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92-11-03: 92-11-03 BRITISH AEROSPACE: Amendment 39-8253. Docket No. 91-NM-280-AD. Applicability: British Aerospace Model DH/BH/HS 125 series airplanes, excluding Models 125-600A, 700A, 800A, and 1000A series airplanes; as listed in British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wings, accomplish the following: (a) Within 3 months after the effective date of this AD, and thereafter at intervals not to exceed 4 years or 2,200 flights, whichever occurs first, perform an eddy current inspection on specified areas of the left and right wing upper skins to detect cracks in countersunk bolt holes in the wing skins and in the internal stringers, in accordance with British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991. (b) If cracks are discovered as a result of the eddy current inspection requiredby paragraph (a) of this AD, prior to further flight, perform a dye penetrant inspection, in accordance with British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991. (c) If cracks are discovered as a result of either the eddy current inspections required by paragraph (a) of this AD, or the dye penetrant inspection required by paragraph (b) of this AD, prior to further flight, repair the crack(s) as follows: (1) Cracks that do not exceed the limits specified in British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991, must be repaired in accordance with the procedures in the Service Bulletin. (2) Cracks that exceed the limits specified in British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991, must be repaired in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) An alternative method 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, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections and repairs shall be done in accordance with British Aerospace Service Bulletin S.B. 57-75, dated July 30, 1991. 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 British Aerospace, PLC. Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (g) This amendment becomes effective on July 9, 1992.
2013-03-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, & CL-604 Variants) airplanes. This AD was prompted by reports of cracking found on the upper and lower Web of the engine support beam. This AD requires revising the maintenance program. We are issuing this AD to detect and correct fatigue cracking of the engine support beam, which could result in failure of the engine support beam and affect the structural integrity of the airplane.
98-19-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Superior Air Parts, Inc., piston pins installed on Teledyne Continental Motors reciprocating engines. This amendment requires removal from service of defective piston pins, and replacement with serviceable parts. This amendment is prompted by reports of numerous piston pin fractures. The actions specified by this AD are intended to prevent a piston pin failure from causing secondary engine damage resulting in loss of oil or total power failure, and from causing jamming of the engine crankshaft resulting in a catastrophic engine failure.
74-20-09: 74-20-09 SIKORSKY AIRCRAFT: Amendment 39-1972 as amended by Amendment 39-2034 is further amended by Amendment 39-2829. Applies to all Sikorsky S-61A, S-61L, S- 61N, S-61R and S-61NM helicopters certificated in all categories that are equipped with S6115- 20501 series, S6115-20601 series, S6117-20101 series and S6188-15001 series main rotor blades. Compliance required as indicated. To prevent operation with loose or missing screws, or with cracks in the outboard end of the main rotor blades, including the tip cap and tip cap bracket, accomplish the following: (a) Inspect main rotor blades that do not have tip cap bracket doubler P/N 61070- 15120 installed, and have less than 2,000 hours time in service on the effective date of this AD, for loose or missing screws or for cracks at the outboard end of the main rotor blade spar, tip cap, or tip cap bracket, in accordance with Section 2., paragraphs A and B., of Sikorsky Service Bulletin No. 61B15-9F, dated November 2, 1976 orlater FAA approved revisions within the next 30 hours time in service after the effective date of this AD, unless already accomplished, and at intervals thereafter within 30 hours time in service from the last inspection. If screws are missing or loose, and cannot be secured, or if there is motion in the joint between the tip cap and the blade, or if cracks are found, replace the main rotor blade or repair it in accordance with Section 2., paragraph C., of the above service bulletin prior to further flight. If a crack is found in the tip cap, tip cap attachment land, or tip cap bracket, replace or repair the main rotor blade in accordance with Section 2., paragraph B., of the above service bulletin prior to further flight. (b) Inspect main rotor blades that do not have tip cap bracket doubler P/N 61070- 15120 installed, and have 2000 hours or more time in service on the effective date of this AD, for loose or missing screws or for cracks at the outboard end of the main rotor blade spar, tip cap, or tip cap bracket, in accordance with Section 2., paragraphs A and B, of the above Service Bulletin prior to the first flight of each day. If screws are missing or loose, and cannot be secured, or if there is motion in the joint between the tip cap and the blade, or if cracks are found, replace the main rotor blade or repair it in accordance with paragraph 2C of the above bulletin prior to further flight. If a crack is found in the tip cap, tip cap attachment land, or tip cap bracket replace or repair the main rotor blade, in accordance with Section 2., paragraph B., of the above service bulletin, prior to further flight. (c) Inspect main rotor blades that have tip cap bracket P/N 61070-15120 installed for cracks at the outboard end of the main rotor blade spar, tip cap, and tip cap bracket, in accordance with Section 2, paragraph B., of the above bulletin, within the next 50 hours time in service after the effective date of this AD, unless already accomplished,and at intervals thereafter within 50 hours time in service from the last inspection. If a crack is found in the tip cap, tip cap attachment land, or tip cap bracket, replace or repair the main rotor blade prior to further flight, in accordance with Section 2., paragraph B., of the above bulletin. (d) For helicopters operating at 19,500 pounds gross weight and below, inspect the outboard end of the main blades, series S6115-20501, series S6115-20601, series S6117-20101, and series S6188-15001, using the dye penetrant method, in accordance with Section 2., paragraph D., of the above Service Bulletin, within the next 200 hours time in service after the effective date of this AD, unless already accomplished, and at intervals thereafter within 200 hours time in service from the last inspection. If a crack is found, replace the main rotor blade prior to further flight. (e) For helicopters operating above a gross weight of 19,500 pounds, inspect the outboard end of the main rotorblades using the dye penetrant method, in accordance with Section 2., paragraph D., of the above Service Bulletin, within the next 50 hours time in service after the effective date of this AD, unless already accomplished, and at intervals thereafter within 50 hours time in service from the last inspection. If a crack is found, replace the main rotor blade prior to further flight. (f) Upon request of the operator, equivalent methods of compliance with the inspection and repair requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, New England Region. Repetitive inspection intervals specified in this AD may be adjusted, by the Chief, Engineering and Manufacturing Branch, New England Region, to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Amendment 39-1972 supersedes Amendment 39-1583 (38 F.R. 1501), AD 73-02-02. Amendment 39-1972 became effective October 4, 1974. Amendment 39-2034 became effective December 12, 1974. This Amendment 39-2829 becomes effective February 25, 1977.
81-02-02: 81-02-02 GENERAL ELECTRIC COMPANY: Amendment 39-4004. Applies to all General Electric CT58 turboshaft engines incorporating stage one turbine wheel, part number 4002T17P02, with the following wheel serial numbers: 7753, 7761, 7762, 7767, 7768, 7783, 7799, 7803, 7811, 7815, 7817, 7819, 7820, 7823, 7824, 7828, 7839, 7845, and 7846. Compliance required as indicated, unless already accomplished. To prevent failure of stage one turbine wheels due to cracks originating from undersize rabbet groove radii, inspect forward and aft radii in accordance with the procedures contained in the accomplishment instruction section of General Electric Alert Service Bulletin CT58 (A72-159) CEB-255, dated July 9, 1979, or later FAA approved revision, or equivalent means approved by the Chief, Engineering and Manufacturing Branch, New England Region. Inspect in accordance with the following schedule: 1. Turbine wheels with 3.950 hours or 7,900 cycles, or more, in service on the effective date of this AD, must be inspected within the next 50 hours or 100 cycles, whichever comes first. 2. Turbine wheels with less than 3,950 hours or 7,900 cycles in service, on the effective date of this AD, must be inspected prior to exceeding 4,000 hours or 8,000 cycles, whichever comes first. Stage one turbine wheels with forward or aft rabbet groove radii of less than 0.010 inch must be removed and replaced with serviceable turbine wheels prior to further flight. 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 General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents 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 FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective February 2, 1981.
47-22-03: 47-22-03 PIPER: (Was Mandatory Note 4 of AD-780-3.) Applies Only to PA-12 Aircraft Serial Numbers 12-1 and Up to 12-249 Except Serial Numbers 12-221, 12-236, 12-239 and 12-244. Compliance required prior to August 1, 1947. Reinforce the upper end of the tie strap on the landing gear with a 0.125 x 1 1/2 x 4 1/2, 4130 steel plate. Bend and trim to fit and install over end of strap by edge welding. (Piper Service Bulletin No. 93 dated August 8, 1946, covers this same subject.)
84-20-51: 84-20-51 GARRETT TURBINE ENGINE COMPANY (GTEC) (formerly AiResearch Manufacturing Company of Arizona): Amendment 39-4965. Applicable to all engine models ATF3-6-4C, -6A-3C, and -6A-4C with exhaust deflector liner and seal assembly, Garrett part number (P/N) 3001313-11 through -14, installed. Compliance required as indicated unless already accomplished. To prevent the possibility of an uncontained engine failure, accomplish the following: A. Prior to the accumulation of an additional 5 hours in service, after the effective date of this AD, and at intervals not to exceed 25 operational hours thereafter, until incorporation of the exhaust deflector liner and seal assembly bolted flange system as specified in Section 2.A., "Accomplishment Instructions," of GTEC SB ATF3-72-6092, dated May 25, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office, visually inspect the stationary seal/sixth stage low pressure turbine rotor assembly area of allaffected engines for evidence of seal/rotor contact and/or seal looseness as specified in the following GTEC Light Maintenance Manual Revisions, or equivalent approved by the Manager, Western Aircraft Certification Office: ENGINE MODEL MANUAL REFERENCE ATF3-6-4C Light Maintenance Manual Report No. 72-00-52, Revision 6 dated November 15, 1983; Temporary Revision No. 72-88, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-89, 72-00-00, Trouble Shooting dated April 16, 1984. ATF3-6A-3C Light Maintenance Manual Report No. 72-03-32, Revision 3 dated November 15, 1983; Temporary Revision No. 72-43, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-44, 72-00-00, Trouble Shooting dated April 16, 1984. ATF3-6A-4C Light Maintenance Manual Report No. 72-03-42, Revision 4 dated November 15, 1983; Temporary Revision No. 72-44, 72-00-00, Trouble Shooting dated April 16, 1984; and Temporary Revision No. 72-45, 72-00-00, TroubleShooting dated April 16, 1984. B. Engines with unsuccessful inspection results found during the accomplishment of paragraph A above are to be disassembled as required to modify the exhaust deflector liner and seal assembly and to inspect the sixth stage turbine rotor assembly. C. Upon removal of the sixth stage low pressure turbine rotor assembly from an affected engine for any reason or within 200 operating hours after the effective date of this AD or prior to April 15, 1985, whichever comes first, incorporate the new exhaust deflector liner and seal assembly bolted flange system as specified in Section 2.A., "Accomplishment Instructions," of GTEC SB ATF3-72-6092, dated May 25, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent meansof compliance with the requirements of this AD may be approved by the Manager, Western Aircraft Certification Office, Northwest Mountain Region, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. 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 person affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, P.O. Box 5217, Phoenix, Arizona 85010; telephone (602) 231-1000. These documents also may be examined at Office of the Regional Counsel, New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment supersedes Amendment 39-4900 (49 FR 35614), AD 84-11-51. This amendment becomes effective December 26, 1984, to all persons except those persons to whom it was made immediately effective by telegraphic AD T84-20-51, issued October 4, 1984.
2013-03-02: We are superseding an existing airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N1, AS-365N2 and AS 365 N3 helicopters. That AD currently requires inspecting certain tail rotor hubs (TRH) for a crack and removing any cracked TRH. This AD requires the same actions but adds more part numbers to the list of affected TRHs. This AD is prompted by further analysis that indicates that additional part-numbered TRHs must be inspected for cracks. The actions specified by this AD are intended to detect a crack in the TRH and prevent the tail rotor from jamming, which could lead to reduced or loss of control of the helicopter.
2013-03-15: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S airplanes. This AD was prompted by reports of chafing of a new configuration of the fuel return line assembly, which was caused by the fuel return line assembly rubbing against the right steering tube assembly during rudder pedal actuation. This AD requires you to install the forward and aft fuel return line support clamps and brackets; inspect for a minimum clearance between the fuel return line assembly and the steering tube assembly and clearance between the fuel return line assembly and the airplane structure; and, if any damage is found, replace the fuel return line assembly. We are issuing this AD to correct the unsafe condition on these products.
98-19-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacing the radio tuning units (RTU's) and associated components with new, improved parts. 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 prevent NAV/COM radios from simultaneously changing tuned frequencies and transponder codes due to a black screen failure or "blanking" of an RTU, which could result in loss of communications capability and air traffic control data.