Results
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.
95-12-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires installation of reinforcement plates at certain fuselage stations. This amendment is prompted by a report indicating that cracks were found in the frame strips at certain fuselage stations on a Model F28 Mark 0100 series airplane test article due to fatigue-related stress. The actions specified by this AD are intended to prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage pressure vessel.
76-22-11: 76-22-11 WEATHERLY AVIATION COMPANY: Amendment 39-2765. Applies to Model 201B and 201C airplanes prior to Serial Number 1011 certificated in all categories. Compliance required as indicated. To prevent an inadvertent activation of the parking brakes and loss of airplane control during ground operation due to a failure of the pilot to move the parking brake levers to the fully off position, accomplish the following: (a) Within the next 200 hours time in service after the effective date of this AD, unless previously accomplished, replace the parking brake handles with a parking brake cable installation in accordance with Weatherly Aviation Company, Inc., Service Note No. 5, dated October 21, 1976, or later FAA-approved revision. (b) The Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent modifications. (c) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base for the accomplishment of this AD. This amendment becomes effective November 15, 1976.
94-01-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Canadair Model CL-600-2B19 (Regional Jet) series airplanes. This action revises the FAA-approved Airplane Flight Manual (AFM) to require that both integrated drive generators (IDG) be operational for dispatch. This AD also requires repetitive inspections of the IDG oil level, and replenishing with oil, if necessary; and, for certain airplanes, an inspection of the oil level, and replacement of the IDG with a serviceable unit. This AD also specifies an optional terminating action for the repetitive inspections and AFM revision. This amendment is prompted by reports of failures of the IDG constant speed drive (CSD) on Canadair Model CL-600-2B19 series airplanes. The actions specified in this AD are intended to prevent loss of engine oil and subsequent engine shutdown during flight.
95-02-06: This amendment supersedes Airworthiness Directive (AD) 91-08-01, which currently requires the following on Jetstream Aircraft Limited (JAL) Jetstream Model 3101 airplanes: revising the maximum speed for flaps at 50 degrees from 153/149 knots indicated airspeed (KIAS) to 130 KIAS; and limiting the maximum flap extension to 20 degrees anytime ice is present on the airplane. This action requires incorporating a flap system modification as terminating action for the requirements of AD 91-08-01. The actions specified by this AD are intended to prevent sudden pitch down of the airplane during icing conditions, which could lead to loss of control of the airplane.
94-22-02: 94-22-02 CONSOLIDATED AERONAUTICS: Amendment 39-9051; Docket No. 94-CE-21-AD. Applicability: Lake Model 250 airplanes (all serial numbers), certificated in any category, that are equipped with a Bendix/King KFC 150 automatic flight control system. Compliance: Required within the next 10 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent automatic flight control system malfunctions caused by failure of the elevator autotrim to disengage, which could result in flight path deviations, accomplish the following: (a) Pull the two circuit breakers, one marked "A/P" and the other marked "TRIM", and attach a collar or tie-wrap to them to prevent resetting. (b) Fabricate a placard with the words: "Use manual trim only.", and install this placard on the instrument panel within the pilot's clear view. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (e) Information related to this AD may be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) This amendment becomes effective on November 4, 1994.
93-18-05: 93-18-05 MCDONNELL DOUGLAS HELICOPTER COMPANY and HUGHES HELICOPTERS, INC.: Amendment 39-8690. Docket Number 92-ASW-33. Applicability: Model 369D, 369E (Serial No. 0001E thru 0508E), 369F (Serial No. 0003 thru 0091), 369FF (Serial No. 0003 thru 0091), and 369H series helicopters, equipped with fuel vent line emergency shutoff valve assemblies, part number (P/N) 369H8108, 369H8108-501 or 369H8108-503, certificated in any category. Compliance: Helicopters with less than 2,400 hours' time-in-service on the effective date of this AD shall be inspected on or before attaining 2,500 hours' time-in-service, and thereafter, at an interval not to exceed 100 hours' time-in-service from the last inspection until an improved fuel vent line emergency shutoff valve assembly (assembly) is installed in accordance with paragraph (d) of this AD. Helicopters with 2,400 hours' or more time-in-service on the effective date of this AD shall be inspected in accordance with this AD within thenext 100 hours' time-in-service, and thereafter, at an interval not to exceed 100 hours' time-in-service from the last inspection until an improved assembly is installed in accordance with paragraph (d) of this AD. To prevent erroneously high inflight fuel quantity indications due to a blocked fuel vent line in the assembly, accomplish the following: (a) Remove the assembly from the helicopter as required by the appropriate Model 369 maintenance manual. (b) Inspect the fuel vent line emergency shutoff valve (valve) in accordance with Part I, Fuel Vent Line Emergency Shutoff Valve Inspection, of McDonnell Douglas Helicopter Company Service Information Notice HN-234, DN-181, EN-73, FN-60, dated January 17, 1992. (c) If the inspections conducted in accordance with the requirements of paragraph (b) uncover an incorrectly closed or obstructed valve, before further flight install an airworthy assembly in accordance with the appropriate Model 369 maintenance manual.(d) Install assembly, P/N 369H8108-505 or higher dash number, as follows, unless already accomplished: (1) For helicopters with 2,400 hours' or more time-in-service on the effective date of this AD, install the assembly on or before attaining the next 600 hours' time-in-service. (2) For helicopters with less than 2,400 hours' time-in-service on the effective date of this AD, install the assembly before attaining 3,000 hours' time-in-service. (e) 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, Propulsion Branch, Los Angeles Aircraft Certification Office, 3229 E. Spring Street, Long Beach, California 90806-2425. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Propulsion Branch, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Propulsion Branch, Los Angeles Aircraft Certification Office. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) The inspection shall be done in accordance with MDHC Service Information Notice HN-234, DN-181, EN-73, FN-60, dated January 17, 1992. 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 McDonnell Douglas Helicopter Company, 5000 East McDowell Road, Mesa, Arizona 85205-9797, Attention: Field Service Department. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg 3B, room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective December 21, 1993.
92-19-01: 92-19-01 AEROSPATIALE: Amendment 39-8358. Docket No. 92-NM-126-AD. Supersedes AD 89-09-05 R1, Amendment 39-6393. Applicability: All Model ATR42 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To minimize the potential hazards associated with operating in icing conditions including freezing rain, accomplish the following: (a) Within 10 hours time-in-service after May 3, 1989 (the effective date of AD 89-09-05, Amendment 39-6197), incorporate the following statement into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "When operating in icing conditions, as defined in the AFM, or when freezing rain is forecast or reported, use of the autopilot is prohibited. WARNING: Prolonged operation in freezing rain should be avoided. Ice accretion due to freezing rain may result in asymmetric wing lift andassociated increased aileron forces necessary to maintain coordinated flight. Whenever the aircraft exhibits buffet onset, uncommanded roll, or unusual control wheel forces, immediately reduce angle-of-attack and avoid excessive maneuvering." (b) Within 60 days after December 15, 1989 (the effective date of AD 89-09-05 R1, Amendment 39-6393), install vortex generators, in accordance with Aerospatiale Service Bulletin ATR42-57-0018, Revision 1, dated June 28, 1989. This action constitutes terminating action for the AFM limitation required by paragraph (a) of this AD, regarding use of the autopilot when operating in icing conditions, and the limitation may be removed from the AFM. (c) Operations may continue with a configuration consisting of one vortex generator missing per wing, provided that the two missing vortex generators form a symmetrical pair in relation to the airplane centerline. 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (e) 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. (f) The installation shall be done in accordance with Aerospatiale Service Bulletin ATR42-57-0018, Revision 1, dated June 28, 1989, which contains the following list of effective pages: Page Number Revision Level Date 1, 3, 5-13 1 June 28, 1989 2, 4 Original May 3, 1989 This incorporation by reference wasapproved 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on September 18, 1992.
94-12-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires replacement of certain bolts that are currently installed in various flight critical components of the airplane. This amendment is prompted by reports of incidents involving corrosion and fatigue cracking in transport category airplanes that are approaching or have exceeded their economic design goal; these incidents have jeopardized the airworthiness of the affected airplanes. The actions specified by this AD are intended to prevent reduced structural integrity of various flight critical components of the airplane.
77-05-03: 77-05-03 HUGHES HELICOPTERS: Amendment 39-2845. Applies to Hughes Model 369D helicopters Serial No. 0003 through 0049, certificated in all categories, that were manufactured without protective boots on the tail rotor output shaft. Compliance required as indicated unless already accomplished. To prevent binding of the tail rotor control system and damage to the tail rotor output shaft, accomplish the following: (a) Within 30 calender days from the effective date of this AD, disassemble the tail rotor control assembly, install Hughes P/N 369D21806 rotating boot and Hughes P/N 369D21807 stationary boot, and reassemble in accordance with Hughes Handbook of Maintenance Instruction. (b) Equivalent replacement parts may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Special flight permits may be issued in accordance with 21.197 and 21.199 to operate helicopters to a base for the accomplishment of the installation requiredby this AD. This amendment becomes effective March 7, 1977.
77-15-03: 77-15-03 CANADAIR: Amendment 39-2976. Applies to Canadair CL-215-1A10 airplanes, Serial Number 1001 thru 1040, and 1046, certificated in all categories. Compliance is required prior to U.S. Airworthiness Certification. To ensure correct engagement of shoulders of input quadrant P/N 215-90252 in left and right outboard bearing assemblies P/N 215-90255 or 215-90291, accomplish the following: On both ends of the elevator torque tube, measure the dimensions between the face of the shoulder of the input quadrant and the face of the bearing inner race. The two dimensions are to be added and their total compared to the following: (a) Aircraft 1001 thru 1015 and 1021 thru 1030, using bearing P/N 215-90255: If greater than 0.200 inches, alter assembly in accordance with the Modification and Procedure paragraph of Canadair Service Bulletin CL-215-201, dated 1/13/76, or approved equivalent alteration. (b) Aircraft 1016 thru 1020 and 1031 thru 1040, and 1046, using bearing P/N 215- 90291: If greater than 0.100 inches, alter assembly in accordance with the Modification and Procedure paragraph of Canadair Service Bulletin CL-215-201, dated 1/13/76, or approved equivalent alteration. Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Canadair Service Information Circular 115-CL-215 pertains to this subject. This amendment is effective July 27, 1977.
78-09-02: 78-09-02 BELL: Amendment 39-3203. Applies to Bell Model 212 helicopters, certificated in all categories, that are equipped with emergency float kits 212-706-021 or 212-706-042 and that are operated under conditions that require ditching capability or aircraft floatation devices. Compliance required as indicated. To permit opening of the passenger emergency exits in the event of a ditching and deployment of the emergency float bags, accomplish the following, unless already accomplished in accordance with data previously approved by the FAA (including STC No. SH2746SW issued April 4, 1978): Prior to further flight, after the effective date of this AD, modify the forward and aft passenger emergency exit on each side of the helicopter in accordance with information and/or data approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, except that the helicopter may be flown in accordance with FAR 21.197 to a base where the work may be performed.This amendment becomes effective May 9, 1978.
77-16-02: 77-16-02 DOWTY ROTOL: Amendment 39-2995. Applies to Dowty Rotol propeller types R245/4-40-4.5/13, R259/4-40-4.5/17 installed on but not necessarily limited to Convair 600 series airplanes and R209/4-40-4.5/2 installed on but not necessarily limited to Nihon YS-11 and 11A airplanes, except those propellers incorporating modification VP 2869 contained in Dowty Rotol Service Bulletin 61-875, Rev. 1 dated October 20, 1976. Compliance is required as indicated. To prevent pitch lock piston cracking and subsequent inability to feather the propeller, accomplish the following: (a) For propeller pitch lock pistons with 19,000 or more flights on the effective date of this AD, before further flight, comply with paragraph (d) of this AD. (b) For propeller pitch lock pistons with less than 19,000 flights on the effective date of this AD, comply with paragraph (c) of this AD. (c) For propeller pitch lock pistons, P/N RA 70089: (1) Prior to the accumulation of 15,000 flights or within the next 100 flights, whichever occurs later, unless already accomplished within the last 900 flights, unless otherwise required by paragraph (e) of this AD, and thereafter at intervals not to exceed 1,000 flights from the last inspection until reaching 19,000 flights, inspect the pitch lock piston for cracks around the outside diameter at the location of the 0.025 inch radius in accordance with the procedures and instructions in Dowty Rotol Service Bulletin 61-873, Revision 1, dated October 20, 1976, or an FAA-approved equivalent. (2) If a crack is found during an inspection required by paragraph (c)(1), before further flight, comply with paragraph (d) of this AD. (d) Replace the pitch lock piston with either - (1) A new zero time part, P/N RA 70089, in accordance with Dowty Rotol Service Bulletin 61-873, Revision 1, dated October 20, 1976, or an FAA-approved equivalent, and thereafter comply with paragraphs (c), (d), and (e) of this AD; or (2) A new redesigned pitch lock piston and cylinder cover bush in accordance with Dowty Rotol Service Bulletin 61-875, dated October 20, 1976, or an FAA- approved equivalent. (e) Prior to the accumulation of 19,000 flights on propeller pitch lock piston P/N RA 70089, comply with paragraph (d) of this AD. (f) For the purposes of this AD, a flight is defined as a single takeoff and landing. (g) This AD requires no further action after compliance with paragraph (d)(2) of this AD. This amendment becomes effective August 31, 1977.
76-18-09: 76-18-09 MESSERSCHMITT-BOLKOW-BLOHM GmbH (MBB): Amendment 39- 2718. Applies to Model BO-105A and BO-105C helicopters, certificated in all categories, incorporating Teledyne Hydra-Power hydraulic actuators, P/N 105-45021, with the following serial numbers: 1012, 1014, 1015, 1016, 1017, 1018, 1019, 1021, 1023, 1027, 1028, 1029, 1030, 1032, 1034, 1035, 1037, 1038, 1040, 1041, 1043, 1044, 1045, 1046, 1049, 1056, 1057, 1062, 1064, 1065, 1066, 1069, 1071, 1075, 1091, 1093, 1101, 1104, 1109, 1113, 1119, 1121, 1123, 1126, 1127, 1156, 1160, and 1161 which have piston rods, P/N D133-750.08E, with S/N's 101 through 440. Compliance is required as indicated, unless already accomplished. To prevent possible failure of the main rotor hydraulic actuator and loss of control of the helicopter, accomplish the following: (a) Before the accumulation of 600 hours total helicopter time in service or within the next 25 hours time in service after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 600 hours time in service from the last inspection until modified in accordance with paragraph (e) of this AD, comply with paragraph (b) of this AD. (b) Inspect the piston rods, P/N D133-750.08E, in the hydraulic actuators, P/N 105- 45021, for cracks, using a dye penetrant method in accordance with Paragraph 2.B. of the "Accomplishment General" section of MBB Service Bulletin No. 40-19, dated June 2, 1975, or an FAA-approved equivalent. (c) If a crack is found in a piston rod during an inspection specified in paragraph (b) of this AD, before further flight, replace the cracked piston rod with a serviceable part of same part number and continue to inspect in accordance with paragraph (b) of this AD at intervals not to exceed 600 hours time in service until the modification specified in paragraph (e) of this AD is accomplished. (d) Comply with paragraph (e) of this AD as follows: (1) For helicopters with less than 1800 hours totaltime in service on the effective date of this AD and for which it has been less than 4 years since the original issuance of its airworthiness certificate, comply with paragraph (e) of this AD in accordance with paragraph (i) or (ii), whichever occurs later. (i) Before the accumulation of 1800 hours total time in service or within four years of the date of original issuance of its airworthiness certificate, whichever occurs sooner. (ii) Within the next 25 hours time in service after the effective date of this AD. (2) For helicopters with 1800 hours or more total time in service on the effective date of this AD or helicopters for which the effective date of this AD is four years or more after the date of original issuance of its airworthiness certificate, comply with paragraph (e) of this AD within the next 25 hours time in service after the effective date of this AD. (e) Disassemble the Teledyne Hydra-Power actuator, P/N 105-45021, and replace the piston rods, P/N D133-750.08E, which have S/N's 101 through 440 with serviceable parts of the same part number which have serial numbers other than 101 through 440. This amendment becomes effective on October 1, 1976.
46-12-02: 46-12-02 DOUGLAS: (Was Service Note 12 of AD-669-3.) Applies to DC3A Aircraft. \n\n\tInspection required immediately and every 100 hours thereafter on all aircraft which have beryllium copper engine mount to firewall attach fittings installed. \n\n\tInspect the engine mount to firewall attach fittings, P/N 5-81486-4 (with 4-power magnifying glass min.) in the fillet of the spot face for cracks or flaws in the material. If evidence of defects are found, replace with P/N 1042764. If cracks are not found, inspect every 100 hours until next engine change. P/N 5-81486-4 should be replaced with P/N 1042764 at engine change. \n\n\t(Douglas Service Bulletin No. 238 covers this same subject.)
94-08-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires installation of fusible trunnion pins in the shock struts and drag braces of the main landing gear (MLG). This amendment is prompted by a report of incorrectly manufactured trunnion pins that may cause the MLG to compromise the structural integrity of the wing fuel tanks. The actions specified in this AD are intended to prevent damage to the wing fuel tanks and the resultant fuel spillage and fire hazard when the maximum intended design load limits are exceeded during landing.
94-24-09 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires repetitive inspections to detect damage to the overwing fairings, and replacement or repair of structurally damaged fairings. That AD was prompted by a report indicating that an overwing fairing detached from an airplane. The actions specified by that AD are intended to prevent reduced controllability of the airplane due to loss of an overwing fairing. This amendment adds an optional terminating action for the currently required inspections, and limits the applicability of the rule.
95-03-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires an inspection to detect cracks in the cleats at certain rib stations of the wing, and replacement of the cracked cleats with new cleats. This amendment is prompted by a report that, during manufacture of the wings of these airplanes, cracks were discovered in the cleats at the left- and right-hand rib station 8200 of the wing due to improper installation of certain bolts. The actions specified by this AD are intended to prevent cracking of the cleats, which could result in reduced structural integrity of the wing.
92-06-04: 92-06-04 BRITISH AEROSPACE: Amendment 39-8184. Docket No. 91-NM-206-AD. Applicability: Model BAe 125-800A series airplanes, Post-Modification 253191A and Pre-Modification 253247A, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent internal arcing in the dimmer units and smoke emission into the cockpit, accomplish the following: (a) Within 60 days after the effective date of this AD, modify the instrument integral lighting system by installing dimmer units having Page Modification AR1477 incorporated, and perform functional tests of the pilot's and co-pilot's instrument integral lighting dimmer system, in accordance with British Aerospace Service Bulletin 33-44-7670A, Revision 1, dated April 4, 1991. (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, Standardization Branch, ANM-113, 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, Standardization Branch. (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 modification shall be done in accordance with British Aerospace Service Bulletin 33- 44-7670A, Revision 1, dated April 4, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. 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. (e) This amendment becomes effective on April 21, 1992.