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93-14-13: 93-14-13 TEXTRON LYCOMING: Amendment 39-8637. Docket 91-ANE-55. Applicability: Textron Lycoming ALF502R and ALF502L turbofan engines installed on but not limited to British Aerospace BAe-146 and Canadair Challenger CL600 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent third stage turbine disk failure, which could result in engine shutdown, accomplish the following: (a) For ALF502R series engines with installed third stage turbine rotor shaft assemblies, Part Number (P/N) 2-143-040-12, P/N 2-143-040-15, or P/N 2-143-040-16, rework the third stage turbine disk blade slots and mark the third stage turbine assembly with a new part number in accordance with the Accomplishment Instructions of Textron Lycoming Service Bulletin (SB) No. ALF502R 72-270, dated March 31, 1992, or replace with a serviceable part as follows: (1) For third stage turbine disks with 15,000 or more cycles in service (CIS) on the effective date of this AD, within 1,000 CIS after the effective date of this AD. (2) For third stage turbine disks with 10,000 or more CIS but less than 15,000 CIS on the effective date of this AD, within 1,000 CIS, after the effective date of this AD, or at the next shop visit, whichever occurs later, but prior to accumulating 16,000 CIS since new. (3) For third stage turbine disks with less than 10,000 CIS on the effective date of this AD, at the next blade removal, but prior to accumulating 13,000 CIS since new. (4) For third stage turbine disks not reworked in accordance with the requirements of this AD and installed on Textron ALF-502R engines as replacement disks when complying with this paragraph, accomplish the requirements of this paragraph as to that replacement disk. (b) For ALF502L series engines with installed third stage turbine rotor shaft assemblies, Part Number (P/N) 2-143-040-10, P/N 2-143-040-11, P/N 2-143-040-12, P/N 2-143-040-15, or P/N 2-143-040-16, rework the third stage turbine disk blade slots and mark the third stage turbine assembly with a new part number in accordance with the Accomplishment Instructions of Textron Lycoming SB ALF502L 72-270, dated April 30, 1993, or replace with a serviceable part as follows: (1) For third stage turbine disks with 15,000 or more CIS on the effective date of this AD, within 1,000 CIS after the effective date of this AD. (2) For third stage turbine disks with 10,000 or more CIS but less than 15,000 CIS on the effective date of this AD, within 1,000 CIS after the effective date of this AD or at the next shop visit, whichever occurs later, but prior to accumulating 16,000 CIS since new. (3) For third stage turbine disks with less than 10,000 CIS on the effective date of this AD, at the next blade removal, but prior to accumulating 13,000 CIS since new. (4) For third stage turbine disks not reworked in accordance with the requirements of this AD and installed on Textron Lycoming ALF-502L engines as replacement disks when complying with this paragraph, accomplish the requirements of this paragraph as to that replacement disk. (c) For the purpose of this AD, a shop visit is defined as the induction of an engine into a shop for maintenance. (d) An 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (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 rework and reidentification shall be done in accordance with the following Textron Lycoming service bulletins: Document No. Pages Revision Date ALF502R 72-270 1-4 1 March 31, 1992 5 Original June 28, 1991 6-7 1 March 31, 1992 8-10 Original June 28, 1991 Total pages: 10 ALF502L 72-270 1-13 Original April 30, 1993 Total pages: 13 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 Textron Lycoming, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2015-21-01: We are adopting a new airworthiness directive (AD) for all Technify Motors GmbH TAE 125-02 reciprocating engines with a dual mass flywheel installed. This AD requires installation of a start phase monitoring system and associated specified software. This AD was prompted by reports of a gearbox drive shaft breaking during starting or restarting of the engine. We are issuing this AD to prevent overload and failure of the gearbox drive shaft, which could result in failure of the engine, in-flight shutdown, and loss of control of the airplane.
51-20-02: 51-20-02 MARTIN: Applies to All Models 202 and 202A Airplanes, Except as Noted. Compliance required as specified. In order to comply with recommendations of the Martin 202 Modification Board, the following items must be accomplished. In all cases, modifications which are demonstrated to provide a level of safety equivalent to that provided by the modifications listed herein will be acceptable in lieu of the listed modifications. 1. Compliance required not later than January 1, 1952. (a) Cover heater ignition interlock relay box tightly. (Applies to Model 202 airplanes only.) (b) Cover autopilot servo control relay box tightly. (Applies to Model 202 airplanes only.) (c) Cover AC distribution panel tightly or replace with enclosed relays. (d) Enclose all uncovered relays in the DC distribution panel in a box or replace with enclosed relays. (e) Cover heating and ventilating control box tightly. 2. Compliance required not later than November 15, 1951. Either replace present dural crossfeed line with a continuous piece of fire-resistant hose where it passes through the fuselage and relocate the fittings to a location outboard of the fuselage, or provide adequately drained liquid and vapor-proof shroud for the fuel crossfeed line where it passes through the main electrical compartment in the fuselage. (Glenn L. Martin Service Bulletin No. 173 covers one method of compliance with this item.) (Applies to Model 202 airplanes only.) 3. Compliance required not later than March 1, 1952. Make electrical hydraulic pump explosion proof. (Glenn L. Martin Service Bulletin No. 188, issued for the Model 202A, covers this same subject and may be used for both 202 and 202A airplanes.) 4. Compliance required not later than March 1, 1952. Install separate circuit breakers for the pitot tube heater circuits. (Glenn L. Martin Service Bulletin No. 118, issued for the Model 202A, covers this same subject and may be used for both 202 and 202A airplanes.) 5. Compliance required not later than March 1, 1952. Replace all 75ST aileron hinge fittings with steel parts. (Glenn L. Martin Maintenance Note No. 164 covers this same subject.) (Applies to Model 202 airplanes only.)
2000-16-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300 B2 and B4 series airplanes, that currently requires inspection of the fuselage longitudinal lap joints and circumferential joints, and of the stringers and doublers for bonding delamination and cracks; and repairs, as necessary. This amendment requires expansions of certain inspection areas; revisions of certain inspection thresholds or intervals; changes in references to inspection methods; and the addition of a modification to certain longitudinal lap joints. 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 delamination and cracking of the fuselage, which could result in rapid decompression of the airplane.
2015-21-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD was prompted by reports of un-annunciated failures of the direct current (DC) starter generator, which caused caution indicators of the affected systems to illuminate and prompted emergency descents and landings. This AD requires replacing the DC generator control units (GCUs) with new GCUs and replacing the GCU label. We are issuing this AD to prevent a low voltage condition on the left main DC bus, which, during critical phases of flight, could result in the loss of flight management, navigation, and transponder systems, and could affect continued safe flight.
92-19-08: 92-19-08 FAIRCHILD AIRCRAFT (formerly Swearingen Aviation Corporation): Amendment 39-8366. Docket No. 92-CE-09-AD. Supersedes AD 81-02-01, Amendment 39-4009. Applicability: The following model and serial numbered airplanes, certificated in any category: Model Serial Numbers SA226-T all serial numbers SA226-T(B) all serial numbers SA226-AT all serial numbers SA226-TC all serial numbers SA227-TT TT421 through TT444 SA227-AT AT423 through AT440 SA227-AC AC406, AC415, AC416, and AC420 through AC448 NOTE 1: The only SA227 series airplanes affected by this AD are those manufactured before the production change that incorporated rudder pedal links with bushings that more efficiently prevent wear. Compliance: Required upon the accumulation of 5,000 hours time-in-service (TIS) or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished within the last 5,000 hours TIS (superseded AD 81-02-01, Amendment 39-4009), and thereafter at intervals not to exceed 5,000 hours TIS. To prevent failure of the rudder cable to rudder pedal link attachments, which could result in loss of control of the airplane, accomplish the following: (a) Remove and discard the rudder cable to rudder pedal link attachment bolts and bushings, and prior to further flight, accomplish the following in accordance with the instructions in either Swearingen Aviation Corporation Service Bulletin (SB) 27-027, issued: July 17, 1980; or Fairchild SB 227-27-029, issued: June 6, 1991, whichever is applicable, and the applicable maintenance manual: (1) Inspect the rudder pedal links, part number 26-72016, for elongated holes. (2) Replace any rudder pedal links that have elongated holes. (3) Install new rudder pedal link attachment bolts and bushings. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location wherethe requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office. (d) The inspections and modifications required by this AD shall be done in accordance with either Swearingen Aviation Corporation Service Bulletin 27-027, issued: July 17, 1980; or Fairchild Service Bulletin 227-27-029, issued: June 6, 1991, whichever is 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 Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment (39-8366) supersedes AD 81-02-01, Amendment 39-4009. (f) This amendment becomes effective on October 16, 1992.
90-14-08: 90-14-08 PRATT & WHITNEY: Amendment 39-6428. Docket No. 89-ANE-15. Applicability: Pratt & Whitney (PW) JT9D-7R4D and -7R4E turbofan engines installed on Boeing B767 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent engine overtemperature and loss of power or engine shutdown inflight, accomplish the following: (a) Adjust the engine vane and bleed control (EVBC), Hamilton Standard, Part Number (P/N) 776555-3, to the 1.27 engine pressure ratio (EPR) bleed trim, and Hamilton Standard, P/N 776555-5, to 1.27 EPR in accordance with the instructions of Appendix 2 of this AD, (unless already adjusted to 1.32 EPR bleed trim in accordance with the instructions of Appendix 1 of this AD) as follows: (1) Within 5 calendar days or 50 cycles in service after the effective date of this AD, whichever occurs later, for those engines with 4,000 or more cycles in service on the effective date of this AD, or since last high pressure compressor (HPC) overhaul. (2) Within 15 calendar days or 150 cycles in service after the effective date of this AD, whichever occurs later, but not to exceed 4,050 cycles in service or since HPC overhaul, for those engines with less than 4,000 cycles in service on the effective date of this AD, or since last HPC overhaul. (3) The 3.0 bleed trim screw may bottom out before the two clockwise turns are completed in accordance with the instructions of Appendix 2 of this AD. If the turn screw bottoms out, this is an acceptable condition. (b) An engine which has had no 3.0 bleed or vane schedule adjustments since it was last trimmed in the test cell (P/N 776555-3 to 1.27 EPR or P/N 776555-5 to 1.32 EPR) is exempt from the requirements of paragraphs (a)(1) and (a)(2). NOTE: For the purpose of this AD, the definition of HPC overhaul is anytime the HPC is disassembled, inspected, and repaired in accordance with PW Engine Manual P/N 785059, Section 72-35-00. (c) Adjust the decel schedule trimof fuel control unit (FCU), P/N 797371, and reidentify the FCU, in accordance with the instructions of Appendix 3 of this AD, within the applicable schedule in paragraph (a)(1) or (a)(2) above. If cycling bleeds occur as a result of the decel schedule uptrim, downtrim the decel schedule in accordance with the instructions of Appendix 4 of this AD. (d) Within the next 30 calendar days after the effective date of this AD accomplish the following: (1) Adjust the EVBC, P/N 776555-3, to the 1.27 EPR bleed trim and, P/N 776555-5, to the 1.32 EPR bleed trim in accordance with the instructions of Appendix 1 of this AD. (2) Modify the 3.0 bleed valve cylinder, P/N 806885 or 774300, in accordance with the instructions of Appendix 5 or Appendix 6 of this AD. (3) Inspect the 3.0 bleed valve linkage for wear in accordance with the instructions of Appendix 7 of this AD and accomplish the following: (i) Remove engines with worn 3.0 valve linkage prior to accumulating 5 cycles inservice since inspection and replace with a serviceable engine. (ii) Reinspect linkages found serviceable in accordance with the requirement of paragraph (c)(3) above, at intervals not to exceed 3,000 hours since last inspection. (e) Incorporate the following modifications to upgrade the EVBC to Hamilton Standard, P/N 776555-5, prior to July 31, 1990, by accomplishing the following: (1) Incorporate the fluid drain between sensor servo piston chevron seals, in accordance with the instructions of Appendix 8 of this AD. (2) Incorporate the pilot valve spring, P/N 801040-1, in accordance with the instructions of Appendix 9 of this AD. (3) Incorporate the decel bleed reset piston spring, P/N 801073-1, in accordance with the instructions of Appendix 10 of this AD. (4) Incorporate the 3.0 bleed cam, P/N 765357-11, and recalibrate the control, in accordance with the instructions of Appendix 11 of this AD. (5) Incorporate the actuator valve, P/N 800997-1, in accordance with the instructions of Appendix 12 of this AD; or remove actuator valve, P/N 728149-3, and replace with a new or serviceable actuator valve, P/N 728149-3. Replacement actuator valves, P/N 728149-3, must be removed from service at, or prior to accumulating 10,000 hours since new. (6) Incorporate the adjust EVBC to 1.32 EPR bleed trim, in accordance with paragraph (c)(1) above. (f) Modify FCU, Hamilton Standard, P/N 773333-3, prior to July 31, 1990, by accomplishing the following: (1) Incorporate the L-22 idle speed cam, P/N 774537-9, in accordance with the instructions of Appendix 13 of this AD. (2) Incorporate the decel cam, P/N 774538-13, in accordance with the instructions of Appendix 14 of this AD. (g) Incorporate the revised test procedure for the fuel control decel bleed override, in accordance with the instructions of Appendix 15 of this AD, prior to July 31, 1990. (h) Install 3.0 bleed dampers at the next shop visit, in accordance with PW Service Bulletin (SB) JT9D- 7R4-72-336, Revision 5, dated June 23, 1988. Installation of 3.0 bleed dampers terminates the reinspection requirements of paragraph (c)(3)(ii) above. NOTE: For the purpose of this AD, the definition of shop visit is any time the engine or module is in a maintenance shop capable of complying with the SB instructions regardless of the planned maintenance action or the reason for engine removal. (i) Restore the leading edge of the first stage compressor blades in accordance with PW SB JT9D-7R4- 72-117, Revision 4, dated June 30, 1989, at the next fan module overhaul after the effective date of this AD and thereafter at every fan module overhaul. NOTE: For the purpose of this AD, the definition of fan module overhaul is anytime the fan module is disassembled, inspected, and repaired, in accordance with PW Engine Manual P/N 785058. (j) 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.(k) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The installation and restoration procedures shall be done in accordance with the following PW documents: Document No. Page No. Issue/Revision Date JT9D-7R4-72-117 1,2,4,5,6, 4 June 30, 1989 7,8,9,10,11 JT9D-7R4-72-117 3 3 Dec. 21, 1987 JT9D-7R4-72-336 1,3,4,8,9,10 5 June 23, 1988 11,12,13,14,15, 4 Aug. 28, 1987 16,17,18,19,20 2 3 June 8, 1987 JT9D-7R4-72-336 5,6,7 Original March 2, 1987 This incorporation by reference was approved by the Director of the Federal Registerin accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Pratt & Whitney Publications Department, P.O. Box 611, Middletown, Connecticut 06457. 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 AD supersedes telegraphic airworthiness directive No. T89-11-51, dated May 23, 1989. This amendment (39-6428, AD 90-14-08) becomes effective on July 2, 1990. Appendix 1 NOTE: This appendix consists of material from: Boeing 767 Maintenance Manual, JT9D engines, Chapter/Section 71-01-00, Test No. 10, dated February 10, 1989. Appendix 2 NOTE: This appendix consists of material from: Pratt & Whitney (PW) Special Instruction (SI) 55F-89, dated May 19,1989. Appendix 3 NOTE: This appendix consists of material from: PW SI 42F-88, Revision A, dated May 19, 1989. Appendix 4 NOTE: This appendix consists of material from: PW SI 53F-89, dated May 23, 1989. Appendix 5 NOTE: This appendix consists of material from: PW SB JT9D-7R4-75-98, Revision 1, dated August 17, 1989. Appendix 6 NOTE: This appendix consists of material from: PW SI 54F-89, dated May 19, 1989. Appendix 7 NOTE: This appendix consists of material from: PW Maintenance Manual, P/N 785050, Chapter/Section 72-00-00, Inspection/Check -06, dated November 1, 1986. Appendix 8 NOTE: This appendix consists of material from: Hamilton Standard Bulletin (HSB) GTA9 No. 9, Revision 1, dated October 15, 1984. Appendix 9 NOTE: This appendix consists of material from: HSB GTA9 No. 16, dated March 20, 1988. Appendix 10 NOTE: This appendix consists of material from: HSB GTS9 No. 17, dated March 31, 1988. Appendix 11 NOTE: This appendix consists of material from: HSB GTS9 No. 18, Revision 1, dated January 15, 1989. Appendix 12 NOTE: This appendix consists of material from: HSB GTA9 No. 19, dated August 12, 1988. Appendix 13 NOTE: This appendix consists of material from: HSB JFC68-7 No. 10, Revision 1, dated October 31, 1989. Appendix 14 NOTE: This appendix consists of material from: HSB JFC68-7 No. 14, Revision 1, dated October 31, 1989. Appendix 15 NOTE: This appendix consists of material from: HSB JFC68-7 No. 12, dated March 31, 1988.
87-22-03: 87-22-03 BRITISH AEROSPACE: Amendment 39-5749. Applies to BAe Model 125- 800A series airplanes, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent failure of the engine fire warning annunciation in the flight deck, accomplish the following: A. Inspect the socket contacts in connectors TA7 and TB7 for adequate crimping, and replace, if necessary, in accordance with British Aerospace Service Bulletin 26-27, dated May 16, 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 inspections required by this AD. All persons affected by this directive whohave not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 November 13, 1987.
2000-16-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385 series airplanes, that currently requires repetitive inspections to detect cracking of the canted pressure bulkhead at fuselage station (FS) 1212, and repetitive inspections to detect cracking of the web at the fastener rows of the vertical stiffener-to-web; and repair or replacement of the web with a new web, if necessary. This amendment requires that the initial inspections be accomplished at a reduced threshold. This amendment is prompted by a report of fatigue cracking of the canted pressure bulkhead at FS 1212. The actions specified by this AD are intended to detect and correct fatigue cracking of the canted pressure bulkhead at FS 1212, which could result in blowout of a panel between adjacent stiffeners and consequent cabin depressurization.
88-15-08: 88-15-08 DE HAVILLAND: Amendment 39-5978. Applies to Model DHC-3 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished in accordance with AD 85-11-01, Amendment 39-5071. To prevent disengagement of the folding utility seat forward leg from the floor mounting rail, which could result in hazards to seat occupants from an inadequately restrained seat during a crash, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD, and at subsequent intervals of 50 hours TIS, attempt to move the lower end of each leg sideways into the open part of the keyhole slot using as much force as can be exerted by hand. If the leg can be released from the keyhole slot, remove the seat from service until DeHavilland Modification No. 3/932 is incorporated. (This modification is contained in DeHavilland Service Bulletin No. 3/42, Revision A, dated September 18, 1987).(b) Repeat the check in Paragraph (a) of this AD each time the seats are moved from the stowed to deployed position. (c) The check required by Paragraph (b) of this AD may be accomplished by a flightcrew member, certificated under FAR 61 or FAR 63 rules, briefed on the procedure. NOTE: When the checks required by Paragraph (b) of this AD are accomplished by a flightcrew member pursuant to the restrictions specified in Paragraph (c) of this AD, maintenance records must be made as required by FAR 43.9 and those records must be maintained as required by FAR 91.173, 121.380, or 135.439 as applicable. (d) When Modification No. 3/932 is installed in accordance with the "ACCOMPLISHMENT INSTRUCTIONS" of DeHavilland S/B No. 3/42, Revision A, on each seat, subsequent checks required by this AD are no longer required. (e) An equivalent means of compliance may be used when approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York 11581. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the DeHavilland Aircraft Company of Canada, a Division of Boeing of Canada, Ltd, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5; Telephone (416) 633- 7310, or these documents may be examined at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This AD supersedes AD 85-11-01, Amendment 39-5071. This amendment, 39-5978, becomes effective on August 27, 1988.