Results
2016-16-15: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of chafing damage due to insufficient clearance on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure, and the adjacent electrical wiring harnesses. An insufficient fillet radius may also exist on certain airplanes. This AD requires, depending on airplane configuration, an inspection of the nacelle A-frame structure for insufficient fillet radius; an inspection for cracking of affected structure, and rework or repair if necessary, and rework of the nacelle A-frame structure; repetitive inspections of the nacelle A-frame structure and the MLG stabilizer brace for insufficient clearance and damage, and repair if necessary, and rework of the nacelle A-frame structure, which would terminate the repetitive inspections; installation of new stop brackets and a shim on each MLG stabilizer brace assembly; andrework of the electrical wiring harnesses in the nacelle area. We are issuing this AD to [[Page 55354]] detect and correct chafing damage and subsequent premature cracking and fracture of the nacelle A-frame structure, which could result in failure of the MLG stabilizer brace and loss of the MLG down-lock indication, which could adversely affect the safe landing of the airplane.
84-22-03: 84-22-03 McDONNELL DOUGLAS: Amendment 39-4952. Applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, -50, and C-9 (Military) series airplanes which have been modified in accordance with McDonnell Douglas Service Bulletin 57-118 and/or production equivalent, certificated in all categories. Compliance required as indicated unless previously accomplished. \n\n\tTo detect cracked wing flap outboard hinge lower stud(s) due to hydrogen embrittlement, and prevent failure of the wing hinge bracket, accomplish the following: \n\n\tA.\tPrior to the accumulation of 10,400 landings or within 400 landings, whichever occurs later, from effective date of this AD, ultrasonically inspect the flap hinge fitting lower studs for cracking in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A57-162, dated April 27, 1984, or later FAA approved revisions. \n\n\tB.\tIf no cracking is found, no further action is required. \n\n\tC.\tIf cracking is found, replace all four studs in accordance withthe Accomplishment Instructions of Paragraph 2 of McDonnell Douglas DC-9 Alert Service Bulletin A57-162, dated April 27, 1984, or later FAA approved revisions. \n\n\tD.\tAlternative inspections, modifications, or other actions 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\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 November 20, 1984.
82-05-03: 82-05-03 BELL: Amendment 39-4330. Applies to Bell Model 206L helicopters, all serial numbers, and 206L-1 helicopters, serial numbers 45154 through 45398, 45400 through 45491, 45493 through 45543, 45545 through 45614, 45616 through 45634, 45636 through 45638, 45643 through 45647, 45649 through 45652, and 45655 through 45657, certificated in all categories (Airworthiness Docket No. 81-ASW-67). Compliance is required as indicated, unless previously accomplished. To prevent possible failure of the horizontal stabilizer, accomplish the following, in accordance with Bell Helicopter Textron Alert Service Bulletin (ASB) 206L-81-23, Revision A, dated October 23, 1981, or FAA approved equivalent. a. Remove horizontal stabilizer assemblies, P/N 206-704-143-105, -113, and -131, from service within 25 hours' time in service after March 31, 1982, and replace with a serviceable stabilizer. b. Inspect horizontal stabilizer assemblies, P/N 206-023-119-011, -075, -107, and - 113, and P/N 206-961-439-003, in accordance with paragraph B1 of Accomplishment Instructions of ASB 206L-81-23, Revision A, or FAA approved equivalent, within 25 hours' time in service after March 31, 1982. c. Remove horizontal stabilizer assemblies, P/N 206-023-119-011, -075, -107, and - 113, and P/N 206-961-439-003, that do not meet the inspection criteria for modification within 25 hours' time in service after March 31, 1982, and replace with a serviceable stabilizer. d. Modify horizontal stabilizer assemblies, P/N 206-023-119-011, -075, -107, and - 113, and 206-961-439-003, that meet the inspection criteria for modification, at one of the approved service centers listed in ASB 206L-81-23, Revision A, or remove from service within 25 hours' time in service after March 31, 1982, and replace with a serviceable stabilizer. e. A serviceable horizontal stabilizer assembly (reference page 5 of ASB 206L-81- 23) is one which is marked with modified P/N 206-704-040-003, -011, -075, -107, or -113, or current production P/N 206-023-119-151 or -703. f. Compliance with this airworthiness directive and AD 78-24-06 is not required if serviceable horizontal stabilizer assemblies, modified P/N 206-704-040-003, -011, -075, -107, or -113, or current production P/N 206-023-119-151, or -703, are installed. g. Compliance with this airworthiness directive eliminates the requirement for modification of the stabilizer supports and the daily inspection requirement for cracks required by AD 78-24-06, Amendment 39-3358, as amended by Amendment 39-4032. h. The helicopter may be flown in accordance with FAR 21.197 to a base where compliance with this AD can be performed. This amendment becomes effective March 30, 1982.
2016-15-05: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 900EX and FALCON 2000EX airplanes. This AD was prompted by a review that identified a nonconformity between the torque value applied to the screw-nuts of aileron servo actuators, and the torque value specified by the type design. This AD requires replacing certain aileron servo actuators with serviceable servo actuators. We are issuing this AD to prevent desynchronization between two servo actuator barrels, which could lead to reduced control of the airplane during roll maneuvers at low altitude.
84-25-05: 84-25-05 TELEDYNE CONTINENTAL MOTORS: Amendment 39-5002. Applies to Teledyne Continental Motor Model TSIO-520BE engines S/N's 528001 through 528125 and 528138 equipped with turbocharger oil scavenge reservoir P/N's 646691 and 646692. Compliance is required as indicated unless already accomplished. To prevent the loss of engine oil, within the next 5 hours time in service, and thereafter at intervals not to exceed 10 hours time in service, until P/N 646954 and P/N 646955 are installed: (a) Visually inspect the turbocharger oil scavenge reservoir P/N's 646691 and 646692 for any indication of cracks, deformation, or oil leaks at, or near, all weld beads. If any crack, deformation, or oil leak is found, replace defective part with a serviceable reservoir. (b) Serviceable P/N's 646691 and/or 646692 may be used while continuing to inspect the turbocharger oil scavenge reservoir every 10 hours time in service, until P/N 646954 and P/N 646955 are installed. NOTE: Piper Aircraft Telex Service Bulletin No.790 refers to this subject. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337; telephone (404) 763-7435. This amendment becomes effective March 4, 1985, to all persons except those persons to whom it was made immediately effective by 1984.
2016-14-10: We are superseding airworthiness directive (AD) 2013-02-02 for certain CFM International, S.A. CFM56-3, CFM56-3B, and CFM56-3C turbofan engines. AD 2013-02-02 required removal from service of certain high-pressure turbine (HPT) disks manufactured by Global Material Solutions of Pratt & Whitney, at reduced maximum life limits. This AD corrects the serial numbers (S/Ns) listed in AD 2013-02-02. This AD was prompted by reports that certain HPT disk S/Ns in AD 2013- 02-02 and in certain Pratt & Whitney service information are incorrect. We are issuing this AD to prevent uncontained release of multiple turbine blades, damage to the engine, and damage to the airplane.
85-10-01: 85-10-01 BRITISH AEROSPACE: Amendment 39-5060. Applies to Model 3101 Jetstream (serial numbers 601 to 624 inclusive, and 627) airplanes certificated in any category. Compliance: Required within 100 hours time-in-service after the effective date of this AD, unless already accomplished. To assure that adequate clearance exists between the rear turbine bearing oil feed pipe and the bleed air pre-cooler accomplish the following: (a) Inspect the rear turbine bearing oil feed pipe for chafing and for adequate clearance between the rear turbine bearing oil feed pipe and the bleed air pre-cooler on LH and RH engines in accordance with sub-paragraphs (a), (b) and (c) of the Part A - Inspection requirement of paragraph 2 of British Aerospace (BAe) Alert Service Bulletin No. 71-A-JM7418. (1) If no damage is apparent and clearance is 0.25 inches (6.35 mm) or greater, no further action is required. (2) If clearance is less than 0.25 inches and no pipe damage is apparent repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 400 hours time-in-service or until either BAe Modification JM7418 or BAe Modification JM7388 is accomplished. (3) If pipe damage is apparent, prior to further flight, accomplish either BAe Modification JM7418 or BAe Modification JM7388. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on June 18, 1985.
81-13-10 R1: 81-13-10 R1 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4140 as amended by Amendment 39-4256. Applies to the following Teledyne Continental Motors IO-360, TSIO-360, and LTSIO-360 series engines: IO-360-C, IO-360-D, IO-360-G, IO-360-H, and IO-360-J, all serial numbers; IO-360-K, all serial numbers, unless AD 80-07-03 already complied with; IO-360-AB, all serial numbers; IO-360-CB, all serial numbers through serial number 350075; IO-360-DB, all serial numbers through serial number 351368; IO-360-GB, all serial numbers through serial number 352894; IO-360-HB, all serial numbers through serial number 353350 (except 353075); IO-360-JB, all serial numbers; IO-360-KB, all serial numbers through serial number 56721 (except 356652, 356672, 356674, 356675, and 356706 through 356719) unless AD 80-07-03 has been complied with; TSIO-360-A, TSIO-360-B, TSIO-360-C, TSIO-360-D, TSIO-360-E, TSIO-360-F, TSIO-360-H and TSIO- 300DB, all serial numbers; TSIO-360-CB, all serial numbers through 300667 (except 300658, 300659, 300662, 3000663, and 3000666); TSIO-360-EB, all serial numbers through serial number 311689 (except 311528, 311538 through 311543, 311546 through 311555, 311656, and 311658 through 311660); TSIO-360-FB, all serial numbers through serial number 310610 (except 310469, 310507 through 310520, 310606, and 310607); TSIO-360-GB, all serial numbers through serial number 309582 (except 309436, 309437, 309439, 309440, 309446 through 309453, 309455, 309457 through 309461, 309565, 309566, 309570 through 309574); TSIO-360-HB, all serial numbers through serial number 308127; IO-360-JB, all serial numbers through serial number 313015; TSIO-360-KB, all serial numbers through serial number 315050; LTSIO-360-E, all serial numbers, LTSIO-360-EB, all serial numbers through serial number 312680 (except 312567 through 312569, 312571, 312574, 312577 through 312587, 312632, 312634 through 312639); LTSIO-360-KB, all serial numbers through serial number 314048 (except 314028); and the following rebuilt engines. IO-360A, all serial numbers through 20128R; IO-360C, all serial numbers through 60516R and 60519R; IO-360D, all serial numbers through 628823R (except 628818R and 628821R); IO-360G, all serial numbers through 224840R; IO-360H, all serial numbers through 226506R; IO-360J, all serial numbers through 238702R; IO-360CB, all serial numbers through 236502R; IO-360DB, all serial numbers through 239608R; IO-360GB, all serial numbers through 236604R; IO-360KB, all serial numbers through 235811R; TSIO-360A, all serial numbers through 197085R; TSIO-360C, all serial numbers through 23698R; TSIO-360E, all serial numbers through 225076R; TSIO-360F, all serial numbers through 232759R; TSIO-360H, all serial numbers through 233252R; TSIO-360AB, all serial numbers through 237609R; TSIO-360CB, all serial numbers through 236022R (except 236012R, 236015R, 236016R and 236019R); TSIO-360DB, all serial numbers through 238401R; TSIO-360EB, all serial numbers through 234613R (except 234611R and 234612R); TSIO-360FB, all serial numbers through 237331R; TSIO-360GB, all serial numbers through 237403R; TSIO-360HB, all serial numbers through 239956R; LTSIO-360E, all serial numbers through 225076R; LTSIO-360EB, all serial numbers through 233818R (except 233812R, 233813R, 233814R, and 233816R); Compliance is required within the next twenty-five (25) hours time in service after the effective date of this AD unless already accomplished. To prevent engine oil pump drive shaft failure and subsequent engine failure due to oil pressure loss, accomplish the following: (a) Remove tach drive cover or tach drive adapter, as applicable, from the crankcase cover assembly. (b) Measure the breakaway torque on the oil pump drive gear nut or the tach drive connector. NOTE: The oil pump drive gear, P/N 640926, used on the LTSIO-360 engines incorporates a left-hand thread. Thus, the breakaway torque must be measured on LTSIO-360 engines in a clockwise direction; the tightening torque must be applied in a counter-clockwise direction. (c) If the breakaway torque is between 200 inch-pounds and 350 inch-pounds, retorque the oil pump drive gear nut or the tach drive connector, whichever is applicable, to 280-300 inch-pounds. Reinstall the tach drive cover or the tach drive adapter and make the appropriate entry in the engine maintenance records, indicating compliance with this AD. (d) If the breakaway torque is less than 200 inch-pounds or greater than 350 inch-pounds, prior to further flight, accomplish either of the following: (1) Replace the TCM oil pump drive gear, P/N 632550, 634010, or 640926, whichever is applicable, with a like serviceable part of the same part number. Omit the Woodruff Key, P/N M535756-1 or P/N 633342-1. (Refer to TCM Manuals Numbers X-30030A and X30031A), or (2) Perform a magnetic particle inspectionof the oil pump drive gear, P/N 632550, 634010, or 640926, whichever is applicable, in accordance with Section VI of the TCM Overhaul Manual Number X- 30030A. Give particular attention to the Woodruff key slot and threaded area. If the oil pump gear is found cracked, damaged, or worn beyond limits, replace with a serviceable part of the same part number. Omit the Woodruff Key, P/N M535756-1 or P/N 633342-1. (Refer to TCM Manuals Numbers X-30030A and X30031A.) (e) Install the oil pump drive gear nut or the tach drive connector, as applicable, and torque to 280-300 inch-pounds. Reinstall the tach drive cover or the tach drive adapter and make the appropriate entry in the engine maintenance records. (f) For all oil pump drive gears found with less than 200 or more than 350 inch-pounds of torque during compliance with this AD, within 10 days mail a written report containing the Engine Model, Serial Number, time in service, and measured torque and results of drive gear inspectionto: Federal Aviation Administration, ASO- 214, Engineering and Manufacturing Branch, P.O. Box 20636, Atlanta, Georgia 30320. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) An equivalent method of complying with this AD may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Amendment 39-4140 became effective June 30, 1981. This amendment 39-4256 becomes effective November 20, 1981.
81-03-01: 81-03-01 MESSERSCHMITT-BOLKOW-BLOHM GMBH: Amendment 39-4033. Applies to Model BO-105 series helicopters, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent failure of the helicopter drive system, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, for all installed Bendix drive shafts, P/N 19E146-1 (all modification indices), hereinafter referred to as drive shaft, inspect all nutplates for selflocking capability in accordance with Action No. 1 of paragraph 2B, "ACCOMPLISHMENT INSTRUCTIONS," of Messerschmitt-Bolkow-Blohm GmbH Alert Service Bulletin AB-19, dated March 7, 1980 (hereinafter referred to as the service bulletin), or an FAA-approved equivalent. (b) If as a result of the inspection required in paragraph (a) of this AD, all selflocking nutplates are found to have the proper selflocking capability - (1) Identify the drive shaft in accordance with Action No. 1, Item (6) of paragraph 2B, "ACCOMPLISHMENT INSTRUCTIONS," of the service bulletin, or an FAA- approved equivalent; and (2) Return the drive shaft to service in accordance with Action No. 1, Item (6), and Action No. 2 of paragraph 2B, "ACCOMPLISHMENT INSTRUCTIONS," of the service bulletin, or an FAA-approved equivalent. (c) If as a result of the inspection required in paragraph (a) of this AD, one or more selflocking nutplates are found to be defective, before further flight - (1) Remove the drive shaft from service and replace the defective shaft with a serviceable or new shaft which has new selflocking nutplates, P/N LN 29679AM9 installed, or have been marked with a blue dot, in accordance with Action No. 3 of paragraph 2B, "ACCOMPLISHMENT INSTRUCTIONS," of the service bulletin, or an FAA-approved equivalent; or (2) Comply with paragraph (d) of this AD. (d) If as a result of the inspection required in paragraph (a) of this AD on an installed drive shaft, one or more nutplates are found to have inadequate selflocking capability, the helicopter may be continued in service provided - (1) Drive shaft tab washers, P/N LN 9023-B8-1.4544.9, are installed in lieu of the standard washer in accordance with Action No. 4 of paragraph 2B, "ACCOMPLISHMENT INSTRUCTIONS," of the service bulletin, or an FAA-approved equivalent; and (2) Paragraph (c)(2) of this AD must be accomplished before the accumulation of an additional 300 hours time in service. (e) For all drive shafts held as spares, before release to service, inspect the selflocking nutplate for proper selflocking capability in accordance with Action No. 2 of paragraph 2B, "ACCOMPLISHMENT INSTRUCTIONS," of the service Bulletin, or an FAA- approved equivalent. (f) Helicopters may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the inspections and repairs required by this AD may be performed. (g) 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. (h) Report defects found to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (Reporting approved by Office of Management and Budget under OMB No. 04-R0174.) NOTE: Messerschmitt-Bolkow-Blohm Gmbh telegraphic message to all operators, dated March 7, 1980, refers to the same subject. This amendment becomes effective January 29, 1981, as to all persons except those persons to whom it was immediately effective by telegraphic AD T80EU23, issued May 8, 1980, which contained this amendment.
2016-13-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767 airplanes. This AD was prompted by a determination that certain splice plate locations of the aft pressure bulkhead web are hidden and cannot be inspected using existing manufacturer service information. This AD requires repetitive open-hole high frequency eddy current (HFEC) inspections for cracking of the aft pressure bulkhead web. We are issuing this AD to detect and correct cracking in the aft pressure bulkhead web, which could result in rapid airplane decompression and loss of structural integrity.