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2015-20-09: We are superseding airworthiness directives (AD) 2001-18-06 and AD 2008-22-16, for all General Electric Company (GE) CT58 turboshaft engines. AD 2001-18-06 and AD 2008-22-16 required recalculating the lives of life-limited rotating parts using a repetitive heavy-lift (RHL) multiplying factor and removal from service of parts that exceed the recalculated cyclic or hourly life limit. This new AD would consolidate AD 2001-18-06 and AD 2008-22-16, and further reduce the life capability of certain parts. This AD was prompted by recalculation of life for parts installed on engines used in Utility operations, and a reduced life for compressor spools in all operations. We are issuing this AD to prevent failure of life-limited rotating parts, uncontained part release, damage to the engine, and damage to the aircraft.
2000-15-19: This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model SA-365N, N1, and AS-365N2, N3 helicopters. This action requires inspecting the sand filter ejection nozzle (nozzle) for cracks and replacing any cracked nozzle. This amendment is prompted by the discovery of a cracked nozzle during a preflight inspection. This condition, if not corrected, could result in loss of the nozzle in flight, impact with the main or tail rotor, and a subsequent forced landing.
79-18-05: 79-18-05 LITHIUM SULFUR DIOXIDE BATTERIES: Amendment 39-3549 as amended by Amendment 39-3708. Applies to all Lithium Sulfur Dioxide (LiSO2) batteries installed in aircraft or in equipment used in aircraft. LiSO2 batteries have been used in, but not necessarily limited to, the following Emergency Locator Transmitters (ELT's): Communications Components Corporation Model CIR 10, all serial numbers Battery pack BP-60, BP-60A, BP-60B, and BP-60C. Model CIR 11-2, all serial numbers Battery pack BP-60-11, BP-60-11A, BP-60-11B, and BP-60-11C. Cessna Aircraft Co. Part Number C589511-0103 Part Number C589510-0202 Part Number C589510-0209 Part Number C589510-0109 Dorne and Margolin, Inc. Model DMELT 6 serial numbers 1 to 24,999 with battery pack DMELT 6.11, except those ELT's which have been modified by the change to battery pack DMELT 6.13. Garrett Manufacturing Ltd. Model No. 627-810 - all serial numbers 627-818 - all serialnumbers 627-934 - all serial numbers 625-088 - all serial numbers Battery part number 616-246-1 616-246-2 Leigh Systems, Inc. Model SHARC 7 with a 3 or 4 cell battery pack. The ELT including battery weighs approximately 1.8 pounds. Pathfinder Corporation Model No. 2052 Pointer Inc. Model 2000 Model 2000, Series Mod A Model 3000, Series Mod A Model 3000-2 LiSO2 battery pack - P/N 2018, P2018, M2018, 2018 HSP, and 2018 HSM. Other aircraft equipment that have used LiSO2 batteries: (1) Bendix RNAV Computer Model RNS3500 Control Display Unit CD-3501A. (2) Emergency lighting, sliderafts, and flashlights. Manufacturer's have not used LiSO2 batteries in the following ELT's. However, such batteries may have been substituted after manufacture. Pacific Communication Corporation Alert Model 50, 60, and 70 Pacific Avionic Company, Inc. Model ELT-1 DME Corporation Model RLB-5 (A)Model RLB-9 (A) and (B) Micro Electronics, Inc. Emergency Beacon Corporation All models LARAGO/MERL, Inc. LARAGO 79007 MERL 1005 Dorne and Margolin Model DMELT 6 serial no. 25,000 and above Compliance is required as indicated, unless already accomplished. To prevent fire, venting violently, explosion, corrosion, or leakage of gas associated with certain LiSO2 batteries, accomplish the following: (a) Before further flight, remove all LiSO2 batteries which do not meet the requirements of TSO-C97 from U.S.-registered civil aircraft, including any installed in equipment used in such aircraft. NOTE: This AD requires that LiSO2 batteries used in U.S.-registered civil aircraft meet the requirements of TSO-C97. LiSO2 batteries removed from equipment in accordance with AD 79-05-02 or this AD may be replaced by LiSO2 batteries which meet the requirements of TSO-C97 or another power source. However, in either case the equipment must meet all applicable requirements of the Federal Aviation Regulations. (b) Before further flight, remove from U.S.-registered civil aircraft any ELT powered by LiSO2 batteries which do not meet the requirements of TSO-C97, and comply with the recordkeeping and placarding requirements of FAR Section 91.52(f)(10)(i). (c) For any aircraft from which an ELT has been removed to comply with AD 79-05-02 or this AD, before March 28, 1980 (October 15, 1980 for ELT's specified in paragraph (f) of the AD) either - (1) Install LiSO2 batteries which meet the requirements of TSO-C97 in the ELT and, provided the ELT meets the requirements of FAR Section 37.200, reinstall it in the aircraft; or (2) Install in the aircraft an ELT which meets the requirements of FAR Section 37.200 which is powered by a source other than LiSO2 batteries. (d) Upon installation of an ELT in accordance with paragraph (c) of this AD, record in the aircraft records the action taken, and remove the placard which states "ELT NOT INSTALLED." (e) Notwithstanding FAR Section 91.52(f)(10)(ii), an aircraft from which an ELT has been removed in accordance with AD 79-05-02 or this AD, may operate without an ELT required by FAR Sections 91.52(a) and (b) until complying with paragraph (c) of this AD, but in no event later than March 28, 1980 (October 15, 1980 for ELT's specified in paragraph (f) of this AD). (f) The later alternate compliance date specified in paragraphs (c) and (e) of this AD applies when a removed ELT was manufactured by: (1) Communications Components Corporation (2) Garrett Manufacturing Ltd; and (3) Leigh Systems, Inc. Amendment 39-3549 superseded Amendment 39-3422, AD 79-05-02. Amendment 39-3549 became effective August 24, 1979. This Amendment 39-3708 becomes effective February 28, 1980.
91-25-09: 91-25-09 EMBRAER (Empresa Brasileira de Aeronautica S.A.): Amendment 39-8110. Docket No. 91-CE-82-AD. Applicability: EMB-110 Series airplanes (all serial numbers), certificated in any category. Compliance: Required within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 300 hours TIS. To prevent loss of control of the airplanes caused by failure of the elevator trim tab support, accomplish the following: (a) Visually inspect the elevator trim tab actuator support, either part number (P/N) 110-3215-56 or P/N 110-3210-04 for cracks and loose fasteners. Prior to further flight, replace any cracked elevator trim tab actuator support with a new support, P/N 10-3210-04, and replace any loose fasteners in accordance with the applicable maintenance manual. (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 initial or repetitive 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 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) Information that is related to this AD may be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri. This amendment (39-8110, AD 91-25-09) becomes effective on December 23, 1991.
2015-20-01: We are adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating the left and right lower surface panels of the wings are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking at these panels, and repair if necessary. The AD also requires a one-time bolt- hole eddy current inspection of all open holes for cracking, repair if necessary, and modification. We are issuing this AD to prevent fatigue cracking of the left and right lower surface panels of the wings, which could result in reduced structural integrity of the airplane.
2006-05-02: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F series airplanes. This AD requires repetitive inspections for cracking of certain fuselage internal structure, and repair if necessary. This AD results from fatigue tests and analysis that identified areas of the fuselage where fatigue cracks can occur. We are issuing this AD to prevent loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.
2000-15-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires inspections of a certain component, and corrective action, if necessary. This action is necessary to detect and correct stress corrosion cracking in the front spar of the center section of the horizontal stabilizer, which could result in structural failure of the horizontal stabilizer and loss of control of the airplane. This action is intended to address the identified unsafe condition.
98-04-12: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-04-12 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R44 helicopters by individual letters. This AD requires an initial and repetitive measurement of the lateral cyclic trim spring shaft (shaft) diameter and replacement of the shaft spring assembly (spring assembly) if the shaft diameter is excessively worn. Replacement of the spring assembly with a modified spring assembly is considered terminating action for this AD. This amendment is prompted by an incident in which a pilot felt binding in the cyclic control when attempting to move it to the left. A precautionary landing was made using only right-hand turns. Subsequent inspection revealed that a notch was worn in the shaft, which caused the shaft and spring to move from the lower mount and interfere with the lateral control. Inspection of a second RHC Model44 helicopter revealed similar wear. Excessive wear can create a notch on the shaft, which can cause the spring assembly to move out of its lower mount. This condition, if not corrected, could lead to the shaft interfering with lateral cyclic control, which could result in loss of control of the helicopter.
2015-20-06: We are adopting a new airworthiness directive (AD) for all Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-7-1 and DHC-7-100 airplanes. This AD was prompted by reports of cracks that were discovered in the outboard nacelles upper longeron channels and angles. This AD requires a one-time detailed visual inspection for cracking in the outboard nacelles upper longeron channels and angles; and repair if necessary. We are issuing this AD to detect and correct cracks in the outboard nacelles upper longeron channels and angles, which could lead to the loss of stiffness in the forward engine mount; and possible catastrophic failure.
51-03-02: 51-03-02 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required by April 1, 1951, on all aircraft having main landing gears with 4,000 hours service or more, and thereafter every 4,360 cycles of landing gear operation. Due to reported occurrences of cracks, the main landing gear crankshafts (P/N 202SD82019 and 202SD82021) should be replaced with new crankshafts bearing the same part numbers and having a ground radius around the periphery of the hole for the retract pin. (Martin Service Bulletin No. 128, dated October 4, 1950, covers this same subject.)