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82-21-03: 82-21-03 MITSUBISHI HEAVY INDUSTRIES, LTD., (MHI): Amendment 39-4472. Applies to MU-2B/-10/-15/-20/-25 (Serial Numbers 005 thru 238), MU-2B-30 (Serial Numbers 502 thru 547), and MU-2B-36 (Serial Number 501) airplanes certificated in any category. (This AD does not apply to MU-2B airplanes having serial numbers with the suffix "SA.") COMPLIANCE: Required as indicated unless already accomplished. To ensure correct engine fire detection and DC power emergency relay wiring, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: a) Inspect and, if necessary, repair the engine fire detecting and DC power emergency relay circuits as prescribed in Sections I and II of MHI Service Bulletin 187, dated May 27, 1982. b) Aircraft may be flown in accordance with FAR 21.197 to a maintenance facility where this inspection can be accomplished. c) An alternate means of compliance with this AD may be used when approved by the Manager,Honolulu Aircraft Certification Field Office, Northwest Mountain Region, Federal Aviation Administration, 300 Ala Moana Boulevard, Honolulu, Hawaii 96850. This amendment becomes effective on October 14, 1982.
2008-04-10: We are adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires revising the FAA-approved maintenance program by incorporating new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD also requires the initial inspection of a certain repetitive AWL inspection to phase in that inspection, and repair if necessary. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
83-10-02: 83-10-02 BRITISH AEROSPACE: Amendment 39-4651. Applies to BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated. For airplanes fitted with pilots windshield No. 1, left and right-hand part numbers AB31A705 and AB31A706 respectively, produced in 1979 and 1980 with serial numbers beginning with 9-H and 0-H, manufactured by P.P.G. Industries, Inc., accomplish the following, unless already accomplished: A. Check the bus-to-bus electrical resistance of the windshield NESA coat within the next 200 hours time in service or 28 days, whichever occurs first, after the effective date of this AD in accordance with paragraph 2.1 of the Accomplishment Instructions of British Aerospace Alert Service Bulletin 56-A-PM5836, dated March 19, 1982. NOTE: If windshield is replaced with another windshield produced in 1979 or 1980, repeat paragraph A after 200 hours time in service but not later than 300 hours time in service on the replacement windshield. B. Accomplish the actions of paragraph 2.2, 203, or 2.4 of the service bulletin based upon the resistance values obtained in the check done in paragraph A. C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. D. 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 31, 1983.
2008-03-17: 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) in June 2001. In their Letters referenced 04/00/02/07/01-L296 dated March 4th, 2002 and 04/00/02/07/03-L024, dated February 3rd, 2003, the JAA (Joint Aviation Authorities) recommended the application of a similar regulation to the National Aviation Authorities (NAA). Under this regulation, all holders of type certificates for passenger transport aircraft with either a passenger capacity of 30 or more, or a payload capacity of 7,500 pounds (3402 kg) or more, which have received their certification since January 1st, 1958, are required to conduct a design review against explosion risks. The unsafe condition is 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. We are issuing this AD to require actions to correct the unsafe condition on these products.
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.
76-14-09: 76-14-09 CURTISS-WRIGHT: Amendment 39-2672. Applies to C632S type propeller equipped with 744-6C2-() series hollow steel blades installed on but not limited to Douglas DC-6 aircraft. Compliance required within 300 hours in service after the effective date of this AD, unless previously accomplished within 1700 hours in service prior to the effective date of this AD, and every 2000 hours in service thereafter. To preclude the possibility of blade failure due to an undetected crack, accomplish the following in accordance with the propeller manufacturer's instructions contained in FAA approved Curtiss-Wright Corporation Service Publications S-242A-550 dated December 1, 1961, S-3B3-550 dated March 1, 1962, Chapter 63.2-2 as revised to May 1, 1962, and Chapter 63.2-4 as revised to November 1, 1964, or equivalent procedures and methods for inspection approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region: (a) Remove propeller from aircraft and remove blades from hub. (b) Remove the electrical de-icing heating elements or fluid anti-icing shoes. (c) Inspect the entire blade surface and the entire internal blade shank area for cracks using the magnetic particle inspection method. When inspecting the internal blade area, visually examine the entire accessible bondline for cracks or separations using a borescope device or a mirror and light combination. (d) Reject blades with "Indications" as defined in Curtiss-Wright Corporation Service Publication Chapter 63.2-4, paragraph 6. Replace with blades which have been inspected pursuant to this airworthiness directive. (e) Reassemble acceptable blades and return to service. Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection interval specified in this AD. This amendment is effective July 23, 1976.
2007-26-13: The FAA is superseding an existing airworthiness directive (AD) for certain MT-Propeller Entwicklung GmbH variable pitch and fixed pitch propellers manufactured before 1995, which had not been overhauled since April 1994. That AD currently requires overhauling the propeller blades and performing initial and repetitive visual inspections of affected propeller blades. That AD also requires removing all propeller blades from service with damaged erosion sheath bonding or loose erosion sheaths and installing any missing or damaged polyurethane protective strips. This AD requires the same actions. This AD results from the need to clarify the population of affected propellers previously listed in AD 2006-05-05. We are issuing this AD to prevent erosion sheath separation leading to damage of the airplane.
77-26-01: 77-26-01 HAWKER SIDDELEY AVIATION, LIMITED: Amendment 39-3099. Applies to DH/BH-125 airplanes, all series except 600A and 700A and excluding those airplanes with Modification 252239 embodied which introduces the Walter Kidde supply valve. Compliance is required as indicated unless already accomplished. To ensure the retainment of the threaded insert and prevent possible sudden discharge of the high pressure oxygen supply into the crew compartment, accomplish the following: (a) Within 10 hours time in service after the effective date of this AD, locate the oxygen master supply valve and passenger supply valve, both P/N SDV 826-1, and check to assure that threaded insert in the gland bushing is secure and spot lock the insert all in accordance with the Section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Limited Alert Service Bulletin 35-A25, dated October 13, 1977, or an FAA-approved equivalent. (b) Prior to installation of any oxygen supplyvalves from spares stock, unless already accomplished, check, tighten, and lock the insert in accordance with paragraph (a) of this AD. This amendment becomes effective January 3, 1978.
92-18-06: 92-18-06 BRITISH AEROSPACE: Amendment 39-8350. Docket No. 92-NM-46-AD. Applicability: Model BAe 146-100A, -200A, and -300A series airplanes, equipped with Dunlop hydraulic fuses, part number ACM29100; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent potential loss of airplane braking and directional control, accomplish the following: (a) Prior to the accumulation of 4,000 landings since installation of Dunlop hydraulic fuses having part number ACM29100 (Mod. states 1 or 2), or within 60 days after the effective date of this AD, whichever occurs later, remove green and yellow hydraulic systems Dunlop hydraulic fuses having part number ACM29100 (Mod. states 1 or 2) and install new hydraulic fuses having part number ACM30506 (Mod. 1), in accordance with British Aerospace Modification Service Bulletin SB.32-130-70295C, dated September 27, 1991. (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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 removal and installation shall be done in accordance with British Aerospace Modification Service Bulletin SB.32-130-70295C, dated September 27, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 20041-0414. 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 October 8, 1992.
68-10-03: 68-10-03 MCCAULEY: Amdt. 39-596. Applies to the following models with hub serial numbers whose first two digits are 62, 63, 64 or 65: D2A34C49, D2A34C49-A installed on Continental IO-470-S engines. D2AF34C54, D2AF34C54-A installed on Continental TSIO-470-D engines. 2AF34C55, 2AF34C55-A, 2AF34C55-8, 2AF34C55-C, 2AF34C55-D, 2AF34C55-E, 2AF34C55-F, 2AF34C55-G installed on Continental IO-470-L engines. D2AF34C60, D2AF34C60-A, D2AF34C60-B installed on Continental IO-360-A engines. To detect and prevent formation of cracks and possible hub failure, accomplish the following on propellers with 1200 hours' or more time in service within the next 25 hours' time in service after the effective date of this AD, unless previously accomplished: (a) Remove propeller from aircraft and disassemble. Remove hub alignment dowels and hub mounting studs from hub. (b) Inspect dowel and stud holes and adjacent areas for cracks by penetrant method. Replace before further flight any crackedhub with an approved replacement hub or hub which has been inspected and altered according to this AD. (c) Remove sharp corners formed where the hub mounting stud holes and hub alignment dowel pin holes intersect the inside of the propeller hub, in accordance with instructions in McCauley Service Manual or an alteration approved by the Chief, Engineering & Manufacturing Branch, Eastern Region. Propellers with 1200 hours' or more time in service which have been inspected according to Paragraph (b) within 300 hours' time in service prior to the effective date of this AD, but which have not been modified according to Paragraph (c), need not comply with this AD until 300 hours' time in service from such previous inspection. This amendment is effective May 11, 1968.
2007-25-11: 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: Two events have been reported of Fokker 100 (F.28 Mk.0100) aircraft, where the Nose Landing Gear (NLG) failed to extend in the normal mode and problems were experienced to open the NLG doors, almost preventing extension of the NLG in the emergency (alternate) mode. Subsequent investigation and tests have shown that the friction of the bearing in the roller of the NLG Door Uplock Bracket Assembly is high, causing increased resistance in the mechanical system that unlocks the NLG doors. This condition, if not corrected, may result in a NLG up landing, which is considered a hazardous event. * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-18-09: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 series airplanes, and Model A320-111 airplanes. That AD currently requires an inspection to determine whether certain braking and steering control units (BSCUs) are installed or have ever been installed. For airplanes on which certain BSCUs are installed or have ever been installed, the existing AD requires an inspection of the nose landing gear (NLG) upper support, and corrective action if necessary; and a check of the NLG strut inflation pressure, and an adjustment if necessary. For some of these airplanes, the existing AD also requires a revision to the aircraft flight manual to incorporate an operating procedure to recover normal steering in the event of a steering failure. This new AD instead requires repetitive inspections of the NLG upper support, and related investigative/corrective actions in accordance with new service information; and removes the one-time inspection that was required by the existing AD. This new AD also provides an optional terminating action for the repetitive inspections. This AD results from a report of an incident where an airplane landed with the NLG turned 90 degrees from centerline, and from additional reports of NLG upper support anti-rotation lugs rupturing in service. We are issuing this AD to prevent landings with the NLG turned 90 degrees from centerline, which could result in reduced controllability of the airplane.
92-02-06: 92-02-06 BOEING: Amendment 39-8142. Docket No. 91-NM-262-AD. \n\n\tApplicability: Model 747-400 series airplanes, listed in Boeing Alert Service Bulletin 747-35A2075, Revision 1, dated September 19, 1991, certificated in any category. \n\n\tCompliance: Required within the next 30 days after the effective date of this AD, unless accomplished previously. \n\n\tTo prevent pilot incapacitation during an emergency situation requiring supplemental oxygen to the flight crew, accomplish the following: \n\n\t(a)\tInspect the captain's and first officer's oxygen hoses below the oxygen mask stowage boxes in accordance with Boeing Alert Service Bulletin 747-35A2075, Revision 1, dated September 19, 1991. Replace damaged or short hoses before further flight, in accordance with the service bulletin. \n\n\t(b)\tAn 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, Seattle Aircraft CertificationOffice (ACO), 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, Seattle ACO. \n\n\t(c)\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\t(d)\tThe inspection and replacement requirements of this AD shall be done in accordance with Boeing Alert Service Bulletin 747-35A2075, Revision 1, dated September 19, 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. 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, D.C.(e)\tThis amendment (39-8142, AD 92-02-06) becomes effective on January 24, 1992.
2007-24-08: The FAA is superseding an existing airworthiness directive (AD) that applies to all Boeing Model 767 airplanes. That AD currently requires repetitive measurements of the rudder and elevator freeplay, repetitive lubrications of rudder and elevator components, and related investigative/corrective actions if necessary. This new AD instead requires revised repetitive measurements of the rudder freeplay and the elevator freeplay for each of the power control actuators (PCAs) that move the rudder and elevator, corrective and related investigative actions if necessary, and repetitive lubrications of the rudder and elevator components. For some airplanes, this AD also requires related concurrent actions. This AD results from reports of freeplay-induced vibration of the rudder and the elevator. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in loss of control of the airplane.
96-09-11: This amendment adopts a new airworthiness directive (AD) that applies to de Havilland DHC-6 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
2007-24-02: The FAA is superseding an existing airworthiness directive (AD) that applies to all Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The existing AD currently requires repetitive detailed inspections for damage of the electrical wire and sleeve that run to the fuel boost pump through a conduit in the fuel tank, and arcing damage of the conduit and signs of fuel leakage into the conduit; replacement of the sleeve with a new, smaller-diameter sleeve; and related investigative and corrective actions, as applicable. This new AD reduces the inspection threshold for certain airplanes. This AD \nresults from a report of a fuel tank explosion on a Model 727-200F airplane on the ground, and a report of chafed wires and a damaged power cable sleeve of a fuel boost pump discovered during an inspection on a Model 737-300 airplane. (The fuel boost pump installation on certain Model 737 airplanes is almost identical to the installation on Model 727 airplanes.) We are issuing this AD to detect and correct chafing of the fuel boost pump electrical wiring and \nleakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank.\n\nDATES: This AD becomes effective December 6, 2007. \n\n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 6, 2007. \n\n\tOn June 6, 2007 (72 FR 28597, May 22, 2007), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 737-28A1263, Revision 1, dated March 19, 2007. \n\n\tWe must receive any comments on this AD by January 22, 2008.