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92-18-07: 92-18-07 FAIRCHILD AIRCRAFT (formerly Swearingen Aircraft Corporation): Amendment 39-8351. Docket No. 92-CE-06-AD. Supersedes AD 91-23-04, Amendment 39-8073. Applicability: The following model and serial numbered airplanes, certificated in any category: Model Serial Numbers SA226-T T201 through T275, and T277 through T291 SA226-T(B) T(B)276, and T(B)292 through T(B)417 SA226-AT AT001 through AT074 SA226-TC TC201 through TC419 SA227-TT TT421 through TT541 SA227-AT AT423 through AT695 SA227-AC AC406, AC415, AC416, and AC420 through AC777 SA227-BC BC762, BC764, BC766, and BC777 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of control of the airplane because of improper operation of the power lever flight idle detent arms, accomplish the following: (a) Modify the power lever detent arms and cover assembly in accordance with the instructions in Fairchild Service Bulletin (SB) No. 226-76-008, issued January 15, 1991, revised December 17, 1991; or Fairchild SB No. 227-76-002, issued January 15, 1991, revised May 9, 1991, whichever is applicable. (b) If the modification required by paragraph (a) of this AD has been accomplished in accordance with either Fairchild SB No. 226-76-008 or Fairchild SB No. 227-76-002, both issued January 15, 1991, revised May 9, 1991, whichever is applicable (superseded AD 91-23-04), then no further action is required by this AD. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Fort Worth Airplane Certification Office, FAA, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Aircraft Certification Office. (e) The modification required by this AD shall be done in accordance with Fairchild Service Bulletin No. 226-76-008, issued January 15, 1991, revised December 17, 1991; or Fairchild Service Bulletin No. 227-76-002, issued January 15, 1991, revised May 9, 1991. The incorporation by reference of Fairchild Service Bulletin No. 226-76-008, issued January 15, 1991, revised December 17, 1991, was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of Fairchild Service Bulletin No. 227-76-002, issued January 15, 1991, revised May 9, 1991, was previously approved by the Director of the Federal Registeron December 10, 1991, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (f) This amendment (39-8351) supersedes AD 91-23-04, Amendment 39-8073. (g) This amendment becomes effective on October 2, 1992.
2023-23-13: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model RB211-Trent 800 engines. This AD is prompted by reports of cracks on certain intermediate-pressure compressor (IPC) rotor shaft balance lands. This AD requires initial and repetitive on-wing or in-shop borescope inspections (BSIs) of certain IPC rotor shaft balance lands for cracks, dents, and nicks, and replacement of the IPC rotor shaft if necessary, and would prohibit the installation of a certain IPC rotor shaft on any engine, 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.
90-11-10: 90-11-10 BOEING: Amendment 39-6608. Docket No. 89-NM-144-AD. \n\n\tApplicability: Model 757 and 767 series airplanes, equipped with Collins flight control computers (FCC), certified in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent intermittent altitude hold, altitude capture, and/or flight director mistracking anomalies, accomplish the following: \n\n\tA.\tWithin the next 24 months after the effective date of this AD, remove Collins manufactured FCC's which have Boeing P/N S241T100-103, and replace with units reworked to P/N S241T100-108, in accordance with Collins Service Bulletins FCC-701-22-10, Revision 2, dated March 24, 1988, and FCC-701-22-16, dated October 14, 1988. \n\n\tB.\tWithin the next 12 months after the effective date of this AD, remove Collins manufactured FCC's which have Boeing P/N S241T100-105 or -106, and replace with units reworked to P/N S241T100-108, in accordance with Collins Service Bulletin FCC-701-22-16, dated October 14, 1988. \n\n\tC.\tAlternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Avionics Inspector, who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle,Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6608, AD 90-11-10) becomes effective on July 2, 1990.
2000-23-26: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR72 series airplanes, that requires a revision to the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate inspections to detect fatigue cracking in certain structure, inspection intervals, and life limits for certain components. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2005-05-08: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100B SUD, -300, -400, and -400D series airplanes. This AD requires a one-time inspection for discrepancies of the fuselage frame to tension tie joints at body stations (BS) 1120 through 1220 and to determine if steel splice plates are installed on the fuselage frames, and related investigative and corrective actions. This AD is prompted by reports indicating that severed tension ties were found at the fuselage frame joints at BS 1120 and 1140. We are issuing this AD to prevent fatigue cracking of the fuselage frame to tension tie joints, which could result in severing of the tension ties and consequent rapid decompression of the airplane fuselage.
91-24-14: 91-24-14 PRATT & WHITNEY: Amendment No. 39-8101. Docket No. 91-ANE-44. Applicability: Pratt & Whitney (PW) JT8D-1, -1A, -1B, -5, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines installed on but not limited to Boeing 727 and 737 series aircraft, McDonnell Douglas DC-9 series and MD-80 series aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent No. 4-1/2 bearing failure, uncontained engine failure, inflight shutdown, or possible aircraft damage accomplish the following: (a) Within 15 days after the effective date of this AD, conduct a search and review of the following: (1) Purchasing records for the No. 4-1/2 bearing seal spacer, P/N 525961, to identify the purchase source. (2) Engine maintenance records to determine if the No. 4-1/2 bearing seal spacer, P/N 525961, was installed by PW in a new or overhauled JT8D engine. (b) If the records indicate that the No. 4-1/2 bearing seal spacer, P/N 525961, was purchased directly from PW customer parts support or the spacer was installed by PW in a new or overhauled JT8D engine, no further action is required. (c) If the records indicate that the No. 4-1/2 bearing seal spacer, P/N 525961, was not obtained directly from PW customer parts support, or was not installed by PW, or if the purchase source is unknown, accomplish the following: (1) For No. 4-1/2 bearing seal spacers, P/N 525961, not installed in JT8D engines, perform the following one-time inspection prior to installation in an engine or within 45 days after the effective date of this AD, whichever occurs first. (i) Visually inspect to confirm the presence of hardface on the spacer. An approved No. 4-1/2 bearing seal spacer will have hardface which exhibits a shiny machined appearance. An unapproved spacer does not have hardface. (ii) Visually inspect to confirm that the spacer is a silver color. The unapproved spaceris manufactured from a different material and has a bronze color. (iii) Determine the material hardness of the No. 4-1/2 bearing seal spacer in accordance with industry standard practices on a non-hardfaced and non-plated surface of the spacer, such as the bore inner diameter. Acceptable material hardness is Rockwell C32 to C38, or its equivalent. (iv) A No. 4-1/2 bearing seal spacer, P/N 525961, that does not satisfy all three of the above inspections is considered unairworthy and shall not be placed in service. NOTE: Data pertaining to the location of the hardface and plated surfaces are contained in Section 72-53-37, of PW Engine Manual, P/N 481672 for JT8D-1 thru -17AR series engines, and PW Engine Manual, P/N 773128 for JT8D-200 series engines. (2) For engines that are not installed on aircraft, and that have a No. 4-1/2 bearing seal spacer, P/N 525961, with less than 600 hours total time in service on the effective date of this AD, disassemble the engine sufficiently to perform a one time inspection in accordance with the inspection requirements of paragraphs (c)(1)(i), (ii), and (iii) of this AD, prior to returning the engine to service. (i) A spacer that does not satisfy all the inspection criteria is considered unairworthy and shall not be returned to service. (ii) A spacer that has been inspected in accordance with the criteria listed in paragraph (c)(1)(i), (ii), and (iii) of this AD, and has satisfied that criteria, does not require a reinspection. (3) For engines that are installed on aircraft and that contain a No. 4-1/2 bearing seal spacer, P/N 525961, with less than 600 hours time in service on the effective date of this AD, accomplish the following: (i) Perform an oil system breather check on the engine within 100 hours time in service after the effective date of this AD in accordance with PW JT8D Maintenance Manual, Section 72-00-00, Troubleshooting-02, pages 120, 121, and 122, dated August 1, 1991, and pages 123, 124, 135, and 136, dated May 15, 1990, or PW JT8D Maintenance Manual, Section 72-00, Engine Troubleshooting, page 117 dated May 1, 1990, and pages 118, 119, 120, 121, 122, 123, and 124, dated September 1, 1986, as applicable. (ii) Thereafter, repeat the oil system breather check required by paragraph (c)(3)(i) of this AD at intervals not exceeding 100 hours time in service since the last check until the No. 4-1/2 bearing seal spacer has accumulated 600 hours total time in service. Engine breather checks are not required when time in service on the seal spacer is greater than or equal to 600 hours. (iii) Remove engines from service if the check indicates high breather pressure as defined in the applicable Sections of PW JT8D Maintenance Manual referenced in Paragraph (c)(3)(i) of this AD. (iv) At the next shop visit after the effective date of this AD, when the engine is disassembled sufficiently to gain access to the affected spacer, perform a one time inspectionin accordance with the inspection requirements of paragraphs (c)(1)(i), (ii), and (iii) of this AD, but no later than January 31, 1999. Performance of the one time inspection constitutes terminating action for the breather check requirements of paragraph (c)(3)(i) and (ii) of this AD. (A) A spacer that does not satisfy all the inspection criteria is considered unairworthy and must not be returned to service. (B) A spacer that has been inspected in accordance with the criteria listed in paragraph (c)(1)(i), (ii), and (iii) of this AD, and has satisfied that criteria, does not require a reinspection. NOTE: Applicable maintenance manuals are JT8D Maintenance Manual, P/N 481671 for JT8D-1 thru -17AR series engines, and JT8D Maintenance Manual, P/N 773127 for JT8D-200 series engines. (4) For engines (uninstalled or installed) containing a No. 4-1/2 bearing seal spacer, P/N 525961, having greater or equal to 600 hours total time in service on the effective date of thisAD, perform a one-time inspection in accordance with the inspection requirements of paragraphs (c)(1)(i), (ii), and (iii) of this AD, at the next shop visit when the engine is disassembled sufficiently to gain access to the affected spacer, but no later than January 31, 1999. (i) A spacer that does not satisfy all the inspection criteria is considered unairworthy and must not be returned to service. (ii) A spacer that has been inspected in accordance with the criteria of paragraph (c)(1)(i), (ii), and (iii) of this AD, and has satisfied that criteria, does not require a reinspection. (d) Within 30 days after the inspection requirements of paragraph (c)(1) of this AD have been accomplished, report the following information, if an unapproved spacer has been found: (1) Inspection results, (2) Time in Service of the spacer, and (3) Source of purchase of the spacer. This information is to be forwarded to the Manager, Engine Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. Information collection requirements contained in this regulation have been approved by the Office of Management Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and have been assigned OMB Control No. 2120-0056. (e) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where this AD can be accomplished. (f) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternative method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (g) The oil system breather checks shall be done in accordancewith the following Sections of Pratt & Whitney JT8D Maintenance Manuals: Document Number Page Number Date 72-00-00 120, 121, 122 8/1/91 123, 124, 135, 136 5/15/90 Total Pages: 7 72-00 117 5/1/90 118, 119, 120, 121, 9/1/86 122, 123, 124 Total Pages: 8 The 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 Pratt & Whitney, Publications Department, P. O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. This amendment (39-8101, AD 91-24-14) becomes effective on January 21, 1992.
2023-23-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a design review of the avionic architecture of the pitch trim indication and alerting system that revealed software errors could generate misleading pitch trim indication to the crew, leading to incorrect horizontal stabilizer positioning at takeoff. This AD requires revising the Emergency Procedures and Normal Procedures of the existing airplane flight manual (AFM) to ensure the horizontal stabilizer is correctly configured prior to takeoff. The FAA is issuing this AD to address the unsafe condition on these products.
97-02-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 and F28 Mark 0100 series airplanes, that requires installation of a bonding cable for the housing of the lavatory pump and filter assembly and the lavatory bowl. This amendment is prompted by a report indicating that the housing of the lavatory pump and filter assembly is not grounded properly. The actions specified by this AD are intended to prevent such improper grounding, which could result in an electrical fire and/or injury to passengers and crewmembers.
2000-23-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires an inspection to ensure correct installation of certain self-seal couplings in each nacelle, and corrective action, if necessary. This amendment also requires installation of a new clamp to the self-seal couplings. This action is necessary to prevent separation of the self-seal couplings, which could result in loss of engine oil pressure and a flight- crew-commanded engine shutdown. This action is intended to address the identified unsafe condition.
2005-05-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires repetitive detailed inspections to detect cracking of the aft and forward surfaces of the bulkhead web at nacelle station 180, and repair if necessary. This AD is prompted by reports of cracking of the web bulkhead at nacelle station 180. We are issuing this AD to detect and correct fatigue cracking of the web bulkhead, and consequent loss of the load path of the bulkhead at nacelle station 180, which when combined with the loss of the midspar load path, could result in the in-flight separation of the engine and strut. Such separation may result in secondary damage to the airplane and consequent reduced controllability of the airplane.
2023-22-06: The FAA is superseding Airworthiness Directive (AD) 96-12-20, which applied to certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 96-12-20 required visual inspections to detect loose, missing, or deformed fasteners in the upper truss mounts of certain engines, visual inspections to detect cracking in the associated lugs, repetitive ultrasonic inspections to detect cracking of the upper lugs, and replacement of damaged or cracked parts. AD 96-12-20 also provided for an optional terminating action for the repetitive inspections. This AD was prompted by reports of fatigue cracking of the lugs of the upper truss mount, and by reports of cracks found prior to the initial inspection times required by AD 96-12-20 and the determination that the terminating action is no longer valid. This AD requires one-time inspections for cracked or severed engine truss mount upper lugs of the outboard engines, and replacement of the engine truss mount if necessary. This AD also revises the applicability to include all Model 382, 382B, 382E, 382F, and 382G airplanes, and all Model EC-130Q, C-130H, HP-C-130A, C-130A, and C-130B (including Model 282- 44A-05) airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
78-17-07: 78-17-07 PRATT & WHITNEY AIRCRAFT OF CANADA, LIMITED: Amendment 39-3287. Applies to all Pratt & Whitney Aircraft of Canada, Limited PT6A-38, PT6A-41 and PT6A-45A engines and Pratt & Whitney Aircraft PT6A-38 engines with fuel control unit Aviation Electric Part Numbers 3244723-3 through -10, 3244738-5, 3244738-6, 3244752-6 through -10, and 3244755-7 through -11. Compliance required within the next 100 hours in service, after the effective date of this AD, unless already accomplished. To preclude rupture of the bypass valve diaphragm in the fuel control unit, replace the part number 2526477 diaphragm with part number 343451 diaphragm in accordance with Paragraph 2, Accomplishment Instructions, in Pratt & Whitney Aircraft of Canada, Limited Service Bulletin No. 3103 or approved equivalent parts and procedure. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197. Any equivalent parts and procedure must be approved by the Chief, Engineering & Manufacturing Branch of the Eastern Region of the Federal Aviation Administration (FAA). This amendment is effective August 31, 1978.
2023-21-12: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report of missing insulation in the engine pylon area. This AD requires, for certain airplanes, inspecting the engine pylon structure for discrepancies and repair if necessary. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate a new certification maintenance requirement (CMR) task. The FAA is issuing this AD to address the unsafe condition on these products.
2005-05-14: The FAA adopts a new airworthiness directive (AD) for certain Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B airplanes. This AD requires you to modify or replace the co-pilot rudder pedal assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Malaysia. We are issuing this AD to prevent binding of the co-pilot rudder pedal assembly due to premature wear of the bushing, which could result in loss of co-pilot rudder and brake control. This failure could result in loss of control of the airplane.
2023-22-04: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 engines. This AD was prompted by reports of cracking and separation of certain low-pressure turbine (LPT) stage 1 blade assemblies. This AD requires initial and repetitive inspections of affected LPT stage 1 blade assemblies for cracking or separation and, depending on the results of the inspections, reduction of the inspection interval or replacement of the LPT stage 1 blade set and disk, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-05-13: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines. That AD currently requires fluorescent penetrant inspection (FPI) of high pressure turbine (HPT) second stage airseals, part numbers (P/Ns) 5002537-01, 788945, 753187, and 807410, knife-edges for cracks, each time the engine's HPT second stage airseal is accessible. This AD requires replacing each existing HPT second stage airseal with an improved design HPT second stage airseal and modifying the 2nd stage HPT vane cluster assembly and 1st stage retaining blade HPT plate assembly at next piece-part exposure, but no later than five years after the effective date of this AD. These actions are considered terminating action to the repetitive inspections required by AD 2002- 10-07. This AD results from the manufacturer introducing an improved design HPT second stage airseal and modifications to increase cooling. We are issuing this AD to prevent failure of the HPT second stage airseal due to cracks in the knife-edges, which if not detected, could result in uncontained engine failure and damage to the airplane.
2023-22-14: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365C1, SA-365C2, and SA-365N helicopters. This AD was prompted by reports of damaged control rod dual bearings (dual bearings) that are installed on the tail rotor gearbox (TGB). This AD requires repetitively inspecting the TGB magnetic plug for particles, analyzing any particles collected, taking corrective actions if necessary, and reporting certain information. Finally, this AD allows an affected dual bearing to be installed on a helicopter if certain actions are accomplished, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-05-05: We are superseding Airworthiness Directive (AD) 2014-04-14 for Agusta S.p.A. (Agusta) Model A109S, AW109SP, A119, and AW119 MKII helicopters. AD 2014-04-14 required removing certain rod end assemblies from service because of reports of fractures. This new AD retains the requirements of AD 2014-04-14 but expands the scope of applicable rod end assemblies. This AD was prompted by reports of additional fractured rod end assemblies. We are issuing this AD to prevent failure of a rod end assembly, which could result in damage to the main rotor assembly and loss of control of the helicopter.
47-51-12: 47-51-12 DOUGLAS: Applies to All converted C-47 Series Aircraft With Ram Non-ram (Hydraulic) Type Carburetor Airscoop. \n\nTo be accomplished not later than March 1, 1948. \n\nCompliance with the following items is necessary to preclude carburetor icing: \n\n1.\tThe carburetor alcohol system must be used. \n\n2.\tThe accessory cowling and engine fire seal must maintain not more than 1/4-inch clearance of the collector ring. \n\n3.\tThe cable system for operation of the hot air door must be rigged to 30 pounds tension. \n\n(Part B of Douglas Service Bulletin DC-3 No. 251 dated April 15, 1947, covers this same subject. Part A of the same Bulletin is not mandatory, but optional compliance may be accomplished when parts are available.)
2023-22-03: The FAA is superseding Airworthiness Directive (AD) 2021-08-02 for all Safran Helicopter Engines, S.A. (Safran) (type certificate previously held by Turbomeca, S.A.) Model Arriel 2D and Arriel 2E engines. AD 2021-08-02 required replacing certain critical parts before reaching their published in-service life limits, performing scheduled maintenance tasks before reaching their published periodicity, and performing unscheduled maintenance tasks when the engine meets certain conditions. Since the FAA issued AD 2021-08-02, Safran has revised the airworthiness limitation section (ALS) of the existing maintenance and overhaul manuals, introducing new and more restrictive instructions and maintenance tasks, which prompted this AD action. This AD requires updating the ALS of the existing engine maintenance manual (EMM) or instructions for continued airworthiness (ICA) and the existing approved maintenance or inspection program, as applicable, by incorporating the actions and associated thresholds and intervals, including life limits, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is proposing this AD to address the unsafe condition on these products.
2004-22-07: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2 turbofan engines with certain part number (P/N) high pressure turbine stage 2 nozzle guide vanes (HPT S2 NGVs) installed. This AD requires flex borescope inspections of HPT S2 NGVs installed in CF6- 80C2 turbofan engines. This AD results from an uncontained engine failure due to HPT S2 NGV distress. We are issuing this AD to prevent blade separation from HPT S2 NGV distress, which could result in an uncontained engine failure.
91-24-12: 91-24-12 BRITISH AEROSPACE: Amendment 39-8098. Docket No. 91-NM-133-AD. Applicability: Model ATP series airplanes, equipped with hydraulic selector valves part number AIR44880 and AIR44882, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a gear-up landing, accomplish the following: (a) Within 12 months after the effective date of this AD, modify and test the landing gear hydraulic selector valves in accordance with AP Precision Hydraulics Service Bulletin AIR44880-29-01, dated April 1991. NOTE: British Aerospace Service Bulletin ATP-29-6, dated April 12, 1991, references AP Precision Hydraulics Service Bulletin AIR44880-29-01, dated April 1991. (b) 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. NOTE:The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. (d) The modification and testing requirements shall be done in accordance with AP Precision Hydraulics Service Bulletin AIR44880-29-01, dated April 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, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington,D.C. This amendment (39-8098, AD 91-24-12) becomes effective on January 7, 1992.
2015-04-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes equipped with Pratt & Whitney Model JT9D or PW4000 engines. This AD was prompted by a report of several cases of low hydraulic pressure or loss of electrical power to the alternating current motor pump (ACMP) on the left engine. This AD requires inspecting for damage of the wiring bundles in the left engine's strut and corrective actions if necessary, and installing new wire support brackets and bundle clamps. We are issuing this AD to detect and correct chafed wire bundles due to rubbing against structure or a hydraulic piping elbow, which could result in electrical arcing in a flammable fluid leakage zone, and provide a possible ignition source for fuel vapors and hydraulic fluids. Ignited fuel vapors or hydraulic fluid in an area without a fire detection or suppression system could result in an uncontained engine strut fire and structural damage to the engine strut.
2000-22-05: This amendment supersedes an existing airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that currently requires a one-time visual inspection to determine the part number of the power control cable assemblies and pulleys of the engine controls; and replacement of the power control cable assemblies and pulleys (as applicable) with new parts, if necessary. This amendment requires accomplishment of the inspection and replacement in accordance with revised procedures. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent breakage of the power control cable assemblies due to the inflexible construction of the cable, which could result in loss of engine power and consequent reduced controllability of the airplane.
95-21-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires replacement of the fire extinguisher distribution pipe and attachments in the lower deck cargo compartment fire extinguishing system. This amendment is prompted by a report indicating that, in response to a smoke warning in the forward cargo compartment on one airplane, bottle 2 of the fire extinguishing system did not discharge extinguishing agent into the cargo compartment due to a blockage of the discharge pipe by debris within it. The actions specified in this AD are intended to ensure that, in the event of a fire, adequate fire extinguishing agent is discharged into the cargo compartment.