Results
91-07-51: 91-07-51 BOEING: Amendment 39-7004. Docket No. 91-NM-84-AD. \n\n\tApplicability: Model 757 series airplanes, line number 154 through 350, except line numbers 332 and 340, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect improperly installed nuts in the upper and lower attachment of the rudder yaw damper pogo assembly, accomplish the following: \n\n\tA.\tWithin the next 60 flight cycles or 20 days after the effective date of this AD, whichever occurs sooner, inspect the upper and lower attachment of the rudder yaw damper pogo assembly for improper installation of the nuts in accordance with Boeing Telegram M-7272-91- 1886, dated March 22, 1991. If less than one thread from the bolt protrudes through the nut, or if the nut is or appears to be cross threaded, replace both the nut and bolt prior to further flight. \n\n\tB.\tWithin 10 days after completion of the inspection required by paragraph A. of this AD, submit a report of findings of discrepancies to the Manager, Seattle Manufacturing Inspection District Office, ANM-108S, FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056; fax: (206) 227-1181. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \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. \n\n\tThe inspection shall be done in accordance with Boeing Telegram M-7272-91-1886, dated March 22, 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tThis amendment (39-7004, AD 91-07-51) becomes effective on July 1, 1991, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T91-07-51, issued March 27, 1991, which contained this amendment.
2023-21-10: The FAA is adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. This AD was prompted by reports of loose fasteners and cracks in the horizontal stabilizer (HS) left- and right- hand leading edge lateral ribs, the box in between, the center box upper panel, and HS forward back-up fitting. This AD requires an inspection of the HS affected areas for discrepancies and applicable corrective action, 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.
95-23-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A airplanes and Model Avro 146-RJ70A, -RJ85A, and RJ-100A airplanes. This action requires inspections to detect cracking and evidence of exhaust leaks in the forward face of the central panel of the forward firewall of the auxiliary power unit (APU) bay, and replacement of the central panel with a new panel, if necessary. This amendment is prompted by a report indicating that cracking due to leakage of hot exhaust gases was found in the forward face of the forward firewall of the APU bay. The actions specified in this AD are intended to prevent such gas leakage and subsequent cracking, which could damage the wiring to the APU fire bottle; this condition could result in failure of the APU fire bottle to discharge in the event of an APU fire.
2005-05-11: The FAA is adopting a new airworthiness directive (AD) for certain Dornier Model 328-300 series airplanes. This AD requires performing repetitive inspections for discrepancies of the heat pack rotor assembly and rotor drive clips of the brake unit of the main landing gear (MLG), and replacing the assembly if any discrepancy is found. This AD is prompted by reports of cracking and breakage of the heat pack rotor assemblies. We are issuing this AD to find and fix discrepancies of the heat pack rotor assembly of the brake unit of the MLG and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing.
2023-23-08: The FAA is superseding Airworthiness Directive (AD) 2019-07- 05, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-07-05 required repetitive inspections for cracking of the 10VU rack fitting lugs and repair of any cracking. This AD continues to require the requirements of AD 2019-07-05, with reduced compliance times and removes airplanes having a certain modification from the applicability. This AD was prompted by a determination that certain repetitive inspection intervals need to be revised. The FAA is issuing this AD to address the unsafe condition on these products.
95-18-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11, CL-600-2A12, CL-600-2B16, and CL-600-2B19 series airplanes, that currently requires an inspection to detect cracking in the rudder control quadrant; replacement of any cracked quadrant with a new assembly; and retorquing of the castellated nut, as necessary. This amendment requires a follow-on inspection of certain rudder control quadrants to detect cracks that start at the inside root radius of the spigot; modification of any cracked quadrant; and eventual modification of certain quadrants. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by the development of a modification, which, when installed, will positively address the identified unsafe condition. The actions specified by this AD are intended to prevent loss of rudder control due to stress corrosion of the rudder control quadrant.
2000-24-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection of the electrical wires routed above the door actuation cables for minimum .50-inch clearance with the door in the open and closed position, damage due to chafing or electrical arcing, or damaged door actuation cables; and corrective actions, if necessary. This action is necessary to prevent damaged electrical wires or damaged door actuation cables due to chafing by the cables during operation of the forward passenger door, which could result in electrical arcing and consequent smoke in the area above the forward passenger door. This action is intended to address the identified unsafe condition.
2005-03-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires initial and repetitive inspections of certain frame stiffeners to detect cracking. If any cracking is found, this AD requires replacement of the stiffener with a new, reinforced stiffener. Replacement of the stiffener constitutes terminating action for certain inspections. This AD also requires a one-time inspection of any new, reinforced stiffener; and repair or replacement of the new, reinforced stiffener if any cracking is found during the one-time inspection. This AD also provides for an optional terminating action for certain requirements of this AD. The actions specified by this AD are intended to prevent fatigue failure of certain frame stiffener fittings, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
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.