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2001-17-13: This amendment supersedes Airworthiness Directive (AD) 2001-08-01, which applies to certain JanAero Devices (JanAero) 14D11 and 23D04 series fuel regulator shutoff valves used with certain JanAero combustion heaters that are installed on aircraft. AD 2001-08-01 currently requires you to visually inspect and pressure test these fuel regulator shutoff valves for leaks, and, if leaks are found, replace the fuel regulator shutoff valve. Numerous reports of fuel regulator shutoff valves leaking fuel caused the Federal Aviation Administration (FAA) to issue AD 2001-08-01. This amendment retains the actions of AD 2001-08-01, except only the visual inspection or the pressure test will be required instead of both. This amendment also specifically calls out the fuel regulator shutoff valves by part number instead of series, includes provisions for disabling the heater as an alternative method of compliance, and makes other minor clarifying revisions and additions to the AD. The actionsspecified by this AD are intended to eliminate or severely reduce the potential for fuel leakage in aircraft with these combustion heaters, which could result in an aircraft fire with consequent damage or destruction. The Director of the Federal Register previously approved the incorporation by reference of JanAero Devices Service Bulletin No. A-107, dated January 8, 2001, as of May 10, 2001 (66 FR 19720, April 17, 2001). The FAA must receive any comments on this rule on or before October 5, 2001.
2016-25-13: We are superseding airworthiness directive (AD) 2016-04-12, that applies to certain Safran Helicopter Engines, S.A. (formerly Turbomeca S.A.) Arriel 2B, 2B1, 2C, 2C1, 2C2, 2D, 2E, 2S1, and 2S2 turboshaft engines. AD 2016-04-12 required spectrometric oil analysis (SOA) inspection of the engine accessory gearbox (AGB), and, depending on the results, removal of the engine AGB. This AD requires initial and repetitive wear inspections of the engine AGB cover. This AD was prompted by a report of an uncommanded in-flight shutdown (IFSD) of an Arriel 2S2 engine caused by rupture of the 41-tooth gear, which forms part of the bevel gear in the engine AGB. We are issuing this AD to correct the unsafe condition on these products.
92-06-08: 92-06-08 GULFSTREAM AMERICAN: Amendment 39-8188; Docket No. 91-CE-66-AD. Applicability: Model GA-7 airplanes (serial numbers GA7-0001 through GA7-0115), certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent elevator binding and loss of pitch control, which could result in loss of control of the airplane, accomplish the following: (a) Dye penetrant inspect the elevator spar between stabilizer station 41.0 and 45.0 for cracks by accomplishing paragraphs A-1, A-2, A-3, B-1, B-2, and B-3 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (1) If cracks are found that extend inboard from station 41.0, outboard of station 45.0, or into the spar caps, prior to further flight, replace the elevator and accomplish the following: (i) Install Service Kit No. 12 by accomplishing paragraphs B-5 through B-20 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (ii) Balance the new elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-1-1. (iii) Install the new elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-3-1. (2) If cracks are found that do not extend inboard from station 41.0, outboard of station 45.0, or into the spar caps, prior to further flight, accomplish the following: (i) Stop drill any cracks found. (ii) Install Service Kit No. 12 by accomplishing paragraphs B-5 through B-20 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (iii) Balance the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-1-1. (iv) Reinstall the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-3-1. (3) If no cracks are found, prior to further flight, accomplish the following: (i) Install Service Kit No. 12 by accomplishing paragraphs B-5 through B-20 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (ii) Balance the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-1-1. (iii) Reinstall the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-3-1. (b) 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.(c) An alternative method of compliance or adjustment of the compliance time 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 should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. (d) The inspection and installation required by this AD shall be done in accordance with the instructions contained in GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 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 American General Aircraft Corporation, Route 1, AB 306, P.O. Box 5757, Greenville, Mississippi 38703. 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. (e) This amendment (39-8188) becomes effective on April 17, 1992.
2001-17-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires performing a general visual inspection to detect chafing or damage of the parallel power feeder cables of the number 2 integrated drive generator (IDG); repairing any chafed cable and damaged structure; and repositioning the parallel power feeder cables of the number 2 IDG. This action is necessary to prevent chafing and arcing of the parallel feeder cables of the number 2 IDG, which could result in smoke and/or fire in the right aft galley area. This action is intended to address the identified unsafe condition.
81-13-12 R1: 81-13-12 R1 DETROIT DIESEL ALLISON: Amendment 39-4179 as amended by Amendment 39-4701. Applies to all Model 250-C30, -C30P, and C30S engines and turbine assemblies equipped with 4th stage turbine nozzle assembly P/N 6898694 installed in aircraft certificated in all categories, EXCEPT: 1. Models 250-C30, -C30S: ENGINE SERIAL NO. TURBINE SERIAL NO. CAE 890690, 890691, CAT 95105, 95106, 890692, 890696, and subsequent 95108, 95109, and subsequent 2. Model 250-C30P: ENGINE SERIAL NO. TURBINE SERIAL NO. CAE 895086, 895087, and subsequent CAT 95110, 95111, 95112, and subsequent Compliance is required as indicated unless already accomplished. To prevent cracks in P/N 6898694 4th stage turbine wheel nozzles leading to uncontained turbine wheel failures accomplish the following: a. Inspect, reduce life limits where applicable based on inspection results, and remove from service affected P/N 6898694 nozzles in compliance with the schedule, instructions, and inspection criteria provided in Detroit Diesel Allison Commercial Engine Alert Bulletin CEB-A-72-3056, Revision 3 dated March 30, 1983, or later FAA approved revisions. b. Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate aircraft to a base where compliance with this AD can be accomplished. c. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Detroit Diesel Allison, Division of General Motors Corporation, Indianapolis, Indiana 46206. These documents also maybe examined at the Office of Regional Counsel, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803 weekdays, except federal holidays, between 8:00 a.m. and 4:30 p.m. Amendment 39-4179 became effective August 10, 1981. This Amendment 39-4701 becomes effective September 26, 1983.
91-05-10: 91-05-10 FOKKER: Amendment 39-6905. Docket No. 90-NM-233-AD. Applicability: Model F-28 Mark 1000, 2000, 3000, and 4000 series airplanes, as listed in Part II of Fokker Report No. SE-243, Issue No. 1, dated June 1, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the airplane, accomplish the following: A. Accomplish the structural modifications according to the service bulletins and the "incorporation threshold" listed in Part II of Fokker Report No. SE-243, Issue No. 1, dated June 1, 1990 as follows: 1. For airplanes that have accumulated time-in-service exceeding the specified "incorporation threshold" as of the effective date of this AD, the structural modifications must be accomplished by the following dates: a. July 1, 1996, for those service bulletins to which [Note 1] applies. b. July 1, 1993, for those service bulletins to which [Note 2] applies. c. July 1, 1993, or 14 years after the airplane's manufacturing date, whichever occurs later, for service bulletins to which [Note 4] applies. 2. For airplanes that have accumulated time-in-service less than the specified "incorporation threshold" as of the effective date of this AD, the structural modifications must be accomplished before the applicable "incorporation threshold" or by the following dates, whichever occurs later: a. July 1, 1996, for service bulletins to which [Note 1] applies. b. July 1, 1993, for service bulletins to which [Note 2] applies. c. July 1, 1993, or 14 years after the airplane's manufacturing date, whichever comes later, for service bulletins to which [Note 4] applies. B. An 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE:The request should be submitted directly to the Manager, Standardization Branch, ANM- 113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6905, AD 91-05-10) becomes effective on March 25, 1991.
2022-27-05: The FAA is superseding Airworthiness Directive (AD) 2022-09- 15, which applied to all Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. AD 2022-09-15 required relocating affected servo- valves and revising the existing airplane flight manual (AFM) to provide temporary information necessary to operate airplanes fitted with at least one affected brake servo-valve. AD 2022-09-15 also limited or prohibited the installation of affected brake servo-valves. This AD was prompted by a determination that replacing certain brake servo-valves is necessary to address the unsafe condition. This AD continues to require the actions in AD 2022-09-15, including the parts installation limitation or prohibition, and also requires replacing an affected part with a serviceable part, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2001-17-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires replacement of the air driven generator (ADG) wire assembly with a new, increased length wire assembly. This amendment requires, among other actions, replacement of the existing ADG wire assembly in the right air conditioning compartment with a certain new wire assembly. This amendment is prompted by an investigation that revealed the length of the new wire assembly is too long and causes the assembly to chafe against the left emergency alternating current bus of the ADG. The actions specified by this AD are intended to prevent loss of the charging capability of the airplane battery due to chafing. Loss of the charging capability of the airplane battery, coupled with a loss of all normal electrical power, could prevent continued safe flight and landing of the airplane.
2001-17-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires an inspection of the upper avionics circuit breaker panel at the main observer's station to detect damage of the wires and to verify the correct routing of the wire bundles; corrective actions, if necessary; and installation of a new clamp, spacer, and sta-straps. This action is necessary to prevent chafing in the upper avionics circuit breaker panel of the main observer's station, which could result in arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
2001-16-10: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-200, -300, -320, and -500 series airplanes; and all Model ATR72 series airplanes. The AD requires revising the Airplane Flight Manual to modify procedures for calculating takeoff performance when Type II or IV de-icing or anti-icing fluids have been used. This amendment is prompted by reports that use of these de-icing or anti-icing fluids may result in an increase in the pitch forces necessary to rotate the airplane during takeoff. This condition could result in a delayed takeoff or even late aborted takeoff. The actions specified by this AD are intended to ensure that the flight crew is advised of the potential effects of Type II or IV de-icing or anti-icing fluids on the airplane's performance during takeoff, and to ensure that the flight crew is advised of the revised performance calculations for takeoff to address these effects.