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91-14-08: 91-14-08 AEROSPATIALE: Amendment 39-7049. Docket No. 91-NM-51-AD. Applicability: Model SN 601 Corvette series airplanes, which have incorporated Modification 1390, certificated in any category. Compliance: Required within 100 landings after the effective date of this AD, unless previously accomplished. To prevent ice formation in the fuel line and subsequent loss of engine power, accomplish the following: A. Remove the existing thermostatic element, Part Number 9914, and install thermostatic element Part Number 5497-1, in accordance with Aerospatiale Corvette Service Bulletin 73-3, Revision 1, dated July 30,1990. 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. This amendment (39-7049, AD 91-14-08) becomes effective on July 29, 1991.
2010-17-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Reports have been received indicating that, if the power control friction wheel is tightened, the reverse thrust latch may stick and subsequently allow the Power Control Lever (PCL) to be inadvertently retarded aft of the idle detent. This condition, if not corrected, could result in undesired reverse thrust activation which, especially during approach, could result in reduced control of the aeroplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-22-11: 95-22-11 AIRBUS: Amendment 39-9419. Docket 95-NM-194-AD. Applicability: Model A320 airplanes; having manufacturer's serial numbers (MSN) 006, 008, 011, 017, 018, 039, 042, 045, 046, and 047; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 use the authority provided in paragraph (b) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe conditionaddressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent the initiation and propagation of fatigue cracking in fuselage frame 20, which could adversely affect the structural integrity of this area of the fuselage, accomplish the following: (a) Prior to the accumulation of 14,000 total landings, or within 6 months after the effective date of this AD, whichever occurs later, reinforce the left fuselage frame (FR) 20 between stringers 30 and 32, in accordance with Airbus Service Bulletin A320-53-1017, Revision 1, dated September 7, 1993. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 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. (c) 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. (d) The reinforcement shall be done in accordance with Airbus Service Bulletin A320-53-1017, Revision 1, dated September 7, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3 1 September 7, 1993 2, 4-16 Original December 4, 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 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. (e) This amendment becomes effective on November 24, 1995.
67-33-03: 67-33-03 GENERAL DYNAMICS: Amdt. 39-528 Part 39 Federal Register December 29, 1967, as amended by Amendment 39-1528. Applies to Model 240/340/440 airplanes using turbo-propeller power which have been modified to incorporate underwing pressure fueling per STC Nos. SA1316WE, SA1132WE, SA1096WE or SA1054WE. Compliance required as indicated. Because of three reports of overpressurization of the wing fuel tank in affected airplane types that have been attributed to failure of the upper and lower diaphragm assemblies in the pressure fueling valves (P/N 2640644 or P/N 2650198), accomplish the following: (1) Before further flight from the next maintenance base where facilities and personnel are available, externally inspect each wing in the area of the fuel tank for fuel leakage; (2) If fuel leakage is found as a result of the inspection per Paragraph (1), before further flight internally inspect each wing fuel tank exhibiting fuel leakage for presence of structural damage; (3) If structural damage is found as a result of the inspection per Paragraph (2), before further flight repair portion of each wing exhibiting structural damage as necessary; and (4) Within thirty days after the effective date of this amendment to AD 67-33-03, unless already accomplished, install adjacent to each underwing refuel valve in clear view of ground fueling crews a placard stating, 'Remove the overwing filler cap(s) while fueling the tank above 80% capacity. If not, further inspection required per AD 67-33-03.' When fueling at or above 80% of the fuel tank capacity, perform all underwing fueling with overwing fuel tank filler cap(s) removed. The placard may be removed, and the procedure described in this paragraph may be discontinued after the accomplishment of (5) below. (5) Compliance with paragraph (4) is no longer required: (a) When underwing pressure fueling system as installed on the Model 240 aircraft is modified to incorporate a pressure vent valve in accordance with Aircraft Tank Service, Incorporated, Drawing 2036, Change "A", entitled 'Refueling Valve Installation-CV 240', dated April 23, 1966, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, Western Region. (b) When the underwing pressure fueling system as installed on the Model 340/440 aircraft is modified to incorporate a pressure vent valve in accordance with Aircraft Tank Service, Incorporated, Drawing 2363, Change "B", entitled 'Installation of Pressure Vent Valve-Wing Fuel Tanks - Convair 340/440', dated July 3, 1968, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, Western Region. (6) If either (a) fuel leakage or overpressurization is detected in operation, or (b), the aircraft is known to have been refueled not in accordance with the procedure set forth in paragraph (4) above, repeat the inspection described in paragraphs (1) and (2) above, and accomplish repairs, per (3) above, if applicable. Amendment 39-528 was effective December 29, 1967, for all persons except those to whom it was made effective immediately by telegram issued previously. This Amendment 39-1528 is effective October 3, 1972.
90-14-01: 90-14-01 FAIRCHILD AIRCRAFT CORPORATION (formerly Swearingen Aviation Corporation): Amendment 39-6866. Docket No. 90-CE-38-AD. Final rule of priority letter AD. Applicability: Models SA226-AT, SA226-TC, SA227-AT, and SA227-AC airplanes (all serial numbers), certificated in any category. Compliance: Required as indicated in the AD, unless already accomplished. To prevent rapid cabin decompression and passenger injury due to window breakage caused by ice shed from the propellers, accomplish the following: (a) Prior to further flight unless accomplished in accordance with AD 90-12-14, modify the passenger seat adjacent to the cabin window at Station 181 on the right side of the cabin on those airplanes whose propellers turn counterclockwise looking forward, or on the left side of the cabin on those airplanes whose propellers turn clockwise looking forward, by accomplishing one of the following actions: (1) Fabricate a placard using letters at least one inch in height on a contrasting background to read: "DO NOT OCCUPY THIS SEAT AT ANY TIME" and install this placard on the passenger seat closest to the cabin window at Station 181 of the passenger cabin in clear view of the occupants, or (2) Remove the passenger seat closest to the cabin window at Station 181 of the passenger cabin. (b) Within the next 30 calendar days after the effective date of this AD, unless accomplished in accordance with AD 90-12-14, reinforce the applicable cabin window located at Station 181 in the passenger cabin in accordance with either paragraph (b)(1) or (b)(2) of this AD. The restrictions required by paragraph (a) of this AD are no longer applicable when this modification has been accomplished. (1) Add an inner pane in accordance with the instructions in Fairchild Aircraft Corporation Service Bulletins 226-56-004, revised January 8, 1990, or 227-56-004, issued July 26, 1989, as applicable, or (2) Add a metal cover over the outside of the window in accordance with Fairchild Aircraft Corporation Kit 27K22005, Revision A, issued June 14, 1990. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An alternate method of compliance or adjustment of the compliance times which provide an equivalent level of safety may be approved by the Manager, Airplane Certification Office, Fort Worth, Texas 76193-0150 (facsimile number (817) 624-5988). NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Airplane Certification Office, Fort Worth, Texas. Airworthiness Directive 90-14-01 supersedes priority letter AD 90-12-14. This amendment (39-6866, AD 90-14-01) becomes effective on February 11, 1991, as to all persons except those persons to whom it was made immediately effective by priority letter AD 90-14-01, issued June 29, 1990, which contained this amendment.
68-21-02: 68-21-02 AERO COMMANDER: Amdt. 39-669. Applies to Aero Commander Model 100, Serial Nos. 1 through 278, and Aero Commander Model 100-180, Serial Nos. 5001 through 5080 airplanes. Compliance required as indicated. To prevent the possibility of aileron cable failure caused by improper swaging of P/N 35606 Aileron Cable Assembly, accomplish the following prior to further flight: (a) Unless already accomplished, inspect P/N 35606 Aileron Cable Assembly in accordance with Aero Commander Service Bulletin No. 1015, dated October 4, 1968, or later FAA approved revisions or in a manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region. (b) If indications of improper swaging or of cable slippage are found, replace the assembly with a new P/N 35606 aileron cable assembly that is properly swaged in accordance with the criteria specified in Figure I of the service bulletin. This amendment becomes effective October 15, 1968.
89-24-09: 89-24-09 BEECH: Amendment 39-6381. Applicability: The airplanes listed below, certificated in any category: MODELS SERIAL NUMBERS A23-19, 19A, M19A, B19 MB-1 through MB-816, except MB-814 23, A23, A23A, B23, C23 M-1 through M-1879, except M-1875 A23-24, A24 MA-1 through MA-368 A24R MC-2 through MC-150 B24R MC-152 through MC-451, except MC-311 and MC-449 Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent the possibility of separation of aileron push rods and possible loss of aileron control, accomplish the following: (a) Within the next 100 hours time-in-service (TIS), accomplish the following in accordance with Beech Service Bulletin No. 2198, dated April 1989: (1) Install inspection openings in the wing lower skins. (2) Inspect the aileron rod ends for corrosion and freedom of movement. If serviceable, lubricate the rod end bearings. If corrosion is evident, prior to further flight replace the rod end with a new P/N 169-380082-3 rod end as specified in the above service bulletin. Corrosion is evident by restriction of movement of the rod ends. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. (c) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6381, AD 89-24-09) becomes effective on December 4, 1989.
72-14-06: 72-14-06 ROLLS-ROYCE: Amdt. 39-1479. Applies to series Dart Model 542-4, -4K, -10, -10J, and -10K engines. These engines are installed on but not necessarily limited to those Convair Model 340/440 airplanes (commonly known as Convair 600 and 640) which have the subject engines installed as a result of modification and NAMC YS-11 airplanes. Compliance is required as indicated. To prevent possible fatigue failure of first stage (low pressure) impellers, accomplish the following: (a) For a first stage (low pressure) impeller that does not incorporate Rolls Royce Dart Modification 1455, within the next 100 flights after the effective date of this AD or before the accumulation of 11,000 flights on that impeller, whichever occurs later, comply with subparagraph (c)(1) or (c)(2) and thereafter comply with paragraph (d) or (e) as applicable. (b) For a first stage (low pressure) impeller that incorporates Rolls Royce Dart Modification 1455, within the next 100 flights after the effective date of this AD or before the accumulation of 11,000 flights after the incorporation of Rolls Royce Dart Modification 1455, whichever occurs later, comply with subparagraph (c)(1) and thereafter comply with paragraph (d) or (e) as applicable. (c) Comply with subparagraph (1) or (2) of this paragraph as prescribed in paragraphs (a), (b), (d), and (e). (1) Remove the first stage (low pressure) impeller from service and replace it with - (i) A first stage (low pressure) impeller that does not incorporate Rolls Royce Dart Modification 1455 and which has accumulated less than 11,000 flights in service; or (ii) A first stage (low pressure) impeller that incorporates Rolls Royce Dart Modification 1455 and which has accumulated less than 11,000 flights in service since the incorporation of that modification. (2) For an impeller that does not have Rolls Royce Dart Modification 1455 incorporated, incorporate that modification. (d) For an impeller that has been installed in compliance with subparagraph (c)(1)(i), before the accumulation of 11,000 flights on that impeller comply with subparagraph (c)(1) or (c)(2). (e) For an impeller that has been installed in compliance with subparagraph (c)(1)(ii) or modified in accordance with subparagraph (c)(2), before the accumulation of 11,000 flights since the incorporation of Rolls Royce Dart Modification 1455 on that impeller comply with subparagraph (c)(1). (f) For the purpose of complying with this AD, a flight shall consist of an engine operating sequence consisting of an engine start, take-off operation, landing, and engine shutdown. The number of flights may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the compressor section's time in service by the operator's fleet average time per flight for airplanes equipped with the subject type engines. This AD supersedes the telegraphic ADon the same subject issued on April 13, 1972. NOTE: Rolls Royce Dart Alert Service Bulletin No. DA 72-391 Revision 1, dated May 1, 1972 refers to this matter. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram dated May 31, 1972, which contained this amendment.
2021-24-20: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of slat transmission jams caused by frozen slat geared rotary actuators (SGRAs) at slat 5 track 12. This AD requires repetitive water drainage and plug cleaning of the left- and right-hand SGRAs having a certain part number installed on slat 5 track 12 with certain functional item numbers, 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.
2010-05-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A review of A340 missions has demonstrated that CFM56-5C forward engine mount thrust links fitted with oversized bearing[s] will not reach the updated link fatigue life limit of 15,500 Flight Cycles (FC) due to an increase in bore diameter. * * * The consequent potential failure of the affected thrust link would reduce the forward engine mounts' structural integrity and could eventually lead to engine separation, constituting an unsafe condition. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.