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2007-24-01: The FAA is adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Model 400A series airplanes. This AD requires inspecting the galley cabinets to determine if a certain part number is installed or if a certain size of wire already exists, and doing related investigative/corrective actions if necessary. This AD results from reports of undersized, and consequently unprotected, wire in the galley cabinets. We are issuing this AD to prevent overheating of wire insulation and consequent fire or smoke in the airplane cabin.
83-22-51: 83-22-51 DeHAVILLAND: Amendment 39-4865. Applies to DeHavilland Model DHC-7 airplanes Serial Numbers 3 through 27 certificated in all categories fitted with wing fuel tank covers P/N's 75710059-007 thru -014 (Inner) and P/N's 75711708-003 thru -006 (Middle). To detect failure of the bonding which could result in a loss of strength and stiffness of the wing, accomplish the following within the next 10 hours time in service, unless previously accomplished within the past 490 hours and thereafter at intervals not to exceed 500 hours time in service from the last inspection: A. Inspect the upper surfaces of the wing inner and mid fuel tank covers P/N 75710059-007 thru -014 and P/N 75711708-003 thru -006, respectively, for a bond failure between the skin and honeycomb core by: 1. Using a calibrated portable ultrasonic tester over the total upper surface of each cover; or 2. Conducting a coin test (at approximately one inch intervals) over the total upper surface of each cover. (The coin test detects unbonded areas by the change in audible response when the surface is systematically tapped with a coin.) NOTE: Tests may be accomplished with covers installed on aircraft. B. Replace covers found to have unbonded surfaces with serviceable covers prior to further flight. C. The repetitive inspections required by this AD may be terminated upon the installation of fuel tank covers P/N 7Z4096-001 (Inner) and P/N 7Z4097-001 (Middle). D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective May 29, 1984, and was effective earlier to those recipients of telegraph AD T83-22-51, dated October 27, 1983.
2008-03-04: 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: [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). * * * Under this regulation, all holders of type certificates for passenger transport aircraft * * * are required to conduct a design review against explosion risks. The replacement of some types of P-clips and improvement of the electrical bonding of the equipment in the fuel tanks are rendered mandatory by this AD. The unsafe condition is damage to wiring in the wing, center, and trim fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the wing, center, or trim fuel tanks. We are issuingthis AD to require actions to correct the unsafe condition on these products.
89-26-10: 89-26-10 McCAULEY ACCESSORY DIVISION, Cessna Aircraft Company: Amendment 39-6398. Applicability: McCauley Accessory Division, Cessna Aircraft Company Model 1A103/TCM6958 fixed- pitch propellers installed on, but not limited to Cessna Aircraft Company Models 152 and A152 and Reims Aviation S. A. Models F152 and FA152 aircraft. Affected propeller serial numbers are 770001 through 777390 and BC-001 up to, but not including JA001. Compliance: Required within the next 100 hours time in service after the effective date of this AD, or before the accumulation of 1200 hours time in service, whichever occurs later, unless already accomplished. To prevent possible fatigue cracks that can lead to blade separation near the hub, which could subsequently lead to engine separation and loss of aircraft control, accomplish the following: (a) Inspect and rework the hub bolt holes adjacent to the leading edge of the propeller blade and the propeller blade-to-hub forward face transition area in accordance with McCauley Accessory Division Service Bulletin 169C, dated September 22, 1989. NOTE: Previous compliance with McCauley Accessory Division Service Bulletin 169B, accomplished prior to the effective date of this AD, does constitute compliance with the requirements of this AD. (b) Remove from service prior to further flight any propeller which, after initial or final inspection following rework, shows evidence of cracks or other unairworthy conditions as described in McCauley Service Bulletin 169C, dated September 22, 1989. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance time specified in this AD may be approved by the Manager, Chicago Aircraft Certification Office, ACE-115C, Small Airplane Certification Directorate, Aircraft Certification Service, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. This amendment (39-6398, AD 89-26-10) becomes effective on January 31, 1990.
2008-02-17: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-50, -80A1/A3, and -80C2A series turbofan engines, installed on Airbus A300, A300-600, and A310 series airplanes. That AD currently requires initial and repetitive inspections and checks of the thrust reverser actuation systems. This AD requires revised inspection thresholds and intervals, and would require the same actions and additional inspections of the thrust reverser actuation system locking features. This AD results from refined safety analyses performed on the thrust reverser systems by GE and Airbus. We are issuing this AD to prevent inadvertent in-flight thrust reverser deployment, which can result in loss of control of the airplane.
91-07-13: 91-07-13 BOEING: Amendment 39-6948. Docket No. 90-NM-213-AD. \n\n\tApplicability: Model 757 series airplanes, listed in Boeing Service Bulletin 757-29- 0042, dated August 9, 1990, certificated in any category. \n\n\tCompliance: Required within 3,000 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent a latent failure of the alternate landing gear extension system, accomplish the following: \n\n\tA.\tInstall a bracket and attach the hydraulic tubing in accordance with Boeing Service Bulletin 757-29-0042, dated August 9, 1990. \n\n\tB.\tAn alternate 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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will thenforward comments or concurrence to the Seattle ACO. \n\n\tC.\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\tAll 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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6948, AD 91-07-13) becomes effective on April 29, 1991.
2008-01-05: The FAA is superseding an existing airworthiness directive (AD), that applies to certain Airbus Model A310 series airplanes. That AD currently requires modification of certain wires in the right-hand (RH) wing. This new AD requires further modification by installing an additional protection sleeve and segregating route 2S in the RH pylon area. This AD results from analysis of wire routing that revealed that route 2S of the fuel electrical circuit, located in the RH wing, does not provide adequate separation of fuel quantity indication wires from wires carrying 115-volt alternating current (AC). We are issuing this AD to ensure that fuel quantity indication wires are properly separated from wires carrying 115-volt AC. Improper separation of such wires, in the event of wire damage, could lead to a short circuit and a possible ignition source, which could result in a fire in the airplane.
92-16-06: 92-16-06 GARRETT AIRRESEARCH: Amendment 39-8315. Docket No. 92-CE-05-AD. \n\n\tApplicability: All aircraft equipped with Garrett AirResearch aircraft starters that are installed in, but not limited to, Boeing Models 707, 727, and 737 airplanes and McDonnell Douglas Models DC-8, DC-9, and DC-10 airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent in-service fatigue or structural failures of the aircraft starter, which could result in an in-flight fire or loss of control of the airplane, accomplish the following: \n\n\tNOTE 1: The 90-calendar day compliance time specified in paragraph (a) of this AD is a grace period and does not constitute FAA approval that the part is safe for operation during this time. \n\n\t(a)\tWithin the next 90 calendar days (see NOTE 1) after the effective date of this AD, inspect the owner/operator parts procurement records dated from January 1, 1987 to the effective date of this AD, and identify any of the following aircraft starter part numbers that have been distributed by Classic Aviation, Inc.: \n\n\t355290-1-1 \n\t355740-1-1 \n\t355760-3-1 \n\t356364-1-1, 356364-8-2, and 356364-8-3 \n\t356564-3-1 \n\t383042-4-1 \n\t383152-1-2, 383152-16-1, and 383152-19-1 \n\t383222-1-1 and 383222-4-1 \n\t383342-1-1, 383342-2-1, and 383342-4-1 \n\t383350-1-1 \n\t383370-1-1, 383370-2-1, 383370-3-1, 383370-4-1, 383370-5-1, 383370-6-1, 383370-7-1, \n\t and 383370-8-1 \n\t383642-1-1 \n\t383780-1-1 \n\t384022-5-1 and 380422 (all dash numbers) \n\n\tNOTE 2: The following serial numbers are known suspect starter serial numbers that have been procured from Classic Aviation, Inc.; however, this listing is provided for informational purposes only and may not include all suspect starters overhauled by Classic Aviation, Inc., and should not replace the thorough procurement records search: \n\n\n89P1265\n89P1281\n89P1282\n89P1425\n89P1460\n89P1476\n89P1487\n89P1488\n90P1644\n90P1503\n90P1505\n90P150790P1518\n90P1522\n90P1533\n90P1551\n90P1554\n90P1561\n90P1578\n90P1624\n90P1645\n90P1646\n90P1651\n90P1664\n90P1665\n90P1670\n90P1685\n90P1694\n90P1695\n90P1696\n90P1747\n90P1760\n90P1768\n90P1802\n90P1804\n90P1837\n90P1866\n90P1874\n90P1902\n90P1907\n90P1908\n90P1927\n90P1930\n90P1934\n90P1966\n91P2034\n91P2063\n91P2191\n91P2192\nP12756\nP10143CL\nP5244\nP16601\nP16726\nP8633\n40P475\n\n\n\n\n\n\t(b)\tIf any of the starters referenced in paragraph (a) of this AD are identified as being distributed by Classic Aviation, Inc., within the next 50 hours time-in-service after the procurement records inspection required by paragraph (a) of this AD, replace any such installed aircraft starter with a new aircraft starter, or overhaul any such installed aircraft starter through an authorized repair station. \n\n\t(c)\tThis AD does not constitute FAA approval of Garrett AirResearch aircraft starters that have been distributed by Classic Aviation, Inc., and the affected aircraft is still subject to the maintenance, preventive maintenance, rebuilding, and alteration requirements of FAR 43. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. \n\n\t(f)\tAll persons affected by this directive may examine information that is applicable to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. \n\n\t(g)\tThis amendment becomes effective on August 31, 1992.
2007-26-19: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620- 15, Tay 650-15, and Tay 651-54 turbofan engines. That AD currently requires initial and repetitive visual inspections of all ice-impact panels and fillers in the low pressure (LP) compressor case for certain conditions and replacing, as necessary, any or all panels. This AD requires the same actions, provides terminating action to those repetitive actions, and adds the Tay 611-8C turbofan engine to the applicability. This AD results from RRD introducing new LP compressor case ice-impact panels with additional retention features to these Tay turbofan engines. We are issuing this AD to prevent release of ice- impact panels due to improper bonding that can result in loss of thrust in both engines. DATES: This AD becomes effective February 11, 2008. The Director of the Federal Register previously approved the incorporation by reference of certainpublications listed in the regulations as of January 21, 2005 (70 FR 1172, January 6, 2005). The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of February 11, 2008.
72-07-03: 72-07-03 HAWKER SIDDELEY AVIATION, LTD.: Amdt. 39-1408 as amended by Amendment 39-1486. Applies to Hawker Siddeley Model DH-114 Series 2 "Heron" airplanes. Compliance is required on or before September 1, 1972. To prevent possible failure of the air bottles, P/N B.2994, used in the two main air reservoir assemblies, P/N C.51626, of the pneumatic system, replace the main air reservoir assemblies, P/N C.51626, located in the fuselage nose with serviceable assemblies, P/N SAS.388- 001, containing air bottles P/N BAT.205-001. (Hawker Siddeley Technical News Sheet, Series: Heron (114) No. S.7., Issues 1 and 2, dated June 21, 1971, and September 28, 1971, respectively, cover this same subject.) Amendment 39-1408 became effective April 15, 1972. This amendment 39-1486 is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by telegram dated May 31, 1972, which contained this amendment.