of the outboard diagonal brace for heat damage and cracking; and follow-on repetitive inspections or corrective actions, if necessary. This action also provides an optional terminating action for the requirements of this AD. This action is necessary to detect and correct heat damage to the diagonal brace, which could cause cracking or fracture of the diagonal brace, and possible loss of the diagonal brace load path and consequent separation of the strut and engine from the airplane.
2020-02-20: The FAA is superseding Airworthiness Directive (AD) 2014-24- 07, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014- 24-07 required repetitive rototest inspections for cracking; corrective actions if necessary; and modification of the torsion box, which terminates the repetitive inspections. This AD continues to require the actions in AD 2014-24-07, with certain revised compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of a crack found in the side box beam flange of the fuselage at the frame (FR) 43 level during a fatigue test campaign. The FAA is issuing this AD to address the unsafe condition on these products.