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88-05-03: 88-05-03 BRITISH AEROSPACE: Amendment 39-5859. Applies to Model HS 748 series airplanes, certificated in any category. Compliance required within 60 days after the effective date of this AD, unless already accomplished. To prevent reduced controllability of the airplane caused by interference between the spring strut rudder lock control and the lower rudder hinge box, accomplish the following: A. Inspect the spring strut rudder lock control and reorient, if necessary, in accordance with British Aerospace HS-748 Service Bulletin 27/109, dated October 29, 1985. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, FAA, Northwest Mountain Region. C. Airplanes may be flown to a maintenance base for repairs or replacements in accordance with FAR 21.197 and 21.199. All persons affected by this airworthiness directive who have not already received copies of the appropriate service bulletin from the manufacturer may obtain copies upon request to British Aerospace PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may also be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way, Seattle, Washington. This amendment becomes effective April 6, 1988.
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.
78-13-03: 78-13-03 BURKHART GROB: Amendment 39-3244. Applies to Model G102 Astir CS gliders, Serial numbers, 1001 to 1234 and 1300 to 1315, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To reduce the possibility of elevator control failure due to possible loss of an elevator control pivot bolt, modify the elevator control assembly by installing a mechanical stop to the elevator control pivot (bearing) bolt, part no. 4205.06, in accordance with Burkhart Grob Technical Information TM102-4 dated August 16, 1976, or an equivalent, approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. This amendment becomes effective July 5, 1978.
2017-19-05: We are adopting a new airworthiness directive (AD) for certain Siemens S.A.S. smoke detectors installed on various transport category airplanes. This AD requires inspection and replacement of the affected smoke detectors. This AD was prompted by a report that the affected smoke detectors failed an acceptance test. We are issuing this AD to correct the unsafe condition on these products.
2017-20-05: We are superseding Airworthiness Directive (AD) 2011-01-15, which applied to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2011-01-15 required repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at certain stringers, and repair if necessary. This AD adds repetitive inspections for cracking in additional areas, and repair if necessary; removes airplanes from the applicability; adds an optional skin panel replacement, which terminates all inspections; adds an optional preventive modification, which terminates certain inspections; and reduces the compliance time for certain inspections. This AD was prompted by reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. We are issuing this AD to address the unsafe condition on these products.
2017-20-08: We are superseding Airworthiness Directive (AD) 2009-17-01, which applied to certain Gulfstream Model G-IV, GIV-X, GV-SP airplanes and Model GV airplanes. AD 2009-17-01 required an inspection for sealant applied to the exterior of the auxiliary power unit (APU) enclosure (firewall), and a revision of the airplane flight manual (AFM), as applicable. This AD requires revising the AFM and revising the applicability to include additional airplanes. This AD was prompted by a report indicating that the type design sealant applied to the APU enclosure failed certain tests. We are issuing this AD to address the unsafe condition on these products.
2002-01-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Type R334/4-82-F/13 with propeller hub assemblies, part number (P/N) 660709201. This action requires a one-time ultrasonic inspection of the propeller hub for cracks. This amendment is prompted by a report of an in-flight loss of a propeller. The actions specified in this AD are intended to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.
78-17-01: 78-17-01 MOONEY AIRCRAFT CORPORATION: Amendment 39-3279. Applies to Model M20C, Serial Number 20-1186 through 20-1258, M20F, Serial Number 22-1306 through 22-1486, and M20J, Serial Number 24-0001 through 24-0454 airplanes, with Pacific Communications, Inc., Aircraft Products Division, Model Alert 50, Part No. 01070-5 emergency locator transmitter system installed. Compliance is required as indicated. To assure that the emergency locator transmitter will radiate a proper signal when activated during emergency conditions, accomplish the following: 1. Rework the aircraft skin in accordance with Mooney Aircraft Corporation Service Bulletin M20-213 dated July 21, 1978, within ten hours operating time but no later than 30 days from the effective date of this AD. 2. Upon completion of the Mooney Service Bulletin No. 20-213 instructions, measure the resistance between the antenna and the aircraft skin using an appropriate meter and assure that a reading of 9,000 to 13,000 ohms isobtained. Determine that the ELT transmits properly by testing it in accordance with FAA Advisory Circular No's. 91-44 or 20-81. 3. The manufacturer's specifications and procedures identified and described in this directive are 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 Mooney Aircraft Corporation, P. O. Box 72, Kerrville, Texas 78028. These documents may also be examined at Southwest Regional Office, Regional Counsel, Building 3B, Room 100, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective August 21, 1978.
2017-19-25: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes; and Model C-295 airplanes. This AD was prompted by reports of leakage of motorized cross-feed fuel valves. This AD requires repetitive inspections and operational checks of the affected fuel valves, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-19-23: We are superseding Airworthiness Directive (AD) 2015-15-10, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015-15-10 required repetitive inspections of the trimmable horizontal stabilizer actuator (THSA) for damage, and replacement if necessary; and replacement of the THSA after reaching a certain life limit. This AD requires repetitive detailed inspections of certain THSAs, and related investigative and corrective actions if necessary. This AD was prompted by the establishment of an additional life limit for the THSA, based on flight cycles. In addition, the THSA manufacturer has issued service information which, when accomplished, increases the life limit of the THSA. We are issuing this AD to address the unsafe condition on these products.
2004-08-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. This AD requires various modifications and repetitive inspections of the throttle control system, and follow-on actions if necessary. This action is necessary to prevent hard points in the throttle control system that could lead to jamming of the throttle control cable. Such jamming could result in an asymmetric thrust condition and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-06-32: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, and L1 helicopters. This action requires greasing and inspecting main rotor blade horn eye bolts (eye bolts), and replacing certain eye bolt bearings (bearings) with airworthy bearings. This amendment is prompted by one report of abnormally high amplitude inflight vibrations due to failure of a bearing. The actions specified in this AD are intended to prevent failure of a bearing, due to premature wear caused by an improper axial pre-load, which could result in loss of main rotor blade pitch control and subsequent loss of control of the helicopter.
2023-03-11: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of smoke in the flightdeck and loss of the right- hand (RH) primary display unit (PDU) and the secondary flight display (SFD). This AD requires inspecting the two electrical power feeders for damage (deterioration), measuring the clearance between the two electrical power feeders and the forward lavatory bulkhead, and applicable corrective actions, 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.
76-21-05: 76-21-05 BELL: Amendment 39-2749. Applies to Bell Model 47K helicopters certificated in all categories. Compliance required as indicated. A report has been received of fatigue cracking of the tubular spar of the synchronized elevator at the rollpin hole. To preclude possible separation of the elevator from the helicopter, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD: (1) Remove the elevators from the tail boom in accordance with the Bell Maintenance Manual. (2) Clean the area around the Rollpin hole and remove any zinc chromate putty from any plugged hole in the tubular spar at B.L. 7.0 for both right and left elevators. (3) Inspect for cracks in the tubular spar of both elevators at the Rollpin hole at B.L. 7.0 using a 5-power or higher magnifying glass. (4) Inspect the inboard rib for cracks using a 5-power or higher magnifying glass. (b) If cracks are found in the tubular spar, modify the elevator with Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, "Improved Design Synchronized Elevator," or FAA engineering approved equivalent prior to further flight. (c) If no cracks are found in the tubular spar, install clevis pin in accordance with subparagraphs (1) through (4) below or in accordance with item 2 of Bell Helicopter Company Service Bulletin No. 135SB dated July 27, 1961, or later approved revision, and reinspect in accordance with subparagraph (5). (1) Position coupling assembly P/N 47-267-483-1 on elevators and line drill through Rollpin holes with a "D" (0.2460-inch diameter) drill. Remove sharp edges from holes. Install MS 20392-3-49 clevis pins, AN 960-4162 washers, and AN 381-3-6 cotter pins. A finger tight slip fit of the clevis pins is desired, approximately 0.0005 inch loose. (2) Reinstall the elevator on the helicopter, shim as required to prevent preload or end play at bearings. (3) Check clearance between skin and end of clevis pins. Trim skin, if necessary, to obtain clearance. (4) Rerig elevator in accordance with the Bell Maintenance Manual. (5) Reinspect in accordance with (a)(1) through (a)(3) within each succeeding 50 hours' time in service until Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, "Improved Design Synchronized Elevator," or FAA approved equivalent is installed. (d) If cracks are found in the inboard rib, repair the elevator as specified below, or modify with Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, or FAA engineering approved equivalent prior to further flight. (1) Remove the inboard rib by drilling out the rivets and remove the Bell P/N 47-267-404-7 shoulder from the rib by drilling out the rivets. (2) Add a doubler of 0.032 thickness, or a new rib of 0.032 thickness, material aluminum alloy 2024-0, or a Bell rib P/N 47-267-453-7 (one required per elevator). (3) Rivet Bell P/N 47-267-404-1 shoulder to the old rib and new doubler or to the newrib. Use the rivet pattern in the shoulder with AN 470-AD3 or -4 rivets. (4) Install the rib assembly, using the rivet pattern in the elevator skin with MS 20600 AD4 or -5 rivets. (e) If no cracks are found in the inboard rib: (1) Reinstall the elevator on the helicopter in accordance with Bell Maintenance Manual. (2) Reinspect rib for cracks in accordance with (a)(4) within each succeeding 50 hours' time in service until Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, "Improved Design Synchronized Elevator," or FAA engineering approved equivalent is installed. (f) Upon request of the operator, an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. The manufacturer's specifications and procedures identified and described in this directive are 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 Service Manager, Bell Helicopter Company, Box 482, Fort Worth, Texas 76101. These documents may also be examined at Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at Office of Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective November 26, 1976.
2023-03-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that certain fasteners attaching the fuselage skin to a certain stringer may be missing. This AD requires inspecting for missing fasteners and damage, including cracking, of the affected area, and repair or installation of fasteners if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-01-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action, if necessary. This action is necessary to prevent failure of the bearings in the link assembly joint, which could result in separation of the outboard flap and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.