Results
99-07-20: This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R2160 airplanes. This AD requires repetitively inspecting the vertical stabilizer spar in the area of the lower fitting of the rudder for cracks, loose rivets, or spar web distortion; and modifying the vertical stabilizer spar either immediately or at a certain time period depending on whether discrepancies are found during the inspections. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect defects (cracks, loose rivets, or spar web distortion) in the vertical stabilizer spar, which could result in structural failure of the vertical stabilizer with possible reduced or loss of control of the airplane.
2013-15-01: We are adopting a new airworthiness directive (AD) for Agusta Model AB139 and AW139 helicopters. This AD requires deactivating the Full Icing Protection System (FIPS) and installing a placard next to the FIPS controller stating that flight into known icing is prohibited. This AD is prompted by a report of a fire in the aft avionics bay and the baggage compartment resulting from an Auto Transformer Rectifier Unit internal circuit overload. These actions are intended to prevent a fire, structural damage, and subsequent loss of control of the helicopter.
99-08-07: This amendment supersedes an existing priority letter airworthiness directive (AD) 98-17-14, applicable to MDHS Model 369E, 369FF, 500N, and 600N helicopters, that currently requires, within the next 14 calendar days, inspecting each relay receptacle contact socket for correct size of the contact socket holes and replacing incorrectly-sized contact sockets with airworthy contact sockets. This amendment requires the same inspections and replacements as the existing priority letter AD, but changes the serial numbers affected for the MDHS Model 500N and 600N helicopters and changes a part number that was incorrectly referenced in the existing AD. This amendment is prompted by three incidences in which a MDHS Model 600 helicopter's Engine Control Unit (ECU) Fail light illuminated, even though the ECU continued to automatically control the engine. The cause of the ECU malfunction indication was determined to be contact sockets that did not properly fit the corresponding pins ofthe affected relay. Improperly sized contact sockets could create multiple unsafe conditions. These conditions, if not corrected, could result in the loss of various engine control or warning systems including the undetected loss of the auto-reignition function after an engine flameout, failure of an engine to reignite, and a subsequent forced landing and the inability to immediately detect an engine-out condition or to properly govern main rotor speed following loss of the Full Authority Digital Engine Control (FADEC), and subsequent loss of control of the helicopter.
2022-13-16: The FAA is adopting a new airworthiness directive (AD) for all GE Aviation Czech s.r.o. (GEAC) M601D-11 model turboprop engines. This AD was prompted by the manufacturer revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM) to include a visual inspection of the centrifugal compressor case for cracks. This AD requires revising the ALS of the existing EMM to incorporate a visual inspection of the centrifugal compressor case. The FAA is issuing this AD to address the unsafe condition on these products.
69-20-07: 69-20-07 FAIRCHILD-HILLER: Amendment 39-857 (Amendment 39-845 was not distributed.) Applies to Fairchild Hiller F-27 and FH-227 type airplanes certificated in all categories. To prevent malfunction of the flap operating system accomplish the following within 15 hours time in service after the effective date of this airworthiness directive unless already accomplished within the last 25 hours time in service, and thereafter when the universal joint pins or bolts at either end of the subject connecting shaft assembly are removed: (a) Inspect the universal joint at each end of the wing flap connecting shaft assembly, P/N 27-727944-1, located between the flap motor gearbox at wing station 141 left (installed in the wheel well of the left nacelle) and the gearbox at wing station 121 left to assure some freedom of movement in all axes. If freedom of movement is not determinable, remove and replace deficient universal joint pin or bolt before further flight except that a ferry flight may be permitted without the use of flaps in accordance with FAR 21.197. (b) Report the results of the findings in compliance with this AD to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region (reporting approved by the Bureau of the Budget under BOB No. 04-R0174). This amendment is effective October 3, 1969 and was effective upon receipt for all recipients of the telegram dated 3 September 1969 which contained this amendment.
99-02-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-02-51 that was sent previously to all known U.S. owners and operators of Allison Engine Company, Inc. AE 3007A and AE 3007C series turbofan engines by individual telegrams. This AD prohibits, prior to further flight, all engine ground starts at oil temperatures below 32 deg. F (0 deg. C) unless preflight operational procedures ensure that engine oil temperature is maintained at or above 32 deg. F (0 deg. C). This amendment is prompted by reports of in-flight engine shutdowns. The in-flight engine shutdowns have been attributed to loss of engine oil from the starter shaft seal. The actions specified by this AD are intended to prevent an in-flight engine shutdown due to loss of engine oil from the starter shaft seal.
47-10-06: 47-10-06 LOCKHEED: (Was Mandatory Note 7 of AD-763-3.) Applies to All Model 49 Serials Incorporating Parker 4-1042-11-2 Plug Valves in the Fuel System. Compliance required prior to March 15, 1947. Rework all fuel tank shutoff and fuel cross transfer valves by installing new type shaft sealing rings, valve caps, packing caps, cap gaskets and cap attachment screws. This rework also applies to valves previously reworked, as identified by the use of countersunk head screws with star lock washers or fillister head screws. (LAC Service Instruction 049/SI-74, revised September 9, 1946, or subsequent, covers this same subject.)
2013-19-11: We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA 42, DA 42 NG, and DA 42 M-NG airplanes. This AD results from mandatory continuing airworthiness [[Page 59224]] information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient clearance between the rod end safety washer and the nose landing gear attachment lever causes the rod end to bend at each gear retraction sequence. We are issuing this AD to require actions to address the unsafe condition on these products.
78-08-07: 78-08-07 PRATT & WHITNEY AIRCRAFT: Amendment 39-3175. Applies to Pratt & Whitney Aircraft Wasp, Jr. and R985 model engines. Compliance required as indicated, unless already accomplished. To prevent cylinder head separation from the barrel, perform the following in accordance with Pratt & Whitney Aircraft Service Bulletin No. 1785 or later FAA-approved revision. 1. Visually inspect cylinder heads in accordance with Part B of the bulletin as follows: A. Cylinders not ultrasonically inspected, inspect within 50 hours time in service after effective date of the AD, and thereafter at intervals not to exceed 100 hours time in service. B. Cylinders ultrasonically inspected, inspect within 150 hours time in service after effective date of the AD, and thereafter at intervals not to exceed 150 hours time in service. 2. Remove visibly cracked cylinders and cylinders with black combustion leakage from service before further flight. 3. After the effective date of this AD, inspect all cylinder assemblies, prior to installation on an engine, by the ultrasonic test procedure in Part A of Service Bulletin 1785 or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 4. Remove from service cylinders which show cracks in excess of the limits of Part A, Section IV, of the bulletin. NOTE: Cylinders which have been ultrasonically tested are stamped "UT" and last two digits of year inspected over the intake port. The manufacturer's service bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corp., 400 Main Street, East Hartford, Connecticut 06108. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and FAA Headquarters, 800 Independence Avenue SW., Washington, D.C. 20591. This supersedes AD 76-20-01, Amendment 39-2728. This amendment becomes effective May 2, 1978.
93-01-03: 93-01-03 AYRES CORPORATION: Amendment 39-8456. Docket No. 92-CE-44-AD. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers S2D all serial numbers S2R 5000 through 5099, 1380R, and 1416R through 2583R S2R-R1340 R1340-001 through R1340-030 (with or without DC suffix) S2R-R3S R3S-001 through R3S-011 (with or without DC suffix) S2R-R1820 R1820-001 through R1820-035 (with or without DC suffix) S2R-T11 T11-001 through T11-005 (with or without DC suffix) S2R-T15 T15-001 through T15-029 (with or without DC suffix) and T15-031 (with or without DC suffix); and T27-001 through T27-029 (with or without DC suffix) and T27-031 (with or without DC suffix) S2R-T34 6000 through 6049, T34-001 through T34-178 (with or without DC suffix) and T34-180 (with or without DC suffix); and T41-001 through T41-178 (with or without DC suffix) and T41-180 (with or without DC suffix) S2R-T45 T45-001 through T45-003 (with or without DC suffix) S2R-T65 and S2RHG-T65 T65-001 through T65-010 (with or without DC suffix S2R-G6 G6-101 through G6-107 (with or without DC suffix) Compliance: Required within the next 3 calendar months after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 12 calendar months. To prevent wing structural damage that, if not detected, could progress to the point of failure, accomplish the following: (a) Inspect the wing front spar for corrosion in accordance with the "ACCOMPLISHMENT INSTRUCTIONS: I. Inspection of Front Spar" section of Ayres Service Bulletin (SB) No. SB-AG-29, dated June 15, 1992. (b) If corrosion is found, prior to further flight, treat and repair the corrosion damage in accordance with the "ACCOMPLISHMENT INSTRUCTIONS: II. Repairs" section of Ayres SB No. SB-AG-29, dated June 15, 1992. (c) Special flight permits may be issued in accordance with FAR 21.197 and21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) 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, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (e) The inspections required by this AD shall be done in accordance with Ayres Service Bulletin No. SB-AG-29, dated June 15, 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 CFRPart 51. Copies may be obtained from the Ayres Corporation, P.O. Box 3090, Albany, Georgia 31708. 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. (f) This amendment becomes effective on February 5, 1993.
99-08-03: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-600, -700, and -800 series airplanes. This action requires an inspection of the power distribution panels (PDP) to verify proper installation of the power feeder terminals and associated hardware, and corrective actions, if necessary. This action also requires repetitive torque checks of the terminal attachment screws. This amendment is prompted by reports indicating the loss of electrical power from the engine-driven generators or the auxiliary power unit due to overheating, melting, and subsequent failure of the power feeder terminals. The actions specified in this AD are intended to prevent such conditions, which could result in increased risk of fire and the loss of electrical power from the associated alternating current power source.
82-08-04: 82-08-04 VARGA AIRCRAFT CORPORATION (Morissey): Amendment 39-4362. Applies to Models 2150A and 2180 (S/Ns VAC 50 thru VAC 181) airplanes, certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent failure of the elevator horn assembly which will result in loss of elevator control, accomplish the following: A) Prior to further flight after the effective date of this AD and thereafter before the first flight of each day: 1) Conduct a visual inspection using a 4X glass of the radius of the P/N VAC 6000L-65 (steel) elevator horn to elevator attach flanges, particularly in the side adjacent to the balance weights. 2) Conduct a visual check of the radius of the P/N VAC 6000J-32 or P/N VAC 6000K-32 (aluminum) elevator horn to elevator attach flanges, particularly in the side opposite the balance weights. 3) The pre-flight checks required by paragraph A)2) of this AD may be performed by the holder of a pilotcertificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person that is not used in air carrier service. Record compliance with the AD by an appropriate entry in the airplane maintenance records as required by FAR 91.173. B) If any cracks are found, prior to further flight, replace with like serviceable part and continue the inspections/checks required by this AD or replace with P/N VAC 30400-100 elevator horn/balance arm assembly in accordance with paragraph C) of this AD. C) On or before June 12, 1982, replace P/N VAC 6000J-32, P/N VAC 6000K-32 and P/N 6000L-65 with P/N VAC 30400-100 elevator horn/balance arm assembly in accordance with Varga Aircraft Corporation Service Instruction SI 0024 dated February 22, 1982. When this is accomplished, the special inspections/checks required by this AD are no longer applicable. D) Special flight permits may be issued in accordance with FAR 21.197 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. E) Any alternate means of compliance with this AD may be used when approved by the Chief, Western Aircraft Certification Field Office, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009; telephone (213) 536-6352. This AD supersedes Amendment 39-4213 (46 FR 46123), AD 81-17-05 and priority letter AD 81-21-07 dated October 7, 1981. This Amendment 39-4362 becomes effective on April 15, 1982.
75-16-15: 75-16-15 BRITISH AIRCRAFT CORPORATION: Amendment 39-2288. Applies to BAC Model 1-11, 200 and 400 Series airplanes, except those which have been modified in accordance with Dunlop Modification C.1559, part (b) to incorporate the strengthened filter housing, P/N ACM.27656. Compliance is required as indicated. To prevent failure of the handbrake control valve filter housing, accomplish the following: (a) For handbrake control valves, P/N AC 61772, prior to the accumulation of 7,000 total landings, or within the next 25 landings after the effective date of this AD, whichever occurs later, unless already accomplished within the last 350 landings - (1) Clean the filter housing on the handbrake control valve, P/N AC 61772; (2) With the No 2 hydraulic system pressurized to 3,000 psi, inspect the face of the filter housing, P/N ACM. 23102 for hydraulic fluid leakage and distortion; and (3) If leakage or distortion is found, before further flight, remove the handbrake control valve from service and comply with paragraph (d). (b) For handbrake control valves, P/N AC 61772, except those which have been modified in accordance with Dunlop Modification C.1559, part (a), prior to the accumulation of 9,500 total landings, or within the next 500 landings after the effective date of this AD, whichever occurs later, remove the handbrake control valve from service, and comply with paragraph (d). (c) For handbrake control valves, P/N AC 61772, which have been modified in accordance with Dunlop Modification C.1559, part (a), prior to the accumulation of 12,000 total landings (including landings before modification), or within the next 500 landings after the effective date of this AD, whichever occurs later, remove the handbrake control valve from service, and comply with paragraph (d). (d) Replace handbrake control valves removed as a result of the action required by paragraphs (a)(3), (b), or (c) of this AD with any of the following: (1) Serviceable handbrake control valves, P/N AC 61772, which have accumulated less than 9,500 landings since new and continue to comply with paragraphs (a) and (b); (2) Serviceable handbrake control valves, P/N AC 61772, which have been modified in accordance with Dunlop Modification C.1559, part (a) and have accumulated less than 12,000 landings since new and continue to comply with paragraphs (a) and (c); or (3) Serviceable handbrake control valves, P/N AC 61772, which have had the old type filter housing, P/N ACM. 23102 replaced with the new strengthened filter housing, P/N ACM. 27656 in accordance with Dunlop Modification C.1559, part (b). (e) For the purpose of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the BAC 1-11 airplane. (Dunlop Alert Service Bulletin No. 29-A131,dated December 16, 1971, Dunlop Service Bulletin No. 29-131, dated December 20, 1971; and Revision 1, dated January 7, 1972; and BAC 1-11 Alert Service Bulletin No. 32-A-PM 5102, dated July 14, 1972, cover this same subject). This amendment becomes effective August 28, 1975.
88-01-11: 88-01-11 SHORT BROTHERS PLC: Amendment 39-5820. Applies to Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3676, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent incorrect installation of aileron control levers and rods, which would result in increased aileron control forces and improper aileron travel, accomplish the following: A. Within the next 4,800 flight hours after the effective date of this AD or at the next time the aileron control system is disassembled following 90 days after the effective date of this AD, whichever occurs first, install the guards (plates) in the aileron control system, as described in the Accomplishment Instructions of Shorts Service Bulletin No. SD360-27-09, Revision No. 3, dated November 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 modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Short Brothers, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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 February 16, 1988.
82-05-06: 82-05-06 AIR CRUISERS COMPANY: Amendment 39-4326. Applies to life rafts P/N D23835-403, S/N 8624978 through 9925181. Compliance required within 60 days after the effective date of this AD, unless already accomplished. To prevent the need for excessive pull force to activate the gas release mechanism, accomplish the modifications described in paragraph 2 of Air Cruisers Company Service Bulletin 111-81-1, dated July 24, 1981. An equivalent method of compliance may be approved upon request to the Chief, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, JFK International Airport, Jamaica, New York 11430. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the compliance time of this AD may be adjusted by the Chief, New York Aircraft Certification Office, ANE-170, Federal Aviation Administration, JFK International Airport, Jamaica, New York 11430. The manufacturer's Service Bulletinidentified and described in this directive is available upon request to Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719. This document may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. This airworthiness directive becomes effective March 31, 1982.
2013-19-12: We are adopting a new airworthiness directive (AD) for GA 8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the fuel system integral sump tank does not meet FAA regulations. We are issuing this AD to require actions to address the unsafe condition on these products.
99-07-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to detect corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer; and corrective actions, if necessary. This amendment is prompted by reports of corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer, apparently due to the improper brushing of cadmium on the hinge plates during manufacture. The actions specified by this AD are intended to detect and correct corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer, which could result in reduced structural integrity of the airplane.
92-18-01: 92-18-01 BRITISH AEROSPACE: Amendment 39-8345. Docket No. 92-NM-45-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2045, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent engine rundown (flame out) due to ice ingestion, accomplish the following: (a) Within 90 days after the effective date of this AD, install bonding straps, Modification 35229A, at the oil cooler temperature controller in Module 3, the throttle stepper motor controller, and the engine de-ice timers, in accordance with British Aerospace Service Bulletin ATP-24-45-35229A, dated December 20, 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 may add 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 installation shall be done in accordance with British Aerospace Service Bulletin ATP-24-45-35229A, dated December 20, 1991, which contains the following list of effective pages: Page Number Revision Level Date 1-7, 9, 11, 13, Original December 20, 1991 15, 17, 19 8, 10, 12, 14, (These pages are not used) 16, 18 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. 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 October 8, 1992.
2022-11-20: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a large crack detected on the tail gearbox (TGB) fitting during a scheduled inspection and the determination that certain TGB fittings are required to be inspected by the use of a borescope. This AD requires a one-time borescope inspection of certain part-numbered TGB fittings, and depending on the inspection results, removing the affected part from service and replacing with an airworthy part, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
93-11-11: 93-11-11 AC, TEXTRON LYCOMING, AND RAJAY/ROTOMASTER: Amendment 39-8584. Docket 93-ANE-16. Supersedes Priority Letter AD 93-05-21, which superseded Priority Letter AD 92-20-07. Applicability: AC, Textron Lycoming, and Rajay/Rotomaster-modified high pressure diaphragm fuel pumps, overhauled by Aero Accessories Inc. (AAI) between June 18, 1991, and November 24, 1992; AC model 41234, having AAI serial numbers (S/Ns) 91F006 through 92E050 and 92E052 through 92K008; AC model 40296, having AAI S/Ns 92B002 through 92I155; AC model 41812, having AAI S/N 91L142; Textron Lycoming model LW15473, having AAI S/Ns 91K049 through 92I151; Rajay/Rotomaster-modified model R00253-501, having AAI S/Ns 92D136 through 92J016; Rajay/Rotomaster modified model R00253-502, having AAI S/Ns 92D120 through 92H075; and Rajay/Rotomaster-modified model 103586-01, having AAI S/N 92J024; installed on but not limited to Textron Lycoming IO-320, LIO-320, IO-360, LIO-360, O-540-L3C5D, IO-540, TIO-540, and LTIO-540 piston engines; installed on but not limited to piston engine powered aircraft manufactured by Beechcraft, Bellanca, Cessna, Mooney, Piper, and Rockwell Commander (Models 112 and 114) aircraft; and AC, Textron Lycoming, and Rajay/Rotomaster-modified low pressure diaphragm fuel pumps, overhauled by AAI between November 1, 1991, and August 20, 1992; AC model numbers 40174, 40295, 40595, 41270, 41271, 41272, 41452, 41617, 75246, 75247; Textron Lycoming model numbers LW14282, LW15399, LW15472, LW16335, LW16775, LW16947; and Rajay/Rotomaster-modified models 103396-01, RJ4033, and R00253-2; having AAI S/Ns 91K073 through 91K125, all S/Ns beginning with prefixes 91L, 92A, 92B, 92C, 92D, 92E, 92F, 92G, and 92H001 through 92H146; installed on but not limited to Textron Lycoming model O-235, O-290, O-320, O-360, LO-360, LTO-360, and O-540 piston engines; installed on but not limited to piston engine powered aircraft manufactured by Beechcraft, Bellanca, Cessna, Mooney, and Piper. Compliance: Required prior to further flight, unless accomplished previously. To prevent disruption of fuel flow to the engine, which can result in a loss of engine power, accomplish the following: (a) Remove from service affected low pressure diaphragm fuel pumps and replace with a serviceable pump. (b) For the purposes of paragraph (a) of this AD, a serviceable low pressure diaphragm fuel pump is either an AC, Textron Lycoming, or Rajay/Rotomaster-modified pump that has never been overhauled by AAI, or has an "S" stamped on the flange above the inlet port of the fuel pump to indicate previous compliance with priority letter AD 92-20-07. (c) No further action is required for all affected low pressure diaphragm fuel pumps that have complied previously with priority letter AD 92-20-07. NOTES: 1. The model number is located on the edge of the mounting flange. 2. The S/N is located on the "housing backbone" between the mounting flange and the round spring housing.3. For further information, see Aero Accessories, Inc. Mandatory Service Bulletin No. 001, dated August 21, 1992. Copies of this service bulletin may be obtained from Aero Accessories, Inc., 1240 Springwood Church Road, Gibsonville, NC 27249, telephone (919) 449-5054. (d) Remove from service affected high pressure diaphragm fuel pumps and replace with a serviceable pump. (e) For the purposes of paragraph (d) of this AD, a serviceable high pressure diaphragm fuel pump is either an AC, Textron Lycoming, or Rajay/Rotomaster-modified pump that has never been overhauled by AAI, or has an "S2" stamped on the flange above the inlet port of the fuel pump to indicate previous compliance with priority letter AD 93-05-21. (f) All affected high pressure diaphragm fuel pumps must be replaced, regardless of compliance with priority letter AD 92-20-07. NOTES: 1. The model number is located on the edge of the mounting flange. 2. The serial number is located on the "housingbackbone" between the mounting flange and the round spring housing. 3. For further information, see Aero Accessories, Inc. Mandatory Service Bulletin No. 002, dated February 25, 1993. Copies of this service bulletin may be obtained from Aero Accessories, Inc., 1240 Springwood Church Road, Gibsonville, NC 27249, telephone (919) 449-5054. (g) 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, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office. (h) This amendment supersedes priority letter AD 93-05-21, issued March 17, 1993. (i) This amendment becomes effective on June 21, 1993.
2010-14-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Certain main landing gear components have experienced premature failure during certification testing. Revision has been made to the DHC-8-400 Maintenance Requirements Manual, Airworthiness Limitation Items, to incorporate the revised safe life limits for the main landing gear lock actuator assembly, retraction actuator assembly rod end and piston, and the upper bearing in the main landing gear shock strut assembly. Failure of these components could adversely affect the structural integrity of the main landing gear. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
99-07-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured Model HH-1K, SW204, SW204HP, SW205, SW205A-1, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters. This action requires inspecting the tail rotor yoke (yoke) assembly historical records to determine if the affected yoke assembly has been involved in any incidents that may have induced a bending load. It further requires replacement of the yoke assembly with a yoke assembly that has been x-ray diffraction inspected or has zero hours time-in-service (TIS); installing and inspecting an airworthy flapping stop or trunnion assembly to detect excessive bending loads; and revising the applicable Rotorcraft Flight Manual. This amendment is prompted by in-flight failures of yokes installed on civilian and military helicopters of similar type design, including three reported accidents. The actions specified in this AD are intended to detect static or dynamic overload on the yoke due to external bending forces, which could result in failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.
84-10-51 R1: 84-10-51 R1 BOEING VERTOL COMPANY: Amendment 39-5024 as amended by Amendment 39-5352. Applies to Model 234 series helicopters, certificated in any category, equipped with forward main rotor drive shaft P/N 114D1245-7. Compliance is required as indicated, unless already accomplished. To prevent possible hazards in flight associated with cracking of the forward main rotor drive shaft, accomplish the following: (a) Within 70 hours time in service after the effective date of this amendment or upon accumulation of 1,600 total hours time in service on the rotor shaft, whichever occurs later, and thereafter at intervals not to exceed 35 hours time in service from the last inspection, inspect the rotor drive shaft in accordance with paragraph 3, "Accomplishment Instructions," Boeing Vertol Service Bulletin No. 234-63-1009, dated June 29, 1984, or Revision 1 dated May 1, 1986, or an FAA-approved equivalent. (b) Remove from service forward main rotor drive shafts havinga crack and replace with a serviceable part prior to further flight. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA New England Region, may adjust the compliance times specified in this AD. (e) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Vertol Company, Boeing Center, P.O. Box 16858, Philadelphia, Pennsylvania 19142. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. Amendment 39-5024 (50 FR 15539) became effective April 22, 1985, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T84-10- 51, issued May 3, 1984, which contained this amendment. This Amendment 39-5352 becomes effective July 24, 1986.
2013-19-01: We are adopting a new airworthiness directive (AD) for AgustaWestland S.p.A. (AgustaWestland) Model A119 and AW119 MKII helicopters to require inspecting the pilot and co-pilot doors to ensure that the windows are properly bonded within the doors. If the windows are not properly bonded, the AD requires applying bonding to the windows, the seals, and the window frames of the pilot and co-pilot doors. This AD was prompted by the loss of a pilot-door window during a test flight. The actions of this AD are intended to ensure the windows do not detach from the doors, potentially injuring persons on the ground and damaging the helicopter's tailboom and the tail rotor blades.
2013-18-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of cracked and corroded nuts on an outboard flap support rib. This AD requires, for certain airplanes, repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, and related investigative and corrective actions if necessary. For certain other airplanes, this AD also requires repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, related investigative and corrective actions if necessary, and if necessary, a detailed inspection to determine the nut type installed in the outboard flap support rib and corrective actions. This AD also provides terminating action for the repetitive inspections under certain conditions. We are issuing this AD to detect and correct cracked and corroded nuts and bolts and the installation of incorrect nuts on certain outboard flap support ribs, which could lead to additional nut and bolt damage in the joint, result in loss of an outboard flap, and adversely affect continued safe flight and landing of the airplane.