Results
2015-23-03: We are superseding Airworthiness Directive (AD) AD 2014-20-13 for certain Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 fatigue cracks on the fin forward pickup plates, which could cause it to fail. We are issuing this AD to require actions to address the unsafe condition on these products.
2002-14-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires an inspection to detect discrepancies of the wire bundles in the avionics compartment in the vicinity of the pedestal extension area of the First Officer's seat; and corrective actions, if necessary. This action is necessary to prevent chafing of wiring in the avionics compartment, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
2002-14-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires performing an inspection of the wiring of the Firex bottle discharge cartridge of the No. 2 engine at station Y=2163.00 bulkhead for chafing on adjacent structure and damaged wiring; repairing damaged wires; and repositioning wires, if necessary. This action is necessary to prevent chafing and possible damage to the wiring of the Firex bottle discharge cartridge of the No. 2 engine, which could result in improper distribution of the fire extinguishing agent within the No. 2 engine in the event of a fire. This action is intended to address the identified unsafe condition.
2015-20-11: We are adopting a new airworthiness directive (AD) for Schempp-Hirth Flugzeugbau GmbH Models Duo Discus and Duo Discus T powered sailplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 excessive load on the air brake system. We are issuing this AD to require actions to address the unsafe condition on these products.
92-14-08: 92-14-08 AEROSPATIALE: Amendment 39-8290. Docket No. 92-NM-118-AD. Supersedes AD 88-26-04, Amendment 39-6094. Applicability: Model ATR42-300 series airplanes; as listed in Aerospatiale Service Bulletins ATR42-76 0002, Revision 1, dated May 16, 1988; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a malfunction of the engine and propeller controls, accomplish the following: (a) Within 60 days after February 3, 1989 (the effective date of AD 88-26-04, Amendment 39-6094), modify the engine and propeller push-pull control cables on the left and right engines by adding a sealing sheath and protective sleeve, in accordance with Aerospatiale Service Bulletin ATR42-76-0002, Revision 1, dated May 16, 1988. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Aerospatiale Service Bulletin ATR42-76-0002, Revision 1, dated May 16, 1988, which incorporates the following list of effective pages: Page Number Revision Level Date 1-3 1 May 16, 1988 4 Original January 18, 1988 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may beobtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on July 1, 1992.
87-24-04: 87-24-04 AIRBUS INDUSTRIE: Amendment 39-5771. Applicable to Model A300 series airplanes, Serial Number 1 through Serial Number 107, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent decompression of the airplane, accomplish the following: A. Prior to the accumulation of 24,000 landings or 12 years since first revenue flight, whichever occurs first, modify the fuselage lap splices in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986. B. For airplanes with more than 9 years since first revenue flight as of the effective date of this AD: The modification required by paragraph A., above, may be deferred not to exceed 26,000 landings or 15 years since first revenue flight, whichever occurs first, provided the conditions specified in paragraph 1.B. of Airbus Service Bulletin A300-53-206, dated December 1, 1986, are met. C. For airplanes which have had lap splices repaired, as noted below, accomplish the following, as applicable: 1. For airplanes repaired with an external doubler in accordance with Chapter 53-10-20, Revision 46 of the Structural Repair Manual: Inspect the repaired area for corrosion when the modification required by paragraph A., above, is accomplished. If there is any sign of corrosion, remove the repair and modify prior to further flight, in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986. 2. For airplanes repaired by cutout in accordance with Chapter 53-10-20 of the Structural Repair Manual, figure 701, sheet 2, Revision dated July 1, 1986, or previous issues; or repaired by cutout in accordance with the Structural Repair Manual Chapter 53-10-20, figure 701, sheet 3, Revision dated January 30, 1985, or previous issues, and where cutout repair exceeds half a frame bay: Prior to the accumulation of 16,000 landings since the repairs were installed, modify the repaired lap splices in accordance with FAA-approved methods. 3. For airplanes repaired in accordance with Airbus Service Bulletin 53-215 or 53-216: No further action is necessary in the repaired areas. D. Modification of the longitudinal lap joints in Sections 13 and 14 in accordance with Airbus Service Bulletin A300-53-206, dated December 1, 1986, constitutes terminating action from the inspections required by AD 85-07-09 for the splices which have been modified. E. An alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. F. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective December 24, 1987.
77-08-05: 77-08-05 CESSNA: Amendment 39-2876. Applies to 337 Series (Serial Numbers 337-0002 thru 33701783), T337 Series (Serial Numbers 337-0001, 337-0526 thru 33701398 and P3370001 thru P3370271) and M337 Series (Serial Numbers 337-M0001 thru 337-M0467) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent single engine takeoffs, within the next 25 hours' time in service after the effective date of this AD, accomplish the following: A) Install a Cessna P/N 1400019-77 placard right of the tachometer instrument which reads as follows: "DO NOT INITIATE SINGLE ENGINE TAKEOFF" and operate the aircraft in accordance with this limitation. B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. C) Cessna Service Letter ME77-8, dated March 28, 1977, or later approved revisions pertains to the subject matter of this AD. This amendment becomes effective April 28, 1977.
77-19-02: 77-19-02\tGATES LEARJET: Amendment 39-3040 as amended by Amendment 39- 3265. Applies to all serial numbers of Models 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D and 25F airplanes certificated in all categories having a 36- inch wide (as opposed to a 24-inch wide) cabin door. \n\n\tCOMPLIANCE: Required as indicated in accordance with Compliance Table I set forth in this AD, unless already accomplished. \n\n\tTo assure proper locking of the cabin upper door when the inside handle is in the locked position and to prevent possible unwanted door openings that may occur if a pilot disregards the door warning system accomplish the following at the time intervals noted in Table I of this AD: \n\nTABLE I COMPLIANCE TIMES\n\n\n\n\n\n\n\n\n\n\n\nI N S P E C T I O N T I M E S\n\nAirplane Total Time\nIn Service\n(Hours)\n\nParagraph "A" Bolt\nInspection & Replacement\n\nParagraph "B" Locking\nMechanism Inspection \n\nInitial Inspection/\nReplacement\nInterval for Repetitive Inspections/ Replacement\nInitial Inspection\nInterval for \nRepetitive Inspections\n0 - 2,999\nPrior to or upon the accumulation of 3,075 hours' time in service\nEach 3,000 hours' time in service thereafter\nIn accordance with asterisk (*) paragraph below or upon accumulation of 6,075 hours' time in service, whichever occurs first \nIn accordance with asterisk (*) paragraph below or upon accumulation of each 6,000 hours' time in service after initial inspection\n3,000 - 5,999\nWithin 75 hours' time in service after the effective date of this AD\nEach 3,000 hours' time in service thereafter\nIn accordance with asterisk (*) paragraph below or upon accumulation of 6,075 hours' time in service, whichever occurs first\nIn accordance with asterisk (*) paragraph below or upon accumulation of each 6,000 hours' time in service after initial inspection\n6,000 - up\nWithin 75 hours' time in service after the effective date of this AD\nEach 3,000 hours' time in servicethereafter\nWithin 75 hours' time in service after the effective date of this AD\nIn accordance with asterisk (*) paragraph below or upon accumulation of each 6,000 hours' time in service after initial inspection\n* The door locking mechanism inspection must be accomplished any time the bolt inspection required by Paragraph "A" of this AD reveals a cracked, bent, broken or worn bolt. \n\n\tA.\tInspect and replace, at the time intervals noted in Table I above, the bolt or pin identified as (5) in Figure I of this AD in accordance with Gates Learjet Service Bulletin SB 23/24/25-280 dated July 15, 1977 or later approved revisions and as summarized below: \n\n\t\t1.\tRemove the bolt, or if applicable, pin from the upper door rod control assembly and visually inspect it for cracks, breaks, bends, or wear. If any of the aforementioned defects are found accomplish the door locking mechanism inspection required by Paragraph "B" of this AD prior to the next flight; and \n\n\t\t2.\tReplace the bolt orpin removed in Paragraph A.1. of this AD with a new Gates Learjet part number 2311490-8 bolt, or a new AN3-21 bolt modified in accordance with the above noted Service Bulletin, and secure using an AN960D10 Washer and either a new MS20365-1032 Nut or AN310-3 Nut and MS24665-132 Cotter Pin. \n\n\tB.\tInspect, at the time intervals noted in Table I above, the cabin door locking mechanism in accordance with Gates Learjet Service Bulletin SB 23/24/25-280 dated July 15, 1977 or later approved revisions, and as summarized below: \n\n\t\t1.\tDrill out rivets and remove cabin upper door inner panel. \n\n\t\t2.\tRemove and inspect door locking mechanism for wear and defects in accordance with Learjet Service Manual Inspection Requirements. The maximum allowable diameter (measured in any direction) of the hole in which the (5) bolt is installed is .201 inches. Replace any excessively worn or defective parts prior to the next flight. \n\n\n\n\t\t3.\tReinstall door locking mechanism and using rivets, reinstall the inner panel. \n\n\t\t4.\tCheck door locking mechanism for free movement with no binding thru entire operating travel. Correct any binding prior to the next flight. \n\n\t\t5.\tEnergize door warning system and check its operation for proper functioning. \n\n\tC.\tSubmit a written report on any cracked, broken, bent or worn (5) (See Figure I of this AD) bolts or pins discovered during inspections required by this AD to the FAA via a letter to FAA, Chief, Engineering and Manufacturing Branch (ACE-210), 601 E. 12th Street, Kansas City, Missouri 64106 or an FAA M or D report (FAA Form 8330-2). \n\n\tThe report must include airplane model, serial number, airplane total time-in-service, bolt or pin total time-in-service and statements describing the condition of the bolt and the hole including dimensions of the hole determined in accordance with Paragraph B.2. of this AD. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) \n\n\tD.\tThe actions made mandatory by Paragraphs A, B, and C of this AD are no longer required when Gates Learjet Door Modification Kit AMK 78-2 is installed. \n\n\tE.\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD can be accomplished. \n\n\tF.\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tAmendment 39-3040 became effective on September 26, 1977. \n\n\tThis amendment 39-3265 becomes effective July 20, 1978.
2015-22-07: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). This AD requires an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are issuing this AD to prevent loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin and potential loss of the airplane.
2025-01-06: The FAA is superseding Airworthiness Directive (AD) 2019-14- 13, which applies to all The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. AD 2019-14-13 required identifying the part number, and the serial number if applicable, of the Captain's and First Officer's seats, and performing applicable on-condition actions for affected seats. AD 2019-14-13 also required a one-time detailed inspection and repetitive checks of the horizontal movement system (HMS) of the Captain's and First Officer's seats, and applicable on- condition actions. AD 2019-14-13 also provided an optional terminating action for the repetitive actions for certain seats. This AD was prompted by reports of uncommanded fore and aft movement of the Captain's and First Officer's seats. This AD retains the actions in AD 2019-14-13 and adds an inspection of previously omitted part numbers. The FAA is issuing this AD to address the unsafe condition on these products.