Results
67-29-03: 67-29-03 FAIRCHILD-HILLER: Amdt. 39-499 Part 39 Federal Register October 25, 1967. Applies to all F-27J and FH-227 aircraft with installed Solar Auxiliary Power Unit Model T-62T-25, Serial Nos. S-408000 to S-408099 inclusive. Compliance required as indicated unless already accomplished, or unless APU is rendered electrically inoperative and APU controls are placarded to prohibit operation. To provide adequate APU fire detection system reliability and sensitivity, accomplish the following modifications: (a) Within the next 100 operational APU hours following the effective date of this AD, install an additional fire detector, Solar P/N 7447-2, (set at 400 25 degrees F) in accordance with Fairchild-Hiller Service Bulletin Nos. F-27-49-4 Revision 3, dated Sept. 25, 1967 or FH-227-49-4 Revision 3 dated Sept. 25, 1967 as applicable, or later FAA approved revision, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Within the next 100 operational APU hours following the effective date of this AD, install MIL-W-25038B fire resistant wire in the fire detection circuit in accordance with Fairchild-Hiller Service Bulletin Nos. F27-49-6 dated July 10, 1967 or FH227-49-6 dated July 10, 1967 as applicable, or later FAA-approved revision, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Within the next 200 operational APU hours following the effective date of this AD, replace the two existing 700 degree fire detectors, Solar P/N 7447-1 with two 400 + 25 degree F Fire detectors Solar P/N 7447-2. NOTE. - Compliance with paragraph (c) may be accomplished by arranging for the detector manufacturer, Fenwal, Inc. of 900 Main Street, Ashland, Massachusetts 01721, Solar P/N 7447-1 with two 400+25 degree F fire and reidentify the detector by P/N 7447-2. (d) Upon the effective date of this AD, APU operational hours will belogged until such time as the entire AD has been complied with. This amendment effective October 27, 1967.
53-12-02: 53-12-02 de HAVILLAND: Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 451 Inclusive. Compliance required as indicated. Cases have been reported of loss of seals in the flap hydraulic hand pump No. 430RDH. To prevent the above condition a modification (No. 2/926) was incorporated on production aircraft and should be incorporated on aircraft in service as soon as possible but not later than the next 100 hours. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet, Series B, No. 63 dated March 19, 1953, available from de Havilland Aircraft of Canada, Ltd., Toronto, Ontario, Canada, covers this same subject and describes method of repair.)
70-16-09: 70-16-09 AIRESEARCH: Amdt. 39-1064. Applies to Model TPE331-3W-301A engines, S/N P01001 through P-01010 and P-01012, P-01014, and P-01015, installed in but not limited to Handley-Page Model C10A aircraft. This directive necessary because of a serious condition which may be caused by backing off of the high speed pinion retaining nut. To prevent engine failures from this cause, the following is required: Replace the high speed pinion assembly P/N 869441-2 in accordance with AiResearch telegraphic service bulletin No. 622, dated July 24, 1970, or later FAA approved revision, prior to further use. This amendment is effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated July 24, 1970.
47-10-19: 47-10-19 LOCKHEED: (Was Mandatory Note 21 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088, Except as Noted. Compliance required not later than 100 hours of operation after June 10, 1947. (a) In each cabin heater installation, relocate and waterproof the fuel solenoid valve and replace and reroute the fuel pump bypass line. (LAC Service Bulletin 49/SB-73 covers this same subject.) (b) In zone 2 of each nacelle, install heat protective shield between propeller feathering line and cowl diaphragm. Applies to all serials up to and including 2082. (LAC Service Bulletin 49/SB-150 covers this same subject.) (c) In each outboard nacelle main junction box, replace existing mounting nuts (tinnerman) and PK screws with AN 366 nuts and NAS 221 screws. (LAC Service Bulletin 49/SB-152 covers this same subject.) (d) Drill one 1/4-inch drain hole on lower center line of spinner fairing lower panel assembly for each engine. (LAC Service Instruction 49/SI-95 covers this same subject.)
50-13-01: 50-13-01 CONVAIR: Applies to All Model 240 Aircraft. Compliance required as indicated. Failures of the wing portion of the aileron hinge brackets and bracket supports have been experienced on Convair Model 240 aircraft. These failures have been the result of excessive lateral vibration of the ailerons experienced mainly during engine operation between 1,000 to 1,200 r.p.m., in aircraft incorporating Hamilton Standard propellers. In order to preclude the possibility of these failures progressing to such a state that the airworthiness of the airplane is impaired, it is considered necessary that the following be accomplished on Convair Model 240 Series aircraft: A. To be accomplished on all individual CV-240 Series aircraft incorporating Hamilton Standard propellers at every No. 2 operation, until part B, is accomplished. Inspect the aileron in area of hinge brackets, aileron hinge brackets and bracket supports with a 10-power glass, for signs of fatigue cracking. Special attention should be paid to the areas around the rivet holes utilized for attaching the brackets to the bracket supports and to that portion of the bracket supports in the areas at which the bracket supports extend from the wing trailing edge structure. Any failed parts should be adequately repaired or replaced prior to the next flight. B. To be accomplished by January 1, 1951, on airplanes incorporating Hamilton Standard propellers. Incorporate steel aileron hinge brackets and incorporate measures to increase the lateral rigidity of the wing portion of the aileron hinges. (CVAC Service Bulletin 240-289 covers this same subject.)
65-13-06: 65-13-06 LOCKHEED: Amdt. 39-88 Part 39 Federal Register June 23, 1965. Applies to Models 1049C, 1049D, 1049E, 1049G, and 1049H Series aircraft. Compliance required as indicated. To detect cracked beam cap tie-in fittings, accomplish the following: (a) Inspect the beam cap tie-in fittings, Lockheed P/N's 311134L and 311134R, on the upper forward face of the rear spar at Wing Stations 80L and 80R for cracks in the area of the 0.16 inch radius near the center of the fitting, using dye penetrant or an FAA-approved equivalent as specified in (b) or (c) as applicable. (b) Inspect fittings with 20,000 or more hours' time in service on the effective date of this AD in accordance with (a) within the next 350 hours' time in service unless already accomplished within the last 3,150 hours' time in service, and at intervals thereafter not to exceed 3,500 hours' time in service from the last inspection. (c) Inspect fittings with less than 20,000 hours' time in service on the effective date of this AD in accordance with (a) within 350 hours' time in service after the effective date of this AD unless already accomplished, and - (1) If the fittings had 16,850 or more hours' time in service at the time of the inspection, reinspect at intervals not to exceed 3,500 hours' time in service from the last inspection; (2) If the fittings has less than 16,850 hours' time in service at the time of the inspection, reinspect before the accumulation of 20,350 hours' time in service and at intervals thereafter not to exceed 3,500 hours' time in service from the last inspection. (d) Replace any fitting found cracked with a new fitting of the same part number before further flight. (e) Operators who have not kept records of hours' time in service on individual fittings shall substitute airplane hours' time in service in lieu thereof. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This supersedes AD 64-06-05. This directive effective July 23, 1965.
94-01-12: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Industrie Model A310-200 and A310-300 series airplanes series airplanes, that currently requires inspections and tests to detect broken or missing vespel bushes in the flap universal joint assemblies, and replacement of universal joint bushes, if necessary. This amendment adds a terminating modification for the currently required inspections and tests. This amendment is prompted by the development of a modification that will improve the integrity of the flap universal joints. The actions specified by this AD are intended to prevent rupture of the flap universal joints, subsequent partial loss of lift in one wing, and reduced controllability of the airplane.
90-08-07: 90-08-07 BRITISH AEROSPACE: Amendment 39-6600. Docket No. 90-NM-60-AD. Final copy of Priority Letter AD. Applicability: Model BH.125-600A, HS.125-700A, and BAe 125-800A series airplanes, equipped with a cabin interior and aft lavatory water system installed in accordance with STC SA2271SW, certificated in any category. Compliance: Required prior to further flight, unless previously accomplished. To prevent loss of aileron control, accomplish the following: A. Drain all water from the aft lavatory water system reservoir, deactivate the water system pressure pump by pulling the circuit breaker located beneath the vanity in the aft lavatory, and install a tie wrap on the circuit breaker to prevent it from being reset. B. 1. The aft lavatory water system pressure pump may be reactivated upon accomplishment of a modification which has been approved by the Manager, Special Programs Office, ASW-190, FAA, Southwest Region. 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, Special Programs Office, ASW-190, FAA, Southwest Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Special Programs Office, ASW-190. 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. This amendment (39-6600, AD 90-08-07) becomes effective on May 29, 1990, as to all persons, except those persons to whom it was made immediately effective by priority letter AD 90-08-07, issued April 10, 1990, which contained this amendment.
90-03-04: 90-03-04 GARRETT ENGINE DIVISION, (hereinafter called "GARRETT") ALLIED SIGNAL INCORPORATED: Amendment 39-6419. Applicability: Models TFE731-3, -3A, -3AR, and -3R turbofan engines equipped with high pressure turbine rotor (HPTR) discs, part numbers 3072316-2, -3, and 3073110-1, -2. Compliance: Required as indicated, unless already accomplished. To prevent an uncontained engine failure, accomplish the following: (a) Remove and replace with a serviceable part, specific serial number HPTR discs, in accordance with the accomplishment instructions in Garrett Alert Service Bulletin TFE731-A72-3388, dated February 28, 1989, at next access to the turbine rotor assembly or within 150 operating cycles after the effective date of this AD or prior to June 1, 1990, whichever occurs first. NOTES: (1) For the purpose of this AD, access to the turbine rotor assembly is defined as whenever the N1 turbine module is separated from the engine. (2) Discs inspected by Garrett as noted in Garrett Alert Service Bulletin TFE731-A72- 3388, dated February 28, 1989, and determined to be airworthy may be returned to service. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate means of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Los Angeles Aircraft Certification Office, Federal Aviation Administration, Transport Airplane Directorate, Aircraft Certification Service, 3229 East Spring Street, Long Beach, California 90806-2425. This amendment (39-6419, AD 90-03-04) becomes effective on February 22, 1990.
90-09-01: 90-09-01 MCDONNELL DOUGLAS: Amendment 39-6580. Docket No. 89-NM-239-AD. \n\n\tApplicability: McDonnell Douglas Model DC-9-81, -82, -83, and -87 series and Model MD-88 airplanes, Fuselage Numbers 909 through 1619, certificated in any category. \n\n\tCompliance: Required within 12 months after the effective date of this airworthiness directive (AD), unless previously accomplished. \n\n\tTo eliminate a potential fire ignition source from the generator power feeder cable installations, accomplish the following: \n\n\tA.\tVisually inspect all generator power feeder cable installations at the firewall receptacles for evidence of arcing, burning, or chafing. If damage is found, prior to further flight, replace the damaged feeder cable. \n\n\tB.\tModify each generator power feeder firewall connector installation in accordance with the Accomplishment Instructions of McDonnell Douglas MD-80 Alert Service Bulletin A24-113, dated October 30, 1989. \n\n\tC.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Avionics Inspector (PAI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Business Unit Manager, Technical Publications, C1-HCW (54-60). This document may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6580, AD 90-09-01) becomes effective on May 29, 1990.
90-07-10 R1: 90-07-10 R1 CESSNA CITATION: Amendment 39-6599. Final copy of, and revision to, priority letter. Docket No. 90-NM-54-AD. Applicability: Model 550, 551, and S550 series airplanes, equipped with STC SA2698SW Freon Air Conditioners installed in the aft section of the baggage compartment, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the elevator or rudder control cables, accomplish the following: A. Prior to further flight, deactivate the air conditioning system by pulling the air conditioner supply breakers on the main junction box and install tie wraps on the breakers. B. Within the next 10 hours time-in-service, perform a visual inspection of the elevator control cables under and in the vicinity of the aft baggage compartment floor for evidence of damage caused by electrical arcing and interference. 1. Replace any damaged cable prior to further flight. 2. If fasteners used to secure the compressor condenser unit mounting rails to the baggage floor interfere with the control cables, replace mounting hardware, prior to further flight, in accordance with Keith Service Bulletin No. 108, dated March 26, 1990. C. Prior to reactivating the air conditioning system, replace mounting hardware on the inboard mounting rail and replace existing ground wire, in accordance with Keith Service Bulletin No. 108, dated March 26, 1990. D. 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, Special Programs Office, ASW-190, FAA, Southwest Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Special Programs Office, ASW-190. E. 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 Keith Products, Inc., 4554 Claire Chennault, Dallas, Texas 75248. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, Southwest Region, Special Programs Office, 4400 Blue Mound Road, Fort Worth, Texas. Portions of this amendment were effective earlier to all recipients of Priority Letter AD 90-07-10, dated March 29, 1990. Airworthiness Directive 90-07-10 R1 supersedes Priority Letter AD 90-07-10, issued on March 29, 1990. Amendment 39-6599, AD 90-07-10 R1 became effective on May 29, 1990.
76-12-05: 76-12-05 AVCO LYCOMING: Amendment 39-2635. Applies to all Avco Lycoming T5508D model engines equipped with P/N 2-160-147-02 retaining plate spacers and P/N 2-161-182-01 compressor air bleed bands. Compliance required as indicated. To prevent partial power loss due to failure of the compressor air bleed band while the engine is operating at a power level which requires the bleed band to be closed, perform the following: (a) Prior to the first flight of each day, conduct an inspection of the compressor air bleed band for edge wear and cracks, and repair or replace as necessary in accordance with the instructions in Avco Lycoming Service Bulletin, Product Support No. 5508-0003, dated November 30, 1975, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (b) Prior to July 1, 1976, replace P/N 2-160-147-02 retaining plate spacers with P/N 2-160-561-01 retainers and replace P/N 2-161-182-01 compressor air bleed band with P/N 2-161-182-03 compressor air bleed band, in accordance with the instructions in Avco Lycoming Service Bulletin, Product Support No. 5508-0007, dated April 30, 1976, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. (c) Equivalent methods of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. The manufacturer's Service Bulletins 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 Avco Lycoming Engine Group, Stratford Division, 550 South Main Street, Stratford, Connecticut 06497. These documents may also be examined at the Office of the Regional Counsel, New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. This amendment becomes effective June 23, 1976.
89-23-16: 89-23-16 CASA: Amendment 39-6391. Docket No. 89-NM-122-AD. Applicability: All Model C-212 series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent, following an engine failure on takeoff, damage to or failure of the remaining engine caused by overtorquing, accomplish the following: A. Modify the Automatic Power Reserve (APR) system in accordance with CASA Service Bulletin 212-72-05, Revision 1, dated June 1, 1989. B. Upon accomplishment of the modification required by paragraph A., above, revise the FAA-approved Airplane Flight Manual to include the appropriate revision, which provides new procedures for setting power, as specified in Paragraph 1.B. of CASA Service Bulletin 212-72-05, Revision 1, dated June 1, 1989. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be usedwhen approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. 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 Construcciones Aeronauticas, S.A. (CASA), Getafe, Madrid, Spain. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6391, AD 89-23-16) becomes effective on December12, 1989.
89-24-01 R1: 89-24-01 R1 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-6358 as revised by Amendment 39-6645. Docket No. 89-ANE-11. Applicability: TCM engines, Models TSIO-520B, BB, D, DB, E, EB, J, JB, K, KB, N, NB, UB, and VB equipped with scavenge oil pump gears, part numbers (P/N's) 635334, 639388, 649157, and 649159 except those engines equipped with starter adapter P/N's 642085A4 or 642085A5, those engines with serial numbers as shown in the Appendix of this AD, or those engines equipped with any starter adapter with a pulley for an air conditioner compressor drive, certificated in any category. NOTE: "Appendix" refers to TCM Service Bulletin M90-6 which is not reprinted in this AD. Compliance: Required within 500 flight hours after the effective date of this AD, or at the next maintenance event, after the effective date of this AD, during which the scavenge oil pump gears are removed from the engine, whichever occurs first, unless already accomplished. To prevent possible failure of scavenge oil pump gears which could result in total loss of engine power, accomplish the following: (a) Remove the scavenge oil pump gears from the scavenge oil pump housing and inspect the gear teeth for a drill point as shown in Figure 1 of the Appendix to this AD. (1) If the drill point is present, inspect the gears in accordance with the procedures outlined in the Appendix to this AD. (2) If the drill point is not present, a Rockwell hardness test may be conducted on the gear. If a Rockwell "A" value of 79 or greater or a Rockwell "C" value of 56 or greater is obtained, inspect the gear in accordance with the procedures outlined in the Appendix to this AD. (3) If the gears fail the inspection specified in (1) or (2) above, replace the gears with serviceable P/N 649157 or P/N 649159 gears having the drill point marking. NOTE: TCM SB M90-6 contains information relating to the requirements of this AD. (b) Make an appropriate log book entry showing compliance with this AD. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance (schedule) times specified in this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. All persons affected by this AD who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601. This information may be examined at the FAA, Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New EnglandRegion, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803. This AD revises Amendment 39-6358, AD 89-24-01. This amendment (39-6645, AD 89-24-01 R1) becomes effective on August 10, 1990.
98-03-05: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes. This action requires removal of three electric motor-driven hydraulic pumps (EHP) and associated wiring, and installation of placards in the flight deck. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent operation of the EHP, which could result in fire in the wheel well area, and consequent damage to airplane structure or injury to airplane occupants.
91-01-03: 91-01-03 PRATT & WHITNEY CANADA: Amendment 39-6843. Docket No. 90-ANE-38-AD. Applicability: Pratt & Whitney Canada (PWC) PW118, PW118A, PW120, PW120A, PW121, and JT15D- 5 model engines, installed on, but not limited to, DeHavilland of Canada DHC-8 Series 100, Embraer EMB120, Aerospatiale ATR-42, Beech Beechjet, Cessna T47A, and Siai-Marchetti S211 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent a fire hazard in the engine nacelle, accomplish the following: (a) For engines equipped with Hamilton-Standard Model JFC118 hydromechanical fuel control units (HMU) identified in Table I of this AD, excluding HMU's marked "MS090-001", perform the following: (1) Perform an HMU leak check inspection in accordance with the applicable Accomplishment Instructions of Appendix I of this AD, within the next 15 hours time in service after the effective date of this AD. (2) Thereafter, reinspect the HMU for leakage in accordance with the applicable Accomplishment Instructions of Appendix I at intervals not to exceed 15 hours time in service since last inspection. (3) Remove from service, prior to further flight, HMU's exhibiting fuel leakage when inspected in accordance with (a)(1) or (a)(2) above. (4) X-ray or disassemble inspect the HMU for correct assembly in accordance with the Accomplishment Instructions of the applicable Hamilton-Standard (HS) service bulletin (SB) listed in Table I of this AD, at the next engine shop visit or HMU removal, or by June 30, 1991, whichever occurs first. (5) Remove from service, prior to further flight, HMU's confirmed incorrectly assembled when inspected in accordance with (a)(4) above. (6) For HMU's determined to be correctly assembled when inspected in accordance with (a)(4) above, the repetitive inspections of (a)(1) or (a)(2) above are no longer required. Table I HMU Model/P/N(s) JFC118-10/786390-3 HS SB JFC118-10-73-14, Revision 1 (Oct. 26, 1990) JFC118-11/786391-3 and 786391-5 JFC118-11-73-15, Revision 1 (Oct. 26, 1990) JFC118-12/786392-4 and 786392-6 JFC118-12-73-16, Revision 1(Oct. 26, 1990) JFC118-30/787230-1 JFC118-30-73-15, Revision 1 (Oct 26, 1990) JFC118-31/776660-3 and 790155-1 JFC118-31-73-14, Revision 1 (Oct. 26, 1990) (b) For the purpose of this AD, shop visit is defined as the induction of an engine into a shop for the conduct of maintenance. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts01803. The x-ray and disassembly inspection shall be done in accordance with the following HS documents: Document Page Revision Date HS SB JFC118-10-73-14 All 1 Oct. 26, 1990 HS SB JFC118-11-73-15 All 1 Oct. 26, 1990 HS SB JFC118-12-73-16 All 1 Oct. 26, 1990 HS SB JFC118-30-73-15 All 1 Oct. 26, 1990 HS SB JFC118-31-73-14 All 1 Oct. 26, 1990 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 the United Technologies Corporation, Hamilton-Standard Division, Technical Publications Department, One Hamilton Road, Windsor Locks, Connecticut 06096-1010. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. 20591. This amendment (39-6843, AD 91-01-03) becomes effective on January 07, 1991. APPENDIX I PART A: PW100 SERIES A. References: - Models PW118 (BS698)/PW118A (BS718): Maintenance Manual P/N 3034622. - Models PW120 (BS633/BS716) and PW121 (BS722/BS725): Maintenance Manual P/N 3034642. - Models PW120A (BS632) and PW121 (BS717): Maintenance Manual P/N 3034632. B. Accomplishment Instructions: Perform the following HMU leak check inspection. 1.) Perform a fuel system leak test in accordance with the applicable maintenance manual, or visually inspect the HMU for external fuel leaks within 30 minutes of shutdown. 2.) Ensure there is no fuel leakage at the HMU electrical connector area. 3.) If any fuel leak is observed, remove the HMU from service. 4.) Annotate engine log to include this AD inspection. NOTE: Information concerning this inspection can be found in Pratt & Whitney Canada (PWC) Service Bulletin (SB) No. 20951. PART B: JT15D SERIES A. References: -Model JT15D-5: Maintenance Manual P/N 3033442 B. Accomplishment Instructions: Perform the following HMU leak check inspection. 1.) Perform a fuel system leak test in accordance with the applicable maintenance manual, or visually inspect the HMU for external fuel leaks within 30 minutes of shutdown. 2.) Ensure there is no fuel leakage at the HMU electrical connector area. 3.) If any fuel leak is observed, remove the HMU from service. 4.) Annotate engine log to include this AD inspection. NOTE: Information concerning this inspection can be found in PWC SB No. A-7295.
76-20-06: 76-20-06 HILLER AVIATION: Amendment 39-2740. Applies to Model UH-12D and UH-12E Helicopters which have been converted to turbine power in accordance with Soloy Conversions, Limited, STC Nos. SH177WE and SH178WE respectively certificated in all categories. Compliance required as indicated. To prevent loss of helicopter control due to freezing of the governor cable, throttle cable, and/or anti-ice cable accomplish the following: (A) Within 15 days time in service after the receipt of this telegraphic AD, install a placard in view of the pilot which states: "Flight in outside air temperature of 32 degrees F. or lower is prohibited." (B) Within 60 days time in service after the receipt of this telegraphic AD, perform the modifications contained in Soloy Conversions, Ltd., Service Bulletin 01-560 dated September 3, 1976, or later FAA approved revisions. (C) The operation restriction prescribed in (A) above may be discontinued and the placard may be removed when the control cable modifications required by (B) above have been completed. (D) Equivalent procedures may be approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, upon the submission of adequate substantiating data. 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 Soloy Conversions, Limited, P. O. Box 60, Chehalis, Washington 98532. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated September 8, 1976.
78-13-02: 78-13-02 BRITISH AEROSPACE: Amendment 39-3245. Applies to Hawker Siddeley Model BH/HS-125 Series 600A and 700A airplanes, certificated in all categories, that have either the RCA AVQ21 or Primus 40 weather radar systems installed. Compliance required as indicated. To prevent failure of the restraint provisions for the weather radar receiver/transmitter, accomplish the following: (a) Within 10 hours time in service after the effective date of this AD, unless already accomplished within the last 40 hours time in service, and thereafter at intervals not to exceed 50 hours time in service from the last inspection, inspect the support brackets for cracks and the "T" bolts for failure of the brazing in accordance with section 2, "Accomplishment Instructions" of British Aerospace Alert Service Bulletin 34-A134, dated April 1, 1978, or an FAA approved equivalent. (b) If a crack in a support bracket or a failure of the brazing of the "T" bolt is found during an inspection required by paragraph (a) of this AD, before further flight, except that the airplane may be flown in accordance with FAR 21.197 and 21.199 to a base where the replacement can be accomplished, replace the mounting tray with a serviceable part of the same part number, or repair the existing mounting tray in accordance with an FAA approved repair scheme and continue to inspect in accordance with paragraph (a) of this AD, or replace the mounting tray in accordance with paragraph (c) of this AD. (c) The inspections required by this AD may be discontinued upon replacement of the mounting tray with an improved standard tray, P/N 1719353-501 (Rev. E), in accordance with British Aerospace Modification 258171 or an FAA approved equivalent. This amendment becomes effective July 5, 1978.
89-25-10: 89-25-10 BEECH: Amendment 39-6409. Applicability: Models 65-90 and 65-A90 (Serial Number (S/N) LJ-1 thru LJ-317); 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90 (all S/N); C90A (S/N LJ-1063 thru LJ-1087, except LJ-1085); E90, 100, A100 and B100 (all S/N) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To detect possible fatigue cracking of the wing main spar lower cap and associated structure, accomplish the following: (a) Within the next 200 hours time-in-service (TIS), after the effective date of this AD, or upon accumulating 3000 hours TIS, whichever occurs later, unless previously accomplished per AD 87-23-09, Amendment No. 39-5765, or AD 70-25-04, Amendment No. 39-1332, and thereafter at intervals not to exceed 1000 hours TIS (except as provided in paragraph (b) below) after the initial inspection, inspect the wing lower forward spar attach fittings, center sectionand outboard wing spar caps adjacent to the attach fittings by visual, fluorescent penetrant and eddy current methods as specified in the applicable section of Beech Structural Inspection and Repair Manual (SIRM), Part Number 98-39006, Revision A4, dated May 1, 1987. The inspection must be performed by personnel specifically trained by Beech Aircraft Corporation. NOTE 1: Beech offers a two-day training course free of charge to qualified personnel who have prior knowledge of eddy current inspection techniques. A listing of Beech Corporate maintenance facilities may be obtained from the sources contained in paragraph (g) of this AD. A listing of other facilities employing qualified inspectors is not available. (b) At each inspection required by paragraph (a) above, inspect any reinforcing strap installed per Supplemental Type Certificate (STC) SA1178CE or SA1583CE for proper tension and condition in accordance with Aviadesign Engineering Order E.O. B-8001, Issue 3, dated May30, 1985. Correct any discrepancy prior to further flight. For airplanes so equipped and inspected, the repetitive inspection interval of 1000 hours TIS in paragraph (a) above may be extended to 3000 hours TIS. (c) If any crack is found in a main spar lower cap or fitting, prior to further flight repair or replace the defective part using the instructions and limitations specified in the Beech SIRM or other FAA approved instructions provided by Beech Aircraft Corporation. (d) Within one week after completion of any inspection required by paragraph (a) or (b) of this AD, complete the reporting form included with this AD as Figure 1 and mail it to the address shown thereon (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056). (e) The initial and repetitive inspections specified in this AD are no longer required when the airplane is modified by Beech Wing Modification Kit No. 90-4077-1S or 100-4007-1S. (f) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (g) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085; or Western Aircraft Maintenance, 4444 Aeronca Street, Boise, Idaho 83705, or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. ThisAD supersedes AD 87-23-09, Amendment 39-5765, and AD 70-25-04, Amendment 39-1332. This amendment (39-6409, AD 89-25-10) becomes effective on January 4, 1990. REPORTING FORM - 89-25-10 Airplane Model No. ___________________________________________________ Airplane Serial No.____________________________________________________ Date of inspection per this AD____________________________________________ Airframe total hours time-in-service________________________________________ Were any fatigue cracks found? No Yes __ If "Yes" was checked above, complete the following: Location of crack_____________________________________________________ Was crack removable by reaming or grinding? No Yes __ Additional Comments __________________________________________________ Mailing Address: FAA, Wichita ACO Airframe Branch, Room 100 1801 Airport Road Wichita, KS 67209 FIGURE 1 - 89-25-10
76-07-04: 76-07-04 HAWKER SIDDELEY AVIATION LTD: Amendment 39-2563. Applies to de Havilland Model DH-114 "Heron" airplanes certificated in all categories which have not been altered in accordance with Heron Modification 1612. Compliance is required as indicated. To detect cracks in the nose landing gear inner casing, and prevent the possible collapse of the nose landing gear upon landing, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter, at intervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casing for cracks in accordance with paragraphs 3.1 and 3.2 of section 3 entitled "Inspection" of Hawker Siddeley Aviation Ltd., Technical News Sheet No. U.17, Issue 1, dated September 17, 1973, or an FAA-approved equivalent. (b) If any cracks are found during an inspection required by paragraph (a) of this AD, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (a) of this AD. Continue to inspect the replacement casing for cracks in accordance with Hawker Siddeley Aviation Ltd., Technical News Sheet, No. U.17, Issue 1, dated September 17, 1973, or an FAA-approved equivalent at intervals not to exceed 600 hours time in service from replacement. This amendment becomes effective April 12, 1976.
77-14-04: 77-14-04 HAWKER SIDDELEY AVIATION, LTD.: Amendment 39-2952. Applies to DH-104 "Dove" and DH-114 "Heron" airplanes. Compliance is required within the next 500 hours time in service after the effective date of this AD unless already accomplished. To prevent the possibility that a loss of generated electrical power would be undetected by the flight crew, accomplish the following: (a) Alter the electrical system to incorporate a bus bar low voltage sensing unit, a bus bar low voltage warning light, and an essential service switch, designed and installed in accordance with paragraphs 5 and 6 of Hawker Siddeley Aviation, Ltd., Technical News Sheet, Series: Heron (114), No. N. 6., Issue 3 (for DH-114 "Heron") and CT104, No. 227, Issue 3 (for DH-104 "Dove"), both dated July 3, 1972, as amended to November 20, 1972, or FAA-approved equivalent of either. (b) Amend the "Normal and Emergency Procedures", Part B, of the "Operating Procedures" section, Section II, of the applicable Airplane Flight Manual by adding the electrical system operation information contained in paragraphs 7 and 8 and Figure 1 of the applicable Technical News Sheet, referred to in paragraph (a) of this AD, or an FAA-approved equivalent. (c) Check the condition of the electrical distribution and generator system in accordance with paragraph 6 of the applicable Technical News Sheet, referred to in paragraph (a) of this AD, or an FAA-approved equivalent, and repair, as necessary. The checks required by this paragraph may be performed by persons authorized to perform preventive maintenance under FAR 43. This amendment becomes effective August 5, 1977.
78-03-05: 78-03-05 MITSUBISHI HEAVY INDUSTRIES, LTD: Amendment 39-3137. Applies to models MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25 and MU-2B-26 airplanes with serial numbers up through and including 347 except 313 and 321 and models MU-2B-30, MU-2B-35, and MU-2B-36 airplanes with serial numbers up through and including 696 except 652 and 661. NOTE: This AD is not applicable to MU-2B series airplanes having serial numbers with the suffix "SA." Compliance is required as indicated. To prevent failure of the cowling latches between the engine nacelle upper door and side doors, subsequent separation of the upper cowling panel, and possible loss of control of the airplane, accomplish the following: Within the next 25 hours time in service after the effective date of this AD, unless already accomplished, replace the cowling latch links between the engine nacelle upper door and side doors in accordance with the instructions contained in Mitsubishi MU-2 Service Bulletin No. 171A datedJuly 14, 1975, as supplemented by Mitsubishi MU-2 Service Bulletin No. 180 dated August 26, 1977, or Mitsubishi Service Bulletin No. 180A dated November 17, 1977, or an FAA- approved equivalent, approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii. This supersedes amendment 39-2695, (41 FR 34009), AD 76-16-05. This amendment becomes effective February 23, 1978.
76-18-12: 76-18-12 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2721. Applies to Model G-1159 airplanes certificated in all categories, serial numbers 1 through 154 and 775. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To detect loose terminal connections at the generator terminal boards and to prevent the loosening of these connections, accomplish the following: 1. Modify each engine electrical junction box to provide an access hole for inspecting the two generator terminal boards and the eight associated wiring connections. Grumman American Aircraft Service Change No. 203 Amendments 1 and 2 provide the information for accomplishing this modification. 2. If the inspection reveals that all generator terminals are secure, i.e., that all lock washers are compressed and torque stripes not broken, the connections are satisfactory. 3. Reinspect in accordance with A.S.C. No. 203 Amendments 1 and 2 in intervals of 300 hours time in service until the basic A.S.C. No. 203 has been accomplished. 4. If the lock washer on any terminal is found not to be compressed, or evidence of arcing at any connection is noted, the affected engine shall be removed and the basic A.S.C. No. 203 accomplished to the corresponding engine junction box. 5. The reinspection procedure must continue for the remaining engine junction box until the basic A.S.C. No. 203 has been accomplished. This service change requires the removal of a plain nut, a plain washer, and lockwasher from each generator terminal, and replacing them with a self-locking nut and a plain washer. 6. Compliance with the basic A.S.C. No. 203 must be accomplished at the next engine removal, if not done prior to that time. This Airworthiness Directive may be accomplished by any other means approved by the Chief, Engineering and Manufacturing Branch of the Southern Region, Atlanta, Georgia. This amendmentbecomes effective September 22, 1976.
77-14-01: 77-14-01 AGUSTA: Amendment 39-2949. Applies to Model A-109A helicopters equipped with main rotor hub flap hinge bearings P/N SJ7355/IR7355. Compliance is required as indicated, unless already accomplished. To prevent possible improper operation of the main rotor flaps due to premature failure of any one of the main rotor hub flap hinge bearings, accomplish the following: (a) For helicopters with serial numbers up to and including S/N 7120, except S/N 7119 - (1) Within the next 10 hours time in service after the effective date of this AD, replace the main rotor hub flap hinge bearings P/N SJ7355/IR7355 in accordance with Part I of Agusta Technical Bulletin No. 109-3, dated May 4, 1977, or an FAA-approved equivalent; and (2) Within 100 hours time in service after complying with paragraph (a)(1) of this AD, and thereafter at intervals not to exceed 100 hours time in service, or any time abnormal oil leaks occur from flap hinges, perform inspections and replace bearings, as necessary, in accordance with Part II of Agusta Technical Bulletin No. 109-3, dated May 4, 1977, or an FAA-approved equivalent. (b) For helicopters with serial numbers S/N 7119, S/N 7121 and up, within the next 25 hours time in service after the effective date of this AD, except for those which have been inspected within the previous 75 hours, and thereafter at intervals not to exceed 100 hours time in service or any time abnormal oil leaks occur from flap hinges, perform inspections and replace bearings, as necessary, in accordance with Part II of Agusta Technical Bulletin No. 109-3, dated May 4, 1977, or an FAA-approved equivalent. (c) Equivalent methods of complying with this AD must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. This amendment becomes effective July 15, 1977.
76-16-01: 76-16-01 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-2683. Applies to the following groups of Model TPE331 series engines: Group A: TPE331-1-101B, S/N 93058 through 93061; TPE331-1-151A, S/N 92249 and 92336 through 92354; TPE331-1-151K, S/N 26001 through 26014; TPE331-1-151G, S/N 91193 through 91198; TPE331- 2-201A, S/N 90218 through 90278, TPE331-3U-303G or TPE331-3UW-303G, S/N 03108, 03109, and 03112 through 03180 and 05031 through 05042; TPE331-3U-307G, S/N 03001 and 03009; TPE331-5-251C, S/N 22006 through 22057; TPE331-5-251K, S/N 06113, 06190 through 06442 and 06444 through 06454; TPE331-6-251M or TPE3310-6-252M, S/N 20144 and 20182 through 20467 and 20469 through 20533; TPE331-6-252B, S/N 27001 and 27002, and any Model TPE331-1, -2, -3, -5, or -6 engines which have been modified in accordance with AiResearch Service Bulletin TPE331-72-0064 dated February 1, 1974 or subsequent revisions. Group B: TPE331-1-101B, S/N 93062, 93063; TPE331-1-151A, S/N 92355 through 92357; TPE331- 1-151K, S/N 26015 through 26023; TPE331-2-201A, S/N 90279 through 90296; TPE331-3U-303G or TPE331-3UW-303G, S/N 03181 through 03197, 05043 through 05052; TPE-5-251C, S/N 22058 through 22119; TPE331-5-251K, S/N 06443, 06455 through 06556; TPE331-6-251M or TPE331-6-252M, S/N 20534 through 20577. Group C: TPE331-1-101F, S/N 98017 through 98019; TPE331-1-151K, S/N 91194 and 91195; TPE331-2- 201A, S/N 90297 through 90303; TPE331-3U-303G or TPE331-3UW-303G, S/N 05053 through 05058, S/N 05016, S/N 03001, S/N 03010, S/N 03011, and S/N 03198 through 03205; TPE331-5-251K, S/N 06557 through 06576; TPE331-5-251C, S/N 22120 through 22139, TPE331-5-251M, S/N 28001 through 28005; TPE331-6-251M, S/N 20468, S/N 20017, and S/N 20018; TPE331-6-252B, S/N 27003 and S/N 27004, and any Model TPE331-1, -2, -3, -5, or -6 engines which have been modified in accordance with AiResearch Service Bulletin TPE331-72-0064, dated February 1, 1974, or subsequent revisions. NOTE: Operators of airplanes incorporating the engines affected by this airworthiness directive are advised to examine the applicability section, Configuration Identification, Table 1, or AiResearch Service Bulletin TPE331-72-0092, Revision 5, dated June 8, 1976, or later FAA-approved revision, to identify the extent of work required by this airworthiness directive which may have been previously performed. Compliance required as indicated. To detect and prevent fatigue failures of the high speed pinion (HSP) bearing oil transfer tube, supply tube, and lubricating adapter, and to detect, correct, and prevent loosening of the HSP bearing carrier bolts, accomplish the following: (a) For engines in Group A, above, within the next 100 hours time in service after December 30, 1974 (the effective date of Amendment 39-2054, AD 74-26-11), unless already accomplished, accomplish the following in accordance with AiResearch Service Bulletin TPE331-72-0092, dated December 9, 1974, or later FAA-approved revision: (1) Replace the two high speed pinion bearing carrier bolts, P/N MS21279-07, with two bolts, P/N MS9489-07, and lockplate, P/N 3101483-1, (2) Inspect to insure proper torque on bolt, P/N MS21279-10, securing lube nozzle, P/N 3101209, and (3) If aluminum lube adapter, P/N 3101210, is not replaced as described in paragraph (d) of this directive, inspect to insure proper torque on bolt, P/N MS21297-07, securing this lube adapter. (b) For engines in Group A and Group B, above, which incorporate the oil transfer tube, P/N 3101187-1, within the next 100 hours time in service after December 30, 1974, unless already accomplished within the last 100 hours time in service prior to December 30, 1974, and thereafter at intervals not to exceed 200 hours time in service from last inspection, until the modifications of paragraph (c) are accomplished, accomplish the following in accordance with AiResearch Service Bulletin TPE331-72-0092, dated December 9, 1974, or later FAA-approved revision: (1) Inspect the integral support bracket on oil transfer tube, P/N 3101187-1, for cracks or separation, and (2) If the oil transfer tube bracket is cracked or separated, before further flight, replace both the oil transfer tube and oil supply tube with new tubes, oil transfer tube, P/N 3101475-1, and oil supply tube, P/N's 3101473-1 or 3101473-2, and associated hardware. (c) For engines in Group A and Group B, above, which incorporate the oil transfer tube, P/N 3101187-1, before accumulating a total of 1800 hours time in service after December 30, 1974, unless already accomplished, replace the oil transfer tube, P/N 3101187-1, with one of the following serviceable oil transfer tubes in accordance with AiResearch Service Bulletin TPE331-72-0092, Revision 1, dated, January 1, 1975, or later FAA-approved revision: (1) P/N 3101187-2 which has been heat-treated and reidentified as P/N 3101187-3, (2) P/N 3101187-3, or (3) P/N3101475-1 (d) For engines in Group A, Group B, and Group C, above, within the next 200 hours time in service after the effective date of this AD, unless already accomplished, accomplish the following in accordance with AiResearch Service Bulletin TPE331-72-0092, Revision 5, dated June 8, 1976, or later FAA-approved revision: (1) Replace the aluminum main journal bearing lubricating adapter, P/N's 3101210-1 or 3101210- 2, with a new steel lubricating adapter, P/N's 3101474-1 or 3101474-2, and (2) If two carrier bolts, P/N MS9489-07, and lockplate, P/N 3101483-1, are not replaced, inspect these carrier bolts manually for any indication of looseness. If loose bolts are found, before further flight install a new lockplate, P/N 3101483-1, and retorque the two carrier bolts, P/N MS9489-07 (e) Equivalent procedures, inspections, modifications, or parts may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Aircraft may be flown to a base for accomplishment of inspections and modifications required by this AD per FAR's 21.197 and 21.199. This supersedes Amendment 39-2054 (39 F.R. 4439), AD 74-26-11, as amended by Amendments 39-2092 (40 F.R. 6771), 39-2214 (40 F.R. 22126), 39-2254 (40 F.R. 28605), 39-2367 (40 F.R. 42740), and 39-2382 (40 F.R. 48499). This amendment becomes effective August 6, 1976.