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80-14-02: 80-14-02 PIPER AIRCRAFT CORPORATION: Amendment 39-3819. Applies to Model PA-28-181, serial numbers 28-7790032 through 28-8090227; Model PA-32-300, serial numbers 32-7640001 through 32-7740032 and Model PA-32R-300, serial numbers 32R-7680001 through 32R-7780148 airplanes certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent separation of the throttle control cable rod end from the throttle arm on the affected Models PA-28 and PA-32 airplanes, and rod end binding with possible subsequent throttle cable failure on the affected Model PA-28 airplanes, accomplished the following. (a) For the Model PA-32-300 and PA-32R-300 series airplanes, replace the throttle linkage connecting hardware in accordance with the instructions contained in Piper Service Bulletin No. 537, dated January 12, 1977. (b) For the Model PA-28-181 airplanes, modify the throttle linkage in accordance with the instructions listed in the "Throttle Linkage Modification Kit," Piper Part Number 764- 009V. NOTE: Piper Service Bulletin No. 679 pertains to this subject. (c) Make an appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment is effective July 10, 1980.
78-10-02: 78-10-02 SHORT BROTHERS LIMITED (Formerly Short Brothers & 78-10-02 Short Harland, Ltd.): Amendment 39-3213. Applies to Model SD3-30 airplanes, Serial Nos. SH3004 to SH3013 inclusive, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent unwanted propeller feathering, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, visually inspect the electrical wiring between the proximity switch and the main cable loom for chafing, contact with engine case, and for security of clamping. (b) If, during the inspection required by paragraph (a), chafing, loose clamps, or contact with engine is found, before further flight, except that the airplane may be flown in accordance with the provisions of FAR 21.197 and 21.199 to a base where the modifications required by this AD may be accomplished, correct the fault in accordance with paragraph 1.C.3. of Short Brothers Limited Service Bulletin No. SD3-61-A03, dated December 21, 1977, or an FAA-approved equivalent. (c) Within 500 hours time in service after the effective date of this AD, accomplish Short Brothers Limited Modification No. 5471 in accordance with Shorts Service Bulletin No. SD3-61-03, dated January 19, 1978 (pages 1 through 4 are dated January 19, 1977) or an FAA- approved equivalent. (d) Record the accomplishment of the AD in accordance with FAR 91.173. (e) Equivalent methods of compliance with this AD or adjustment of the inspection intervals required by this AD may be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, 09667, if the request is submitted through an FAA Maintenance Inspector and contains substantiating data to justify the interval or method of compliance for that operator. This amendment becomes effective May 29, 1978.
74-08-03: 74-08-03 BELL: Amendment 39-1806. Applies to Bell Model 212 helicopters, S/N 30504 through 30593, certificated in all categories. Compliance required as indicated. To detect and prevent possible cracks in the tail fin forward spar cap angle and in the tail boom skin adjacent to the fin, accomplish the following repetitive inspections and modification. (a) Within 25 hours time in service after the effective date of this A.D. and thereafter at intervals not to exceed 25 hours time in service from the last inspection, accomplish the following inspections until the modification of paragraph (b) is completed. (1) Remove the 42 degree gear box cover from the tail boom. (2) Remove the first rivet above the tail boom on the left side of the vertical fin forward spar cap angle. Remove the paint finish and clean the area around the rivet hole (inboard and outboard sides of the spar cap angle), using cloth and Methyl Ethyl Ketone or equivalent. Do not reinstall thefirst rivet. (3) Inspect the rivet hole and clear area of the spar for cracks using a three power or higher magnifying glass or a dye penetrant or equivalent inspection method. (4) If no cracks are found, protect the clear area of the spar and rivet hole using a clear lacquer or light film of clear grease or equivalent transparent protection and install the gear box cover. (5) If cracks are found, remove the tail boom and replace with an uncracked tail boom in accordance with the procedures specified in the Bell Model 212 maintenance manual. (b) Within 100 hours time in service after the effective date of this A.D., modify the tail fin and tail boom in accordance with Part III, Bell Helicopter Co., Service Bulletin No. 212- 01-73-1, Rev. B, dated October 9, 1973 or later FAA approved revision. 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 the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D.C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective May 6, 1974.
2020-07-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-271N airplanes and Model A321-271N, - 271NX, and -272N airplanes. This AD was prompted by a report of a gap found on an engine pylon nose fire seal during an inspection of an in- production airplane. This AD requires a one-time detailed inspection of certain engine pylon nose fire seals for correct installation, and applicable corrective actions if necessary, 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.
98-12-27: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive magnetic particle inspections to detect cracking of the splined operating shaft of the internal door handle on the forward passenger door, rear passenger door, and rear baggage door; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the splined operating shaft of the internal door handle, which could result in failure of the internal door handle, inability to operate the door during an emergency evacuation, and consequent injury to airplane occupants.
90-09-11: 90-09-11 BOEING: Amendment 39-6588. Docket No. 90-NM-05-AD. \n\n\tApplicability: Model 737-300 and -400 series airplanes, equipped with Air Cruisers Company forward door evacuation slides identified in paragraph 1A of Air Cruisers Service Bulletin 103-25-17, dated November 10, 1989, certificated in any category. \n\n\tCompliance: Required within 3 years after the effective date of this AD, unless previously accomplished. \n\n\tTo assure that forward door evacuation slides will automatically inflate when needed, accomplish the following: \n\n\tA.\tModify affected slides by installing a frangible link in accordance with Air Cruisers Service Bulletin 103-25-17, dated November 10, 1989. \n\n\tB.\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, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA PrincipalMaintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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 Air Cruisers Company, P.O. Box 180, Belmar, New Jersey, 07719-0180. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6588, AD 90-09-11) becomes effective on June 4, 1990.
2020-06-13: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires determining the accumulated hours time- in-service (TIS) of certain part-numbered main gearbox (MGB) suspension bar attachment fittings (fittings) and bolts, and establishes new life limits. This AD was prompted by the outcome of tests and analyses performed by Airbus Helicopters. The actions of this AD are intended to address an unsafe condition on these products.
76-10-03: 76-10-03 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-2614. Applies to Model DH-104 airplanes, certificated in all categories not altered in accordance with Hawker Siddeley Aviation Ltd. Modification 1067. Compliance is required as indicated, unless already accomplished. To detect corrosion and cracking of the drag brace fittings at the center section spar lower cap, and prevent possible structural failure of the wing, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, inspect the drag brace fittings, P/N 4FS.1797(L.H.) and 4FS.1798(R.H.) for corrosion and cracks in accordance with paragraph No. 4, entitled "Inspection of Fittings," of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA- approved equivalent. (b) If a crack or evidence of severe corrosion is found in either drag brace fitting, during an inspection specified in paragraph (a) of this AD, before further flight, replace the drag brace fitting with an improved fitting, P/N 14FS.6069-70, in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA-approved equivalent. (c) "Severe corrosion" as used in this AD is internal corrosion that has progressed to a point where there is evidence of corrosion breaking through the exterior surface of the fitting. "Surface corrosion" as used in this AD means corrosion limited to surface pitting. NOTE: The Hawker Siddeley Aviation Ltd. Model DH-104 Maintenance and Repair Manual further defines the terms "severe corrosion" and "surface corrosion." (d) If, during an inspection specified in paragraph (a) of this AD, no crack is found and evidence of corrosion is found but it is limited to surface corrosion and does not constitute the severe corrosion specified in paragraph (b) of this AD, remove the corrosion, protectthe surface from further corrosion in accordance with FAR 43.13, and re-inspect the drag brace fittings in accordance with the inspection requirements of paragraph (a) of this AD, at intervals not to exceed 100 hours time in service from the last inspection. NOTE: Advisory Circular AC 43.13-1A "Acceptable Methods, Techniques and Practices-Aircraft Inspection and Repair" contains information relating to corrosion protection and removal. (e) If, during an inspection specified in paragraph (a) of this AD, no crack is found in the fittings, and the fittings are free of evidence of any corrosion, re-inspect the fittings in accordance with the inspection requirements of paragraph (a) of this AD at intervals not to exceed 100 hours time in service from the last inspection. (f) The repetitive inspections required by paragraphs (d) and (e) of this AD may be terminated upon the installation of the improved fitting P/N 14FS.6069-70, in accordance with the instructions set forth in paragraph 5.2 of Hawker Siddeley Aviation Ltd. Technical News Sheet, Series CT104, No. 230, dated April 9, 1973, or an FAA-approved equivalent. This amendment becomes effective June 1, 1976.
78-24-02: 78-24-02 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39- 3346. Applies to Agusta Model A109 Series helicopters, S/N 7107, 7111, 7126, and 7129, certificated in all categories. Compliance required before further flight, unless already accomplished, but helicopter may be flown in accordance with FAR 21.197 and 21.199 to a base where the required work can be performed. To prevent possible failure of main transmission P/N 109-0400-02-01, remove pinion gear P/N 109- 0403-06-01, S/N 18, 24, 25 or 27, from main transmissions S/N 31, 36, 11 and 10, respectively, and replace with new pinion gear of same part number having serial number other than 17 through 32. This amendment is effective November 24, 1978, as to all persons except those persons to whom it was made immediately effective by the letter dated April 26, 1978, which contained this amendment
2020-06-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a recent maintenance repair organization's report to Airbus of deviations from the component maintenance manual acceptance test procedure for certain trimmable horizontal stabilizer actuators (THSAs). This AD requires replacement of affected THSAs with serviceable THSAs, 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.