Results
2023-03-14: The FAA is adopting a new airworthiness directive (AD) for all Schempp-Hirth Flugzeugbau GmbH Model Duo Discus and Duo Discus T gliders. This AD was prompted by 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 identifies the unsafe condition as the airbrake becoming blocked or jammed in an extended position during high airspeed due to an incorrect adjustment on the airbrake system. This AD requires repetitively inspecting the airbrake system and taking corrective action as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-02-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Eagle Aircraft Pty. Ltd. (Eagle) Model 150B airplanes. This AD requires you to modify the attachment of the port and starboard throttle arms, and the starboard bushing of the throttle torque tube. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified by this AD are intended to prevent failure of the throttle control assembly caused by rivets of the wrong size. Such failure could lead to reduced control of the airplane.
85-01-51: 85-01-51 EMBRAER: Amendment 39-5004. Applies to Models EMB-110P1 and EMB-110P2 (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 18 hours time-in-service after the effective date of this AD unless either previously accomplished within the past 50 hours time-in-service or modified per paragraphs d) and e) of AD 83-14-09. To preclude possible structural failure of the empennage assembly, accomplish the following: (1) Remove elevator preload springs from cross brace in empennage. (2) Remove the cross brace in the empennage that contains the elevator preload springs (rivets will have to be drilled out). (3) Gain access to the affected area through the inspection panel forward of bulkhead 33, releasing the elevator and rudder control cables if necessary for good access. (4) Position a person in the empennage and inspect for loose, cocked or sheared rivets and signs of fretting in the areas indicated on Figure 2, Page 17 of EMBRAER Service Bulletin No. 110-53-019, Change 2, dated April 13, 1984, using mirror, light, and .010-inch feeler gauge. Attempt to insert feeler gauge between machined "U" channel and reinforcement ribs to determine if gap exists. (5) The person stationed in the empennage should place his finger up against the machined "U" channel resting on reinforcement ribs left and right sides (P/N 4A-1419-07 L/H, P/N 4A-1419-08, P/N 4A-1419-05 L/H, and P/N 4A-1419-06) (see above service bulletin) while the horizontal stabilizer is deflected as indicated in (6) below. (6) Position a person at a horizontal stabilizer tip and attempt to deflect the stabilizer tip "up and down approximately 3 inches, but no more than 3 inches. The person stationed inside the tail should try to detect any relative movement between structural members. Any movement requires removing all rivets attaching machined "U" channel and replacing them as specified in AD 83-14-09. (7) Prior to further flight, correct any discrepancies found, reassemble and inspect assembly per AD 83-14-09. (8) Report completion of inspection and any unsatisfactory conditions within 24 hours to the FAA, Airframe Branch, Atlanta Aircraft Certification Office; Telephone (404) 763-7407. Include in such reports the type and location of discrepancies, specifically identifying the discrepancy, location, material or component. (9) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (10) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. This amendment becomes effective on February 26, 1985, to all persons except"those to whom it has already been made effective by telegram from the FAA dated January 10, 1985, and is identified as AD T85-01-51.
2017-20-14: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by a determination that supplemental inspections are required for timely detection of fatigue cracking for certain structural significant items (SSIs). This AD requires revising the maintenance or inspection program, as applicable, to add supplemental inspections. This AD also requires inspections to detect cracks in each SSI, and repair of any cracked structure. We are issuing this AD to address the unsafe condition on these products.
2002-01-31: This amendment supersedes an existing airworthiness directive (AD) that applies to Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, UH-1P, and Southwest Florida Aviation Model SW204, SW204HP, SW205, and SW205A-1 helicopters, manufactured by Bell Helicopter Textron, Inc. (BHTI) for the Armed Forces of the United States. That AD currently requires establishing retirement lives for certain main rotor masts, creating a component history card or equivalent record, and identifying and replacing any unairworthy masts. That AD also contains certain requirements regarding the hub spring, conducting inspections based on the retirement index number (RIN), and sending information to the FAA. This AD contains the same requirements but would establish a retirement life for the main rotor trunnion (trunnion) based on monitoring the number of torque events and flight hours rather than flight hours only as currently required. This AD also adds a note clarifying that the mast serial number (S/N) is defined by 5 or fewer digits plus various prefixes. This amendment is prompted by the determination that monitoring the number of torque events and flight hours for the trunnion is more accurate than by monitoring flight hours only to establish a retirement life. The actions specified by this AD are intended to prevent failure of a mast or trunnion, separation of the main rotor system, and subsequent loss of control of the helicopter.
2002-01-26: This amendment adopts a new airworthiness directive (AD), applicable to all Israel Aircraft Industries, Ltd., Model 1124 and 1124A, and certain Model 1125 Westwind Astra series airplanes, that requires a one-time inspection of the attachment bolts installed on the engine inlet cowl and aft nacelle attachment flanges to verify correct part numbers of the bolts, and replacement of any discrepant/incorrect bolt with a correct attachment bolt. The actions specified by this AD are intended to prevent failure of attachment bolts due to fatigue, which could result in separation of the engine inlet cowl and aft nacelle, and consequent damage to the horizontal or vertical stabilizer. This action is intended to address the identified unsafe condition.
68-12-03: 68-12-03 PRATT & WHITNEY: Amendment 39-608. Applies to all Model JT4A Series Turbojet Engines. Compliance required as indicated unless previously accomplished.: To preclude penetration of the diffuser case in the event of a high compressor rotor blade failure, accomplish the following: Within the next 11,000 hours' time in service after the effective date of this AD, rework all P/N's 361176, 397231, 419006, 406242, 429614, 447328, and 450862 diffuser case assemblies in accordance with Pratt & Whitney Aircraft Turbojet Engine Service Bulletin No. 1033 dated September 8, 1965, and FAA-approved revisions or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment becomes effective June 12, 1968.
2017-20-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A319 series airplanes, Model A320-211, -212, -214, -231, - 232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a runway excursion due to an unexpected thrust increase leading to an unstable approach performed using the current flight management and guidance computer (FMGC) standard. This AD requires identification of potentially affected FMGCs, replacement of any affected FMGC, and applicable concurrent actions. We are issuing this AD to address the unsafe condition on these products.
2017-20-03: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a review showing that inadequate clearance may exist between certain electrical wiring and nearby structures. This AD requires an inspection of certain electrical wiring bundles and feeders, modifications, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-01-22: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires a one-time inspection of the installation of the bearing housings of the elevator torque shaft assembly, and corrective action if necessary. This action is necessary to prevent failure of the elevator torque shaft, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.