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92-07-12: 92-07-12 BOEING: Amendment 39-8208. Docket No. 91-NM-164-AD.\n\n\tApplicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-25-0137, Revision 1, dated May 9, 1991, certificated in any category.\n\n\tCompliance: Required within the next 18 months after the effective date of this AD, unless accomplished previously.\n\n\tTo ensure proper deployment of the off-wing escape system, accomplish the following:\n\n\t(a) Modify the off-wing escape system in accordance with Boeing Service Bulletin 767-25-0137, Revision 1, dated May 9, 1991.\n\n\t(b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(c) Special flight permits maybe 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.\n\n\t(d) The modification shall be done in accordance with Boeing Service Bulletin 767-25-0137, Revision 1, dated May 9, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(e) This amendment becomes effective on May 4, 1992.
94-08-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model ATP series airplanes, that requires modification of the wiring for the electric-powered disconnect unit for the elevator control system and a subsequent functional test of the elevator control system. This amendment is prompted by an in-service report of damaged wire insulation in the electrical power circuit for the elevator disconnect unit, which resulted in grounding of the circuit and consequent uncommanded operation of the disconnect unit. The actions specified by this AD are intended to prevent uncommanded operation of the elevator disconnect unit, which would result in single elevator operation and, consequently, reduced controllability of the airplane.
78-22-05: 78-22-05 BEECH: Amendment 39-3329. Applies to the following models and serial number airplanes, certificated in all categories: \n\n\nMODEL\nSERIAL NUMBERS\n50\nH-1 through H-11\nB50, C50\nCH-12 through CH-360\nD50, D50A, D50B, D50C and D50E\nDH-1 through DH-347 \nE50\nEH-1 through EH-70\nF50\nFH-71 through FH-93, FH-95, FH-96\nG50\nGH-94, GH-97 through GH-119\nH50\nHH-120 through HH-149\nJ50\nJH-150 through JH-176\n65, A65, A65-8200\nL-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335\n70\nLB-1 through LB-35\n65-80, 65-A80, 65-A80-8800, 65-B80\nLD-1 through LD-511 \n65-88\nLP-1 through LP-28, LP-30 through LP-47\n65-90, 65-A90, B90, C90\nLJ-1 through LJ-797 \nE90\nLW-1 through LW-297\n99, 99A, A99A, B99\nU-1 through U-164\n100, A100\nB-1 through B-247 \nB100\nBE-1 through BE-55\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent partial loss of elevator control due to possible failure of elevator control push rods, in accordance with instructions set forth herein and in Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions, accomplish the following: \n\n\tA)\tOn the following airplanes: \n\n\nMODEL\nSERIAL NUMBERS\n50\nH-1 through H-11\nB50, C50\nCH-12 through CH-360 \nD50, D50A, D50B, D50C and D50E\nDH-1 through DH-347 \nE50\nEH-1 through EH-70\nF50\nFH-71 through FH-93, FH-95, FH-96\nG50\nGH-94, GH-97 through GH-119\nH50\nHH-120 through HH-149\nJ50\nJH-150 through JH-176\n65, A65, A65-8200\nL-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335\n70\nLB-1 through LB-35\n65-80, 65-A80, 65-A80-8800 and 65-B80\nLD-1 through LD-511 \n65-88\nLP-1 through LP-28 and LP-30 through LP-47\n65-90, 65-A90, B90 and C90\nLJ-1 through LJ-716 \nE90\nLW-1 through LW-222\n99, 99A, A99A and B99\nU-1 through U-164\n100, A100\nB-1 through B-233\nB100\nBE-1 through BE-23\n\n\tUpon the accumulation of 1,050 hours total time-in-service for airplanes with less than 1,000 hours total time-in-service on the effective date of this AD,or \n\n\tWithin 50 hours time-in-service after the effective date of this AD, for airplanes with more than 1,000 hours total time-in-service on the effective date of this AD, that have not complied with AD 70-18-02, or \n\n\tWithin 500 hours time-in-service after the last inspection in accordance with AD 70-18- 02, for airplanes with more than 1,000 hours total time-in-service that have complied with AD 70-18-02: \n\n\t\t1.\tReview the airplane maintenance records for entries showing that Beechcraft Service Instructions No. 0334-152, Revision II, has been complied with. If Revision II of the Service Instructions has not been complied with, accomplish Paragraph A)2 of this AD. If Revision II of the Service Instructions has been complied with, accomplish Paragraph A)3 of this AD within an additional 100 hours time-in-service after this finding. \n\n\t\t2.\tGain access to the elevator control push rods (reference Figures I and II of this AD) and visually inspect for the words "CORROSION PROOFED"ink stamped near the center of the rods. If the words "CORROSION PROOFED" are ink stamped on a rod, no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on the rods, remove the elevator control push rods, clean, dye penetrant and visually inspect, check for bows, apply corrosion preventative treatment, identify and reinstall, all in accordance with Part I of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\t\t3.\tGain access to the elevator control push rods (reference Figures I and II of this AD) and visually inspect for the words "CORROSION PROOFED" ink stamped near the center of each rod. If the words "CORROSION PROOFED" are ink stamped on a rod, then no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on any rod and new rods were not installed during compliance with Revision II of the Service Instructions, paint a black stripe around the center of each rod in accordance with Part II of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. If any new rods were installed during compliance with Revision II of the Service Instructions and the new rods are not ink stamped "CORROSION PROOFED", on each new rod so installed, remove the elevator control push rod, disassemble, inspect for corrosion preventative treatment and alignment, and if not found accomplished, apply the corrosion preventative treatment, identify, reassemble and reinstall, all in accordance with Part III of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\tB)\tOn the following airplanes: \n\n\nMODEL\nSERIAL NUMBERS\nC90\nLJ-717 through LJ-797\nE90\nLW-223 through LW-297\nA100\nB-234 through B-247 \nB100\nBE-24 through BE-55\n\n\tWithin 100 hours time-in-service after the effective date of this AD: \n\n\t\t1.\tGain access to the elevator control push rods (reference Figures Iand II of this AD) and visually inspect for the words "CORROSION PROOFED" ink stamped near the center of the rods. If the words "CORROSION PROOFED" are ink stamped on a rod, no further action on that rod is required by this AD. If the words "CORROSION PROOFED" are not ink stamped on the rods, remove the elevator control push rod tubes, disassemble, inspect for corrosion preventative treatment and alignment, and if not found accomplished, apply the corrosion preventative treatment, identify, reassemble and reinstall, all in accordance with Part III of Beechcraft Service Instructions No. 0334-152, Revision III, or later approved revisions. \n\n\tC)\tOn all airplanes affected by this AD, replace any elevator control push rods found cracked or otherwise unserviceable during any inspection required by this AD with serviceable rods that comply with the requirements of this AD prior to returning the airplane to service. \n\n\tD)\tAny equivalent means of compliance with this AD must be approvedby the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis AD supersedes AD 70-18-02, Amendment 39-907 (35 FR 305) as amended by Amendments 39-1074 (35 FR 13722 and 13723) and 39-1879 (39 FR 21120). \n\n\tThis amendment becomes effective November 6, 1978.
76-13-07: 76-13-07 CESSNA: Amendment 39-2656. Applies to Models 401, 402, 411, 414 and 421 Series Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent failure of the fork bolt located at the aft end of the main landing gear retraction system torque tube connecting the torque tube to the outboard push/pull tube, accomplish the following: A) Within 200 hours' time in service on those airplanes having 1,800 or more hours' time in service or prior to 2,000 hours' time in service on those airplanes having less than 1,800 hours' time in service, and at each subsequent 2,000 hours' time in service thereafter, replace right and left 1/2-inch diameter P/Ns 0843518-1, 0843518-2, 0843500-35, 0843500-54, 5243518-1 and 5243518-3 fork bolts with new P/N 5243518-3 or FAA-approved superseding part number fork bolts on the airplanes specified below except airplanes on which P/N 5141052-1 fork bolts have been installed as field replacements: 401 - 401-0001 thru 401B0053 402 - 402-0001 thru 4-2B0035 411 - All Serials 414 - 414-0001 thru 414-0098 421 - 421-0001 thru 421A0158 B) Within 200 hours' time in service on those airplanes having 4,800 or more hours' time in service or prior to 5,000 hours' time in service on those airplanes having less than 4,800 hours' time in service, and at each subsequent 5,000 hours' time in service thereafter, replace right and left 5/8-inch diameter P/N 5141052-1 fork bolts with new P/N 5141052-1 or FAA-approved superseding part number fork bolts on the airplanes specified below or any lower airplane serial numbers on which these fork bolts have been installed as field replacements. 401 - 401B0054 and on 401 - 402B0036 and on 414 - 414-0099 and on 421 - 421B0001 and on C) Fork bolt life limits set by this AD may be extended 25 hours, up to 2,025 hours for 1/2-inch diameter fork bolts and 5,025 hours for 5/8-inch diameter fork bolts, to allow replacement at regular scheduled maintenance or inspections. D) Aircraft may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished. E) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Cessna Service Letter ME75-23 or later approved revisions refers to this subject. This amendment becomes effective July 7, 1976.
77-13-02: 77-13-02 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2926. Applies to Model DH/BH-125 airplanes, all series, certificated in all categories. Compliance is required as indicated. To prevent the failure of the knife edges of the brake control valve, P/N AC. 61520, and the possible complete loss of braking on one side of the airplane with no advance warning to the flight crew, accomplish the following: (a) Comply with paragraph (b) or (c) of this AD as follows, and, thereafter, continue to comply with paragraph (b) or (c) of this AD at intervals not to exceed 4,500 landings since last compliance: (1) For airplanes having brake control valve knife edges that have accumulated less than 4,300 landings on the effective date of this AD, compliance is required prior to the accumulation of 4,500 landings. (2) For airplanes having brake control valve knife edges that have accumulated 4,300 or more landings, but less than 5,900 landings, on the effective date ofthis AD, compliance is required prior to the accumulation of an additional 200 landings. (3) For airplanes having brake control valve knife edges that have accumulated 5,900 or more landings on the effective date of this AD, compliance is required prior to the accumulation of 6,100 landings or an additional 100 landings whichever occurs later. (4) For airplanes for which no records exist that indicate the number of landings the brake control valve knife edges have accumulated, compliance is required prior to the accumulation of 100 landings after the effective date of this AD. (b) Replace the knife edges with new parts, P/Ns ACO. 34629, ACO. 34630, and ACO. 36133, in accordance with Paragraph A, of Section 2, titled "Accomplishment Instructions," of Hawker Siddeley Aviation, Ltd. Service Bulletin 32-166, dated January 27, 1976, or an FAA- approved equivalent. (c) Replace the brake control valve, P/N AC. 61520, with a valve of the same part number that incorporates knife edges having part numbers specified in paragraph (b) of this AD in accordance with Paragraph B, of Section 2, titled "Accomplishment Instructions," of Hawker Siddeley Aviation, Ltd. Service Bulletin 32- 166, dated January 27, 1976, or an FAA-approved equivalent. This amendment becomes effective July 20, 1977.
77-10-12: 77-10-12 MCDONNELL DOUGLAS: Amendment 39-2906. Applies to Model DC-8 Series airplanes, certificated in all categories. \n\n\tCompliance required within the next 300 hours time in service or 30 days after the effective date of this AD, whichever comes first, unless already accomplished within the past 30 days. \n\n\tTo detect cracks and prevent failure or jamming of the elevator geared tab crank arm and gust lock assemblies, comply with the following: \n\n\t(a)\tVisually inspect both the left and right side inboard and outboard elevator geared tab crank arm assemblies, P/N's 4710541 and 4710542 for failure and/or cracks. \n\n\t(b)\tVisually inspect the P/N 5644178 gust lock assembly, and specifically, the torque tube section of the P/N 4644181 crank assembly, for failure and/or cracks. \n\n\t(c)\tFailed or cracked parts must be replaced with like serviceable parts before further flight. \n\n\t(d)\tVerify that clearance exists between the crank assemblies, P/N 4710541 and 4710542, and the boxsection for all positions along elevator travel. \n\n\tNote: McDonnell Douglas DC-8 Alert Service Bulletin A27-262, dated April 28, 1977, covers the same subject. \n\n\t(e)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base to perform the inspections required by this AD. \n\n\tThis amendment becomes effective May 26, 1977.
78-20-03: 78-20-03 HUGHES: Amendment 39-3307 as amended by Amendment 39-3599. Applies to Hughes Model 369D and 369H helicopters which have either the C-500 aerial spray system, STC No. SH184NW or the Chadwick C-500 fire suppression kit, STC No. SH567NW installed. To prevent hydraulic fluid from entering the engine after a seal failure of the Chadwick hydraulic motor, accomplish the following: Within the next 100 hours time in service or 30 days, whichever comes first, after the effective date of this AD, install a drain line on the engine mounting flange, Chadwick P/N 500- 60405-1, in accordance with Chadwick Service Bulletin 500-78-02 dated September 1, 1978, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. To prevent possible fatigue cracking of the helicopter undercarriage, accomplish the following: Within the next 50 hours flying time or six months, whichever comes first, after the effectivedate of this amended AD, install a doubler, P/N 500-60487-1, and grommet, P/N AN931-7-11, in accordance with Chadwick Service Bulletin 500-79-01 dated September 27, 1979, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. 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 Chadwick Inc., 11969 SW Herman Road, Sherwood, Oregon 97140. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. Amendment 39-3307 became effective November 2, 1978. This Amendment 39-3599 becomes effective November 7, 1979.
93-08-08: 93-08-08 DE HAVILLAND, INC.: Amendment 39-8555. Docket 92-NM-144-AD. Applicability: Model DHC-8 series airplanes equipped with microwave landing system (MLS) provisions, as listed in de Havilland Service Bulletin S.B. 8-34-60, Revision 'C,' dated November 1, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the airplane from landing short of the runway, accomplish the following: (a) Prior to installation of an MLS, or within 45 days after the effective date of this AD, whichever occurs later, perform a general visual inspection to determine whether the vertical deviation wiring has been properly installed and/or connected to link the MLS with the ground proximity warning system (GPWS), in accordance with de Havilland Service Bulletin S.B. 8-34-60, Revision 'C,' dated November 1, 1991. (1) If any vertical deviation wiring has been found that has not been properly installed and/or connected to link the MLS with the GPWS, prior to further flight, correct the wiring and perform a functional test of the system in accordance with the service bulletin. (2) If vertical deviation wiring has been found that has been properly installed and/or connected to link the MLS with the GPWS, no further action is necessary. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) 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. (d) The inspection, wiring correction, and functional test shall be done in accordance with de Havilland Service Bulletin S.B. 8-34-60, Revision 'C,' dated November 1, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on May 26, 1993.
94-07-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that requires modification of the fuel crossfeed low level dump system shutoff. This amendment is prompted by an FAA determination that, in the event of a failure of the number 2 bus tie relay and the subsequent loss of the number 2 electrical power source, an all-engine flameout event could occur due to fuel starvation during or shortly after a fuel dumping operation. The actions specified by this AD are intended to prevent loss of the fuel dump system shutoff due to a failure of the number 2 DC bus electrical relay and the subsequent loss of the number 2 electrical power source.
91-17-01: 91-17-01 BEECH: Amendment 39-7099. Docket No. 90-CE-71-AD. Applicability: The following Model airplanes, certificated in any category: Models Serial Numbers 35-33, 35-A33, 35-B33, CD-1 through CD-981 and 35-C33, E33, F33, G33 CD-983 through CD-1304 35-C33A, E33A, F33A CE-1 through CE-235, CE-249, CE-250, CE-256, CE-260, CE-264 through CE-268, and CE-270 through CE-1565 E33C, F33C CJ-1 through CJ-179 36, A36 E-1 through E-2103, E-2105 through E-2110 A36TC, B36TC EA-1 through EA-319, and EA-321 through EA-388 T34C-1 GM-1 through GM-142 34C GP-1 through GP-50 T-34C GL-1 through GL-353 45 G-3 through G-6 A45 G-7 through G-156, G-257 through G-306, G-696 through G-845, CG-1 through CG-47, CG-58 through CG-60, CG-68, CG-73, CG-75, CG-78, CG-79, CG-105, CG-106, CG-108, CG-111 through CG-179, CG-200 through CG-223, CG-279 through CG-319 D45 BG-1 through BG-423 95 TD-2 through TD-302 B95 TD-303 through TD-452 B95A TD-453 through TD-533 D95A TD-534 through TD-707 E95 TD-708 through TD-721 95-55 TC-1 through TC-190 95-A55 TC-191 through TC-349, TC-351 through TC-370, and TC-372 through TC-501 95-B55, 95-B55A TC-371, TC-502 through TC-2456 95-C55 TC-350 95-C55A TE-1 through TE-49, and TE-51 through TE-451 D55, D55A TE-452 through TE-767 E55, E55A TE-768 through TE-1201 56TC TG-2 through TG-83 A56TC TG-84 through TG-94 58, 58A TH-1 through TH-1388, and TH-1390 through TH-1395 58P, 58PA TJ-3 through TJ-435, and TJ-437 through TJ-443 58TC, 58TCA TK-1 through TK-150 Compliance: Required the next time the elevator trim tab actuators are removed for any reason, but no later than 12 calendar months after the effective date of this AD, unless already accomplished. To prevent loss of control of the airplane because of interchanging the right-hand and left-hand elevator trim tab actuators, accomplish the following: (a)Paint a stripe on each stabilizer rear spar (right-hand black; and left-hand blue) in accordance with the Accomplishment Instructions of Beech Service Bulletin No. 2399, dated March 1991. (b) Remove the cover over the actuator inspection hole on each stabilizer and paint the inspection hole ledges (right-hand black; and left-hand blue) in accordance with the Accomplishment Instructions of Beech Service Bulletin No. 2399, dated March 1991. (c) Paint a stripe .50 by 1 inch on each actuator housing through the inspection holes (right-hand black; and left-hand blue) in accordance with the Accomplishment Instructions in Beech Service Bulletin No. 2399, dated March 1991. Actuators must not be removed to paint the .50 by 1 inch stripe on the housing. NOTE: A left-hand trim tab actuator will have threads on its actuator screw that will rotate clockwise when screwed into the actuator assembly, and a right-hand trim tab actuator will have threads on its actuator screw that willrotate counterclockwise when screwed into the actuator assembly. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (e) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (f) The modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2399, dated March 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-7099, AD 91-17-01) becomes effective on November 25, 1991.