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93-02-05: 93-02-05 TEXTRON LYCOMING: Amendment 39-8487. Docket 92-ANE-56. Applicability: Textron Lycoming reciprocating opposed piston engines incorporating fuel injection lines as listed in Textron Lycoming Service Bulletin No. (SB) 342A, dated May 29, 1992, except for Model TIO-540-S1AD engines. Affected engine models are installed on but not limited to Piper PA-24 Comanche, PA-30 and PA-39 Twin Comanche, PA-28 Arrow, and PA-23 Aztec; Beech 60 Duke and 23 Musketeer; Mooney M20; and Cessna 177 Cardinal aircraft. NOTE: Engines with an "I" in the prefix of the model designation incorporate fuel injection. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the fuel injector fuel lines allowing fuel to spray into the engine compartment, resulting in an engine fire, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, inspect the fuel injector fuel lines between the fuel manifold and the fuel injector nozzles in accordance with Textron Lycoming Service Bulletin No. 342A, dated May 26, 1992. (b) Prior to further flight, replace any fuel injector fuel line that does not meet all the return to service conditions specified in Textron Lycoming SB No. 342A, dated May 26, 1992. (c) Thereafter, at each annual inspection, at each 100-hour inspection, at each engine overhaul, and after any maintenance has been performed on the engine where the fuel injector fuel lines have been disconnected, moved, or loosened, reinspect the fuel injector fuel lines in accordance with Textron Lycoming SB No. 342A, dated May 26, 1992, and replace as necessary any fuel injector fuel line that does not meet all the return to service conditions specified in that SB. (d) 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, New York Aircraft Certification Office. The request should beforwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the New York Aircraft Certification Office. (e) 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. (f) The inspection, and replacement, if necessary of the fuel injector fuel lines shall be done in accordance with the following service document: Document No. Pages Date Textron Lycoming SB No. 342A 1-31 May 26, 1992 Total pages: 31 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 Textron Lycoming Reciprocating Engine Division, 652 Oliver Street, Williamsport, Pennsylvania 17701. Copies may be inspected at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on June 14, 1993.
98-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-200A series airplanes, that requires a one-time inspection of the gust damper of the elevator control system to determine if the gust damper is properly charged, and of the horizontal stabilizer to detect cracking of elevator hinge rib 1; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of elevator hinge rib 1 of the horizontal stabilizer, which could occur if the gust damper of the elevator control system discharges and allows the elevator to move freely in ground gust conditions. Such cracking could result in damage to the structural attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane.
2007-08-01: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, - 9B1, and -9B2, -9C, -9C3, -9D, and -9D2 turboprop engines, with certain part number (P/N) and serial number stage 2 turbine aft cooling plates installed. That AD currently requires a onetime eddy current inspection (ECI) of boltholes in certain P/N stage 2 turbine aft cooling plates. This AD expands the population of affected CT7 turboprop engine models, but reduces the number of cooling plates affected. It also requires a onetime ECI of boltholes in certain P/N stage 2 turbine aft cooling plates with specific serial numbers. This AD results from the manufacturer expanding the list of affected engine models and identifying the affected stage 2 turbine aft cooling plates by serial number. We are issuing this AD to prevent separation of the stage 2 turbine aft cooling plate, resulting in uncontained engine failure and damage to the airplane.
82-01-06: 82-01-06 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39-4290. Applies to Model A109A series helicopters through Serial Number 7169 equipped with engine mount central legs, P/N 109-0605-06 and 109-0605-07, certificated in all categories (Airworthiness Docket No. 81-ASW-43). Compliance is required within 200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of the engine mount central leg and possible loss of engine support, accomplish the following: (a) Remove the engine mount central legs, P/N 109-0605-06-13, 109-0605-06-14, 109-0605-07-13, and 109-0605-07-14. (b) Install engine mount central leg assemblies, P/N 109-0640-84-1 and -2, and P/N 109-0640-85-1 and -2 as described in Section 71-20-00 of the A109A maintenance manual. (c) Install engines and check engine to transmission alignment as described in Section 71-00-00 of the A109A maintenance manual. (d) If an equivalent means of compliance is used in complying with this AD, that equivalency must be approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa and Middle East Office, c/o American Embassy, Brussels, Belgium. Compliance with Agusta Technical Bulletin No. 109-25, dated August 29, 1980, constitutes compliance with this AD. This amendment becomes effective February 8, 1982.
2007-07-15: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 B4-600, B4-600R, C4- 605R Variant F, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. That AD currently requires a one-time inspection for damage of the integrated drive generator (IDG) electrical harness and pyramid arm, and repair if necessary. This new AD adds new repetitive inspections, which, when initiated, terminate the inspection required by the existing AD. This new AD also requires repairing damage and protecting the harness. This new AD also provides for optional terminating action for the repetitive inspections. This new AD also removes certain airplanes from the applicability of the existing AD. This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the IDG electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control of the airplane. DATES: This AD becomes effective May 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 14, 2007. On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A310-54A2038, dated February 19, 2004; and Airbus All Operators Telex A300-54A6037, dated February 19, 2004.
2007-06-06: 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: * * * incidences have been reported to Britten-Norman Aircraft Ltd where cracks have been found in the inner shell of the pitot/ static pressure heads. This could result in incorrect readings on the pressure instrumentation, e.g. altimeters, vertical speed indicators (rate-of-climb) and airspeed indicators. We are issuing this AD to require actions to correct the unsafe condition on these products.
80-07-07: 80-07-07 BEECH: Amendment 39-3729. Applies to Model 77 (Serial Numbers WA-1 through WA-78, WA-80 through WA-86, and WA-88) certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To prevent excessive aileron control forces or jamming of the aileron control system, within the next twenty-five (25) hours time-in-service after the effective date of this AD accomplish the following: A) Replace the aileron bearings (P/N 108-130010-17) with aileron bushings (P/N 108-160010-39) in accordance with procedures set forth in Beechcraft Service Instructions No. 1119. B) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective April 3, 1980.
2019-19-11: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. This AD requires initial and repetitive inspections of the low-pressure compressor (LPC) inlet guide vane (IGV) and the LPC rotor 1 (R1) and, depending on the results of the inspections, possible replacement of the LPC. This AD was prompted by two recent in-flight shutdowns (IFSDs) that occurred as the result of failures of the LPC R1. The FAA is issuing this AD to address the unsafe condition on these products.
95-12-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed Model L-1011-385 series airplanes. This action requires an inspection to detect cracking of the bulkhead at fuselage station (FS) 1363 at butt line (BL) 42.5, and repair or additional inspections, if necessary. This amendment is prompted by reports indicating that fatigue cracking was found in the rear bulkhead at FS 1363. The actions specified in this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking of the pressure bulkhead.
95-21-12: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) (Eurocopter) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that requires initial and repetitive inspections of the main rotor (M/R) blade upper and lower surfaces for bulging. This amendment is prompted by two reported incidents in which a balance weight became detached from inside the M/R blade structure and migrated toward the tip of the M/R blade. The actions specified by this AD are intended to detect movement of a balance weight and to prevent severe vibrations and a subsequent precautionary landing.