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71-13-01: 71-13-01 AVCO LYCOMING: Amdt. 39-1231. Applies to TIO 540-A series engines with serial numbers lower than 1931-61. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible failures of the fuel injector manifold to nozzle tube assemblies accomplish the following: 1. Visually inspect each tube assembly for fuel stains, cracks, dents and bend radii under 5/8 inch. Replace cracked or dented lines and increase bends to 5/8 inch or more without denting or kinking before further flight. 2. Install support clamps in accordance with the instructions contained in Lycoming Service Bulletin No. 335 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 22, 1971.
97-17-01: 97-17-01 BOEING: Amendment 39-10102. Docket 96-NM-152-AD. \n\n\tApplicability: Model 737-100 and -200 series airplanes equipped with Bendix main wheel assemblies having part number 2601571-1, certificated in any category. \n\n\tNOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures and consequent reduced controllability of the airplane, accomplish the following: \n\n\tNOTE 2: Allied Signal, Aircraft Landing Systems, Service Information Letter #619, dated February 26, 1997, is an additional source of service information for appropriate wheel half serial numbers.\n \n\t(a)\tFor airplanes equipped with a Bendix main wheel assembly having part number (P/N) 2601571-1 with an inboard wheel half with serial number (S/N) B-5898 or lower, or S/N H-1721 or lower; or with an outboard wheel half with S/N B-5898 or lower, or S/N H-0863 or lower; accomplish the following: \n\n\t\t(1)\tWithin 180 days after the effective date of this AD, and thereafter at each tire change until the replacement required by paragraph (b) of this AD is accomplished: Accomplish the actions specified in paragraphs (a)(1)(i), (a)(1)(ii), and (a)(1)(iii) of this AD, in accordance with the Accomplishment Instructions of Allied Signal Service Bulletin No. 737-32-026, dated April 26, 1988. \n\n\t\t\t(i)\tClean any inboard and outboard wheel half specified in paragraph (a) of this AD. And\n \n\t\t\t(ii)\tInspect the wheel halves for corrosion or missing paint. If any corrosion is found, or if any paint is missing in large areas, prior to further flight, strip or remove paint, and remove any corrosion. And \n\n\t\t\t(iii)\tPerform an eddy current inspection to detect cracks of the bead seat area. \n\n\t\t(2)\tIf any cracking is found during the inspections required by this paragraph, prior to further flight, repair or replace the wheel halves with serviceable wheel halves in accordance with procedures specified in the Component Maintenance Manual. \n\n\t(b)\tFor airplanes equipped with a Bendix main wheel assembly having P/N 2601571-1 with an inboard wheel half with S/N B-5898 or lower, or S/N H-1721 or lower; or with an outboard wheel half with S/N B-5898 or lower, or S/N H-0863 or lower; accomplish the following: Within 2 years after the effective date of this AD, accomplish the actions specified in paragraphs (b)(1) and (b)(2) of this AD, in accordance with Bendix Service Information Letter (SIL) 392, Revision 1, dated November 15, 1979. Accomplishment of the replacement constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD. \n\n\t\t(1)\tRemove any inboard wheel half specified in paragraph (b) of this AD, and replace it with an inboard wheel half having P/N 2607046, S/N 5899 or greater, or S/N H-1722 or greater. And \n\n\t\t(2)\tRemove any outboard wheel half specified in paragraph (b) of this AD, and replace it with an outboard wheel half having P/N 2607047, S/N B-5899 or greater, or S/N H- 0864 or greater.\n \n\t(c)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tCertain actions shall be done in accordance with Bendix Service Information Letter (SIL) 392, Revision 1, dated November 15, 1979. Certain other actions shall be done in accordance with Allied Signal Service Bulletin No. 737-32-026, dated April 26, 1988. This incorporationby reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Allied Signal Aerospace Company, Aircraft Landing Systems, 3520 Westmoor Street, South Bend, Indiana 46628-1373. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(f)\tThis amendment becomes effective on September 16, 1997.
91-09-07: 91-09-07 BOEING: Amendment 39-6982. Docket No. 90-NM-218-AD. Supersedes AD 83- 03-01 R1. \n\n\tApplicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-53- 0153, Revision 5, dated December 14, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure the structural integrity of the forward entry doorway forward frame, accomplish the following: \n\n\tA.\tVisually inspect the forward entry doorway frame for cracks in accordance with Boeing Service Bulletin 727-53-0153, dated February 1, 1980, or Revisions 1 through 5, at the earlier of the times indicated in subparagraphs A.1. or A.2. of this AD, and repeat the inspection at intervals not to exceed 3,700 landings: \n\n\t\t1.\tWithin the next 1,850 landings after March 11, 1983 (the effective date of Amendment 39-4561), or prior to accumulating a total of 25,000 landings, whichever occurs later; or \n\n\t\t2.\tWithin the next 1,850 landings after May 16, 1986, (the effective date of Amendment 39-5283), or prior to accumulating a total of 15,000 landings, whichever occurs later. \n\n\tB.\tFor airplanes modified in accordance with Boeing Service Bulletin 727-53-0153, dated February 1, 1980, through Revision 4, dated November 8, 1985, conduct the inspections described in paragraph A. of this AD prior to the accumulation of 10,000 landings after the modification or within the next 3,700 landings after the effective date of this AD, whichever occurs later. Repeat the inspection at intervals not to exceed 3,700 landings. \n\n\tC.\tCracked structure must be repaired prior to further flight, in accordance with Boeing Service Bulletin 727-53-0153, Revision 5, dated December 14, 1989, or earlier FAA- approved revisions. Repair in accordance with Revision 2 through 5 of the service bulletin constitutes terminating action for the requirements of this AD. \n\n\tD.\tModification in accordance with Boeing Service Bulletin 727-53-0153, Revision 5, dated December 14, 1989, constitutes terminating action for the requirements of this AD. \n\n\tE.\tFor the purpose of complying with this AD, subject to acceptance by the assigned FAA Principal Maintenance Inspector, the number of landings may be determined by dividing each airplane's number of hours time-in-service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tF.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment and then send it to the Manager, Seattle ACO.\n \n\tG.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tAirworthiness Directive 91-09-07 supersedes AD 83-03-01 R1 (Amendment 39-5283), which revised AD 83-03-01 (Amendment 39-4561). \n\n\tThis amendment (39-6982, AD 91-09-07) becomes effective on May 28, 1991.
2019-19-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of disconnections of certain hinge arms of the bulk cargo door (BCD) due to disbonding of the hinge arm bushes. This AD requires either modifying and re-identifying affected BCDs or replacing affected BCDs, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
87-01-03: 87-01-03 AEROSPATIALE: Amendment 39-5492. Applies to Model ATR-42 airplanes listed in Aerospatiale Service Bulletin ATR 42-79-0002 dated September 3, 1986, certificated in any category. To ensure acceptable engine anti-icing capability, accomplish the following within 10 days after the effective date of the AD, unless previously accomplished. A. Modify the engine oil cooler thermostatic valve system, in accordance with Aerospatiale Service Bulletin ATR 42-79-0002, dated September 3, 1986. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, 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 the modification required by this AD. All persons affected by this directive who have not already received theappropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective January 20, 1987.
97-15-06: 97-15-06 BOEING: Amendment 39-10079. Docket 97-NM-123-AD.\n \n\tApplicability: Model 737, 747, 757, and 767 series airplanes equipped with IPECO pilots' seats; as listed in Boeing Service Bulletins 737-25-1334, 747-25-3132, 757-25-0183, and 767-25-0244; all dated December 19, 1996; certificated in any category. \n\n\tNOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the requestshould include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent uncommanded movement of the pilots' seats during acceleration and take-off of the airplane; accomplish the following: \n\n\t(a)\tWithin 90 days after the effective date of this AD, perform a one-time operational test of the pilots' seats and the seat locks to determine that the lock pin of the seat track fully engages in all lock positions of the seat track, in accordance with Boeing Service Bulletin 737-25-1334 (for Model 737 series airplanes), 747-25-3132 (for Model 747 series airplanes), 757-25-0183 (for Model 757 series airplanes), or 767-25-0244 (for Model 767 series airplanes); all dated December 19, 1996; as applicable. \n\n\t\t(1)\tIf the seat lock pin fully engages in all lock positions of the seat track, no further action is required by this AD. \n\n\t\t(2)\tIf the seat lock pin does not fully engage in all positions of the seat track, priorto further flight, re-align the seat tracks, in accordance with the applicable service bulletin specified in paragraph (a) of this AD. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.\n \n\t(c)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(d)\tThe actions shall be done in accordance with Boeing Service Bulletin 737-25-1334, dated December 19, 1996; Boeing Service Bulletin 747-25-3132, dated December 19, 1996; Boeing Service Bulletin 757-25-0183, dated December 19, 1996; or Boeing Service Bulletin 767-25-0244, dated December 19, 1996. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(e)\tThis amendment becomes effective on July 31, 1997.
78-01-16: 78-01-16 MCDONNELL DOUGLAS: Amendment 39-3117. Applies to Model DC-9 and Military C-9 Series Airplanes certificated in all categories, Fuselage Numbers 1 through 851, inclusive which correspond to the factory serial numbers listed in Douglas DC-9 Service Bulletin No. 54-31, dated August 24, 1976, or later FAA approved revisions. \n\n\tTo detect cracks and prevent possible failure of the engine pylon aft upper spar straps (caps) comply with the following: \n\n\t(a)\tFor airplanes with 35,000 or more landings on the effective date of this AD, within the next 600 landings unless already accomplished within the last 1800 landings and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(b)\tFor airplanes with 30,000 to 34,999 landings on the effective date of this AD, within the next 900 landings, unless already accomplished within the last 1500 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(c)\tFor airplanes with 25,000 to 29,999 landings on the effective date of this AD, within the next 1200 landings, unless already accomplished within the last 1200 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(d)\tFor airplanes with 15,000 to 24,999 landings on the effective date of this AD, within the next 2,000 landings, unless already accomplished within the last 400 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(e)\tFor airplanes with less than 15,000 landings on the effective date of this AD, within the first 2,000 landings, after accumulating 15,000 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(f)\tAs required by Paragraphs (a) through (e): \n\n\t\t(1)\tUltrasonically inspect the engine pylon aft upper spar straps (caps), Part Number 9958154-5/-6 or 9958154-37/-38 per Paragraph 2.B of Douglas DC-9 Service Bulletin A54-31 dated December 22, 1976 orlater FAA approved revision, or an alternate method approved by the Chief, Aircraft Engineering Division, Western Region. If there is evidence of cracking, magnetic particle inspection per Paragraph 2.C may be used to confirm the evidence of cracking. \n\n\t\t(2)\tIf cracks are detected, before further flight replace the strap with new Part Numbers 9958154-5/-6 or 9958154-37/-38 and resume the inspections after the part has accumulated 15,000 landings or modify in accordance with Douglas Service Bulletin 54-31 dated August 24, 1976 or later FAA approved revision. \n\n\t\t(3)\tAt the option of the operator, the ultrasonic inspection may be deleted if the magnetic particle inspection is accomplished. If the magnetic particle inspection procedure is used, after two bearing replacements it is necessary to replace the strap with a new Part Number 9958154-5/-6 or 9958154-37/-38 or modified per Douglas Service Bulletin 54-31 dated August 24, 1976 or later FAA approved revision. \n\n\t(g)\tUpon completion of modification of the engine pylon rear spar straps (caps) per Douglas Service Bulletin 54-31 dated August 24, 1976 or later FAA approved revision the inspection requirements of this AD are terminated. \n\n\t(h)\tFor the purpose of complying with this AD, if records of landings are not available, the number of landings for the purpose of establishing initial compliance may be determined by dividing each airplane's hours in service by the operator's appropriate fleet average time from takeoff to landing. This procedure is subject to acceptance by the assigned FAA maintenance inspector. \n\n\t(i)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base for the accomplishment of the inspections required by this AD. \n\n\tThis Amendment becomes effective February 13, 1978.
2019-19-12: The FAA is superseding Airworthiness Directive (AD) 2018-10-07 for Sikorsky Aircraft Corporation (Sikorsky) Model S-76C helicopters. AD 2018-10-07 required inspecting the engine collective position transducer (CPT). This new AD retains the requirements of AD 2018-10-07 and expands the applicability. This AD is prompted by the determination that an additional part-numbered engine CPT is affected by the same unsafe condition. [[Page 53009]] The FAA is issuing this AD to address the unsafe condition on these products.
83-24-02: 83-24-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-4771. Applies to all Model Falcon 10 airplanes specified in the Planning Information of the service bulletins, certificated in all categories. To assure adequate exterior emergency lighting accomplish the following unless previously accomplished: A. Within the next 400 hours time in service or 270 days, whichever occurs first, after the effective date of this AD, perform the actions described in the Accomplishment Instructions of one of the following Service Bulletins: (1) Avions Marcel Dassault-Breguet Aviation AMD-BA F10 0222, (F10 33 003), dated November 12, 1981, for airplanes completed by AMD-BA with option 25-20-02, or (2) Falcon Jet Corporation No. 15 (ATA No. 33-1), dated August 17, 1983, for airplanes completed in the United States. 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. NOTE: Incorporation of the emergency exit lighting features of Supplemental Type Certificate SA4996SW constitutes compliance with this AD. 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 December 23, 1983.
97-15-16: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-15-16, which was sent previously to all known U.S. owners and operators of BHTC Model 430 helicopters by individual letters. This AD requires inspections of all 4 main rotor adapter assemblies for evidence of flapping contact between the adapter liners and the upper stop assembly plugs, and for evidence of lead-lag contact between the adapter pads and the yoke assembly; installing a never-exceed-velocity (VNE) placard; marking the airspeed indicator to reflect the airspeed restriction; installing a slippage mark on the airspeed indicator glass and instrument case; and inserting revisions to the rotorcraft flight manual to reflect the airspeed revision. This amendment is prompted by a report of a main rotor tip path plane separation, which occurred during a ferry flight at an airspeed of more than 140 knots indicated airspeed (KIAS). The actions specified by this AD are intended to prevent tip path plane separation, increased vibrations, possible damage to the main rotor system, and subsequent loss of control of the helicopter.