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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.