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2020-06-01: The FAA is adopting a new airworthiness directive (AD) for all CFM International S.A. (CFM) LEAP-1B21, -1B23, -1B25, -1B27, -1B28, - 1B28B1, -1B28B2, -1B28B2C, -1B28B3, -1B28BBJ1, and -1B28BBJ2 model turbofan engines. This AD was prompted by reports of two new unsafe conditions and the need to supersede corrective actions for two previously addressed unsafe conditions. This AD supersedes AD 2018-25- 09 and AD 2019-12-01, which apply to the affected LEAP-1B model turbofan engines. This AD requires revising the Airworthiness Limitations Section (ALS) of the applicable CFM LEAP-1B Engine Shop Manual and the operator's approved continuous airworthiness maintenance program. The FAA is issuing this AD to address the unsafe conditions on these products.
78-26-06: 78-26-06 PIPER: Amendment 39-3378. Applies to Model PA-38-112, Serial Numbers 38-78A0001 thru 38-78A0652, 38-78A0653, 38-78A0655, 38-78A0656, 38-78A0658, 38- 78A0660, 38-78A0661, 38-78A0664 thru 38-78A0672, 38-78A0674, 38-78A0676, 38-78A0677, 38-78A0680 thru 38-78A0682, 38-78A0686, 38-78A0690, 38-78A0693, 38-78A0701, 38-78A0702, 38-78A0708, 38-78A0711, 38-78A0717, 38-78A0723, 38-78A0729, 38-78A0734 and 38-78A0749 certificated in all categories. To avoid possible hazards in flight associated with a crack in the vertical fin forward spar attachment plate accomplish the following within the next five hours in service unless previously accomplished. a. Remove the dorsal fin fairing P/N 77607-02 and inspect the forward bend radius of the vertical fin forward spar attachment plate P/N 77553-5 for cracks using a dye penetrant inspection method. b. If a cracked plate is found, replace with an undamaged part of the same part number before further flight, except a ferry flight to a place of repair may be authorized in accordance with FAR 21.197 with prior approval of the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin No. 628A refers to this same subject.) This amendment is effective December 26, 1978.
2008-03-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) * * * [which] required * * * [conducting] a design review against explosion risks. The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
78-25-03: 78-25-03 THE DEUTSCH COMPANY, METAL COMPONENTS DIVISION: Amendment 39-3363. Applies to P/N 94B0100004F0160 and 94F0100004F0166 hose assemblies marked with identification 4Q77 or 1Q78 which may be installed on various aircraft but which are known to be installed on Piper Models PA-23-250, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-31, PA-31-300, PA-31-325, PA-31-350, PA-31P, PA-31-TI, PA-31-T, PA-34-200T, and PA-44-180 aircraft. NOTE 1: Hose P/N and manufacturing date codes (e.g. 4Q77 and 1Q78) are shown on a metal tag attached to the hose assemblies. a) Deutsch P/N 94B0100004F0160 is Piper P/N 17766-27, TSO C-53a Type A. b) Deutsch Part No. 94F0100004F0166 is Piper P/N 63901-41, TSO C-53a Type C. Compliance required as indicated, unless already accomplished. To prevent an unsafe condition in the various aircraft systems in which these hoses may be installed, accomplish the following: A. Within the next ten hours time in service after the effective date of this (AD), inspect to determine if hose assembly P/N 94B0100004F0160 or 94F0100004F0166 with manufacturing date 4Q77 or 1Q78 is installed. B. If the hose assemblies as in A above are not installed no further action is required by this (AD). C. If the hose assemblies in A above are installed, prior to further flight, (1) Remove and replace hose assemblies. (2) Check system for contamination. Purge system if evidence of contamination is found. NOTE 2: Piper Service Bulletin No. 611 refers to purging procedures for Piper Models PA -28, -34, and -44. Piper Service Bulletin No. 629 refers to purging procedures for Piper Models PA-31 and PA-23. NOTE 3: The following is a list of Piper Model, Serial Nos. and hose application which are believed to have suspect hoses installed. Possible hose application is not limited to this list. Model Serial Number Application Qty. of hoses PA-23-250 Aztec F 27-7854007 thru 27-7954018 Pressure nose gear cylinder up and pressure anti-retract valve 2 PA-28R-180 Possible Retrofit NLG actuating cylinder 2 PA-28R-200 Possible Retrofit NLG actuating cylinder 2 PA-28R-201 78-37105 thru 78-37317 NLG actuating cylinder 2 PA-28R-201T 78-03154 thru 78-03372 NLG actuating cylinder 2 Manifold pressure at left hand rear of engine 1 PA-31 31-1 thru 31-7812122 and 31-5001 thru 31-7852166 Main landing gear actuating cylinders 2 PA-31-300 Possible Retrofit Main landing gear actuating cylinders 2 PA-31-325 Navaho C/H 31-7812016 thru 31-7912004 Main landing gear actuating cylinders 2 PA-31-350 & PA-31-P Possible Retrofit Main landing gear actuating cylinders 2 PA-31TI Cheyenne I 31T-7804001 thru 31T-7904006 Main landing gear actuating cylinders 2 PA-31T Cheyenne, Cheyenne II 31T-77200069 thru 31T-7920012 Main landing gear actuating cylinders 2 PA-34-200T 78-70100 thru 78-70474 Fuel drains 4 PA-44-180 79-95001thru 79-95127 Engine oil pressure line at filter 2 D. Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base for the accomplishment of the inspection required by paragraph A of this AD. E. Equivalent inspections and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. F. Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Engineering Division, FAA Western Region may adjust the compliance time for hose replacement. This amendment becomes effective January 15, 1979, for all persons except those to whom it was made effective by priority message dated October 27, 1978.
63-23-03: 63-23-03 VICKERS: Amdt. 641 Part 507 Federal Register November 9, 1963. Applies to All Viscount Model 810 Series Aircraft. Compliance required as indicated. Fatigue failures have been reported on flap beams in the areas shown in Figure 1 of Preliminary Technical Leaflet No. 107 (800/810 Series). To preclude further failures accomplish the following on Nos. 2 and 3 flap units: (a) Within 500 flights* after the effective date of this AD, on aircraft which have accumulated 10,000 or less flights, unless already accomplished within the past 1,000 flights, conduct dye penetrant or FAA approved equivalent inspection for cracks in accordance with PTL 107. If no cracks are found, reinspect at intervals not exceeding 1,500 flights until the aircraft accumulates between 10,000 and 11,000 flights during which time the aircraft must be reinspected. Thereafter, the aircraft must be reinspected at intervals not exceeding 600 flights until a total of not more than 12,000 flightsare accumulated, at which time either of the following or FAA approved equivalent must be incorporated. (1) Modification FG.1946, or (2) The repair/reinforcing scheme defined in the referenced PTL. (b) Within 100 flights after the effective date of this AD on aircraft which have attained over 10,000 flights, unless already accomplished within the past 500 flights, conduct the inspection of paragraph (a). If no cracks are found, reinspect at intervals not exceeding 600 flights until reinforcing scheme (a)(1) or (a)(2), or FAA approved equivalent, has been incorporated. Incorporate the reinforcing scheme within 2,000 flights after the effective date of this AD. (c) Cracked flap beams may be considered serviceable for a further 500 flights provided that the cracks are confined to one doubler plate each side of the beam only, and extend no further than the bolt hole, per Figure 1 of PTL 107, and provided that the area is reinspected in accordance with (a) within every100 flights to ensure that no crack propagation has occurred. Incorporate repair/reinforcing scheme paragraph (a)(1) or (a)(2), or FAA approved equivalent, as follows: (1) Within 10 flights from the time of crack detection for aircraft with unacceptable cracks, and within 10 flights for aircraft with cracks that are found to propagate in length. (2) On or before the completion of 500 flights from the time of crack detection for aircraft with acceptable cracks. (d) After incorporating the modification of (a)(1) or (a)(2), or FAA approved equivalent, the special inspection in this AD may be discontinued. (Vickers-Armstrongs PTL No. 107 (800/810 Series) and Modification FG. 1946 cover this subject.) This directive effective December 11, 1963. *This will require operators to maintain a record of flights to ascertain compliance with this AD. If past records are unavailable the number of flights prior to this AD may be estimated.
85-16-08: 85-16-08 SHORT BROTHERS LTD.: Amendment 39-5101. Applies to Model SD3-60 airplanes as listed in Short Brothers Ltd. Service Bulletin SD360-53-11, Revision 1, dated November 1984, certificated in any category. Compliance is required within twelve months after the effective date of this AD, unless previously accomplished. To prevent structural failure under ditching conditions, accomplish the following: A. Install Cherrymax rivets in the bottom section of fuselage frame 475 in accordance with Short Brothers Ltd. Service Bulletin SD360-53-11, Revision 1, dated November 1984. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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. This amendmentbecomes effective August 22, 1985.
99-19-40: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a detailed visual inspection to detect damage to the terminal lugs on the 12XC and 15XE connectors and the mounting lugs on the 15XE connector; and repair or replacement of the terminal lugs or the 15XE connector with new parts, if necessary. This amendment is prompted by the issuance of a mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct broken terminal and mounting lugs on the 15XE and 12XC connectors in the 101VU panel in the avionics compartment, which could result in loss of electrical power from the standby generator.
2020-04-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-941 airplanes. This AD was prompted by reports indicating premature aging of certain chemical oxygen generators. This AD requires repetitively removing the affected chemical oxygen generators and replacing them with serviceable parts, 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.
79-11-01: 79-11-01 SHORT BROTHERS LIMITED: Amendment 39-3476. Applies to Model SD3-30 airplanes, S/N's 3003 through 3017, certificated in all categories. Compliance is required prior to the accumulation of 6000 total landings or prior to the accumulation of 25 landings after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent fatigue failure of the bolts, P/N A111-5-G (10 places) and A111-5-J (2 places), attaching the engine support tube brackets to the engine ring, replace the bolts and associated hardware with new bolts, P/N MS. 21250-05008 (10 places) and MS. 21250-06008 (2 places), and associated hardware in accordance with Section 2, "ACCOMPLISHMENT INSTRUCTIONS," of Short Brothers Limited Service Bulletin No. SD3-71-04, dated February 14, 1978, or an FAA-approved equivalent. This amendment becomes effective June 25, 1979.
2008-04-17: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: Several cases have been reported where the pilot, co-pilot or observer utility light system has failed, resulting in a burning smell within the cockpit. An investigation has revealed that, due to the orientation and location of the carbon molded potentiometers used to control the intensity of the light, the potentiometers can fail and overheat in such a way that burning of the ceiling panel and the associated insulation blanket could occur. This could lead to the presence of smoke in the cockpit, requiring that the pilots carry out the appropriate emergency procedure. We are issuing this AD to require actions to correct the unsafe condition on theseproducts.