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74-26-05: 74-26-05 PRATT & WHITNEY AIRCRAFT and UNITED AIRCRAFT OF CANADA, LIMITED: Amendment 39-2046. Applies to all Pratt & Whitney Aircraft and United Aircraft of Canada Limited JT15D-1 and JT15D-4 turbofan engines containing fuel control P/Ns 3022332 and 3023349. Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished. To prevent fuel leaks, inspect fuel control units for possible interference between the fuel outlet housing and the fuel control main body by placing a .003 inch feeler gage between the mating faces of the fuel outlet housing (P/N 3240082) and the fuel control main body (P/N 3240451). If the feeler gage can be inserted between the mating faces, replace fuel control with dimensionally correct fuel control prior to next flight. United Aircraft of Canada Limited's Special Instruction No. 3-74, dated September 20, 1974, pertains to this subject. This amendment becomes effective January 2,1975.
85-18-06: 85-18-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5541. Applies to all Bell Helicopter Model 214B/B1 and 214ST series helicopters certificated in all categories. Compliance is required within the next 10 hours' time in service, unless previously accomplished, and thereafter at 250 hour intervals. To prevent failure of the main rotor drag brace accomplish the following: (a) Inspect main rotor drag brace assembly, Part Number (P/N) 214-010-113-001 or 003, in accordance with Bell Helicopter Textron, Inc. (BHTI), Alert Service Bulletin 214-85-28, dated September 3, 1985, or 214ST-85-29, dated September 3, 1985, as applicable. (b) If cracks are found, or if corrosion is found which cannot be removed within the limits of the rework criteria in the Alert Service Bulletins, replace with serviceable parts. (c) An alternative means of compliance or adjustment of the compliance time, which provides an equivalent level of safety, must be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This procedure shall be done in accordance with BHTI Alert Service Bulletin 214-85-28, dated September 3, 1985, or 214ST-85-29, dated September 3, 1985, as applicable. 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of Regional Counsel, FAA, 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 April 20, 1987, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 85-18-06, issued September 11, 1985, which contained this amendment.
86-24-10: 86-24-10 BRITISH AEROSPACE, PLC, Aircraft Group, Civil Division-Prestwick: Amendment 39-5480. Applies to Jetstream Model 3101 (including 3100) (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent engine flameout when in or departing an icing environment, accomplish the following: (a) Revise the airplane Pilot's Operating Handbook and Airplane Flight Manual (POH/AFM) by inserting Appendix 1 of this AD in the "LIMITATIONS" section of the POH/AFM. Appendix 1 procedures supersede any other POH/AFM procedures which may be contradictory. (b) The requirements of paragraph (a) of this AD are no longer required when the airplane is modified by the addition of an FAA approved automatic-relite ignition system. NOTE: Automatic-relite ignition is a system which automatically energizes engine ignition without pilot action when engine RPM or torque decays below a specified level, and deenergizes engine ignition when RPM or torque exceeds the specified level. It is not synonymous with CONTINUOUS IGNITION. (c) The requirements of paragraph (a) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent method of compliance with this AD, if used, must be approved by contacting the Manager, Brussels Certification Office, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium; Telephone 513.38.30, extension 2710/2711. All persons affected by this AD may obtain copies of the document referred to herein upon request to GTEC, Post Office Box 5217, Phoenix, Arizona 85010; or British Aerospace, Engineering Department, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on December 15, 1986. APPENDIX 1 Supplement to the POH/AFM BAe Model 3101 Airplanes "The ENGINE ICE PROTECTION switch shall be selected to ANTI-ICE/IGN during all operations in actual or potential icing conditions described herein: (1) During takeoff and climb out in actual or potential icing conditions. *(2) When ice is visible on, or shedding from propeller(s), spinner(s), or leading edge(s). (3) Immediately, any time engine flameout occurs as a possible result of ice ingestion. (4) During approach and landing while in or shortly following flight in actual or potential icing conditions. *NOTE: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to ANTI-ICE/IGN position. If the engine runs satisfactorily, switch the second ENGINE system to the ANTI-ICE/IGN position and check that the second engine continues to run satisfactorily. CAUTION Flight in actual or potential icing conditions will be limited by duty cycle of the ignition system. Ignition system time limits must be observed to prevent exceeding duty cycle times. Operator should verify these limits for his particular installation. "Potential icing conditions in precipitation or visible meteorological conditions: (1) Begin when the OAT is plus 5 degrees C (plus 41 degrees F) or colder, or (2) End when the OAT is plus 10 degrees C (plus 50 degrees F) or warmer." The procedures and conditions described in this appendix supersede any other POH/AFM procedures and conditions which may be contradictory.
2010-17-18 R1: We are revising an existing airworthiness directive (AD) for Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. That AD currently requires you to repetitively inspect (using the eddy current method) the two outboard fastener holes in both of the wing main spar lower caps at the center splice joint for cracks and repair or replace any cracked spar, and changes the safe life for certain serial (SN) ranges. This AD retains the actions of AD 2010-17-18 and reduces the applicability from all serial numbers beginning with SN- 0001 as required by the previous AD to SN-0001 through SN-0269. This AD was prompted by our evaluation of a comment from David Ligon, Air Tractor, and our determination that we should reduce the applicability from that already required by the previous AD. We are issuing this AD to detect and correct cracks in the wing main spar lower cap at the center splice joint, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane.
86-10-05: 86-10-05 PRATT & WHITNEY CANADA: Amendment 39-5266. Applies to Pratt & Whitney Canada (PWC) PT6A-42 turboprop engines. Compliance is required as indicated unless already accomplished. To prevent first stage compressor hub failure, and possible engine failure, accomplish the following: Remove from service Part Number (P/N) 3030356 first stage compressor hub on PWC Engine Model PT6A-42 with engine Serial Numbers 93001 thru 93804 inclusive at or before 5,000 total cycles in accordance with PWC Service Bulletin (SB) 3002, Revision 12, dated November 9, 1983, or FAA approved equivalent. NOTE: The 15,000 hour life limit remains unaffected by this airworthiness directive (AD). 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. PWC SB 3002, Revision 12, dated November 9, 1983, is 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 this document from the manufacturer may obtain copies upon request to Pratt & Whitney Canada, Longueuil, Quebec, Canada, J4K-4X9. This document also may be examined at the Office of the Regional Counsel, Rules Docket 85-ANE-29, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on June 5, 1986.
2010-26-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: \n\n\tDuring maintenance on one aircraft, it was discovered that the overpressure capsules were broken on both pressurization valves. Failure of the pressurization control regulating valve (overpressure capsule) will affect the aircraft's overpressure protection * * *. \n\n* * * * *\n\n\tThe unsafe condition is overpressurization, which can result in injury to the occupants and possible structural failure leading to loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
84-15-06: 84-15-06 McDONNELL DOUGLAS: Amendment 39-4896. Applies to McDonnell Douglas DC-10 and KC-10A (military) airplanes, certificated in all categories. Compliance required within 30 days after the effective date of this AD unless previously accomplished. \n\n\tTo determine wire harness condition and ensure proper wire routing, accomplish the following: \n\n\tA.\tInspect both the left-hand and right-hand wiring bundles beneath the cockpit glareshield for chafing and proper routing in accordance with Douglas All Operators Letter 10-1759, dated May 30, 1984, and Service Sketch 3597. \n\n\tB.\tRepair all chafed wires by replacement or use of methods outlined in the Douglas DC-10 Maintenance Manual. \n\n\tC.\tVerify proper routing of both the left-hand and right-hand wire bundles beneath the cockpit glareshield over the fluorescent light shroud in accordance with Douglas All Operators Letter 10-1759, dated May 30, 1984, and Service Sketch 3597. \n\n\tD.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\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 these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective August 20, 1984.
2010-24-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires doing a one-time general visual inspection for a keyway in two fuel tank access door cutouts, and related investigative and corrective actions if necessary. This AD was prompted by reports of cracks emanating from the keyway of the fuel tank access hole. We are issuing this AD to detect and correct such cracking, which could result in the loss of the lower wing skin load path and consequent structural failure of the wing.
86-21-01: 86-21-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5431. Applies to all Aerospatiale Model SA 365 series helicopters certificated in all categories. Compliance is required as indicted, unless already accomplished. To prevent failure of the main rotor head sleeves, accomplish the following: (a) For those helicopters exhibiting a severe tracking defect, inspect the main rotor head sleeves as follows before further flight: (1) Remove main rotor blades and visually inspect the sleeves for cracks, delaminations, or separated bushes; and (2) Replace any sleeves found damaged with serviceable sleeves. (b) For Model SA 365C, C1, C2, and C3 helicopters, replace Part Numbers (P/N's) 365A.31.1831.00, .01, .02, .03, and 365A31.1851.00 and .01 main rotor head sleeves as follows: (1) For sleeves which have 1,900 or more hours' time in service on the effective date of this AD, replace the sleeves within 100 hours' time in service; and(2) For sleeves which have less than 1,900 hours' time in service on the effective date of this AD, replace the sleeves before they reach 2,000 hours' time in service. (c) For Model SA 365N and N-1 helicopters, replace P/N's 365A31.1829.02 and .03 and 365A31.1828.00 and .01 main rotor head sleeves as follows: (1) For sleeves which have 900 or more hours' time in service on the effective date of this AD, replace the sleeves within 100 hours' time in service; and (2) For sleeves which have less than 900 hours' time in service on the effective date of this AD, replace the sleeves before they reach 1,000 hours' time in service. (d) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101, or by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (e) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the maintenance required by this AD may be accomplished. NOTE: Aerospatiale Telex Service SA 365C Nos. 01.18 and .01.19 and Aerospatiale Telex Service SA 365N-FS No. 01.18 pertain to this subject. This amendment becomes effective October 24, 1986.
87-25-06: 87-25-06 BRITISH AEROSPACE: Amendment 39-5788. Applies to all Model H.S. 748 series airplanes as listed in BAe Service Bulletin 78/9, Revision 1, dated September 1985, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent inflight loss of the jet pipe or restricted fuel drainage through the jet pipe retention assemblies, with resultant fire or heat damage to the nacelle and wing, accomplish the following: A. Within the next 60 days after the effective date of this AD, perform an inspection to ensure correct installation of the three retaining plate assemblies, which secure the jet pipe inside the jet pipe manifold, in accordance with British Aerospace Service Bulletin 78/9, Revision 1, dated September 1985. Any discrepancies found must be corrected prior to further flight. B. Repeat the inspection required by paragraph A. above, any time the jet pipe is replaced. C. 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. D. 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 proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective January 19, 1988.