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2016-12-12: We are superseding Airworthiness Directive (AD) 2008-05-18 R1 for certain Fokker Services B.V. Model F.27 Mark 050, 200, 300, 400, 500, 600, and 700 airplanes. AD 2008-05-18 R1 required revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires a new maintenance or inspection program revision to incorporate the revised Airworthiness Limitation Items (ALIs) and critical design configuration control limitations (CDCCLs). This new AD also adds certain airplanes to the applicability. This AD was prompted by the issuance of revised service information to update the Fuel ALIs and CDCCLs that address fuel tank system ignition sources. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2001-08-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires an inspection of the antifogging or heating wiring to detect chafing or damage, as applicable; inspection of the insulation blankets to detect damage; and repair, if necessary. This amendment also requires revising the clearview window heating wiring installations. This amendment is prompted by a report of an electrical short that resulted in damage to the antifogging circuit wiring and insulation blanket above the Captain's clearview window. The actions specified by this AD are intended to prevent chafed and damaged wires as a result of a sharp bend and restricted space between the fuselage frame and the clearview window in the full open position, which could result in an electrical short, damage to the antifogging circuit wiring and insulation blanket, and consequent smoke and fire in the flight deck.
2016-11-14: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD was prompted by a design review that revealed no controlled bonding provisions are present on a number of critical locations inside the fuel tanks or connected to the walls of the fuel tanks. This AD requires installing additional and improved bonding provisions in the fuel tanks and revising the airplane maintenance or inspection program, as applicable, by incorporating fuel airworthiness limitation items and critical design configuration control limitations (CDCCLs). We are issuing this AD to prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
90-15-15 R1: 90-15-15 R1 AMERICAN CHAMPION AIRCRAFT (BELLANCA, CHAMPION): Amendment 39-6671 as amended by Amendment 39-6785; Docket No. 90-CE-25-AD. Applicability: Model 8KCAB airplanes (all serial numbers) that are equipped with upper wing front spar fittings part number (P/N) 2-1976, certificated in any category. Compliance: Required as indicated after the effective date of this AD. To prevent failure of the upper wing front spar strut fittings, P/N 2-1976, that could result in an in-flight separation of the wing, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD or prior to the accumulation of 500 hours TIS on the front spar strut fittings (P/N 2-1976), whichever occurs later, unless previously accomplished within the last 250 hours TIS, and thereafter at intervals not to exceed 250 hours TIS from the last inspection, accomplish the following: NOTE: Operators who have not kept records of hours TIS on individual front spar strut fittings (P/N 2-1976) may substitute airplane hours TIS instead. (1) Remove the front spar strut fittings (P/N 2-1976) and strip all paint with a chemical stripper. Clean and prepare the fittings for a magnetic particle inspection. (2) Conduct a magnetic particle inspection of the fittings for cracks, paying close attention to the areas near the welds. (3) If cracks are not found, prior to further flight, clean the fittings and apply a spray coat or a dip coat of zinc chromate primer, reinstall the fittings, and return the airplane to service. (b) If cracks are found as a result of the inspection required by paragraph (a)(2) of this AD, prior to further flight, replace any cracked fittings with one of the following: (1) A new or serviceable fitting (P/N 2-1976) that has been inspected and treated per the requirements of paragraph (a) of this AD. (2) A new American Champion Aircraft fitting (P/N 3-1658) that is installed inaccordance with the instructions in American Champion Aircraft Service Kit 302, revised October 1, 1990. (3) A new Safe Aircraft Repair, Inc. fitting (P/N SAR2-1976) and stiffener (P/N SAR2-5001) that are installed in accordance with the instructions in STC SA1514GL, issued to Safe Aircraft Repair, Inc. on August 27, 1990. (c) Upper wing front spar strut fittings (P/N 2-1976) may be replaced with new parts in accordance with paragraphs (b)(2) or (b)(3) of this AD regardless of whether cracks are found during the inspection required by paragraph (a) of this AD. (d) Replacement of the upper wing front spar strut fittings (P/N 2-1976) with new parts in accordance with paragraphs (b)(2) or (b)(3) of this AD constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD. (e) 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. (f) An alternate method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Chicago Aircraft Certification Office, 2300 E. Devon Avenue, Des Plaines, Illinois 60018. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office. (g) All persons affected by this directive may obtain copies of the documents referred to herein upon request to American Champion Aircraft, P.O. Box 37, Rochester, Wisconsin 53167; Telephone (414) 534-6315; or Safe Air Repair, Inc., 3325 Bridge Avenue, Albert Lea, Minnesota 56007; Telephone (507) 373-5408; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 90-15-15 R1 revises AD 90-15-15, Amendment 39-6671. This amendment (39-6785, AD 90-15-15 R1) becomes effective on May 15, 1991.
72-13-03: 72-13-03 BELLANCA: Amdt. 39-1461. Applies to Model 17-30 Airplanes. Compliance: As indicated below, unless already accomplished. To prevent possible engine flooding when using the fuel boost pump, accomplish either Part A or Part B as applicable: PART A 1. On those airplanes equipped with Airborne Model 2B6-9 fuel boost pumps (Airplane serial numbers 30217 through 30262 were delivered from the factory with this model pump installed) which have not been modified in accordance with AD 71-13-04: a. Within 50 hours' time in service after June 26, 1971, modify the fuel boost pump electrical circuit by installing a three (3) position toggle switch, a three (3) ohm twenty (20) watt resistor, a switch guard and a five (5) amp circuit breaker between the bus and the switch in accordance with Bellanca Service Letter No. 61A, Revision A, dated April 26, 1971, or later FAA approved revisions, and Bellanca Drawing SK-2-1040, Sheet 1, Revision D. Do not connect any other equipment to the fuel boost pump circuit. b. Within 50 hours' time in service after June 26, 1971, insert Airplane Flight Manual, Revision No. 13, dated May 26, 1971, in the Airplane Flight Manual. (Revision No. 13 is included in Bellanca Service Kit SK-2-1040 referred to in Service Letter No. 61A, Revision A.) c. Any alternate equivalent method of compliance with Paragraphs a and b above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. 2. On those airplanes equipped with Airborne Model 2B6-9 fuel boost pumps (Airplane serial numbers 30217 through 30262 were delivered from the factory with this model pump installed) which have complied with AD 71-13-04: a. Within 50 hours' time in service after the effective date of this AD and install a five (5) amp circuit breaker between the bus and the fuel boost pump switch in accordance with Bellanca Drawing SK-2-1040, Sheet 1, Revision D. Do not connect any other equipment to the fuel boost pump circuit. b. Any alternate equivalent method of compliance with Paragraph a above must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. PART B On those airplanes equipped with Weldon fuel boost pump Models 4020-A2A or 10050- A (Airplane serial numbers 30002 through 30216) were delivered from the factory with one of these model pumps installed: 1. Effective immediately, do not operate the fuel boost pump any longer than is necessary to achieve required fuel pressure. (Continued use of the fuel boost pump may cause engine flooding under certain operating conditions.) 2. Within 10 hours' time in service after September 14, 1971, install a placard beneath or adjacent to the fuel boost pump switch to read as follows: "TO PREVENT ENGINE FLOODING TURN OFF FUEL BOOST PUMP IMMEDIATELY AFTER FUEL PRESSURE IS RESTORED." NOTE: The operator may make and install this placard using letters approximately 1/8 inch in height. 3. Within 50 hours' time in service after the effective date of this AD: a. Install a two (2) position spring loaded switch and a five (5) amp circuit breaker between the bus and the fuel boost pump switch in accordance with Bellanca Service Letter No. 71, dated February 16, 1972, or later FAA approved revisions, and Bellanca Drawing SK-2-1040, Sheet 2, Revision A. Do not connect any other equipment to the fuel boost pump circuit. b. Insert Airplane Flight Manual, Revision No. 14, dated April 17, 1972, in the Airplane Flight Manual. (Revision No. 14 is included in kit referred to in Service Letter No. 71.) c. Remove placard installed under Part B, Paragraph 2, and install, in same location, placard Bellanca Part No. SK-2-1043 which reads as follows: "AUX FUEL PUMP USE TO RESTORE FUEL PRESSURE RELEASE TO PREVENT ENGINE FLOODING" 4. Any alternate equivalent method of compliance with Part B must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except that an equivalent five (5) amp circuit breaker may be utilized. This AD supersedes AD 71-13-04. This amendment becomes effective June 20, 1972.
2001-08-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires revising the Airplane Flight Manual to prohibit extended dry operation of the center tank fuel pumps (with no fuel passing through the pumps). This action is necessary to prevent ignition of fuel vapors due to the generation of sparks and a potential ignition source inside the center tank caused by metal-to-metal contact during dry fuel pump operation, which could result in a fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
82-03-09: 82-03-09 SHORT BROTHERS LIMITED: Amendment 39-4308. Applies to Model SD3-30 series airplanes, serial numbers SH3001 through SH3024 inclusive, certificated in all categories. Compliance required prior to the accumulation of 12,000 landings, or 300 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings. To prevent fatigue failures of the stub wing spar and stub wing bolted joints, accomplish the following: (a) Inspect the bolt holes in the stub wing spars for cracks using the eddy current method described in Short Brothers "Non-destructive Test Specification," NDTI RD 1, dated October 1979, and in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraph 2, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent, and for airplane serial numbers SH3008 through SH3013 inclusive, replace the laminated aluminum shims in the stub wing boltedjoints with single thickness shims in accordance with Short Brothers Limited Service Bulletin SD3-53-21, Revision 1, dated September 5, 1979, or an FAA-approved equivalent. (b) If as a result of the inspection in paragraph (a) of this AD, no cracks are found, reassemble the stub wing in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 2A.15 and 2A.11(b) for the front spar frame, and paragraphs 2A.15 and 2A.12(b) for the rear spar frame, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent. (c) If as a result of the inspection required in paragraph (a) of this AD, cracks are found - (1) Before further flight, except as provided in paragraph (f) of this AD, install Short Brothers Limited SD3-30 Modifications 5514, 5600 and 5790, in accordance with Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, or an FAA-approved equivalent; and (2) Repair any bolt holes in which cracks are found and fit oversize bolts in accordance with paragraph 2A.11 for the front spar frame, and paragraph 2A.12 for the rear spar frame, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent; and (3) Reassemble the stub wing in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 2A, and 29 through 47, of Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, or an FAA-approved equivalent. (d) If cracks in the stub wing spar bolt holes cannot be removed by the procedure specified in paragraph (c)(2) of this AD, report those findings to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, AEU-100, FAA, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04- R0174). Additional repair procedures must be approved by that office prior to returning aircraft to service. (e) Upon incorporation of Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, the repetitive inspection required by this AD may be discontinued. (f) In accordance with FAR Sections 21.197 and 21.199, the airplane may be flown to a base where the inspections, modifications, and repairs required by this AD may be accomplished. (g) If an equivalent means of compliance is used in complying with any paragraph of this AD, that equivalent means must be approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. (h) Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, Brussels, Belgium, may adjust the inspection intervals. (i) For the purpose of this AD, when conclusive records are not available to show the total number of landings accumulated by a particular part (or assembly), the number of landings may be computed by dividing the airplane time-in-service since the part (or assembly) was installed in the airplane by the operator's fleet average time per flight for his Model SD3-30 series airplanes. All persons affected by this directive who have not already received the referenced documents from the manufacturer may obtain copies upon request to Short Brothers Limited, P.O. Box 241, Airport Road, Belfast, BT 9DZ, Northern Ireland, Attention: Product Support Manager. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591. This amendment becomes effective March 1, 1982.
88-25-02: 88-25-02 PIPER (AEROSTAR): Amendment 39-6080. Applies to Models PA-60-601 equipped with an automatic waste gate controller per Retrofit Option 106 (S/N 61-0001-004 through 61-0334-111), PA-60-601 (S/N 61-0342-112 through 61-0880-8162157), PA-60-601P (S/N 61P-0157-001 through 61P-0860-8163455), PA-60-602P (S/N 62P-0750-8165001, and 62P-0861-8165002 through 60-8365010), PA-60-700P (S/N 60-8423001 through 60-8423025) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD unless already accomplished. To reduce the possibility of damage to the oil supply hoses which, if not corrected, could result in an in-flight fire, oil starvation and/or engine failure, accomplish the following: (a) For all the above applicable airplanes except Model PA-60-700P (S/N 60- 8423001 through 60-8423025) airplanes, replace and modify the engine fluid-carrying hoses and associated hardware in accordance withthe instructions contained in Piper Service Bulletin (SB) No. 761, dated April 18, 1983, and Piper SB No. 815, dated January 3, 1986. (b) For Model PA-60-700P Aerostars (S/N 60-8423001 through 60- 8423025) airplanes replace and modify the engine fluid-carrying hoses and associated hardware in accordance with the instructions contained in Piper SB No. 815, dated January 3, 1986. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6080, becomes effective on December 26, 1988.
86-17-03: 86-17-03 SOCATA: Amendment 39-5392. Applies to Model TB20 (Serial Numbers up to and including No. 479) airplanes certificated in any category. Compliance: Required within 100 hours time-in-service after the effective date of this AD, unless already accomplished. To assure the integrity of the trim control system, accomplish the following: (a) Replace the attachment of the elevator tab control to the elevator tab levers in accordance with Operation II of the Description paragraph of SOCATA Service Bulletin (S/B) No. 24, dated January 1985, as follows: (1) Remove and discard the bolt, washers, spacer, nut and pin attaching the elevator trim tab rod eye-end-fitting to the trim tab levers. (Ref. Detail A of the figure in SOCATA Service Bulletin No. 24) (2) Measure the rod length in order to reposition the eye-end-fitting. (3) Remove the eye-end-fitting. (4) Bore the eye-end-fitting at dia. 10 mm (.3937 inches + .0009, - .0000). (5) Bore the two tab levers at dia. 6 mm (.2363 inches + .0007, - .0000). (6) Grease the new bolt of dia. 6 mm (nominal 0.24 in.). (7) Install the eye-end-fitting at the rod length measured using a new lock plate (Z00.5544.1.10.000). (8) Install the dia. 6 mm bolt, the spacer and washers according to Detail A of the figure shown in SOCATA S/B No. 24. (9) Tighten the castellated nut (apply a tightening torque of 0.42 m.daN-37 inch.Pound), if necessary loosen to the lower notch. (10) Install pin and grease. (11) Bore the tab levers according to Detail B of the figure shown in SOCATA S/B No. 24 to 5 mm (.1969 inches + .0003, -.0000) diameter. (12) Grease the bolt. (13) Install the spacer, the dia. 5 mm (nominal 0.20 in.) bolt, the washer and nut according to Detail B of the figure in SOCATA S/B No. 24. (14) Tighten the nut (apply a tightening torque of 0.25 m.daN - 23 inch.Pound). (15) Check the tab deflection angles (SOCATA TB20 Maintenance Manual Section V.5). (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to SOCATA Groupe Aerospatiale, B. P. 38, 65001 Tarbes, France; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 22, 1986.
91-11-14: 91-11-14 PARTENAVIA COSTRUZIONI AERONAUTICHE: Amendment 39-6992. Docket No. 91-CE-39-AD. Applicability: Models P68C-TC airplanes (all serial numbers (S/N)), P68-OTC airplanes (S/N 344-01-OTC and 340-02-OTC), and P68C and P68 Observer airplanes (S/N 268 to 381), certificated in any category. Compliance: Within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent fuel leakage into the airplane cabin that could result in ignition and explosion of the airplane, accomplish the following: (a) For Models P68C-TC and P68-OTC, remove the fuel and Janitrol system lines in accordance with the instructions in Partenavia Service Instruction No. 39, dated February 14, 1991. (1) Install the applicable service kit in accordance with the instructions in Partenavia Instruction No. 39. (2) Replace the light alloy line of the Janitrol system (part number (P/N) 7.6131-2) with P/N 7.6131C-2 on the applicable Model P68C-TC airplanes in accordance with the instructions in Partenavia Service Instruction No. 39. (b) For Models P68C and P68 Observer, remove the fuel and Janitrol system lines in accordance with the instructions in Partenavia Service Instruction No. 40, dated February 14, 1991. (1) Install the applicable service kit in accordance with the instructions in Partenavia Instruction No. 40. (2) Replace the light alloy line of the Janitrol system (part number (P/N) 7.6131-2) with P/N 7.6131C-2 on the applicable Model P68C airplanes in accordance with the instructions in Partenavia Service Instruction No. 40. (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, Brussels Aircraft Certification Office, Europe, Africa, Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (e) The replacements and modifications required by this AD shall be done in accordance with Partenavia Service Instruction No. 39 or Partenavia Service Instruction No. 40, both dated February 14, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from Partenavia Costruzioni Aeronautiche, S.p.A., Via G. Pascoli N. 7, 80026 Casoria (NA), Italy. 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, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-6992, AD 91-11-14) becomes effective on June 14, 1991.