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2020-21-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
80-15-03: 80-15-03 MITSUBISHI HEAVY INDUSTRIES, LIMITED: Amendment 39-3843. Applies to Models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, and MU-2B-25 Airplanes with serial numbers 005 through 164, certificated in all categories. Compliance required as indicated. To prevent possible fire due to the baggage of the rear baggage compartment coming into contact with engine bleed air tubing, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, install heatproof insulation between the engine bleed air tubing and the rear baggage compartment in accordance with the "Instructions" section of Mitsubishi Service Bulletin No. 070C, dated January 7, 1976, or an FAA-approved equivalent. (b) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, modify the baggage compartment ceiling in accordance with Mitsubishi MU-2 Service Bulletin No. 182, dated November 16, 1979, or an FAA-approved equivalent. (c) Aircraft that have been modified in accordance with Mitsubishi MU-2 Service Recommendation No. 033 or No. 033A are exempt from complying with paragraph (b) of this AD. (d) For purposes of complying with this AD, an FAA-approved equivalent may be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. NOTE: All persons affected by this directive who have not already received the service bulletins from the manufacturer may obtain copies upon request to Mitsubishi Heavy Industries, Ltd., 10, Oye-cho, Minato-ku, Nagoya, Japan, or Mitsubishi Aircraft International, Inc., P.O. Box 3848, San Angelo, Texas 76901. These documents may also be examined at FAA, Engineering and Manufacturing District Office, Rm. 7321, 300 Ala Moana Blvd., Honolulu, Hawaii 96850, or Rules Docket, Rm. 916, FAA, 800 Independence Avenue, S.W., Washington, D.C. 20591. This supersedes Amendment 39-2748 (41 FR 44997), AD 76-21-02. This amendment becomes effective July 24, 1980.
83-02-04 R1: 83-02-04 R1 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4558 as amended by Amendment 39-4663. Applies to Model HS 125 series airplanes, serial numbers NA0201 to NA0299 and serial numbers 257001 to 257139, plus all airplanes retrofitted with Garrett TFE 731 engines, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible failure of windshield heat from external high voltage static charge conditions and to prevent potential generator tripping from electrical interference effects, accomplish the following: 1. Within the next 200 hours time in service or two months, whichever occurs first, after the effective date of this AD, perform the modifications specified in Part 2, Accomplishment Instructions, of British Aerospace Aircraft Group, Hatfield-Chester Division, 125 Service Bulletin 24-230-(2790), Revision 3, dated June 11, 1982. 2. Alternate means of compliance which provide an equivalent level of safety may beused when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 3. 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. 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). Amendment 39-4558 became effective February 10, 1983. This Amendment 39-4663 becomes effective June 22, 1983.
61-16-03: 61-16-03 BRANTLY: Amdt. 317 Part 507 Federal Register August 4, 1961. Applies to All B-2 Helicopters Prior to Serial No. 104. Compliance required within the next 25 hours' time in service after the effective date of this AD. Three accidents have resulted from the restriction of collective control due to interference by the seat. This interference is caused by improper seat installation which allows the seat to slide forward of its normal position. To minimize the possibility of restriction to the collective control by the seat, all Brantly B-2 helicopters prior to Serial No. 104 shall have the left hand seat angle at the rear of each seat modified to incorporate seat safety brackets, Brantly P/N 163-22 or equivalent. (Brantly Service Bulletin No. 13, dated June 8, 1961, pertains to this same subject.) This directive effective August 4, 1961.
2020-18-11: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by reports that the adhesive seal prevented the doors from jettisoning properly. This AD requires removing certain seals, replacing certain seals with newly certified seals and revising the existing Rotorcraft Flight Manual (RFM) for your helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
79-20-02: 79-20-02 FOKKER-VFW: Amendment 39-3571. Applies to Model F-27 Mark 100, 200, 300, 400, 500, 600, 700 airplanes, certificated in all categories, all aircraft serial numbers up to and including 10569 which have Dowty Rotol nose landing gear assembly other than type 200565001, 200568001, or 200678001 installed, except aircraft serial numbers 10549, 10561, 10562, and 10563. Compliance is required as indicated, unless already accomplished. To prevent fatigue failure of improperly machined nose wheel axles, accomplish the following: (a) Within the next 500 hours time in service after the effective date of this AD or at the next nose wheel change, whichever occurs first, inspect the bore of the nose wheel axle (Dowty Rotol P/N 9009Y12) in accordance with Section 2, "Accomplishment Instructions", of Fokker Service Bulletin No. F27/32-129 dated May 1, 1978, and Section 2, "Accomplishment Instructions" of Dowty Rotol Service Bulletin No. 32-100B, dated April 25, 1978 or DowtyRotol Service Bulletin No. 32-30S, dated April 25, 1978, as appropriate, (hereinafter referred to as the Dowty Rotol Service Bulletin) or an FAA-approved equivalent, and - (1) If no undercut is found and the change in section from the central bore to the threaded bore is a 0.25 inch maximum radius or a 20 degree tapered chamfer, identify the axle in accordance with item 2.B.(1) of the Dowty Rotol Service Bulletin, or an FAA-approved equivalent, and return the axle to service. (2) If an undercut is found and both ends have a smooth transition to the adjacent area and provided the axle wall thickness is 0.115 inches or more, identify the axles in accordance with paragraph item 2.B.(1) of the Dowty Rotol Service Bulletin, or an FAA- approved equivalent, and return the axle to service. (3) If an undercut is found and the axle wall thickness is less than 0.115 inches, or if either or both ends of the undercut do not have a smooth transition to the adjacent area, remove theaxle from service and replace with an axle which is identified in accordance with paragraph (a)(1) or (a)(2) of this AD. (b) Before releasing to service any nose wheel axles (Dowty Rotol P/N 9009Y12) held as spares, inspect each nose wheel axle and if it is not already identified in accordance with paragraph 2.B.(1) of the Dowty Rotol Service Bulletin or an FAA-approved equivalent, inspect the axle, and identify it or remove it from service in accordance with paragraph (a) of this AD. (c) Before releasing to service any spare nose wheel landing gears assemblies other than type 200565001, 200568001, or 200678001, inspect the nose axle (Dowty Rotol P/N 9009Y12) installed in such nose wheel landing gear assembly and if it is not already identified in accordance with paragraph 2.B.(1) of the Dowty Rotol Service Bulletin or an FAA-approved equivalent, inspect the axle, and identify it or remove it from service and replace it in accordance with paragraph (a) of this AD. (d) For the purposes of this AD, an FAA equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Region, c/o American Embassy, Brussels, Belgium. NOTE: Dowty Rotol Service Bulletin 32-30S is identical to Dowty Rotol Service Bulletin No. 32-100B but applies only to Fokker Model F-27 Mk 500. This amendment becomes effective October 19, 1979.
80-25-03: 80-25-03 BOEING: Amendment 39-3982. Applies to all Model 747 airplanes equipped with B.F. Goodrich off-wing slides: \n\n\tA.\tWithin three (3) years after the effective date of this AD, unless already accomplished, install shear pin mechanical restraints to affected off-wing escape slides in accordance with B.F. Goodrich Service Bulletin 25-054 dated March 4, 1980, or later FAA approved revisions, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office FAA Northwest Region.\n \n\tB.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region, may adjust the compliance date if the request contains substantiating data to justify the change.\n \n\t\tNOTE: This installation is considered an equivalent modification to the bayonet/spring restraints required by Amendment 39-1128 (35FR19170) AD 70-26-01. \n\n\tThis amendment becomes effective January 2, 1981.
2020-20-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Corporation (RRC) AE 2100D3 model turboprop engines. This AD requires revising the airworthiness limitations section (ALS) of the RRC AE 2100D3 Maintenance Manual and the operator's approved continuous airworthiness maintenance program. This AD was prompted by a report of a propeller gearbox (PGB) development test in which high vibration occurred due to a fatigue crack that initiated in the propeller shaft. The FAA is issuing this AD to address the unsafe condition on these products.
81-25-02: 81-25-02 MCDONNELL DOUGLAS: Amendment 39-4270. Applies to McDonnell Douglas Model DC-8 series airplanes certificated in all categories. Compliance required within six months from the effective date of this AD, unless already accomplished. To assure that proper windshield heat generation is available for bird impact protection and anti-ice functions, on aircraft that have had left, center, or right windshield panels replaced since November 1, 1978, accomplish the following: \n\n\tA.\tInspect windshield panels to determine manufacturer and year of manufacture. Windshield panels may be identified by the manufacturer's logo "PPG" or "LOF" in large capital letters with part number specification, and serial number adjacent to logo. These are located at the top panel on the left and right-hand windshield panels, and at the bottom or top of the center windshield panel. \n\n\t\t1.\tPanels manufactured by Libbey Owens Ford (LOF), no further action is required. \n\n\t\t2.\tPanels manufactured byPPG: \n\n\t\t\ta.\tDetermine the year of manufacture, which is contained in the serial number. Serial number samples are shown below: \n\n\t\t\t\t8-H-11-20-220-315 (first digit indicates year of manufacture, 1978; third digit indicates month, November) \n\n\t\t\t\t9-H-5-21-315-373 (first digit indicates year of manufacture, 1979; third digit indicates month, May) \n\n\t\t\t\tO-H-4-6-219-215 (first digit indicates year of manufacture, 1980; third digit indicates month, April) \n\n\t\t\t\t1-H-3-6-317-212 (first digit indicates year of manufacture, 1981; third digit indicates month, March) \n\n\t\t\tb.\tWindshield panels with an October 1978 or prior manufacturing date coded or January 1981 or subsequent manufacturing date coded, no further action is required. \n\n\t\t\tc.\tAircraft with less than 200 flight hours on replacement panel(s), accomplish the following resistance check of PPG November 1, 1978, through December 31, 1980, date coded windshield panels: \n\n\t\t\t\t(1)\tDC-8-60 series windshield resistance check:(a)\tOpen anti-ice windshield heat right, center, left, and right, center, left anti-fog circuit breakers on EPG circuit breaker panel. \n\n\t\t\t\t\t(b)\tDisconnect windshield electrical conductor from receptacle on left, right, and center windshield panels. \n\n\t\t\t\t\t(c)\tUsing an ohmmeter check resistance between Terminal L and P at the receptacle on left (right) windshield panel. Resistance should be 61.2-82.8 ohms. \n\n\t\t\t\t\t(d)\tUsing an ohmmeter check resistance between Terminals E and G at receptacle on center windshield panel. Resistance should be 67.5-92.5 ohms. \n\n\t\t\t\t\t(e)\tReconnect the windshield electrical conductor to receptacle on windshields and close the power system circuit breakers. \n\n\t\t\t\t(2)\tDC-8-50 series and prior windshield resistance check: \n\n\t\t\t\t\t(a)\tOpen the outer pane windshield heat circuit breakers for the left, right, and center windshields on the heat, vent, and ice protection (AC bus) circuit breaker panel. \n\n\t\t\t\t\t(b)\tRemove access door No. 623 onthe first officer's console and electrical power center. \n\n\t\t\t\t\t(c)\tDisconnect the conductor connected to transformer Terminal X, Y, or Z on three tap transformer or V, W, X, Y or Z on five tap transformer of windshield to be tested. \n\n\t\t\t\t\t(d)\tUsing an ohmmeter, check resistance between transformer Terminal 1 and the conductor disconnected from the transformer. Resistance should be 81.6 to 110.4 ohms for left (right) windshield. \n\n\t\t\t\t\t(e)\tUsing an ohmmeter, check the resistance between transformer Terminal 1 and the conductor disconnected from the transformer. Resistance should be 96 to 130 ohms for the center windshield. \n\n\t\t\t\t\t(f)\tReconnect conductors to terminals. \n\n\t\t\t\t(3)\tIf windshield resistance is: \n\n\t\t\t\t\t(a)\tWithin tolerance on all three panels, aircraft may be continued in service and panels must be respectively inspected at 50-hour intervals until the accumulation of 200 flight hours. \n\n\t\t\t\t\t(b)\tWithin tolerance after the accumulation of 200 flight hours, nofurther action is required. \n\n\t\t\t\t(4)\tIf resistance is out of tolerance on one or more of the three windshield panels: \n\n\t\t\t\t\t(a)\tFor DC-8-60 series center panel out of tolerance install the following placard in full view of pilot: "Do Not Exceed 260 kts IAS Below 10,000 Feet Altitude." \n\n\t\t\t\t\t(b)\tFor DC-8-60 series with only side panel(s) out of tolerance, install the following placard in full view of the pilot: "Do Not Exceed 285 kts IAS Below 10,000 Feet Altitude." \n\n\t\t\t\t\t(c)\tFor DC-8-60 series, if left (right) windshield panel(s) resistance is 82.9 to 130 ohms and/or center windshield panel resistance is 92.6 to 130 ohms, full anti-ice capability is available. Panels must be repetitively inspected at 50-hour intervals, until the accumulation of 200 flight hours, to ascertain that the resistance remains at or below 130 ohms. After the accumulation of 200 flight hours, the repetitive inspection interval can be extended to 1500 flight hours. \n\n\t\t\t\t\t(d)\tFor DC-8-50 series and prior with resistance out of tolerance on one or more of the three windshield panels, install the following placard in full view of the pilot: "Do Not Exceed 245 kts IAS Below 10,000 Feet Altitude." \n\n\t\t\t\t\t(e)\tIf windshield heat is unavailable for ice protection, install the following placard in full view of the pilot: "Windshield Heat Inoperative." In certain cases, the rain removal system can be used to de-ice or anti-ice windshields. See procedures in the Airplane Flight Manual. \n\n\t\t\t\t\t(f)\tThe above restrictions can be removed when the out-of-tolerance panel(s) is/are replaced with panel(s) manufactured by LOF or any PPG manufactured panel(s) with a date code other than November 1, 1978, through December 31, 1980. \n\n\t\t\td.\tFor November 1, 1978, through December 31, 1980, date coded windshield panels which have over 200 flight hours, accomplish the resistance check per paragraph c(1) or c(2), as applicable. \n\n\t\t\t\t(1)\tIf windshield resistance is within tolerance on panels,no further action is required. \n\n\t\t\t\t(2)\tIf resistance is out of tolerance on any of the three panels, accomplish the instructions as outlined under paragraph c(4). \n\n\tB.\tAlternative inspections, repairs, or other action to be accomplished on or after the effective date of this AD which provide an equivalent level of safety, may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\n\tSpecial 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. \n\n\tThis amendment becomes effective January 4, 1982.
83-26-02: 83-26-02 BRITISH AEROSPACE: Amendment 39-4788. Applies to all Model BAC 1- 11 200 and 400 series airplanes certificated in all categories. Compliance is required as indicated. To assure detection of improperly closed doors and prevent the forward passenger or forward service door from opening during flight, accomplish the following, unless already accomplished: A. Within 9 months after the effective date of this AD, install an auxiliary forward passenger and forward service door status warning system in accordance with paragraph 2, "Accomplishment Instructions," of British Aerospace Service Bulletin 52-PM3329 Part 2, Revision No. 2, dated November 12, 1980. B. Alternate means of compliance which provide an equivalent 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 amendment becomes effective January 30, 1984.
2020-18-12: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, and -300 series airplanes. This AD was prompted by the FAA's analysis of the Model 777 fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. This AD also provides alternative actions for cargo airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
80-10-04 R1: 80-10-04 R1 BELL: Amendment 39-3770 as amended by Amendment 39-4060. Applies to all Model 47 series helicopters and military Model H-13, OH-13, and TH13T series helicopters certificated in all categories that are equipped with tail rotor blades, P/N 47-642-102, except for those helicopters equipped with Franklin (or Aircooled Motors) engines. (Airworthiness Docket No. 67-SW-68.) Compliance required as indicated. To prevent possible failure of tail rotor blades, P/N 47-642-102, due to fatigue cracks, accomplish the following: (a) Blades with 250 or more hours' time in service on the effective date of this AD must be removed from service within the next 50 hours' time in service and must be destroyed. (b) Blades with less than 250 hours' time in service on the effective date of this AD must be removed from service prior to or on attaining 300 hours' time in service and must be destroyed on attaining 300 hours' total time in service. (c) Prior to further flight after November 30, 1981, install improved tail rotor blades, P/N 47-642-117, unless already accomplished, in accordance with Bell Helicopter Textron Service Instruction No. 428 (47G-2A, G-2A-1, G-3, G-3B, G-3B-1, G-3B-2, G-4, G-4A, G-5, J-2, and J-2A) or No. 438 (47G and 47G-2), as appropriate, or data approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. (d) The helicopters may be flown in accordance with FAR 21.197 to a base where compliance with this AD can be performed. (e) Equivalent means of compliance with paragraph (c) may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. (f) This AD applies to modified versions of the military H-13, OH-13, and TH-13T series helicopter models. Examples of such modified versions are the Continental Copters or Tomcat helicopters, OH-13H/Tomcat Mark 5 series and 6 series, or the Texas Helicopter OH-13/M74 series helicopters. NOTE: The inspections and checks specified in AD 70-10-08, Amdt. 39-983, as amended by Amdt. 39-1063 and Amdt. 39-2642, have not been canceled or superseded by this AD and are still required. (Bell Helicopter Textron OSN 47-79-2, Service Bulletin 47-76-2, Alert Service Bulletin Nos. 47-79-3 and 47-79-4 pertain to this subject.) Amendment 39-3770 became effective June 9, 1980. This amendment 39-4060 becomes effective February 28, 1981.
81-07-08: 81-07-08 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39-4074. Applies to Model P68 and P68B series airplanes, Serial Numbers 1 to 75 inclusive which do not have Partenavia Kit P/N 68-010 installed, and Serial Numbers 76 to 159 inclusive which do not have Partenavia Kit P/N 68-009 installed, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent inadvertent positioning of the longitudinal trim tab to an incorrect position for takeoff, accomplish the following: (a) Before each flight, until the airplane is modified in accordance with paragraph (e) of this AD - (1) Set the longitudinal trim tab position indicator to the zero position. (2) Position the leading edge of the stabilator to the zero reference point on the left, aft side of the fuselage, as described in Partenavia Service Bulletin No. 41, dated October 5, 1978 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent. (b) If, as a result of the check in paragraph (a) of this AD, the longitudinal trim tab is streamlined, the longitudinal trim tab position indicator is positioned correctly. (c) If, as a result of the check in paragraph (a) of this AD, the longitudinal trim tab is not streamlined with the stabilator: (1) Reposition the longitudinal trim tab position indicator to read zero when the longitudinal trim tab and stabilator are streamlined with the stabilator leading edge set to its zero reference; or (2) Set the stabilator leading edge to the zero reference as in paragraph (a)(2) of this AD, and rotate the trim wheel until the stabilator and the longitudinal trim tab are streamlined to obtain a new zero position for the trim tab position indicator. Note the amount and direction the new zero point varies from the originally marked zero point and install, adjacent to the longitudinal trim tab position indicator, a placard which shows the amount and direction of thecorrection that must be used when setting the longitudinal trim tab for takeoff. (d) The check required by paragraph (a) of this AD and the repositioning required by paragraph (c) of this AD may be performed by the pilot and an entry made in the airplane maintenance records in accordance with Part 43 of the Federal Aviation Regulations. (e) Within 50 hours time in service after the effective date of this AD (1) For airplanes with Serial Numbers 1 to 75 inclusive, install Partenavia Kit P/N 68-010 in accordance with the kit manufacturer's instructions, or an FAA-approved equivalent. (2) For airplanes with Serial Numbers 76 to 159 inclusive install Partenavia Kit P/N 68-009 in accordance with the kit manufacturer's instructions, or an FAA-approved equivalent. (f) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Office,c/o American Embassy, Brussels, Belgium. 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 Partenavia Costruzioni Aeronautiche S.p.A., Via Cava, Casoria - Napoli, Italy. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, DC 20591. This amendment becomes effective April 6, 1981.
2020-18-19: The FAA is superseding Airworthiness Directive (AD) 2014-12-07 for Agusta S.p.A (Agusta) Model AB412 and AB412EP helicopters. AD 2014- 12-07 requires inspecting the rotor brake pinion (pinion) for a crack and replacing it if there is a crack. This AD retains the requirements of AD 2014-12-07 and also requires removing \n\n((Page 55172)) \n\ncertain serial-numbered pinions from service. This AD was prompted by a report of an additional cracked pinion. The actions of this AD are intended to address an unsafe condition on these products.
81-15-01: 81-15-01 SWEARINGEN: Amendment 39-4163. Applies to Swearingen Models SA226-T, S/N T201 through T275 and T277 through T291; SA226-AT, S/N AT001 through AT074, and SA226-TC, S/N TC201 through TC407 airplanes certificated in all categories. Compliance required within the next 200 hours' time in service, after the effective date of this AD, unless Swearingen Bulletin SB53-006 issued November 27, 1980, has been accomplished. (Airworthiness Docket No. 80-ASW-54.) Inspect the lower wing-to-fuselage aerodynamic fairing stiffeners, the attached grommets, and the lower fuselage pressure vessel skin for deterioration, wear, or damage. Repair any damaged areas and modify the structure in accordance with Swearingen Service Bulletin SB53-006 issued November 24, 1980, or equivalent means approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. A special flight permit may be issued in accordance with FAR 21.197 to allow flight of the aircraft to a location where this AD can be accomplished. This amendment becomes effective August 15, 1981.
60-11-01: 60-11-01\tBOEING: Amdt 158 Part 507 Federal Register May 24, 1960. Applies to the following 707-200 and -300 Series Airplanes And All Spare Quick Change Engine Build-up Units Which May Be Available. Serial Numbers 17592 Through 17606, 17613 Through 17618, 17623 Through 17626, 17673 Through 17684, And 17692 Through 17695. Boeing will incorporate the modification required by this airworthiness directive on all production airplanes other than those listed above. \n\tCompliance required by July 1, 1960. \n\tAs a result of several failures which have occurred to the engine nose dome installation of the Boeing 707-300 series airplanes resulting in major engine failures, inspections and modifications to the nose dome attaching means is required. To preclude further difficulty the following shall be accomplished as indicated: \n\t(a)\tInspect and rework each engine nose dome and attachment in accordance with the information included in Boeing Service Bulletin No. 799 dated January 28, 1960.(b)\tRework the nose dome stub and bolt, Boeing P/N's 66-2079 or 66-2078 and 66-2075 in accordance with the instructions contained in Boeing Service Bulletin No. 790 dated January 27, 1960.
64-09-01: 64-09-01\tBOEING: Amdt. 715 Part 507 Federal Register April 18, 1964. Applies to All Models 707 and 720 Series Aircraft, Serial Numbers 17586 through 17612, 17614 through 17652, 17658 through 17690, 17692 through 17724, 17903 through 17905, 17907 through 17930, 18012 through 18037, 18041 through 18050, 18054 through 18087, 18154 through 18167, 18240 through 18246, 18248 through 18251, 18334 through 18339, 18351 through 18357, 18372 through 18397, 18400 through 18404, 18406 through 18408, 18411 and 18412, 18414 through 18425, 18451 through 18457, 18460 and 18461. \n\n\tCompliance required within 1,000 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent slippage of the crank arms on the shafts of the respective stabilizer and spoiler position transmitters, and to prevent rotation of the position transmitter in its brackets, rework the crank arms or replace with modified crank arms, and add a washer under the nut of each clamping boltin accordance with the Modification Data (PRR 15506) of Boeing Service Bulletin No. 1836 or FAA approved equivalent. \n\n\t(Boeing Service Bulletin No. 1836 covers this same subject.) \n\n\tThis directive effective May 19, 1964.
2020-18-05: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PT6B-37A model turboshaft engines with engine serial number PCE-PU0289 and earlier. This AD was prompted by a report of contamination from galvanic corrosion between the fuel control unit (FCU) aluminum body and the steel union fitting causing the loss of engine control, resulting in an engine over-speed condition and subsequent in-flight shutdown (IFSD). This AD requires replacing the FCU with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
79-08-06: 79-08-06 MARVEL-SCHEBLER/TILLOTSON: Amendment 39-3450. Applies to HAJ-6 Part Number 10-5243 carburetors with the following serial numbers installed on aircraft certificated in all categories: DF-1-100 118 133 151 174 191 216 250 276 300 101 119 134 154 175 193 218 251 277 301 102 120 135 176 157 194 219 255 278 302 103 121 136 159 177 195 220 256 279 303 104 122 137 161 179 200 222 258 282 304 106 123 138 162 180 202 223 260 287 307 107 124 139 163 182 204 225 261 290 312 110 125 143 164 183 205 227 263 292 313 111 127 144 167 184 208 229 264 293 318 112 128 145 168 185 209 231 266 295 113 129 147 170 186 210 237 269 296 114 130 148 171 187 211 238 271 297 116 131 149 172 189 212 240 274 298 117 132 150 173 190 241 245 275 299 These carburetors are installed on, but are not limited to Cessna TR182 aircraft with Lycoming O-540-L3C5D engines. Compliance required within 30 days after the effective date of this AD, unless previously accomplished. To preclude failure of the engine during idle conditions, remove the carburetor from service and replace with an airworthy carburetor of the same part number with serial number DF-1-500 or subsequent. The aircraft may be flown in accordance with FAR 21.197 to a base where the modification can be performed. This amendment becomes effective April 25, 1979.
65-05-04: 65-05-04 FAIRCHILD: Amdt. 39-40 Part 39 Federal Register February 25, 1965. Applies to Model F-27 Series Aircraft Serial Numbers 1 through 107. Compliance required as indicated. To prevent damage to the rudder and rudder trim tab from rudder vibration, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 75 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the rudder trim tab for cracks in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) If a crack is found, modify the rudder trim tab in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight, except that one flight may be made in accordance with the provisions of FAR 21.197 to a base where the repair can be made. During this flight, a maximum operating limit speed (Vmo) of 160 knots CAS or MACH number 0.35 shall be observed. (c) Inspect in accordance with Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, aircraft modified in accordance with (b) prior to the accumulation of 600 hours' time in service after modification, and thereafter at intervals not to exceed 150 hours' time in service from the last inspection. (d) Within the next 100 hours' time in service after the effective date of this amendment unless already accomplished, modify the rudder trim tab in accordance with Fairchild Alert Bulletin No. 27-39A, dated March 12, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (e) The repetitive inspections required by (a) and (c) may be discontinued when the modification required by (d) is incorporated. (f) Upon request of the operator, an FAA maintenance inspectors, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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. (Fairchild Service Bulletin No. F27-55-8A, Revision 1, dated February 3, 1965, covers this subject.) This directive effective February 25, 1965. Revised May 13, 1965.
2020-17-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115 and -153N; A320-214, -216, -232, - 251N, -252N, -271N, and -273N; and A321-211, -231, -251N, -253N, -271N, -272N, -251NX, -252NX, -253NX, and -271NX airplanes. This AD was prompted by reports of fuel leaks at the interface of the low pressure shut off valves on the pylon areas of engines 1 and 2 due to improperly installed parts during production. This AD requires a one-time detailed inspection of each low pressure shut off valve on the pylon areas of engines 1 and 2 for correct installation, and replacing the O-rings and torqueing the mounting bolts within specified values as applicable, as specified in a European Union Aviation Safety Agency (EASA) AD 2020- 0148, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
80-26-01: 80-26-01 ROCKWELL INTERNATIONAL: Amendment 39-3988. Applies to Model NA265-40 Series, Serial numbers 282-1 through 282-137, and -60 Series, Serial Numbers 306-1 through 306-64, 306-68, 306-71 through 306-103 airplanes certificated in all categories, not modified in accordance with Life Extension Modification per North American Rockwell Drawing 306-053010 or Service Kit SK 13808-40. Compliance required as indicated, unless already accomplished. To prevent inadvertent cabin depressurization accomplish the following: (a) On aircraft with 2,000 or more hours' total time in service, within the next 600 hours' additional time in service or within the next 12 months from the effective date of this AD, whichever occurs first. (1) Gain access and conduct a close visual inspection of the fuselage structure below the cabin entrance door and adjacent areas in accordance with "Modification Instructions 1 through 3" of Sabreliner Service Bulletin No. 56 dated September 22, 1980. Access is gained by modification in accordance with Service Kit SK 13808-10. (2) If no cracks are detected, repeat the inspections required in paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (3) If cracks are detected which are less than one inch long in the outboard bays only, repair per Sabreliner Service Bulletin Repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (4) If cracks are detected which are less than one inch long in the inboard bays or inboard and outboard bays, repair per Sabreliner Service Bulletin No. 56, dated September 22, 1980, and accomplish Service Kit SK 13808-30. Repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (5) If cracks are detected which are one inch or longer, repairin a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region, or by the installation of Service Kit SK 13808-40. The installation of Service Kit SK 13808-40 terminates the inspections required by this AD. For other repairs, unless specifically authorized by the Chief, Engineering and Manufacturing Branch, FAA Western Region, repeat the inspections required by paragraph (a)(1) of this AD at intervals not to exceed 600 hours' time in service since the last such inspection. (b) 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 required by this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective January 19, 1981.
80-23-01: 80-23-01 ROLLS-ROYCE, LTD.: Amendment 39-3966. Applies to Rolls-Royce, Ltd., DART 506, 510, 511, 514, 515, 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 542, 543, 550, and all variants turboprop engines. Compliance required as indicated, unless already accomplished. To preclude possible frettage fatigue failure of low pressure impellers, inspect for cracks and modify or remove from service all low pressure impellers installed in the following DART model engines: 1. DART 506, 510, 511, 514, 515, and their variants; and DART 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 550, and all variants of these marks equipped with a low pressure impeller which has run previously in a DART 506, 510, 511, 514, 515, or any variant of these engines. a. After November 30, 1980, no low pressure impeller may exceed 5,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After November 30, 1980, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732; in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service, low pressure impellers having crack indications. c. Remove from service not later than May 31, 1981, all low pressure impellers which have not been inspected for cracks and do not have modification 1732 incorporated. 2. DART 520, 525, 526, 527, 528, 529, 530, 531, 532, 533, 534, 535, 536, 550, and their variants equipped with a low pressure impeller which has not run previously in a DART 506, 510, 511, 514, 515 or any variant of these engines. a. After December 31, 1982, no low pressure impeller may exceed 9,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After December 31, 1982, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. c. Remove from service not later than December 31, 1984, all low pressure impellers which have not been inspected for cracks and do not have Modification 1732 incorporated. 3. DART 542 and 543 model engines and their variants. a. After December 31, 1981, no low pressure impeller may exceed 9,000 flight cycles since new without inspection for cracks and incorporation of Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. b. After December 31, 1981, prior to further flight, all low pressure impellers for which the flight cycles since new cannot be positively established, must be inspected and modified to incorporate Modification 1732, in accordance with Rolls-Royce DART Alert Service Bulletin No. Da72-A445, Revision 4, dated October 27, 1980. Remove from service low pressure impellers having crack indications. c. Remove from service not later than December 31, 1983, all low pressure impellers which have not been inspected for cracks and do not have modification 1732 incorporated. NOTE: For the purposes of this AD, a flight cycle is considered to be an engine operating sequence fromtakeoff to landing. Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator, equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England. The Manufacturer's Alert Service Bulletin identified and described in this directive 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 Technical Publications Department, Rolls-Royce, Ltd., East Kilbride G74 4PY, Scotland. The document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts, 01803, 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 the New England Region Office. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date(s) 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 that operator. This amendment becomes effective October 30, 1980.
2020-16-08: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. The AD applies to certain Aspen Avionics, Inc., Evolution Flight Display (EFD) EFD1000 Emergency Backup Display, EFD1000 Multi-Function Display, and EFD1000 Primary Flight Display systems installed on various airplanes. As published, the docket number and product identifier in the Comments Invited section of the preamble are incorrect. This document corrects that error. In all other respects, the original document remains the same; however, for clarity, the FAA is publishing the entire rule in the Federal Register.
60-16-04: 60-16-04 HARTZELL: Amdt. 182 Part 507 Federal Register July 29, 1960. Applies to All Propellers HC-82XF-1D, HC-82XF-1DB, HC-82XG-1D, HC-82XG-6DL, HC-82XL-1D, and HC-92ZK-8L; and to HC-82XK-1D Serial Numbers 100G Through 846G; and to HC-92ZK-8D Serial Numbers 100L Through 491L. These Propellers May Be Used On Such Aircraft As Piper PA-24, Cessna 180 and 182, Meyers 200, Mooney Mark 20, and Lake (Colonial) C-2. Compliance required as indicated. Because of failure or cracking of several cast guide collars, P/N 834-4, -8, -9, the following shall be accomplished: (a) Within the next 25 hours of propeller operation and each 25 hours of operation thereafter, visually inspect for cracks, all guide collars not marked with a letter "P" or "F". This inspection can be accomplished by looking through the spinner blade cutouts without removing the spinner. Cracked collars must be replaced prior to further flight. (b) At the next propeller overhaul or by January 1, 1961,whichever occurs first, replace all unmarked guide collars with marked guide collars. Cast collars which are marked with the letter "P" and forged collars which bear part number as cast collars but are marked with letter "F" have been tested and need not be inspected or replaced. (Hartzell Service Bulletin No. 71 covers this same subject.) This directive shall become effective 30 days after publication in the Federal Register.