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81-24-03: 81-24-03 GULFSTREAM AMERICAN CORPORATION: Amendment 39-4257. Applies to Model AA5, Serial Numbers AA5-0641 through AA5-0834; Model AA5A, Serial Numbers AA5A-0001 through AA5A-0900; Model AA5B, Serial Numbers AA5B-0001 through AA5B- 1323, airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent an engine power loss, accomplish the following: PART I For Model AA5 Serial Numbers AA5-0641 through AA5-0834; Model AA5A Serial Numbers AA5A-0001 through AA5A-0900, accomplish the following: For airplanes with 400 or more hours time in service on the effective date of this AD, comply with paragraphs (a) and (c) within 25 hours time in service from the effective date of this AD. Thereafter comply with paragraph (a) at intervals not to exceed 25 hours time in service from the last inspection until paragraph (b) has been accomplished and with paragraph (d) within the next 50 hours time in service from the effectivedate of this AD. For airplanes with less than 400 hours time in service on the effective date of this AD, comply with paragraph (d) within the next 50 hours time in service from the effective date of this AD and with paragraphs (a) and (c) prior to the accumulation of 425 hours total time in service. Thereafter comply with paragraph (a) at intervals not to exceed 25 hours time in service from the last inspection until paragraph (b) has been accomplished. (a) Inspect both forward and aft carburetor airbox screens (Gulfstream American P/N 5503006-9) to determine if any of the wires are broken. (1) If there are less than five broken wires per screen, inspect the induction system and the carburetor throat for filter material and correct, if necessary. Comply with paragraph (b) within 50 hours time in service from the first inspection under this paragraph. (2) If there are five or more broken wires per screen, inspect the induction system and the carburetor throat forfilter material and correct, if necessary. Comply with paragraph (b) before further flight. (b) Install the improved filter retention screens (Gulfstream American P/N 5503006- 20). (c) Inspect the carburetor airbox for damage and the carburetor air filter for deterioration. (1) If the airbox is found to have cracks, or loose or missing fasteners, replace or repair, as necessary, before further flight. (2) If the air filter is found to be separated and/or deteriorated, replace with an appropriate serviceable filter before further flight. (d) Within the next 50 hours time in service from the effective date of the AD, install a permanent warning placard, Gulfstream P/N 5503014, on exterior of the airbox which reads: "WARNING Air Filter deterioration can cause engine power loss. Consult Aircraft Maintenance Manual for air filter servicing and replacement requirements." Part II For Model AA5B, Serial Numbers AA5B-0001 through AA5B-1323, accomplishthe following: For airplanes with 400 or more hours time in service on the effective date of this AD, comply with paragraph (a) within 25 hours time in service from the effective date of this AD. For airplanes with less time than 400 hours time in service on the effective date of this AD, comply with paragraph (a) prior to the accumulation of 425 hours time in service. (a) Inspect the carburetor airbox for damage and the carburetor air filter for deterioration. (1) If the airbox is found to have cracks, or loose or missing fasteners, replace or repair, as necessary, before further flight. (2) If the air filter is found to be separated and/or deteriorated, replace with an appropriate serviceable filter before further flight. (b) Within the next 50 hours time in service from the effective date of the AD, install a permanent warning placard, Gulfstream P/N 5503014, on exterior of the airbox which reads: "WARNING Air Filter deterioration can cause enginepower loss. Consult Aircraft Maintenance Manual for air filter servicing and replacement requirements." An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. The airplane may be flown in accordance with FAR 21.197 and FAR 21.199 to a base where these repairs and/or replacements can be performed. Make the appropriate maintenance record entry for Parts I and II. Gulfstream American Service Bulletin No. 170 dated July 23, 1981, pertains to Part I of this AD. Gulfstream American Service Letter No. 81-1 dated October 9, 1981, pertains to Part II of this AD. This amendment becomes effective November 16, 1981.
98-21-12: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369D, 369E, 369FF, 500N, AH-6 and MH-6 helicopters. This action requires visual inspections of the overrunning clutch retainer, carrier, housing, and pin for wear from spinning of the bearing outer race. This amendment is prompted by a report of inflight vibrations and subsequent investigations of three other overrunning clutches, which indicated wear of the bearing carrier due to spinning of the bearing outer race. The actions specified in this AD are intended to detect wear of other clutch components, excessive vibration which could lead to failure of the overrunning clutch, wear on the bearing carrier, and subsequent loss of power to the helicopter rotor drive system.
98-21-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200 and -300 series airplanes, that requires repetitive inspections for cracking of the lower skin panels of the outer wings; and repair, if necessary. This amendment also requires modification of the panels and a follow-on inspection to detect cracking of the modified areas, which constitute terminating action for the repetitive inspections. 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 prevent fatigue cracking of the lower skin panels of the outer wings, and consequent reduced structural integrity of the airplane.
2013-06-06: We are adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8C and CF34-8E turbofan engines with certain part numbers (P/N) of operability bleed valves (OBV) installed. This AD was prompted by three failure events of ring lock fuel fittings on the OBV. Two of those events led to an engine fire. This AD requires the affected OBVs be removed from service and replaced with OBVs eligible for installation. We are issuing this AD to prevent failure of OBV ring lock fuel fittings, engine fuel leakage, uncontrolled fire, and damage to the airplane.
91-11-05: 91-11-05 GENERAL ELECTRIC COMPANY: Amendment 39-7001. Docket No. 90-ANE- 35. Applicability: General Electric Company (GE) CF6-80A and CF6-80C2 series engines installed on, but not limited to, Airbus A300 and A310; and Boeing 747 and 767 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent aborted takeoff and uncontained engine failure, accomplish the following: (a) Ultrasonic inspect the inertia weld of affected high pressure compressor rotor (HPCR) stages 11-14 spool-shafts at the next engine shop visit after the effective date of this AD but no later than 5,000 cycles in service (CIS) after the effective date of this AD, according to the following: (1) Inspect CF6-80A HPCR stages 11-14 spool-shafts, Part Numbers (P/N) 9225M37G11, 9225M37G14, 9225M37G16, 9225M37G18, 9225M37G19, 9225M37G20, 9225M37G21, and 1509M71G01, in accordance with the Accomplishment Instructions in GE CF6-80A Service Bulletin (SB) 72-531, Revision 2, dated May 18, 1990. (2) Inspect CF6-80C2 HPCR stages 11-14 spool-shafts, P/N 9380M30G07, 9380M30G08, 9380M30G09, 9380M30G10, 1531M21G01, 1509M71G02, 1509M71G03, 1509M71G04, 1509M71G05, and 1509M71G06, in accordance with the Accomplishment Instructions in GE CF6-80C2 SB 72-314, Revision 2, dated June 20, 1990. (3) Remove from service prior to further flight and replace with serviceable parts, HPCR stages 11-14 spool-shafts with ultrasonic indications greater than or equal to 50 percent full-screen height. (4) For the purpose of this AD, an engine shop visit is defined as the induction of the engine into a shop where the subsequent maintenance entails removal of the high pressure turbine module. (5) For the purpose of this AD, definition of ultrasonic indication is provided in GE CF6-80A SB 72-531, Revision 2, dated May 18, 1990, and GE CF6-80C2 SB 72-314, Revision 2, dated June 20, 1990, for the CF6-80A and CF6-80C2 engine models, respectively. (b) Aircraft may be ferried inaccordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate) an alternate 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, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The ultrasonic inspections shall be done in accordance with the following GE documents: DOCUMENT PAGE NO. ISSUE/REVISION DATE GE CF6-80A 2-12, 15, 17-27, Rev. 1 4/3/89 SB 72-531 30, 31 1, 13, 14, 16, 28, 29 Rev. 2 5/18/90 GE CF6-80C2 2-12, 15, 17-27, Rev. 1 4/19/89 SB 72-314 30, 31 1, 13, 14, 16, 28, 29 Rev. 2 6/20/90 This incorporation by reference was approved bythe Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. This amendment (39-7001, AD 91-11-05) becomes effective on July 5, 1991.
92-12-06: 92-12-06 AIRBUS INDUSTRIE: Amendment 39-8267. Docket No. 91-NM-13-AD. Applicability: Model A310, A320, and A300-600 series airplanes; as listed in Airbus Industrie Service Bulletins A310-35-2002, Revision 2, dated April 30, 1991; A320-35-1002, Revision 1, dated December 3, 1990; and A300-35-6001, Revision 2, dated April 30, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent passengers from being unable to receive oxygen during an emergency situation, accomplish the following: (a) Within 90 days after the effective date of this AD, replace Puritan Bennett passenger emergency oxygen container door latch seals with modified seals, and test all units for correct operation, in accordance with Airbus Industrie Service Bulletins A310-35-2002, Revision 2, dated April 30, 1991 (for the Model A310); A320 35-1002, Revision 1, dated December 3, 1990 (for the Model A320); and A300-35-6001, Revision 2, dated April 30, 1991 (for the Model A300-600). (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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch, ANM-113. (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 replacement and testing shall be done in accordance with Airbus Industrie Service Bulletins A310-35-2002, Revision 2, dated April 30, 1991 (for the Model A310); A320- 35-1002, Revision 1, dated December 3, 1990 (for the Model A320); and A300-35-6001, Revision 2, dated April 30, 1991 (for the Model A300-600); as applicable. Airbus Industrie Service Bulletin A320-35-1002, Revision 1, dated December 3, 1990 contains the following list of effective pages: Page Number Revision Level Date 1, 3-9 1 December 3, 1990 2 (removed) 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, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on July 31, 1992.
2022-10-07: The FAA is superseding Airworthiness Directive (AD) 89-24-06 R1, which applied to all Boeing of Canada, Ltd. and de Havilland (now Viking Air Limited) Model DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes. AD 89-24-06 R1 required repetitively inspecting the elevator quadrant for damage and taking corrective action as necessary. Since the FAA issued AD 89-24-06 R1, Transport Canada, the aviation authority for Canada, revised its mandatory continuing airworthiness information (MCAI) to correct this unsafe condition on these products. This AD retains the actions required by AD 89-24-06 R1, extends the compliance time intervals for the repetitive inspections, adds Model DHC-6-400 airplanes to the applicability, and adds a fluorescent penetrant inspection requirement. The FAA is issuing this AD to address the unsafe condition on these products.
59-21-03: 59-21-03 ALLISON: Applies to Models 501-D13 and -D13A Engines. Compliance required not later than November 15, 1959. Ten cases of compressor blade retention failures have occurred in service including one case that resulted in serious bulging and separation on the split line of the compressor case and flash fire inside the cowling during ground running. To preclude the possibility of serious engine damage resulting from failure of first stage compressor blade retention one of the following modifications must be incorporated not later than November 15, 1959. Install first stage compressor wheel assembly P/N 67 92821 or first stage compressor wheel assembly P/N 67 93351 or compressor rotor assembly P/N 67 92332. Allison Commercial Engine Bulletins Numbers 61 or 80 cover the first two modifications while the last is a new design.
98-21-06: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that requires either a one-time non-destructive test (NDT) or a visual inspection for cracking of the fuselage skin in the vicinity of frame 29 between stringers 12 and 13, and repair, if necessary. 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 detect and correct fatigue cracking of the fuselage skin in the specified area, which could result in reduced structural integrity of the airplane.
98-21-01: This amendment adopts a new airworthiness directive (AD) that is applicable to International Aero Engines AG (IAE) V2500-A1 series turbofan engines. This action requires a one-time ultrasonic inspection of fan blade roots for cracks, and, if necessary, replacement of cracked fan blades with serviceable parts. This amendment is prompted by a report of dovetail root cracks visually detected on three fan blades from one engine during a routine inspection. The actions specified in this AD are intended to prevent fan blade root cracks, which could result in fan blade root failures, an uncontained engine failure, and damage to the aircraft.