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81-22-02: 81-22-02 GENERAL DYNAMICS: Amendment 39-4236. Applies to Model 340, 440 and military models eligible for civil use under Type Certificate 6A6, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent potential loss of elevator control resulting from loosening and ultimate shearing of the elevator flange to outer torque tube aluminum (rivet) fasteners, accomplish the following: (a) Within 250 hours' additional time in service after the effective date of this AD, unless previously accomplished within 450 hours' time in service prior to the effective date of this AD, and at intervals not to exceed 700 hours' time in service thereafter, conduct a visual inspection of both left and right hand elevator outer torque tube assembly P/N 340-3540304 attachment to flange P/N 240-3540320 for evidence of loose or sheared rivets in accordance with the accomplishment instructions of paragraph two (2) of General Dynamics Convair Division Service Bulletin 640(340D)27-6 dated February 23, 1981 (hereinafter referred to as SB 640(340D)27-6). If any loose or sheared rivets in the elevator torque tube to flange attachment are found, replace all rivets with interference fitting steel fasteners in accordance with paragraph two (2) of SB 640(340D)27-6 prior to return of aircraft to service. (b) The inspections required by this AD may be terminated when all 12 torque tube to flange attachment aluminum rivets are replaced by interference fitting steel fasteners with a minimum tensile strength of 160,000 psi in accordance with paragraph two (2) of SB 640(340D)27-6. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (d) Alternative inspections, modifications or other actions which provide an equivalent level ofsafety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western-Pacific Region. (e) Reports of the discrepancies found are requested. The reports should cite: Airplane "N" number and serial number, nature of defect and part identification, total airplane operating hours, time since last inspection and AD compliance paragraph. Forward reports to Chief, Engineering and Manufacturing Branch, FAA Western- Pacific Region by mail within 10 days of discovery. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to General Dynamics, Attn: Mr. Larry Hayes, Manager, Product Support, Convair Division, P.O. Box80877, San Diego, California 92138. These documents may also be examined at FAA Western-Pacific Region Office, Office of the Regional Counsel, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 90261, and at FAA Headquarters, Rules Docket in Room 916, 800 Independence Avenue, S.W., Washington, D.C. 20591. This amendment becomes effective October 29, 1981.
2000-09-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F, and -40 series airplanes, and KC-10A (military) airplanes, that requires a one-time general visual inspection of circuit breakers to determine the manufacturer of the circuit breakers, and corrective action, if necessary. This amendment is prompted by incidents of smoke and electrical odor in the flight compartment and cabin area as a result of failure of circuit breakers. The actions specified by this AD are intended to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin.
2015-08-05: We are superseding Airworthiness Directive (AD) 2013-26-05 for all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200 airplanes; and Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. AD 2013-26-05 required repetitive weighing of fire extinguisher bottles having a certain part number, and eventual replacement of those bottles to terminate the repetitive weighing. This new AD continues to require repetitive weighing of fire extinguisher bottles having a certain part number, and eventual replacement of those bottles to terminate the repetitive weighing. This AD was prompted by our determination that certain text in the method of compliance language specified in AD 2013- 26-05 incorrectly refers to Airbus, instead of ``Dassault Aviation.'' We are issuing this AD to detect and correct a dormant failure in the fire suppression system, which could result in the inability to put out a fire in an engine, auxiliary power unit (APU), or rear compartment.
2000-09-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, 747SP, and 747SR series airplanes, that requires one-time detailed visual and eddy current inspections to detect cracking of the nose cowl mounting flange; rework of the nose cowl mounting flange; eddy current inspection to detect cracking of the reworked nose cowl mounting flange; and corrective action, if necessary. This amendment is prompted by reports of the nose cowl separating from the engine and departing the airplane following severe engine vibration. The actions specified by this AD are intended to prevent separation of the nose cowl from the engine, which could cause collateral damage to the airplane, and, possibly, reduced controllability of the airplane.
57-19-02: 57-19-02 SIKORSKY: Applies to all Model S-58 Helicopters. Compliance required as soon as possible but not later than October 30, 1957. To avoid the possibility of slippage in S-58 hydromechanical clutch due to adverse tolerance conditions replace S1635-91046-1 rollers with S1635-91065 rollers. The new rollers are three-thousandths (0.003) larger in diameter and may be identified by their dulite finish. (Sikorsky telegraphic message SST-1-281 dated September 12, 1957, covers the same subject.)
86-07-12: 86-07-12 PRATT & WHITNEY: Amendment 39-5267. Applies to PW JT9D-7R4G2 engines. Compliance is required as indicated unless already accomplished. To prevent possible engine support clevis failure, accomplish the following: (a) Remove P/N 5006482-01 engine support clevis on PW JT9D-7R4G2 at or before 3,000 cycles in accordance with PW SB JT9D-7R4-72-119, Revision 3, dated November 5, 1985, or FAA approved equivalent. (b) Replace any engine support clevis with greater than 3,000 cycles prior to next flight. NOTES: (1) For the purpose of this AD, the number of flight cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing and engine shutdown. (2) The hourly life limit is not affected by this AD. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. SB JT9D-7R4-72-119, Revision 3, dated November 5,1985, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. These documents also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on April 11, 1986.
2015-05-52: We are publishing a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A119, A109S, AW119 MKII, and AW109SP helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain tail rotor (T/R) pitch control links (pitch links) for freedom of movement, corrosion, excessive friction of the spherical bearings, and cracks. This AD is prompted by a report of an in-flight failure of a pitch link on an Agusta Model AW119 MKII helicopter. These actions are intended to prevent loss of T/ R pitch control and subsequent loss of control of the helicopter.
2015-07-03: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 402C and 414A airplanes. This AD requires repetitively inspecting the engine mount beams for cracks and contacting Cessna for FAA-approved corrective action if cracks are found. This AD also requires sending an inspection report to the FAA and to Cessna. This AD was prompted by reports of cracks found across the engine mount beams. We are issuing this AD to correct the unsafe condition on these products.
97-26-13: This amendment adopts a new airworthiness directive (AD) that applies to all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Models EMB-110P1 and EMB-110P2 airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent increased propeller drag beyond the certificated limits caused by the power levers being positioned below the flight idle stop while the airplane is in flight, which could result in loss of airplane control or engine overspeed with consequent loss of engine power.
86-07-08: 86-07-08 DEHAVILLAND: Amendment 39-5279. Applies to all Model DHC-7 series airplanes, certificated in any category. Compliance is required as indicated, unless already accomplished. To ensure observation of wet starts, detection of heat-damaged wing upper surface structure behind the engine, and protection against wet starts of the engine resulting in external combustion of fuel, accomplish the following: A. Except as provided in paragraph C., below, within the next 25 hours time-in- service after the effective date of this AD, insert a copy of this AD following Page 2-2-4B of the DHC-7 Airplane Flight Manual (AFM). After every aborted engine start in conjunction with either flight or other operations, follow AFM limitations and applicable procedures for starter cranking cycles, proper fuel draining, and dry motoring/clearing of the engine. An appropriately stationed observer must witness the subsequent starting attempt to determine whether external flames from the exhaust stacks and any burning of residual fuel on wing surfaces occurs. 1. If no external flame or external flame lasting for less than 5 seconds is observed, the airplane may be dispatched. 2. If external flame lasting 5 seconds or more is observed, a visual inspection of the affected wing area must be performed before further flight, in accordance with the Accomplishment Instructions, Paragraph 1, of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. a. If distortion or buckling of the skin is evident during the visual inspection, perform an internal conductivity survey of the affected area, and repair, as necessary, before further flight, in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing.b. If blistering or charring of the paint due to engine exhaust heat is evident during the visual inspection, before further flight, perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repairs, as necessary, in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. c. If no visible damage (i.e., no blistering or charring of paint or buckling of the wing skin) is apparent, within 100 flight hours perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repairs, as necessary, of the affected area in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. B. Except as provided in paragraph C., below, within the next 25 hours time-in- service after the effective date of this AD, visually inspect the upper wing skin behind each engine nacelle in accordance with the Accomplishment Instructions, Paragraph 1, of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. 1. If distortion or buckling of the skin is evident during the visual inspection, repairs must be effected before further flight. In order to determine the extent of repairs, perform an internal conductivity survey of the affected area in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. 2. If blistering or charring of the paint due to engine exhaust heat is evident during the visual inspection, before further flight, perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repair, as necessary, of the affected area in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. C. Accomplishment of DeHavilland Modification No. 7/2414 - "Wing - Upper Skin Structure - Special Inspection and Installation of Heat Shields," described in DeHavilland Service Bulletin No. 7-57-25 constitutes terminating action for the visual inspection and conductivity surveys required by paragraphs A. and B., above. When that modification has been accomplished, this AD may then be removed from the Airplane Flight Manual. 1. Prior to installation of Modification No. 7/2414, the following must be accomplished: a. Perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repairs, as necessary before further flight, of the upper wing skin behind each engine nacelle, in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. b. For airplanes, serial numbers 1 through 27, Modification Nos. 7/2377 and 7/2378 - "Fuel Tank Access Panel Replacement," described in DeHavilland Service Bulletin No. 7-57-17 (originally issued October 12, 1983), must be accomplished. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved bythe Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by 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 DeHavilland Aircraft of Canada, Ltd., Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment becomes effective April 22, 1986.