Results
98-07-20: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, and L1 helicopters that have not been modified in accordance with Eurocopter France Modifications 332A07-41.569 and 332A07-66.150. This action requires revisions to the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit flight into meteorological conditions that may produce lightning for helicopters that are not equipped with lightning-resistant tail rotor blades. A terminating action is provided in the AD by the installation of tail rotor blades having a lightning-resistant system. This amendment is prompted by the forced ditching of a Model AS 332 helicopter after experiencing a lightning strike. The actions specified in this AD are intended to prevent damage to the tail rotor blades that could result in loss of a tail rotor blade and subsequent loss of control of the helicopter.
61-25-02: 61-25-02 CONVAIR: Amdt. 373 Part 507 Federal Register November 29, 1961. Applies to All Model 22 (880) and Model 22M (880M) Aircraft. Compliance with paragraphs (a) and (b) required within 4,000 hours' time in service after effective date of this directive. Compliance with paragraph (c) is required on effective date of this directive. An inflight engine pod explosion occurred on a Model 22 airplane causing the loss of a nose cowl and portions of the side cowl panel doors. This incident has been attributed to an open starter bleed air supply valve causing continued rotation and subsequent overheating and disintegration of the air turbine starter. The following modifications and procedures are required to prevent the recurrence of this incident: (a) Provide a FAA approved cockpit indicating means by which it can be determined that each engine starter is de-energized. Approval of this item shall be processed through the FAA, Flight Standards Service, Engineeringand Manufacturing Branch, Western Region. (b) Concurrently with the incorporation of the modification described in paragraph (a), the Normal Procedures Section of the Models 22 and 22M FAA Approved Airplane Flight Manual, under that portion entitled "Engine Starting Procedure - Ground", shall be revised to include a provision that the flight crew determine that the cockpit indicating means required by paragraph (a) indicates that the starter is de-energized after each engine start. (c) Pending completion of the modifications required by paragraph (a) of this AD either install placard in the flight compartment on the pilot's start switch panel to read as follows: "Engine ground starts shall be made according to Convair Alert Service Bulletin No. 80-3", or revise the Normal Procedures Section of the Models 22 and 22M FAA Approved Airplane Flight Manual, under that portion entitled "Engine Starting Procedure - Ground", to provide for engine ground starts to be made according toConvair Alert Service Bulletin No. 80-3 or FAA Approved equivalent. This directive effective December 29, 1961.
2005-19-03: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAe Systems (Operations) Limited Model ATP airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This new AD requires a revision to the ALS of the Instructions for Continued Airworthiness to incorporate new inspections to detect fatigue cracking of certain significant structural items (SSIs) and to revise life limits for certain equipment and various components. This AD is prompted by a determination that existing inspection techniques are not adequate for certain SSIs and by the revision of certain life limits. We are issuing this AD to detect and correct fatigue cracking of certain structural elements, which could adversely affect the structural integrity of these airplanes.
2010-24-06: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. * * * * * Weare issuing this AD to require actions to correct the unsafe condition on these products.
98-07-08: This amendment adopts a new airworthiness directive (AD) that is applicable to all IAI, Ltd., Model 1125 Westwind Astra and Astra SPX series airplanes. This action requires disabling of the baggage compartment electrical heating blankets. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent overheating of the electrical heating blankets, and consequent increased risk of fire in the baggage compartment.
98-07-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the main landing gear (MLG) trunnion fittings with reinforced trunnion fittings. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent collapse of the MLG due to fatigue cracking of the MLG trunnion fittings.
79-22-01: 79-22-01 BELLANCA: Amendment 39-3596. Compliance is required within the next 30 days or 10 hours of aircraft time in service, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent exhaust system cracking, accomplish the following on Bellanca Model 7ECA (S/N 985-74 thru 1319-79), 8KCAB (S/N 120-74 thru 550-79 equipped with Lycoming AEIO-360 series engine), and 8GCBC(S/N 1-74 thru 323-79) aircraft: 1. Remove the upper and lower engine cowling. 2. Inspect exhaust system with particular attention to the welded area between the riser tube and the exhaust flange, for cracks, fractures or evidence of exhaust leakage. Remove the heater shroud and inspect the muffler body for cracks, fractures or evidence of exhaust leakage. If any exhaust system component is cracked or otherwise damaged, remove the exhaust system and repair/replace damaged parts in accordance with FAA Advisory Circular 43.13-1A. 3. Loosen exhaust port studnuts several turns; check bead clamps for tightness such that the clamps cannot rotate on the exhaust system with hand pressure. The riser flanges (1) must have equal spacing to the exhaust port pad at both studs (a small amount of flange bow is acceptable), (2) must be free to move up and down on the exhaust port studs without binding and (3) must all contact the exhaust port pads together. 4. If any of the alignment checks are unsatisfactory, determine the cause for the misalignment and repair or replace the part as required. 5. Assemble exhaust system and install on engine with loose exhaust port stud nuts and bead clamp bolts. Torque exhaust port stud nuts to the correct value. Tighten bead clamp bolts until clamps secure risers to exhaust system but allow clamps to rotate with hand pressure; the bead clamps should not be rigidly clamped to the tubes but should be able to rotate on the tubes with moderate hand pressure on the clamp assembly. NOTE: Torque all exhaust port stud nuts evenly and tighten bead clamp bolts evenly to insure uniform loads within the exhaust system parts; torquing bolts individually can cause very large stresses. 6. Inspect exhaust system for proper clearance between ducts, wiring, controls, etc. before reinstallation of the cowling. Install lower cowling and inspect for proper clearance between exhaust outlet and cowl. 7. Reinstall the lower and upper engine cowling. Bellanca Service Letter Number C-138 covers this same subject. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Engine.. This amendment becomes effective October 29, 1979.
98-06-25: This amendment adopts a new airworthiness directive (AD) that applies to Fairchild Aircraft Inc. (Fairchild) Models SA226-AT, SA226-TC, SA227-AC, and SA227-AT airplanes. This action would require inspecting the cargo door lower belt frames at the cargo latch receptacles for cracks in the belt frames, repairing any cracks, and reinforcing the cargo door lower belt frames by installing doublers. The AD is the result of a decompression incident during flight caused by fatigue at the bottom of the cargo door on a Fairchild Model SA226-TC. The actions specified by this AD are intended to prevent the failure of the cargo door in flight, which could cause decompression injuries to passengers and substantial structural damage to the airplane.
2017-10-22: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the web lap splices in the aft pressure bulkhead are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the web lap splices in the aft pressure bulkhead for cracking of the fastener holes, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-09-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Helicopters (Airbus Helicopters) Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters. This AD requires installing rivets to the air inlet cover rings (rings). This AD was prompted by reports of rings detaching. The actions of this AD are intended to prevent the unsafe condition on these products.