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90-24-06: 90-24-06 GARRETT ENGINE DIVISION, ALLIED-SIGNAL, INC. (formerly Garrett Turbine Engine Co., GTEC, formerly AiResearch Manufacturing Company of Arizona): Amendment 39-6685. Docket No. 90-ANE-15. Applicability: Models TFE731-2, -2A, -3, -3A, -3AR, -3B, -3BR, -3R, -5, -5AR, and -5R turbofan engines equipped with thermocouple lead assemblies, part numbers (P/N) 3073950-1/-2/-7/-15, 3074175-1, and P/N 3073950-1 reworked to P/N 3077031-1/-2, installed in aircraft certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent overtemperature and damage of turbine components, accomplish the following: a. Remove from service and replace with a serviceable part thermocouple lead assemblies with serial numbers listed in Table 1, in Garrett Service Bulletin (SB) TFE731-A77-3020, dated April 27, 1990, within 25 operating hours in service after the effective date of this AD, in accordance with the accomplishment instructions of the above Garrett SB. Engines with thermocouple lead assemblies with serial numbers having a "T" suffix are excluded from the requirements of this AD. b. Test suspect lead assemblies in accordance with Accomplishment Instructions of Garrett SB TFE731-A77-3020, to determine if additional maintenance action is required before further operation of the engine in service. c. Remove from service engines that had suspect lead assemblies removed as required by paragraph a. of this AD, in which the removed lead assembly tested faulty, until the engine has been determined to be airworthy in accordance with the accomplishment instruction of the SB. d. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. e. Upon submission of substantiating data by an owner or operator through a FAA Airworthiness Inspector, the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 3229 East Spring Street, Long Beach, California 90806- 2425, may approve an equivalent means of compliance or an adjustment of the compliance schedule which provides an equivalent level of safety. The removal, replacement, and testing of certain thermocouple lead assemblies and the testing of certain engines shall be done in accordance with Garrett SB TFE731-A77-3020, dated April 27, 1990. 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 Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85034. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW., Room 8301, Washington, DC 20591. This amendment (39-6685, AD 90-24-06) becomes effective on November 13, 1990.
2015-22-02: We are superseding emergency airworthiness directive (AD) No. 2015-16-51 (Emergency AD 2015-16-51) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. Emergency AD 2015-16-51 required inspections of each inboard and outboard tail rotor pitch link assembly for axial or radial bearing play, and if there was axial or radial bearing play, removing the tail rotor pitch link and inspecting for wear. Emergency AD 2015-16-51 was prompted by several reports of worn tail rotor pitch link spherical bearings. We are issuing this supersedure to retain the inspection requirements in Emergency AD 2015- 16-51 while revising the applicability and compliance time to clarify that all Bell Model 429 helicopters require recurring inspections regardless of hours time-in-service (TIS) accumulated on the helicopter. These actions are intended to prevent pitch link failure and subsequent loss of control of the helicopter.
2002-13-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -30F (KC10A and KDC-10), -40, and -40F airplanes; Model MD-10-10F and -30F airplanes; and Model MD-11 and -11F airplanes. This AD requires repetitive tests for electrical continuity and resistance and repetitive inspections to detect discrepancies of the fuel boost/transfer pump connectors; and corrective actions, if necessary. This action is necessary to prevent arcing of connectors in the fuel boost/transfer pump circuit, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
87-01-02: 87-01-02 BOEING: Amendment 39-5494. Applies to all Model 747 airplanes, certificated in any category, equipped with the single-piece escape slide at Door No. 3. To ensure that the escape slide pack remains in proper position on the door in the event of a minor crash landing, accomplish the following, unless already accomplished: \n\n\tA.\tWithin twelve months after the effective date of this AD, modify the escape slide attachment in accordance with Boeing Alert Service Bulletin 747-25A2710, dated July 15, 1986, or later FAA-approved revisions. \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\tC.\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 the modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\tThis amendment becomes effective January 20, 1987.
2025-01-01: The FAA is adopting a new airworthiness directive (AD) for certain Britten-Norman Aerospace Ltd. Model BN-2, BN-2A, BN-2A-2, BN- 2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A- 27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, BN2T-4R, and BN2T-4S airplanes; and certain Model BN2A MK. III, BN2A MK. III-2, and BN2A MK. III-3 airplanes. This AD was prompted by the determination that, in order to ensure the continued structural integrity of certain landing gear and associated components, it is necessary to require removal of these components from service prior to exceeding established fatigue lives. This AD requires determining the number of landings on affected main landing gears (MLGs), nose landing gears (NLGs), and associated components; removing from service any part that has reached or exceeded the established fatigue life and installing a replacement part; and prohibiting the installation of any affected part unless the number of landings for that part is below the established fatigue life. The FAA is issuing this AD to address the unsafe condition on these products.
2015-22-03: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4164, PW4168, PW4168A, PW4164C, PW4164C/B, PW4164-1D, PW4168-1D, PW4168A-1D, PW4170, PW4164C-1D, PW4164C/B-1D, PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines including models with a ``-3'' suffix with a low-pressure turbine (LPT) 4th stage inner air seal (IAS), part number (P/N) 51N038, installed. This AD was prompted by the discovery, during routine overhaul of the LPT, of cracks in the barrel section of the LPT 4th stage IAS. This AD requires removal of the LPT 4th stage IAS, P/N 51N038, according to a prescribed schedule. We are issuing this AD to prevent failure of the LPT 4th stage IAS, which could lead to an uncontained IAS release, damage to the engine, and damage to the airplane.
89-03-07: 89-03-07 BRITISH AEROSPACE (BAe) PLC: Amendment 39-6118. Applicability: Model HP 137 Mk l Jetstream Model 200, and Jetstream Model 3101 (includes Model 3100) (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated in the body of the AD after the effective date of this AD, unless already accomplished. To prevent reduction of strength of the main wing spar attachment structure, accomplish the following: (a) Upon the accumulation of 4,000 landings or within the next 400 landings, whichever occurs later, and thereafter at intervals of 2,000 landings, visually or dye penetrant inspect, as required, the Part Number (P/N) 13707B99 and P/N 13707B100 shear angles for cracks as described in BAe Alert Service Bulletin (ASB) Jetstream 57-A-JA880144, dated June 14, 1988, Section 2, ACCOMPLISHMENT INSTRUCTIONS. (1) If a crack is detected that is 1-1/2 inch (37 mm) in total length, or 1 inch (25 mm) vertically or longer, prior to further flight modify the airplane in accordance with BAe Modification JM5303, dated June 14, 1988, by replacing the shear angles with P/N 13707B125 and P/N 13707B126 shear angles. (2) If a crack is detected that is less than 1 inch vertically or 1-1/2 inch total length, re-inspect the shear angles thereafter at intervals not to exceed 100 landings, and prior to an additional 400 landings modify the airplane in accordance with BAe Modification JM5303, dated June 14, 1988. (b) If no record of landings is available, 1 hour time-in-service equals 2 landings may be used in determining the compliance times in this AD. (c) The inspections described in paragraph (a) above are not required when the airplane's left and right shear angles have been modified by BAe Modification JM5303, dated June 14, 1988. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace PLC, Manager, Product Support, Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6118, AD 89-03-07) becomes effective on February 26, 1989.
85-26-04: 85-26-04 FOKKER B.V.: Amendment 39-5195. Applies to Model F27 airplanes as indicated in the applicability statement of each service bulletin listed below, certificated in any category. Compliance is required within the time interval specified in each of the following paragraphs, unless already accomplished: A. To prevent collapse of the main landing gear, within 120 days after the effective date of this AD, inspect the drag stay tube for cracks, in accordance with Fokker Service Bulletin F27/32-147 dated September 1, 1981, and replace if cracks are found. B. To prevent damage to the elevator trim tab, the elevator control bracket support, and the elevator control bracket supporting rib structure, modify the structure in accordance with Fokker Service Bulletin F27/55-31 dated May 31, 1965, within 120 days after the effective date of this AD. C. To prevent failure of the wing/fuselage joint, inspect and modify the joint in accordance with Fokker Service Bulletin F27/57-54, Revision 1, dated April 2, 1984, within 180 days after the effective date of this AD or prior to the accumulation of 45,000 landings, whichever occurs later. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. E. 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. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Manager, Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 EastMarginal Way South, Seattle, Washington. This amendment becomes effective January 26, 1986.
87-18-11: 87-18-11 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC) (Hughes Helicopters, Inc.): Amendment 39-5678. Applies to all Model 369D, E, F, and FF helicopters, certificated in any category, equipped with MDHC main transmission (P/N 369D25100-BSC or- 501) which has tail rotor output drive pinion shaft (P/N 369D25125-BSC or -11) installed. Compliance is required as indicated, unless previously accomplished. To prevent possible loss of tail rotor control, accomplish the following: (a) Within the next 25 hours' time-in-service after the effective date of this AD, perform a one-time magnetic particle and visual inspection on the main transmission tail rotor output drive pinion shaft (P/N 369D25125-BSC or -11) on helicopters with the following serialized main rotor transmission in accordance with procedures detailed in paragraphs (c) through (f) of this AD. TRANSMISSION SERIAL NUMBER 1989 1992 and 1993 1998 through 2000 2002 through 2082 2084 and 2085 If the tail rotor output drive pinion shaft serial number is contained in the list below, remove the shaft from service prior to further flight. TAIL ROTOR OUTPUT DRIVE PINION SHAFT SERIAL NUMBERS 1474 through 1502 1504 through 1547 1549 through 1561 1563 and 1564 1566 (b) Within the next 100 hours' time-in-service after the effective date of this AD, perform a one-time magnetic particle and visual inspection on the main transmission tail rotor output drive pinion shaft (P/N 369D25125-BSC or -11) on all affected helicopters with transmission serial numbers other than those listed above in accordance with procedures detailed in paragraphs (c) through (f) of this AD. (c) Verify that the tail rotor output drive pinion shaft has an undercut style fillet radius as shown in Figure 1 of MDHC Mandatory SIN DN-147/EN-35/FN-24, dated April 23, 1987, or FAA-approved equivalent. Remove parts which do not have the undercut from service prior to further flight. NOTE:Tail rotor output drive pinion shafts removed from service in accordance with paragraph (c) may be returned to MDHC for rework if a magnetic particle inspection of the part does not show any crack indications. (d) Perform a magnetic particle inspection of the tail rotor output drive pinion shaft. Remove parts which show indications of cracking found during magnetic particle inspection from service prior to further flight. (e) Inspect the tail rotor output drive pinion shafts for scratches, tooling marks, corrosion, or other minor surface defects in the fillet radius or elsewhere on the shaft in accordance with paragraphs c. (4), c. (5), and c. (6) of MDHC Mandatory SIN DN-147/EN- 35/FN-24, dated April 23, 1987. Prior to further flight, rework discrepant shafts that show no indication of cracks in accordance with procedures stated in paragraph d. of MDHC Mandatory SIN DN-147/EN-35/FN-24, dated April 23, 1987. (f) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. The procedure shall be done in accordance with MDHC SIN DN-147/EN-35/FN-24, dated April 23, 1987. This incorporation by reference was approved by the Director of-the Federal Register in accordance with 5 U.S.C. 552 (a) (1). Copies may be obtained from MDHC, 500 E. McDowell Road, Mesa, Arizona. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L. Street, NW., Room 8401, Washington, D.C. This amendment becomes effective September 1, 1987.
74-09-06: 74-09-06 CONSOLIDATED AERONAUTICS: Amendment 39-1826. Applies to all Model LA-4-200 airplanes through Serial Number 601. Compliance required, unless already accomplished, within the next twenty-five (25) hours time in service after the effective date of this AD. To preclude the possibility of engine stoppage resulting from contamination in the fuel injector, accomplish the following: 1. Inspect the restrictor fitting, P/N 2-6750-41, to determine if it has a flush or recessed insert in accordance with Lake Aircraft, Division of Consolidated Aeronautics, Service Bulletin No. B51, or later FAA approved revision. 2. If the restrictor fitting has a recessed insert, no further action is required. 3. If the restrictor fitting has a flush insert, accomplish the following: a. Disassemble and clean the areas of the fuel injector specified in Lake Aircraft, Division of Consolidated Aeronautics, Service Bulletin No. B51, or later FAA approved revision or by FAA approved equivalent method. b. Remove the restrictor fitting and replace with P/N 2-6750-83, or later FAA approved equivalent. 4. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. 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 Chief Engineer, Lake Aircraft, Division of Consolidated Aeronautics, Inc., P. O. Box 312, Sanford, Maine 04073. These documents may also be examined at the Office of the Regional Counsel, New England Region, FAA, 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 theincorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. This amendment becomes effective May 10, 1974.