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80-04-03 R2: 80-04-03 R2 AVCO LYCOMING: Amendment 39-3692 as amended by Amendment 39-3977 is further amended by Amendment 39-5893. Applies to O-320-H series engines and O-360-E, LO-360-E, TO-360-E and LTO-360-E series engines; (all serial numbers and hydraulic lifter (tappet) configurations). Compliance required as indicated, unless already accomplished. a. To prevent hazards in flight associated with bent push rods on Model O-320-H series engines, accomplish the following: Within the next 50 hours in service after the effective date of this AD, replace the upper exhaust valve spring seats with P/N LW-16475-KLI and the exhaust hydraulic lifters with P/N LW-16586 in accordance with AVCO Lycoming Service Bulletin No. 435 dated March 17, 1979, or FAA-approved equivalent, on all O- 320-H series engines with serial numbers up to and including L-6182-76 and on all O-320-H series engines overhauled (remanufactured by Lycoming) before March 19, 1979. b. To prevent excessive wear and oil system contamination associated with hydraulic lifters spalling on O-320-H, and O-360-E, LO-360-E, TO-360-E and LTO-360-E series engines, accomplish the following: 1. At the next engine oil change but no later than 50 hours in service after the effective date of this AD, and at each subsequent oil change or 50-hour interval, whichever occurs earlier, add one 6-ounce can of Lycoming P/N LW-16702 oil additive in accordance with Lycoming Service Bulletin No. 446B. 2. Within the next 50 hours in service after the effective date of this AD and at every subsequent oil change thereafter, not to exceed 100-hour intervals, inspect lubrication system for metal contaminants. Inspection of the lubrication system consists of visual examination for minute particles of metal suspended in the oil, examination of the engine oil suction screen for presence of metal particles and the inspection of the external full flow oil filter for metal particles by cutting it open so that the pleated element can be unfolded and examined. If ferrous metal contaminants are detected during the above inspections, the camshaft lobes and all hydraulic lifters must be inspected for wear or loss of metal. Replace the camshaft and hydraulic lifters found to have such indications. 3. If contaminants are detected, engine maintenance entries shall be made. If the engine is one of the affected Textron Lycoming engine models with the 'T mod' modification (larger diameter hydraulic lifters), notification in writing must be sent to the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, specifying the following information: 1. Engine Model and Serial Number. 2. Total time and time since overhaul. 3. Total time on cam and hydraulic lifters. 4. Total time since oil additive first used. 5. Visual condition of cam lobe and lifter contact surfaces. (Information collection requirements contained in this regulation (Section 39.13) have been approved by the Office of Management and Budget under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96- 511) and have been assigned OMB control number 2120-0056). NOTE: The 'T mod' is the latest design crankcase that incorporates large diameter hydraulic lifters and wide lobe camshafts and is described in Textron Lycoming Service Instruction No. 1406B. Engines incorporating this configuration are identified by the letter 'T' stamped as a suffix to the engine serial number which appears on the engine nameplate for overhaul modified, remanufactured, and new production engines (e.g., L-6005-76T). c. Equivalent methods of compliance may be approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. d. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, may adjust the compliance time specified in this AD. e. Special Flight Permits may be issued per FAR's 21.197 and 21.199 to authorize operation of aircraft to a base where the modification and inspection required by this AD may be performed. Amendment 39-3692 was effective February 8, 1980. Amendment 39-3977 was effective November 24, 1980. This amendment 39-5893, becomes effective on April 25, 1988.
99-02-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385-1 series airplanes, that requires modification of the power drive units and the lower drive sprocket assemblies of the galley lift system. This amendment is prompted by a report indicating that, due to fatigue cracking, the primary and secondary drive shafts of the galley lift failed and caused the galley lift to drop to the lower level, injuring a flight attendant. The actions specified by this AD are intended to prevent such fatigue cracking of the primary and secondary drive shafts, which could result in complete fracturing of the secondary shaft; such fracturing could allow the galley lift to drop to the bottom of the shaft, and could result in possible injury to crewmembers.
83-07-09 R1: 83-07-09 R1 CANADAIR: Amendment 39-8675. Docket 92-NM-231-AD. Revises AD 83-07-09, Amendment 39-4609. Applicability: All Model CL-600-1A11 and CL-600-2A12 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: This AD requires the same actions as required by AD 83-07-09, Amendment 39-4609, but is applicable to fewer airplanes. Operators affected by this AD who have accomplished these actions previously in accordance with AD 83-07-09 are considered to be in compliance with this revised AD. To prevent possible wire overheating, which could result in a cabin fire, accomplish the following: (a) Within 300 hours time-in-service or within 3 calendar months after April 13, 1983 (the effective date of AD 83-07-09, Amendment 39-4609), whichever occurs earlier, perform an inspection to verify proper installation of the 8 gage feeder wires from generators 1 and 2 and the auxiliary power unit (APU), in accordance with Canadair Drawings 600-58001, Note 17, or 600-58031, Note 14; and CL-600 Completion Centre Handbook Section 6. Prior to further flight, correct any discrepant wires in accordance with the drawings or handbook. (b) Replacement of the 8 gage generator 1, generator 2, and APU feeder wires with 4 gage feeder wires of the same type constitutes an approved alternative method of compliance for the requirements of this AD. (c) 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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (d) 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. (e) This amendment becomes effective on November 12, 1993.
90-02-09: 90-02-09 GROB WERKE GmbH & COMPANY KG (BURKHART GROB): Amendment 39-6447. Applicability: Models TWIN ASTIR and TWIN ASTIR TRAINER (Serial Numbers (S/N) 3000 through 3291); G103 TWIN II (S/N 3501 through 3878, and 33879 through 34078); and G103A TWIN II ACRO (S/N 3544 through 34078) gliders certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude failure of the wing spar spigots, accomplish the following: (a) Within the next 500 takeoffs after the effective date of this AD, inspect the wing spar spigots for damage in accordance with the ultrasonic inspection procedures specified in GROB WERKE GmbH Technical Information TM 315-36, dated June 23, 1988. (1) If damage is found, prior to further flight remove and replace the spigot with a Fail-Safe Spigot using the procedures specified in the above-referenced service information. (2) If no damage is found, within the next 500 takeoffs remove and replace the spigots with Fail-Safe Spigots using the procedures specified in the above-referenced service information. NOTE 1: Note 5 in the Type Certificate Data Sheet G39EU Burkhart Grob Model G103 Twin Astir, Model G103 Twin II, and Model G103A Twin II Acro, Revision 3, dated April 2, 1984, states: "Major airframe repairs must be accomplished at FAA certified repair stations rated for composite construction of small aircraft, using Grob Werke repair methods for the model of interest, approved by the FAA." The replacement of the wing spigots is considered major airframe repair. (b) An alternate method of compliance or adjustment of the compliance times which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, c/o American Embassy, 15 Rue de la Loi B1040, Brussels, Belgium. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Brussels Aircraft Certification Staff. All persons affected by this directive may obtain copies of the document referred to herein upon request to Grob Systems, Incorporated; Aircraft Division; I-75 and Airport Drive, Bluffton, Ohio 45817; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6447, AD 90-02-09) becomes effective on February 5, 1990.
83-16-01 R1: 83-16-01 R1 SUNDSTRAND DATA CONTROL, INC.: Amendment 39-4705 as amended by Amendment 39-4857. Applies to Sundstrand Model AV-557B, and AV-557C Cockpit Voice Recorders. To prevent loss of recorded data, accomplish the following within the next 4,000 hours time in service (on the cockpit voice recorder (CVR)) after the effective date of this AD, unless already accomplished: A. Inspect the CVR's for the type of tape deck housing connector sockets used in accordance with Sundstrand Service Bulletin 012-0296-109 dated January 25, 1982, or a later FAA approved revision. Remove CVR's from service that have incorrect connectors for repair to be accomplished at the factory. Return to service CVR's that have correct connectors and have met the requirements of this AD. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. Amendment 39-4705became effective September 12, 1983. This Amendment 39-4857 becomes effective May 15, 1984.
98-25-11 R1: This amendment corrects and clarifies information in an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. The actions specified in that AD are intended to prevent chafing of the electrical wire assemblies, which could result in an electrical fire in the passenger compartment. This amendment corrects and clarifies the requirements of the current AD by specifying the specific area in which the subject inspection must be conducted and by correcting the part number of the ramp deflector assembly. This amendment is prompted by communication received from the manufacturer that the current requirements of the AD are unclear.
99-01-11: This amendment adopts a new airworthiness directive (AD) that applies to all The Uninsured Relative Workshop Inc. (doing business as and referred to herein as Relative Workshop) vector parachute systems that were manufactured between January 1, 1996, and September 10, 1998. This AD requires inspecting the amp fittings on the end of the breakaway housing for proper swaging, and re-swaging any incorrectly swaged fittings using the Nicopress or Swage-It swaging tool. This AD is the result of a quality control problem on Relative Workshop vector parachute systems. In particular, a loose amp fitting was found on the breakaway housing during packing of one of these vector parachute systems. Further analysis reveals that the amp fittings on the end of the stainless steel breakaway housing were improperly swaged, and that this condition could exist on any of the 2,127 parachute systems that were manufactured during the above-referenced time period. The actions specified by thisAD are intended to prevent the amp fittings from coming off the stainless steel breakaway housing, which could result in an unintentional partial breakaway of the main chute and interference with the deployment of the reserve parachute.
98-26-24: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that currently requires replacement of certain outboard and inboard wheel halves with improved wheel halves; cleaning and inspecting certain outboard and inboard wheel halves for corrosion, missing paint in large areas, and cracks; and repair or replacement of the wheel halves with serviceable wheel halves, if necessary. That AD was prompted by a review of the design of the flight control systems on Model 737 series airplanes. This amendment requires that the actions be accomplished in accordance with revised service information. The actions specified by this AD are intended to prevent failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures; and consequent reduced controllability of the airplane.
99-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney (PW) JT8D and JT3D series turbofan engines. This action requires operators to remove and replace with serviceable parts, certain stage 7 through stage 15 high-pressure compressor (HPC) disks identified by part number and serial number. This amendment is prompted by a report of an uncontained failure of a stage 8 HPC disk during a takeoff roll that resulted in damage to the airplane. The actions specified in this AD are intended to prevent the failure of a high-pressure compressor disk due to Cadmium embrittlement, resulting in uncontained engine failure and damage to the airplane. Comments for inclusion in the Rules Docket must be received on or before March 1, 1999.
92-17-12: 92-17-12 BRITISH AEROSPACE: Amendment 39-8341. Docket No. 92-NM-64-AD. Applicability: Model HS/BH 125-600A, HS 125-700A, and BAe 125-800A series airplanes; as listed in British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing and a resultant fire, accomplish the following: (a) Within 180 days after the effective date of this AD, modify the cabin and toilet fluorescent lighting systems, in accordance with British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who mayadd comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) 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. (d) The modification shall be done in accordance with British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 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, DC 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, 800 North Capitol Street NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 28, 1992.
88-03-53: 88-03-53 PRATT & WHITNEY: Amendment 39-6270. Final copy of telegraphic AD T88-03-53 which was issued on February 3, 1988. Applicability: Pratt & Whitney (PW) PW4152 turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent the inability to reduce engine thrust that can lead to asymmetrical power and possible aircraft directional control problems, accomplish the following: (a) For fuel metering units (FMU), Part Number (P/N) 51T217 or 53T419, with 140 operating hours or greater on the effective date of this Airworthiness Directive (AD), since new or since refurbished with new sector gears and a new or reconditioned resolver pinion gear, accomplish the following: Remove and replace the FMU with a new or serviceable unit in accordance with the instructions in Appendix I of this AD within 10 operating hours after the effective date of this AD. (Appendix I refers to Pratt & Whitney Alert Service Bulletin Number PW4ENG A73-37, Revision 1, dated January 26, 1988, which is not reprinted in this AD.) (b) For FMU's, P/N 51T217 or 53T419, with less than 140 operating hours on the effective date of this AD, since new or since refurbished with new sector gears and a new or reconditioned resolver pinion gear, accomplish the following: Remove and replace the FMU with a new or serviceable unit in accordance with the instructions in Appendix I of this AD on or before accumulating 150 operating hours since new or since refurbished with new sector gears and a new or reconditioned resolver pinion gear. (c) Thereafter, remove the FMU, P/N 51T217 or 53T419, and install a new or serviceable unit in accordance with the instructions in Appendix I of this AD at intervals not to exceed 150 FMU operating hours in service. NOTE: PW ASB Number PW4ENG A73-37, Revision 1, dated January 26, 1988, further recommends removal and replacement of the FMU whenever the engine parameters indicate an impending hot start or excessive ground idle rotor speed (N2 in excess of 68 percent at normal bleed air extraction). FMU removal and replacement due to these operating characteristics are not mandated by this AD at this time. (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 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, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The FMU replacement shall be done in accordance with the instructions in Appendix I of this AD. This amendment (39-6270, AD 88-03-53) becomes effective on September 1, 1989, as to all persons except those persons to whom it was made immediately effective by individual Telegraphic AD T88-03-53, issued February 3, 1988, which contained this amendment.
2013-14-10: We are superseding airworthiness directive (AD) 2010-11-02 for all Gulfstream Aerospace LP (Type Certificate Previously Held by Israel Aircraft Industries, Ltd.) Model Gulfstream 100 airplanes, and Model Astra SPX and 1125 Westwind Astra airplanes. AD 2010-11-02 required amending the airplane flight manuals (AFMs) to include additional procedures for verifying complete closure and locking of the main entry door (MED). AD 2010-11-02 also required modifying the warning and caution lights panel (WACLP), changing the WACLP and MED wiring, changing the wiring harness connecting the MED to the WACLP, and revising the log of modification of the AFM if necessary. This new AD revises the compliance time and removes an airplane from the applicability. This AD was prompted by a report of a MED opening in flight on an unmodified airplane. We are issuing this AD to prevent incomplete closure of the MED, which may result in the door opening in flight and possible separation of the door, causing damage to the airplane structure and left engine by flying debris and objects.
2013-15-02: We are superseding Airworthiness Directive (AD) 2008-10-03 for Bell Helicopter Textron Helicopters (Bell) Model 204B, 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters. AD 2008-10-03 required certain checks and inspections of each tail rotor blade assembly (T/R blade) at specified intervals and repairing or replacing, as applicable, any cracked or damaged T/R blade. Since we issued AD 2008-10-03, an accident attributed to a T/R failure occurred. This new AD retains the requirements of AD 2008-10-03 and adds a second, more detailed inspection that allows for an earlier detection of a crack or other damage in a T/R blade. These actions are intended to prevent a failure of the T/R blade and subsequent loss of helicopter control.
86-03-03: 86-03-03 PRATT & WHITNEY: Amendment 39-5219. Applies to Pratt & Whitney model JT9D-7R4D, 7R4E, and -7R4E4 turbofan engines. Compliance is required as indicated unless already accomplished. To prevent deterioration of fuel nozzle flow and spray cone angle characteristics which could lead to engine surge, overtemperature, or the inability to restart inflight, accomplish the following: (a) Conduct a flow check on JT9D-7R4 series engine incorporating PW P/N 792842 and/or 794731 fuel nozzles following any on-wing cleaning procedure prior to returning the aircraft to service in accordance with PW Maintenance Manual P/N 785050, Chapter 73-13-07, Cleaning/Painting Section as revised by Temporary Revision 73-3, or FAA approved equivalent. (1) A flow reduction of 10 percent or less is acceptable. (2) A flow reduction greater than 10 percent but less than 20 percent requires selected fuel nozzles to be replaced with new or ultrasonically cleaned nozzles within 300flight cycles. The fuel nozzles may be replaced in quantities and locations as needed to restore the flow to 10 percent flow reduction or less. (3) A flow reduction of 20 percent or greater requires selected fuel nozzles to be replaced with new or ultrasonically cleaned nozzles within 25 flight cycles. If there have been any unresolved aborted ground starts (since the last cleaning and flow check) that are not attributed to an ignition system fault or a mechanical problem which is unrelated to the fuel nozzles, fuel nozzles must be selectively replaced within 5 cycles. The fuel nozzles may be replaced in quantities and locations as needed to restore the flow to 10 percent flow reduction or less. (b) Ground starts must be initiated using single ignition, either ignition selector position 1 or 2. If an aborted start is experienced using single ignition that is related to a fuel nozzle problem, the engine may be started on the opposite ignition system or dual ignition and the fuel nozzles must be cleaned and flow checked within 25 flight cycles in accordance with PW Maintenance Manual P/N 785050, Chapter 73-13-07, Cleaning/Painting Section as revised by Temporary Revision 73-3, or FAA approved equivalent. The flow check limits in Paragraph (a) are applicable to Paragraph (b). 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, may adjust the compliance time specified in this AD. PW Maintenance Manual P/N 785050, Chapter 73-13-07, Cleaning/Painting Section as revised by Temporary Revision 73-3 is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a)(1). (Boeing Maintenance Manual, Chapter 73-11-05, Cleaning/Painting Section is an equivalent means of compliance.) All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. This document also may be examined at the Office of the Regional Counsel, Rules Docket 85-ANE-8, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on March 14, 1986.
99-01-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect discrepancies of the diagonal brace lugs of the engine strut, and rework of the diagonal brace lugs, if necessary. That AD also provides an option to defer the rework for certain cases by accomplishing repetitive inspections and resealing the bushing. That AD also provides for an optional terminating modification for the repetitive inspections. This amendment adds a requirement to repetitively inspect a new area of the diagonal brace of the engine strut. For certain airplanes, this amendment also adds new repetitive inspections of the subject area and requires that certain previously required repetitive inspections be accomplished at reduced intervals. This amendment is prompted by reports of fatigue or stress corrosion cracking in new areas of the diagonal brace. The actions specified inthis AD are intended to prevent such fatigue or stress corrosion cracking, which could result in failure of the strut and consequent separation of the engine from the airplane.
2013-15-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD requires either removal or inspection of the Honeywell fixed emergency locator transmitter (ELT), and corrective action if necessary. This AD was prompted by a report of a fire involving a Honeywell fixed ELT. We are issuing this AD to prevent a fire in the aft crown of the airplane, or to detect and correct discrepancies within the ELT that could cause such a fire.
92-10-04: 92-10-04 BRITISH AEROSPACE: Amendment 39-8238. Docket No. 91-NM-261-AD. Applicability: Model DH/BH/HS 125 series airplanes, excluding Model 125-700A, -800A, and -1000A series airplanes; as listed in British Aerospace Service Bulletin S.B. 57-73, 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, visually inspect left and right wing upper skins for corrosion beneath the boundary layer fence, in accordance with British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991. (1) If any corroded parts are found in which the corrosion is within the limits specified in British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991, prior to further flight, repair in accordance with that service bulletin. (2) If any corroded parts are found in which the corrosion exceeds the limits specified in British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) Within 10 days after accomplishing the inspection required by paragraph (a) of this AD, submit a report of inspection findings to British Aerospace, in accordance with Appendix A of British Aerospace Service Bulletin S.B. 57-73, dated July 30, 1991. Report all findings, including nil defects to: Service Support Manager, BAe 125, British Aerospace (Commercial Aircraft) Ltd., Corporate Aircraft Division (H121), Customer Support Department, Comet Way, Hatfield, Hertfordshire, AL 10 9TL, England; fax 0707 251216; telex 21429 (BAA HPS-G). Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork ReductionAct of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) 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. (d) 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. (e) The inspections and repairs shall be done in accordance with British Aerospace Service Bulletin S.B. 57-73, 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, DC. 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. (f) This amendment becomes effective on June 11, 1992.
98-26-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive detailed visual inspections to detect corrosion on the rear spar web of the wing center section and adjacent bulkhead fittings at body station 1241; and corrective action, if necessary. This amendment is prompted by reports of corrosion found on the rear spar web and bulkhead fitting. The actions specified by this AD are intended to detect and correct such corrosion, which could cause cracking of the rear spar web, and result in a fuel leak and consequent fire/explosion in the wheel well of the main landing gear.
96-12-13: 96-12-13 DORNIER: Amendment 39-9656. Docket 96-NM-112-AD. Applicability: Model 328 series airplanes, equipped with Honeywell GP-300 guidance and display controller having part number (P/N) 7015327-901 or -902; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.Compliance: Required as indicated, unless accomplished previously. To prevent a defective light bulb from causing a short circuit that emits smoke and fumes into the cockpit, or causing damage to the circuit cards and various components, which may lock the autopilot into the engaged mode, accomplish the following: (a) Within 60 days after the effective date of this AD, modify the Honeywell GP-300 guidance and display controller, having P/N 7015327-901 or -902, in accordance with Honeywell Service Bulletin 7015327-22-2, dated March 4, 1996. (b) 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with Honeywell Service Bulletin 7015327- 22-2, dated March 4, 1996. 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 Honeywell, Inc., Attn: Customer Support Materiel, P.O. Box 21111, Phoenix, Arizona 85036. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard,Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 26, 1996.
80-16-52: 80-16-52 AIRBUS INDUSTRIE: Amendment 39-4105. Applies to Model A300 series airplanes, serial numbers 002 through 095 inclusive, except serial numbers 058, 061, 080, 082, 089, 090 and 094, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent reduction in brake performance, accomplish the following: (a) Within the next 50 landings after the effective date of this AD, and thereafter at intervals not to exceed 50 landings, visually inspect the two rear attachment lugs of brake pedal position transmitter cast brace assembly, P/N A3241000000002 or A3241000000003, for cracks in accordance with Airbus Industrie Service Bulletin A300-32-264 dated May 27, 1980, or an FAA-approved equivalent. Report defects found to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.)(b) If a crack or cracks are found as a result of any inspection required by paragraph (a) of this AD, replace the brace assembly prior to further flight with a serviceable brace assembly. (c) The inspections required by paragraph (a) of this AD may be discontinued after installation of a cast brace assembly modified in accordance with Airbus Industrie Service Bulletin A300-32-267 dated July 4, 1980, or an FAA approved equivalent. (d) Airplanes may be ferried in accordance with FAR Sections 21.197 and 21.199 to a facility where inspections and repairs can be accomplished. (e) If an equivalent means of compliance is used in complying with this AD, that equivalent must be approved by the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. 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 Airbus Industrie, Airbus Support Division, BP 33, 31700 Blagnac, France. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. This amendment becomes effective April 30, 1981, as to all persons except those persons to whom it was immediately effective by telegraphic AD T80-16-52, issued August 1, 1980, which contained this amendment.
2013-14-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and 747-400F series airplanes. This AD was prompted by reports of cracking in the outboard flange of the longeron extension fittings, which attach to the wing-to-body fairing support frame. This AD requires repetitive inspections of the longeron extension fittings for cracking, and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the longeron extension fittings, which can become large and adversely affect the structural integrity of the airplane.
98-26-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires repetitive inspections to detect cracking of the lower cap of the wing rear spar, and repair, if necessary. For certain airplanes, this AD also provides for an optional terminating modification for the repetitive inspections. This amendment is prompted by reports of fatigue cracks found in the lower cap of the wing rear spar. The actions specified by this AD are intended to detect and correct fatigue cracking of the lower cap of the wing rear spar, which could result in reduced structural integrity of the airplane.
98-26-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes. This AD requires modifying the emergency exit doors and installing interior and exterior placards on each of the emergency exit doors. Difficulty in opening the emergency exit doors prompted this action. The actions specified by this AD are intended to prevent passengers and crew from not being able to open the emergency exit doors during an airplane emergency, which could result in passenger and crew injuries.
2013-13-15: We are superseding airworthiness directive (AD) 87-02-07, which applied to all The Boeing Company Model 737-100 and -200 series airplanes. AD 87-02-07 required replacement of certain underwing fuel tank access covers with stronger, fire-resistant covers. This new AD also requires inspecting fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, inspecting application of stencils and index markers of impact- resistant access doors, doing corrective actions if necessary, revising the maintenance program, and adding airplanes to the applicability. This AD was prompted by reports of standard access doors installed where impact-resistant access doors are required, and reports of impact-resistant doors without stencils. We are issuing this AD to prevent foreign object penetration of the wing tank, which could lead to a fuel leak near ignition sources (engine, hot brakes), consequently leading to a fuel-fed fire.
93-01-13: 93-01-13 FOKKER: Amendment 39-8467. Docket 92-NM-236-AD. Applicability: Model F27 series airplanes; except Model F27 Mark 050 series airplanes; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent uncontrolled fuel leakage into the wheel well, accomplish the following: (a) Within 30 days after the effective date of this AD, perform a visual inspection to detect chafing, scratches, or dents on the fuel lines on the left- and right-hand nacelles, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F27/28-61, dated September 3, 1992. (b) If no chafing, scratches, or dents are found during the inspection required by paragraph (a) of this AD, the fuel line may remain installed. However, within 100 hours time-in-service after the effective date of this AD, perform a visual inspection for clearances between the fuel line and the landing gear parts, in accordance with Part2 of the Accomplishment Instructions of Fokker Service Bulletin F27/28-61, dated September 3, 1992; and accomplish either paragraph (b)(1) or (b)(2) of this AD, as applicable. (1) If the clearance between the fuel line and the landing gear parts is less than 0.25 inch, prior to further flight, adjust the landing gear components to achieve a minimum clearance of 0.25 inch, in accordance with the service bulletin. (2) If the clearance between the fuel line and the landing gear parts is 0.25 inch or greater, no further action is required by this AD. (c) If any chafing or scratches are found during the inspection required by paragraph (a) of this AD, prior to further flight, accomplish both paragraphs (c)(1) and (c)(2) of this AD: (1) Measure the damage depth and accomplish either paragraph (c)(1)(i), (c)(1)(ii,) or (c)(1)(iii) of this AD, as applicable. (i) If the depth of chafing or scratch damage is equal to or greater than 0.009 inch, prior to further flight, replace the damaged fuel line, in accordance with Chapter 28-00-00 of the Airplane Maintenance Manual. (ii) If the depth of chafing or scratch damage is 0.004 inch or more, but less than 0.009 inch, re-inspect the damaged fuel line in accordance with paragraph (a) of this AD thereafter at intervals not to exceed 10 hours time-in-service; and replace the damaged fuel line within 50 hours time-in- service after the effective date of this AD, in accordance with Chapter 28-00-00 of the Airplane Maintenance Manual. (iii) If the depth of chafing or scratch damage is less than 0.004 inch, the fuel line may remain in place. (2) Perform a visual inspection for clearances between the fuel line and the landing gear parts, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/28-61, dated September 3, 1992, and accomplish either paragraph (c)(2)(i) or (c)(2)(ii) of this AD, as applicable. (i) If the clearance between the fuel lineand the landing gear parts is less than 0.25 inch, prior to further flight, adjust the landing gear components to achieve a minimum clearance of 0.25 inch, in accordance with the service bulletin. (ii) If the clearance between the fuel line and the landing gear parts is 0.25 inch or greater, no further action is required by this AD. (d) If any dent is found during the inspection required by paragraph (a) of this AD, prior to further flight, accomplish both paragraphs (d)(1) and (d)(2) of this AD: (1) Measure the damage depth and accomplish either paragraph (d)(1)(i) or (d)(1)(ii) of this AD, as applicable. (i) If the depth of the dent is equal to or greater than 0.1 inch, prior to further flight, replace the dented fuel line, in accordance with Chapter 28-00-00 of the Airplane Maintenance Manual. (ii) If the depth of the dent is less than 0.1 inch, the fuel line may remain installed. (2) Perform a visual inspection for clearances between the fuel line and the landing gear parts, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/28-61, dated September 3, 1992; and accomplish either paragraph (d)(2)(i) or (d)(2)(ii) of this AD, as applicable. (i) If the clearance between the fuel line and the landing gear parts is less than 0.25 inch, prior to further flight, adjust the landing gear components to achieve a minimum clearance of 0.25 inch, in accordance with the service bulletin. (ii) If the clearance between the fuel line and the landing gear parts is 0.25 inch or greater, no further action is required by this AD. (e) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then sendit to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (f) 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. (g) The inspections, replacement, and adjustment shall be done in accordance with Fokker Service Bulletin F27/28-61, dated September 3, 1992. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.(h) This amendment becomes effective on February 5, 1993.