Results
86-09-11: 86-09-11 SIKORSKY AIRCRAFT: Amendment 39-5298. Applies to Model S-76A helicopters certificated in any category. Compliance is required as indicated unless already accomplished. To preclude possible fatigue failures of the main and nose landing gear components, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD or before the accumulation of the component hours time in service listed below, whichever occurs later, replace the following components with new or airworthy components that have not exceeded the component listed hours time in service. Thereafter, replace the following components with new or airworthy components before the accumulation of the components hours time in service listed below: COMPONENT PART NUMBER REPLACEMENT TIME/HOURS Nose Landing Gear Fork 1944E60 42,500 Cylinder 1944E2, 1944C2 18,500 Retraction Actuator Cylinder Terminal 1944D201 28,800 Piston Rod 1944E204 25,000 Main Landing Gear Cylinder 1945E2 30,300 Axle Support Fitting 1945C12 9,600 Pin, Universal to Cylinder 1945C29 23,800 Drag Brace Rod End 1945E35 38,200 Upper Torque Arm 1945E46 37,900 Lower Torque Arm 1945C47 16,200 Axle 1945E85 7,200 Rod End, Positioning Rod 1945E235 19,100 Retraction Actuator Outer Cylinder 1945E302 7,100 Piston 1945E314 33,300 Piston Rod End 01-747-061 8,000 (b) Operators who have not kept records of hours time in service on individual component parts that were installed at time of issuance of the initial rotorcraft airworthiness certificate shall substitute rotorcraft hours time in service in lieu thereof. (c) For purposes of complying with this AD, the hours time in service for individual components that were not installed at the time of issuance of the initial rotorcraft airworthiness certificate must be determined from operator's rotorcraft records. (d) Upon request, an alternate means ofcompliance which provides a level of say equivalent to the requirements of this AD may be used when approved by the Manager, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone 1617) 237-7118, may adjust the compliance time specified in this AD. NOTE: Sikorsky Alert Service Bulletin 76-32-20 applies to this subject. This amendment becomes effective on May 14, 1986.
96-20-02: 96-20-02 AIRBUS INDUSTRIE : Amendment 39-9768. Docket 92-NM-225-AD. Applicability: Model A300 B2-1C, B2K-3C, B2-203, B4-2C, and B4-103, series airplanes, on which Modification 2626 has not been installed; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992, at the times specified in paragraphs (a)(1), (a)(2), or (a)(3), as applicable. (1) For Model A300 B2-1C, B2K-3C, and B2-203 series airplanes: Perform the inspection prior to the accumulation of 15,000 total landings, or within 50 landings after the effective date of this AD, whichever occurs later. (2) For Model A300 B4-2C and B4-103 series airplanes: Perform the inspection prior to the accumulation of 18,700 total landings, or within 50 landings after the effective date of this AD, whichever occurs later. (3) For Model A300 B4-203 series airplanes: Perform the inspection prior to the accumulation of 14,100 total landings, or within 50 landings after the effective date of this AD, whichever occurs later. (b) If no crack is detected during the inspection required by paragraph (a) of this AD, repeat the detailed visual inspection at intervals not to exceed 200 landings. (c) If a crack is detected during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, repair in accordance with either paragraph (c)(1), (c)(2), or (c)(3) of this AD: (1) Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or (2) Repair in accordance with crack repair procedures specified in Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992; or (3) Repair in accordance with crack repair procedures specified in Airbus Service Bulletin A300-53-299, dated December 14, 1993. (d) Conducting a repetitive Rototest inspection of hole "I" in accordance with Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992, or Airbus Service Bulletin A300-53-299, dated December 14, 1993, constitutes terminating action for the detailed visual inspections required by this AD. If any crack is found, prior to further flight, repair it in accordance with that service bulletin. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The visual inspection shall be done in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on November 4, 1996.
99-04-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time operational test to detect discrepancies of the delay valves and check valves of the main landing gear (MLG); and corrective actions, if necessary. This amendment also requires replacement of the retraction bracket assemblies of the MLG with new or reworked retraction bracket assemblies. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the retraction bracket assemblies of the MLG, which could result in an undampened extension of the MLG, damage to the sidestay and attachment structure, and possible collapse of the MLG.
98-21-28: This action confirms the effective date of Airworthiness Directive (AD) 98-21-28, which applies to certain British Aerospace Jetstream Model 3101 airplanes. AD 98-21-28 requires modifying the propeller de-icing system to assure system performance at low ambient temperatures. This AD was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified in this AD are intended to prevent propeller-induced vibrations from occurring during icing encounters at low ambient temperatures, which could result in decreased performance of the de-icing system during icing encounters with possible loss of control of the airplane.
2007-02-24: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This AD requires repetitive inspections for cracking of the web of the station (STA) 2360 aft pressure bulkhead around the fastener heads in the critical fastener rows in the web lap joints, from the Y-chord to the inner ring; and repair if necessary. This AD also requires a modification, which terminates the repetitive inspections. This AD results from analysis by the manufacturer that the radial lap splices of the STA 2360 aft pressure bulkhead are subject to widespread fatigue damage. We are issuing this AD to detect and correct cracking of the bulkhead web at multiple sites along the radial lap splice, which could join together to form cracks of critical length, and result in rapid decompression and loss of control of the airplane.
87-23-08: 87-23-08 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5735. Applies to TCM IO-520 and TSIO-520 series engines. Compliance is required as indicated, unless already accomplished. To prevent the installation of crankshafts with existing subsurface fatigue cracks which could result in crankshaft failure with resultant loss of engine power, at the next and every subsequent crankshaft removal from the engine case or installation of a replacement crankshaft, accomplish the following: (a) Prior to installation in the engine, conduct an ultrasonic inspection in accordance with TCM Service Bulletin M87-5, Revision 1, dated May 25, 1987, and Crankshaft Ultrasonic Inspection Procedure, Form X30554, dated February 1981. (b) If any cracks are found, replace crankshaft with serviceable crankshaft in accordance with TCM Service Bulletin M87-5, Revision 1, dated May 25, 1987. (c) If no cracks are found, mark the propeller mounting flange in accordance with TCM Service BulletinM87-5, Revision 1, dated May 25, 1987. NOTE: Accomplishment of the ultrasonic inspection does not set aside any requirements for magnaflux or other inspections specified in TCM overhaul manuals. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, Central Region, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349. TCM Service Bulletin M87-5, Revision 1, dated May 25, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). Copies may be obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601. Copies may be examined in the Regional Rules Docket, Office of the Regional Counsel, Room 311, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803 or at the Office of the Federal Register, 1100 LStreet NW, Room 8401, Washington, DC. This amendment becomes effective November 30, 1987.
97-07-04: 97-07-04 ROLLS-ROYCE PLC: Amendment 39-9978. Docket 95-ANE-56. Applicability: Rolls-Royce plc (R-R) Models RB.211-524G and -524H turbofan engines that have not been modified in accordance with R-R Service Bulletin (SB) No. RB.211-72-9764, Revision 2, dated November 10, 1995, installed on but not limited to Boeing 747-400 and 767- 300 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent engine combustor liner deterioration due to thermal fatigue, which can result in combustor liner and case burn-through and engine fire, accomplish the following: (a) Perform initial and repetitive borescope inspections of the engine combustor liner head section in accordance with the intervals listed in Section 1.C. Compliance (1), and the procedures described in Section 1.D. Action (1) of R-R SB No. RB.211-72-B482, Revision 3, dated September 27, 1996. Prior to further flight, remove combustors that do not meet the return to service criteria specified in Section 1.E. Acceptance Limits of the SB and replace with serviceable parts. (b) Perform initial and repetitive borescope inspections of the meterpanel in accordance with the intervals listed in Section 1.C. Compliance (2), andthe procedures described in Section 1.D. Action (2) of R-R SB No. RB.211-72-B482, Revision 3, dated September 27, 1996. Prior to further flight, remove combustors that do not meet the return to service criteria specified in Section 1.E. Acceptance Limits of the SB and replace with serviceable parts. (c) Installation of a front combustion liner with a strengthened head section in C263 material in accordance with R-R SB No. RB.211-72-9764, Revision 2, dated November 10, 1995, constitutes terminating action to the inspection requirements of this AD. (d) 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternativemethods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (f) The actions required by this AD shall be done in accordance with the following R-R SBs: Document No Pages Revision Date RB.211-72-B482 1 3 September 27, 1996 2 2 March 11, 1996 3 3 September 27, 1996 4 2 March 11, 1996 5 3 September 27, 1996 6 2 March 11, 1996 7,8 3 September 27, 1996 9 2 March 11, 1996 Total Pages: 9. RB.211-72-9764 1 2 November 10, 1995 2 Original August 20, 1993 3 2 November 10, 1995 4-6 1 August 25, 1995 7-30 Original August 20, 1993 Supplement 1 Original August 20, 1993 Total Pages: 31. Thisincorporation 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 Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone (317) 230-3995, fax (317) 230-4743. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on June 6, 1997.
93-02-05: 93-02-05 TEXTRON LYCOMING: Amendment 39-8487. Docket 92-ANE-56. Applicability: Textron Lycoming reciprocating opposed piston engines incorporating fuel injection lines as listed in Textron Lycoming Service Bulletin No. (SB) 342A, dated May 29, 1992, except for Model TIO-540-S1AD engines. Affected engine models are installed on but not limited to Piper PA-24 Comanche, PA-30 and PA-39 Twin Comanche, PA-28 Arrow, and PA-23 Aztec; Beech 60 Duke and 23 Musketeer; Mooney M20; and Cessna 177 Cardinal aircraft. NOTE: Engines with an "I" in the prefix of the model designation incorporate fuel injection. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the fuel injector fuel lines allowing fuel to spray into the engine compartment, resulting in an engine fire, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, inspect the fuel injector fuel lines between the fuel manifold and the fuel injector nozzles in accordance with Textron Lycoming Service Bulletin No. 342A, dated May 26, 1992. (b) Prior to further flight, replace any fuel injector fuel line that does not meet all the return to service conditions specified in Textron Lycoming SB No. 342A, dated May 26, 1992. (c) Thereafter, at each annual inspection, at each 100-hour inspection, at each engine overhaul, and after any maintenance has been performed on the engine where the fuel injector fuel lines have been disconnected, moved, or loosened, reinspect the fuel injector fuel lines in accordance with Textron Lycoming SB No. 342A, dated May 26, 1992, and replace as necessary any fuel injector fuel line that does not meet all the return to service conditions specified in that SB. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office. The request should beforwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York 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 New York Aircraft Certification Office. (e) 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. (f) The inspection, and replacement, if necessary of the fuel injector fuel lines shall be done in accordance with the following service document: Document No. Pages Date Textron Lycoming SB No. 342A 1-31 May 26, 1992 Total pages: 31 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 Textron Lycoming Reciprocating Engine Division, 652 Oliver Street, Williamsport, Pennsylvania 17701. Copies may be inspected at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on June 14, 1993.
98-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-200A series airplanes, that requires a one-time inspection of the gust damper of the elevator control system to determine if the gust damper is properly charged, and of the horizontal stabilizer to detect cracking of elevator hinge rib 1; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of elevator hinge rib 1 of the horizontal stabilizer, which could occur if the gust damper of the elevator control system discharges and allows the elevator to move freely in ground gust conditions. Such cracking could result in damage to the structural attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane.
2007-08-01: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, - 9B1, and -9B2, -9C, -9C3, -9D, and -9D2 turboprop engines, with certain part number (P/N) and serial number stage 2 turbine aft cooling plates installed. That AD currently requires a onetime eddy current inspection (ECI) of boltholes in certain P/N stage 2 turbine aft cooling plates. This AD expands the population of affected CT7 turboprop engine models, but reduces the number of cooling plates affected. It also requires a onetime ECI of boltholes in certain P/N stage 2 turbine aft cooling plates with specific serial numbers. This AD results from the manufacturer expanding the list of affected engine models and identifying the affected stage 2 turbine aft cooling plates by serial number. We are issuing this AD to prevent separation of the stage 2 turbine aft cooling plate, resulting in uncontained engine failure and damage to the airplane.