Results
2016-08-10: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6- 80C2A5, CF6-80C2A5F, CF6-80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B3F, CF6-80C2B4, CF6- 80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6- 80C2B7F, CF6-80C2B8F, CF6-80C2D1F, CF6-80C2L1F, CF6-80C2K1F and CF6- 80E1A1, CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B turbofan engines. This AD was prompted by reports of a burn-through of the accessory heat shield during an engine fire, propagating the fire into the accessory compartment and igniting additional flammable fuel source. This AD requires replacing the accessory heat shield assembly. We are issuing this AD to prevent fires from propagating into the accessory compartment, resulting in an uncontrolled engine fire, and damage to the airplane.
83-24-01: 83-24-01 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4770. Applies to Model HS 748 series 2A airplanes, certificated in all categories. To prevent failure of the wing structure, accomplish the following, unless already accomplished: A. Prior to accumulation of 10,000 landings, or within the next 750 landings after the effective date of this AD, whichever occurs later, visually inspect the wing structure in accordance with paragraph 2.B of the Accomplishment Instructions of British Aerospace HS 748 Aircraft Service Bulletin 57/34, Revision 3, dated March 3, 1980. B. Repeat the inspections as specified in Table No. 1 of the service bulletin. C. If any cracks are found, accomplish paragraph 2.D of the service bulletin. D. For the purpose of this AD, and when approved by an FAA maintenance inspector, the number of landings may be computed by dividing each airplane's time in service by the operator's fleet average time from takeoff to landing for the aircraft type. E. 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. F. 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 December 23, 1983.
79-11-04: 79-11-04 FAIRCHILD (HILLER): Amendment 39-3479. Applies to Model 1100 and FH-1100 type helicopters certificated in all categories. Compliance required as indicated unless already accomplished. In order to prevent cracking of the transmission lower housing gimbal ring support, accomplish the following: a. For P/N 24-23030-7 transmission lower housings (installed in P/N 24-23000-11, -31, and -41 transmission assemblies) which have accumulated 500 or more hours since new or overhauled, inspect and repair as necessary within 50 hours after the effective date of this AD, unless already accomplished within the last 500 hours, in accordance with Fairchild Service Bulletin No. FH-1100-23-10 dated September 25, 1974, revised April 24, 1979. This inspection shall be repeated at each 500-hour interval thereafter. b. For P/N 24-23030-7 transmission lower housings which have accumulated 1200 or more hours, unless already accomplished within the last 1100 hours, ream the gimbalring mounting holes to the next larger size in accordance with Fairchild Service Bulletin No. FH-1100-23-10 dated September 25, 1974, revised April 24, 1979, within 100 hours after the effective date of this AD and at each 1200-hour interval thereafter. c. As a result of the inspection and repair required under paragraphs a and b herein, if the gimbal ring mounting hole diameter exceeds 0.8755 inch or a total time of 3600 hours is attained on the P/N 24-23030-7 lower housing assembly the housing shall be retired from further service. d. Upon installation of transmission lower housing assembly P/N 24-23030-11, the requirements of this AD are no longer applicable. e. Equivalent inspections or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this airworthiness directive. f. Rotorcraft may be flown to a base where the maintenance required by this airworthiness directive is to be performed per FARs 21.197 and 21.199. This amendment is effective June 4, 1979.
2016-08-03: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. This AD requires an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. This AD also provides an optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane.
2000-23-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the flight control computers (FCC) with new, improved FCC's having updated software installed. This amendment also requires, for some airplanes, modification of the wiring of the FCC's. The actions specified by this AD are intended to prevent autopilot reversions in certain flight conditions, which could result in misunderstanding by the flight crew and consequent reduced ability to take appropriate action. This action is intended to address the identified unsafe condition.
2016-07-15: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a fuel leak that occurred in the baggage compartment during fuel system pressurization. This AD requires opening the fuel boxes and restoring the sealing. We are issuing this AD to prevent failure of a connector or coupling on a fuel line, which, in combination with a leak in the corresponding enclosure (i.e., fuel box), could result in a fire in the baggage compartment and affect the safe flight of the airplane.
2011-01-02: 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 published SFAR 88 (Special Federal Aviation Regulation 88). By mail referenced 04/00/02/07/01-L296 of March 4th, 2002 and 04/00/02/07/03-L024 of February 3rd, 2003 the JAA [Joint Aviation Authorities] recommended to the National Aviation Authorities (NAA) the application of a similar regulation. The aim of this regulation is to require * * * a definition review against explosion hazards. * * * * * Failure of the auxiliary power unit (APU) bleed leak detection system could result in overheat of the fuel tank located in the horizontal stabilizer and ignition of the fuel vapors in that tank, which could result in a fuel tank explosion and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
68-26-02: 68-26-02 DE HAVILLAND: Amdt. 39-694. Applies to DHC-6 Type Airplanes. To detect loose or missing jo-bolts in wing struts which have accumulated 150 or more hours time in service as of the effective date of this A.D., accomplish the following: (a) Within the next 50 hours time in service, unless already accomplished, visually inspect the top and bottom of the right and left wing struts, P/N C6W1005-3, -4, for loose or missing jo-bolts in accordance with the procedure described in deHavilland Service Bulletin No. 6/166, or an FAA approved equivalent procedure. (b) Identical inspections must be conducted at subsequent times in service of 450 to 550 hours, 2450 to 2550 hours and 7450 to 7550 hours after the inspection required by (a) and thereafter at intervals not to exceed 5000 hours time in service. (c) Prior to further flight, missing jo-bolts must be replaced with jo-bolts of the same part number or an FAA approved equivalent part; but a maximum of four (4)missing in any strut may be replaced within the next 250 hours time in service provided: (1) they are not all next to each other in the same row of twelve (12); or (2) they do not include more than two (2) which are next to each other in the same row of twelve (12) within six (6) inches of the strut end. (d) Equivalent parts and inspection procedures must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector. This amendment is effective December 20, 1968.
2016-06-14: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80E1 turbofan engines with rotating compressor discharge pressure (CDP) seal, part number (P/N) 1669M73P02, installed. This AD was prompted by reports from the manufacturer of cracks in the teeth of two rotating CDP seals found during engine shop visits. This AD requires stripping of the coating, inspecting, and recoating the teeth of the affected rotating CDP seals. We are issuing this AD to prevent cracking of the CDP seal teeth, uncontained part release, damage to the engine, and damage to the airplane.
2011-01-01: We are superseding an existing 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 earlier MCAI, Brazilian Airworthiness Directive 2007-08-01, effective September 27, 2007, describes the unsafe condition as: Fuel system reassessment, performed according to RBHA-E88/SFAR- 88 (Regulamento Brasileiro de Homologacao Aeronautica 88/Special Federal Aviation Regulation No. 88), requires the inclusion of new maintenance tasks in the Critical Design Configuration Control Limitations (CDCCL) and in the Fuel System Limitations (FSL), necessary to preclude ignition sources in the fuel system. * * * The new MCAI, Brazilian Airworthiness Directive 2009-08-03, effective August 20, 2009, describes the unsafe condition as: An airplane fuel tank systems review required by Special Federal Aviation Regulation Number 88 (SFAR 88) and "RBHA Especial N mero 88'' (RBHA E 88) has shown that additional maintenance and inspection instructions are necessary to maintain the design features required to preclude the existence or development of an ignition source within the fuel tanks of the airplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
63-16-05: 63-16-05 UNIVERSAL: Amdt. 589 Part 507 Federal Register July 24, 1963. Applies to All Models Temco D-16 and D-16A Aircraft. Compliance required within 25 hours' time in service following the effective date of this AD and at each periodic inspection thereafter. (a) Inspect the flap and landing gear actuating cylinders for cracks. If any cracks appear, the cylinder must be replaced. (b) Determine, by means of a hydraulic gage, that the hydraulic system pressure relief valve is adjusted to 1125 + 25, -0 p.s.i. Excessive pressures could cause damage to the components of the system. (c) Unless already installed, install hydraulic fluid restrictors in the nose gear lines, Serial Numbers 1271 and subsequent, main gear lines, Serial Numbers 1790 and subsequent, and flap lines, all serial numbers. (d) Inspect the linkage adjustments of the landing gear bungee springs and the flap stops and determine that they have been properly adjusted in accordance with appropriate service manuals. (Tusco Corporation Service Letter No. 79 dated December 23, 1958, covers this same subject.) This directive effective August 23, 1963.
2016-07-01: We are superseding Airworthiness Directive (AD) 2014-07-04R1 for certain Model S-92A helicopters. AD 2014-07-04R1 required repetitive inspections in the upper deck area for incorrectly installed clamps and chafing between the electrical wires and the hydraulic lines and replacing any unairworthy wires or hydraulic lines. This new AD requires altering the wiring system in the upper deck area to correct the unsafe condition described in AD 2014-07-04R1. We are issuing this AD to prevent a fire in an area of the helicopter without extinguishing capability and subsequent loss of control of the helicopter.
84-21-03: 84-21-03 McDONNELL DOUGLAS: Amendment 39-4939. Applies to McDonnell Douglas Model DC-9, and C-9 (Military) series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent jamming of the elevator controls by a detached forward rod end, accomplish the following: \n\n\tA.\tWithin the next 650 hours time in service or 90 calendar days, whichever occurs first after the effective date of this AD, visually inspect the fitting assembly (rod end) part number (P/N) 3938704-1 and pushrod P/N 3938705-501, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-266, dated March 12, 1984, hereinafter referred to as ASB27-266, or later FAA approved revisions. \n\n\tB.\tIf results of visual inspection are satisfactory, accomplish paragraph 4 of Part 2, Accomplishment Instructions, of ASB27-266. \n\n\tC.\tIf results of visual inspection are unsatisfactory, proceed in accordance with paragraph 5, Accomplishment Instructions of ASB27-266. \n\n\tNOTE: If rod end P/N SM4-6T3 (exclude DC-9-80 series) is required and not available, P/N SM4-6T may be substituted. The latter has only one grease fitting which must be oriented to allow access for scheduled lubrication. \n\n\tD.\tAlternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective November 26, 1984.
83-23-06: 83-23-06 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-4767. Applies to Model HS 748 series 2A and 2B airplanes certificated in all categories. To prevent structural failure of the engine subframe, accomplish the following, unless already accomplished: A. Prior to 7 years from date of manufacture, or within the next 12 months after the effective date of this AD, whichever occurs later, inspect engine subframe struts and perform the appropriate actions in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace Aircraft Group HS 748 Service Bulletin 54/25, Revision 4, dated May 1979. B. Repeat the inspections of the subframe struts at seven year intervals from the last inspection. 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 December 15, 1983.
2016-06-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of fire and smoke at the engine aft pylon area resulting from fuel leakage caused by a damaged O-ring in the fuel coupling attached to the wing front spar. This AD requires applying sealant to fill the gap between the lower wing panels adjacent to the strut aft vapor barrier. We are issuing this AD to prevent fire and smoke at the engine aft pylon area in the event of a fuel leak, which could cause personal injury during ground operations. A fire spreading back and up to the aft fairing pylon can result in an uncontrolled fire in the strut and ignite the fuel tank.
80-01-05 R1: 80-01-05 R1 PACIFIC SCIENTIFIC COMPANY KIN-TECH DIVISION: Amendment 39-3646 as amended by Amendment 39-3851. Applies to Pacific Scientific Restraint Systems rotary buckles manufactured through 1970. \n\n\tCompliance required within 240 days from January 31, 1980. \n\n\tTo prevent failure to open of the flight crew and attendants' seat belts, accomplish the following: \n\n\ta.\tInspect crew and attendants' restraint systems to determine if a Pacific Scientific rotary buckle is installed. \n\n\tb.\tIf installed, determine if the rotary buckle assembly contains a black body plate assembly as identified in Figure I of this AD. No further action is required per this AD if the rotary buckle assembly includes a black body plate assembly. \n\n\tc.\tFor those restraint systems incorporating Pacific Scientific rotary buckles without a black body plate assembly as specified in Figure I of this AD: \n\n\t\t1.\tSubstitute of any approved restraint system not incorporating the above described rotary buckle; or, \n\n\t\t2.\tReplace the buckle element of the restraint system with a Pacific Scientific buckle element incorporating a black body plate assembly as identified in Figure I of this AD. \n\n\t\tNOTE: Pacific Scientific Service Bulletin 1101550-25-11 Revision "A" dated August 2, 1979 pertains to this subject. \n\n\td.\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-3646 became effective January 31, 1980. \n\n\tThis Amendment 39-3851 becomes effective on July 10, 1980.
2016-04-16: We are superseding Airworthiness Directive (AD) 2013-08-23 for all The Boeing Company Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10- 30F, MD-11, and MD-11F airplanes. AD 2013-08-23 required adding design features to detect electrical faults and to detect a pump running in an empty fuel tank. This new AD would clarify certain requirements and remove a terminating action. This new AD would also provide an optional method of compliance for the proposed actions. This AD was prompted by a determination that it is necessary to clarify the requirements for the design features and to remove a terminating action for certain inspections. We are issuing this AD to reduce 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.
85-11-52 R1: 85-11-52 R1 BOEING: Amendment 39-5105. Applies to Model 737-300 series airplanes equipped with Plessey Type 8240 Mark 1, 2, or 3 fuel boost pumps or TRW 10-60533-1 fuel boost pumps, certificated in any category. \n\n\tTo prevent engine flameouts during climb, accomplish the following, unless already accomplished: \n\n\t1.\tBefore further flight ensure that the fuel being used is one of the following types: \n\t\to\tJet A or A1 conforming to specification ASTM-D-1655; \n\t\to\tJP5 conforming to MIL-T-5624; \n\t\to\tFuels conforming to DERD 2494 or 2498; or \n\t\to\tFuels conforming to AIR 3404 or 3405. \n\n\t2.\tWithin 48 hours incorporate the following information into the Limitations Section of the Airplane Flight Manual and provide to crews: \n\n\t"The only approved fuels are Jet A and A1 conforming to Specification ASTM-D-1655, JP5 conforming to MIL-T-5624, fuels conforming to DERD 2494 or 2498, and fuels conforming to AIR 3404 or 3405." \n\n\t3.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: Compliance with paragraph 2. of this directive may be effected by including a copy of this AD in the Airplane Flight Manual and Operating Manual. \n\n\tThis amendment becomes effective August 6, 1985. It was effective earlier to all recipients of telegraphic AD 85-11-52, issued June 7, 1985, which contained this amendment.
2016-05-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of cracked aluminum support struts of the trimmable horizontal stabilizer (THS) caused by stress corrosion. This AD requires inspections to identify the part number of each support strut, repetitive inspections for cracking of the THS support strut ends, installation of reinforcing clamps on strut ends, and replacement of support struts, if necessary. We are issuing this AD to detect and correct cracked THS support struts, which could lead to the rupture of all four support struts making the remaining structure unable to carry limit loads, which could result in loss of the THS and reduced control of the airplane.
62-23-05: 62-23-05 LYCOMING: Amdt. 501 Part 507 Federal Register October 30, 1962. Applies to All GO, IGO, GSO and IGSO Series Lycoming Engines Listed in Lycoming Service Bulletin No. 290 When Installed in Twin Engine Aircraft With Full Feathering Hartzell Propellers: MODEL SERIES APPLICABLE SERIAL NOS. EXCEPTED SERIAL NOS. GO-435 3306-11 through 3324-11 3315-11 and 3316-11 GO-580-B 1161-28 through 1221-28 1173-28 GO-480-F 607-29 through 614-29 GO-480-D 402-32 through 404-32 GSO-480 3010-33 through 3065-33 3336-33 through 3338-33 GO-480-C and -G 1446-34 through 1492-34 1481-34 and 1483-34 through 1488-34 GO-480-C and -G 1315-35 through 1326-35 GO-480-C and -G 219-37 through 290-37 276-37, 286-37, 287-37 and 289-37 GO-480-G 203-42 and 204-42 IGSO-480 701-44 through 1038-44 755-44, 756-44, 797-44, 798-44, 833-44, 834-44, 1007-44 through 1012-44, 1014-44 through 1016-44, 1022-44 through 1025-44 IGO-540 101-49 through 226-49 204-49 through 207-49, 210-49, 211-49, 214-49, 217-49, 223-49, 224-49 IGSO-540 101-50 through 537-50 322-50, 323-50, 395-50, 439-50, 442-50, 443-50, 450-50 through 452-50, 478-50 through 482-50, 484-50, 485-50, 489-50, 490-50, 495-50, 498-50, 501-50 through 509-50, 511-50 through 513-50, 516-50 through 521-50, 523-50, 526-50, 528-50 through 530-50, 212-50, 213-50, 215-50, 216-50, 218-50, 219-50, 303-50, 304-50, 307-50, 308-50, 326-50, 327-50, 335-50, through 338-50, 341-50, 342-50, 345-50 through 350-50, 376-50 through 379-50, 382-50, 383-50, 387-50, 388-50, 399-50, 400-50, 402-50, 403-50, 436-50, 437-50, 460-50, 461-50, 464-50, 465-50, 468-50 through 472-50, 483-50, 486-50, 487-50, 491-50 through 494-50; and to Remanufactured and Factory Overhauled Engines shipped from the Lycoming Division During the Period of February 16, 1961, through August 31, 1962; and to All Applicable Engines Overhauled at Facilities Other than the Manufacturer, in Which the Provisions of Lycoming Service Instruction No. 1033 Have Been Incorporated. (Note: If the Compliance Status of Service Instruction No. 1033 is Unknown, Inspection per this AD is Required.) Compliance required within 10 hours' time in service after the effective date of this AD; 25 hours' time in service after the first inspection; 25 hours' time in service after the second inspection, and every 100 hours' time in service thereafter. To detect excessive wear of the propeller shaft oil seal rings, a propeller oil leakdown inspection shall be made in accordance with the instructions contained in Lycoming Service Bulletin No. 290. These inspections shall be continued until Lycoming P/N 67722 propeller shaft oil seal rings are installed in the reduction gear assembly at which time the inspections may be discontinued. Reductiongear assemblies incorporating P/N 67722 oil seal rings shall be identified by stamping an "M" following the reduction gear serial number on the machined pad to the right side of the timing plug in the reduction gear housing. (Lycoming Service Bulletin No. 290 covers this subject.) This directive effective November 14, 1962.
82-15-02: 82-15-02 HILLER AVIATION: Amendment 39-4416. Applies to Model UH-12D, UH- 12E, UH-12E4, UH-12E-L, UH-12L, UH-12L4, and military OH-23D, OH-23F and OH-23G series helicopters, certificated in all categories, through serial No. 5187. Compliance required as indicated, unless already accomplished. To prevent loss of power to the main and tail rotors, accomplish the following: Within 50 hours' additional time in service after the effective date of this AD, remove the four P/N 21041 bolts and four AN 960-716L washers which attach the mercury clutch to the torsional coupling and replace with new P/N 21041 bolts and P/N 21074-3 washers in accordance with Part 2, Accomplishment Instruction, of Hiller Aviation Service Bulletin No. 21-2 dated January 20, 1982, or FAA approved equivalent. The four P/N 21041 bolts removed per this action must be considered unairworthy and marked accordingly. NOTE: Hiller Model UH-12 series helicopters converted to turbine power by Supplemental Type Certificate (STC) SH178WE or SH177WE do not incorporate the subject parts and therefore are not affected by this AD unless restored to the original configuration. Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the FAR to operate rotorcraft to a base for the accomplishment of inspections or modifications required by this AD. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region. This amendment supersedes AD 82-10-06. This amendment becomes effective July 16, 1982.
2016-04-14: We are adopting a new airworthiness directive (AD) for certain [[Page 9745]] Turbomeca S.A. Arriel 1E2 turboshaft engines. This AD requires removing the tachometer box on affected engines. This AD was prompted by reports of uncommanded in-flight shutdowns (IFSDs). We are issuing this AD to prevent failure of the tachometer box, which could lead to failure of the engine, IFSD, and loss of control of the helicopter.
64-11-02: 64-11-02 HILLER: Amdt. 730 Part 507 Federal Register May 16, 1964. Applies to All Model UH-12E Helicopters. Compliance required as indicated. A number of failures of the tail rotor pinion gear have been experienced. These failures have been experienced with several different gear heat treat lots and on helicopters both with and without rotor brakes installed. To preclude any additional failures, accomplish the following: (a) Replace tail rotor pinion gears identified as Hiller P/N 23522 or P/N 23634 with a tail rotor pinion gear P/N 23634-3 as follows: (1) Gears with less than 50 hours total time in service on the effective date of this AD shall be replaced prior to the accumulation of 100 hours' total time in service. (2) Gears with 50 hours or more total time in service on the effective date of this AD shall be replaced within the next 50 hours' time in service. (b) Tail rotor pinion gears identified as P/N 23634-3 are satisfactory for unlimitedservice life. NOTE: An "-A" following P/N 23634 should be disregarded inasmuch as this is a gear vendor's marking and not part of the Hiller part number. (Hiller Service Information Letter No. 3036 "C" covers this same subject.) This supersedes AD 63-26-02. This directive effective May 16, 1964.
52-04-04: 52-04-04 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required not later than July 1, 1952. Provide two separate and individually protected circuits for instrument panel lighting- each circuit to provide adequate panel illumination for necessary flight instruments. (G. L. Martin Co. Service Bulletin 118 and Trans World Airlines Engineering Order 5643 cover this same subject for the 202A).
87-04-14: 87-04-14 BRITISH AEROSPACE: Amendment 39-5540. Applies to British Aerospace (BAe) Model DH/HS/BH-125 series airplanes identified in BAe Service Bulletins 49-31-9286A and 49-32-9210A, both Revision 1, and both dated March 24, 1986, certificated in any category. Compliance is required within 6 months after the effective date of this AD. To reduce the possibility of APU fuel leakage in the rear equipment bay, and assure electrical bonding of the starter/generator to the airplane, accomplish the following, unless previously accomplished: A. Seal the APU plenum shroud at the turbine plenum drain outlet in accordance with BAe Service Bulletin 49-31-9286A, Revision 1, dated March 24, 1986, Modification No. 259286A. B. Install twin heavy duty bonding cables between the APU accessory case and ground terminal post 16 on the main engine beam in accordance with BAe Service Bulletin 49-32- 9210A, Revision 1, dated March 24, 1986, Modification No. 259210A. C. An alternate meansof 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. 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 the modifications required by 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 British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents 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 March 9, 1987.