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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.)
2006-04-14: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 and -300 series airplanes. This AD requires installing clamps on certain end caps of the overhead distribution ducts, and doing other specified and related investigative actions as necessary. This AD results from finding that the end caps of the overhead distribution ducts for the air conditioning system were not bonded to the ducts with an adhesive. We are issuing this AD to detect and correct loosened end caps, which could change the air flow balance in the airplane. During a smoke event in the cargo or main electronics compartment, the incorrect balance of air flow could change the smoke clearance air capacity and result in smoke and toxic fumes penetrating the flight deck and main cabin.
98-18-04: This amendment adopts a new airworthiness directive (AD), applicable to all Aerospatiale Model SN-601 (Corvette) series airplanes, that requires repetitive inspections to detect corrosion, cracking, or rupture of the support arms of the aileron balance weights; and repair, if necessary. Accomplishment of the repair terminates the repetitive inspection requirement of this AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent corrosion, cracking, or rupture of the support arms of the aileron balance weights, which may cause reduced flutter damping or jamming of the aileron, and consequent reduced controllability of the airplane.
95-19-08 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 727-100 and -200 series airplanes, that currently requires replacing the attaching nutplates on certain engine nose cowls with washers and self-locking nuts. This amendment changes the responsible office for approval of an alternative method of compliance. This amendment is prompted by the transfer of the supplemental type certificate. The actions specified in this AD are intended to prevent the attach bolts from becoming loose, which could result in subsequent separation of the nose cowl from the engine.
83-23-01: 83-23-01 PILATUS BRITTEN-NORMAN LTD: Amendment 39-4764. Applies to Models BN-2, BN-2A and BN-2B Islander Series Airplanes equipped with wing tip tanks (Mod NB/M/364) certificated in any category except BN-2A MKIII Series Trislander Airplanes. Compliance: Required within 100 hours time-in-service after the effective date of this AD, but no later than December 31, 1983, unless already accomplished. To preclude fuel mismanagement and possible fuel starvation, accomplish the following: a) Modify the wing tip tank fuel management system in accordance with steps 1. through 12. of the ACTION section of Pilatus Britten-Norman Ltd. Service Bulletin No. BN- 2/SB.157, dated March 14, 1983. 1) Upon completion of the modification described in paragraph a) update and annotate the appropriate airplane flight manual as follows: i) BN-2A-3 Model: insert Issue 4 of Supplement No. 8 to Section 7 of Flight Manual FM/10 dated March 4, 1983; ii) BN-2A-9 Model: insert Issue 2 of Supplement No. 16 to Section 7 of Flight Manual FM/2 dated March 4, 1983; iii) BN-2A-21 Model: insert Issue 4 of Supplement No. 8 to Section 7 of Flight Manual FM/10 dated March 4, 1983; iv) BN-2A-27 Model: insert Issue 2 of Supplement No. 1 to Section 7 of Flight Manual FM/20 dated March 4, 1983; v) BN-2B-21 Model: insert Issue 3 of Supplement No. 1 to Section 7 of Flight Manual FM/43 dated March 4, 1983; vi) BN-2B-27 Model: insert Issue 5 of Supplement No. 1 to Section 7 of Flight Manual FM/42 dated March 4, 1983. NOTE: The requirement for insertion of specific revisions in the affected Airplane Flight Manuals does not prohibit incorporation of later revisions containing the same information. 2) The requirement of paragraph a)1) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him. The person accomplishing this action must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. b) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on December 8, 1983.
2015-19-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports that six fasteners may not have been installed in the left and right stringer 37 (S-37) between body stations (BS) 428 and 431 lap splices on certain airplanes. This AD requires a general visual inspection of S-37 lap splices for missing fasteners, and all applicable related investigative and corrective actions. We are issuing this AD to detect and correct missing fasteners, which could result in cracks in the fuselage skin that could adversely affect the structural integrity of the airplane.
2010-20-10: The FAA is superseding an existing airworthiness directive (AD), which applies to all Model 750 airplanes. That AD currently requires inspecting the inboard-hinge brackets of the left and right elevators for cracking and doing related investigative and corrective actions if necessary. For certain airplanes, this new AD requires inspecting for cracks of the bracket of the inboard horizontal stabilizer and measuring the lug thickness of the horizontal stabilizer hinges; doing corrective actions if necessary; and modifying the left and right elevators and left and right horizontal stabilizer. For all airplanes, this new AD requires replacing the existing elevator assemblies with new elevator assemblies, which terminates the requirements of the existing AD. This new AD also revises the applicability to remove certain airplanes. This AD results from a report of cracking found on the elevator inboard-hinge brackets and the horizontal stabilizer hinges. We are issuing this AD to prevent such cracking of the elevator inboard-hinge brackets and the horizontal stabilizer hinges, which could result in structural failure of the elevators and consequent loss of control of the airplane.
2015-19-13: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of inadvertent deployment of a single outboard spoiler during flight. This AD requires replacement of the power control units (PCUs) for the outboard spoilers with upgraded PCUs. We are issuing this AD to prevent leakage of the piston head seal and piston rod seals of the outboard spoiler PCUs, which could result in inadvertent spoiler deployment and reduced controllability of the airplane.
2010-19-01: The FAA is superseding an existing airworthiness directive (AD) for RRC AE 3007A series turbofan engines. That AD currently requires performing an eddy current inspection (ECI) or surface wave ultrasonic test (SWUT) inspection on each affected high-pressure turbine (HPT) wheel. This AD requires removing or performing initial and repetitive ECIs or SWUT inspections on HPT stage 2 wheels for cracks. This AD also reduces the approved life limits of certain HPT stage 2 wheels. This AD results from reports of cracked HPT stage 2 wheels. We are issuing this AD to prevent uncontained failure of the HPT stage 2 wheel and damage to the airplane.
2000-15-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-400 series airplanes. This action requires a one-time inspection to determine if certain wire bundles are routed incorrectly and to detect damage, and corrective actions, if necessary. This action is necessary to prevent damage of certain wire bundles routed to the fuel tank transfer pumps in the horizontal stabilizer, which could result in electrical arcing and a possible fire adjacent to the fuel tank. This action is intended to address the identified unsafe condition.
2000-14-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain BFGoodrich main brake assemblies as installed on Airbus Model A319 and A320 series airplanes. This action requires repetitive inspections to determine the length of the wear indicator pins of the main brake assemblies of the main landing gear (MLG); follow-on inspections; and corrective actions, if necessary. This amendment is prompted by reports from several operators that severe oxidation was found on the rotor disk assemblies of the main brake assemblies. This action is necessary to detect and correct thermal oxidation of the main brake assemblies, which could result in deterioration of the MLG brakes, and consequent reduced braking performance.
2015-19-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8 airplanes. This AD was prompted by reports of a potential latent failure of the fuel shutoff valve actuator circuitry, which was not identified during actuator development. This AD requires replacing certain engine and auxiliary power unit (APU) fuel shutoff valve actuators with new actuators, and also requires revising the maintenance or inspection program to include a new airworthiness limitation into the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA). We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.
2015-19-06: We are superseding Airworthiness Directive (AD) 2012-24-10 for certain The Boeing Company Model 747-400 and -400F series airplanes. AD 2012-24-10 required installing new software, replacing the duct assembly with a new duct assembly, making wiring changes, and routing certain wire bundles. This new AD retains the requirements of AD 2012- 24-10 and requires installing a new or serviceable pressure switch bracket and altitude pressure switch. This new AD also adds an airplane to the applicability. This AD was prompted by reports of intermittent or blank displays of a certain integrated display unit (IDU) that were due to an intermittent false electrical ground that was not addressed by the software installation or wiring changes required by AD 2012-24- 10. We are issuing this AD to prevent IDU malfunctions, which could affect the ability of the flightcrew to read primary displays for airplane attitude, altitude, or airspeed, and consequently reduce the ability of the flightcrewto maintain control of the airplane.
2000-14-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires replacement of the upper and lower reading lights in the forward crew rest area with a redesigned light fixture. This amendment is prompted by reports of burning and smoldering blankets in the forward crew rest area due to a reading light fixture that came into contact with the blankets after the light was inadvertently left on. The actions specified by this AD are intended to prevent a possible flammable condition, which could result in smoke and fire in the forward crew rest area.
86-09-04: 86-09-04 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-5290. Applies to Model HS 748, constructor numbers 1793, 1794, and 1795 (Mod 402); and 1796 (Mod 400); and to any other airplanes which incorporate Modification 6953, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To prevent the accidental disarming of the emergency lighting system, accomplish the following, unless previously accomplished: 1. Modify the emergency lighting system in accordance with BAe HS 748 Service Bulletin 33/29, dated April 2, 1984. 2. 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, Northwest Mountain Region. 3. 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. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective May 26, 1986.
81-26-06: 81-26-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4283. Applies to Lockheed Model L-1011 series airplanes, Serial Numbers as listed below, certificated in all categories. Compliance required within 30 days after the effective date of this AD, unless previously accomplished: A. To prevent an unnecessary shutdown of the number 2 engine due to false Airborne Vibration Monitor System indications, incorporate electrical system modifications in accordance with Part 2, Accomplishment Instructions, of Lockheed-California Company L-1011 Service Bulletin 093-23-083 dated October 13, 1981, for the following 42 aircraft: S/N 1083-1090 S/N 1117-1119 S/N 1134-1136 S/N 1092-1097 S/N 1121-1123 S/N 1139 S/N 1099-1103 S/N 1126-1129 S/N 1141 S/N 1105-1106 S/N 1132 S/N 1145-1147 S/N 1112-1113 B. Alternative means of compliance providing an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. 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. 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 Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108; or the Los Angeles Area Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California 90808. This Amendment becomes effective December 31, 1981.
2015-19-08: We are superseding Airworthiness Directive (AD) 2011-19-04, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-19-04 required repetitive inspections for cracking of the left- hand and right-hand inboard and outboard elevator servo-control rod eye-ends, and corrective actions if necessary. This new AD requires an inspection to determine if certain elevator servo-control parts are installed, and replacement if necessary. This AD was prompted by a determination that certain elevator servo-control parts that do not conform to the approved type design have been installed and may have the potential of cracks in the rod eye-end. We are issuing this AD to detect and correct rod eye-end cracking, which could result in uncontrolled elevator surface and consequent reduced control of the airplane.
2000-14-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes equipped with General Electric Model CF6-45 or -50 series engines, that requires repetitive inspections and tests of the thrust reverser control and indication system, and corrective actions, if necessary. This amendment also requires installation of a thrust reverser actuation system (TRAS) lock, repetitive functional tests of that installation, and repair, if necessary. Installation of the TRAS lock terminates the repetitive inspections and certain tests. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in a significant reduction in airplane controllability. The actions specified by this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.