Results
98-15-22: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection for delamination, erosion, and condition of fillet sealant and conductive edge sealer of the wing and empennage leading edge area behind the de-ice boots, and follow-on corrective actions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent delamination of the wing and empennage leading edge due to improper installation of the wing de-ice boot, which could result in reduced controllability of the airplane.
78-08-01: 78-08-01 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-3180. Applies to BH/HS 125-600A airplanes, certificated in all categories. Compliance required within one month after the effective date of this AD, unless already accomplished. To prevent possible inability to activate the engine blow-off valve switches in the event that birds are ingested into the engines on take-off, accomplish the following: Remove the existing switch guards for the engine blow-off valve switches and replace with the new design guard, P/N 25-6 NF 2629, in accordance with the section entitled "Accomplishment Instructions" and the associated drawing, contained in Hawker Siddeley Aviation, Ltd. Service Bulletin 75-3(2580), dated June 21, 1977, or an FAA-approved equivalent. This amendment becomes effective May 10, 1978.
95-16-06: This amendment supersedes Airworthiness Directive (AD) 83-05-01, which currently requires the following on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream series 200 airplanes: repetitively inspecting the wing lower skin panels at the main gear bay cutouts for loose or damaged rivets and cracks, replacing loose or damaged rivets, and repairing any cracked wing lower skin panel. The Federal Aviation Administration's policy on commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. The proposed action would require reinforcing the wing lower skin at both the landing gear cutouts at Wing Station (WS) 115 and the undercarriage bay cutouts at WS 60 and WS 90, as terminating action for the repetitive inspections that are currently required by AD 83-05-01. The actions specified in the proposed AD are intended to prevent wing damage caused by cracks or loose or damaged rivets in the wing lower skin panels, which, if not detected and corrected, could result in structural damage to the point of failure.
91-14-17: 91-14-17 SAAB-SCANIA: Amendment 39-7058. Docket No. 91-NM-35-AD. Applicability: Model SF-340A series airplanes, Serial Numbers 079 through 159; and Model SAAB 340B series airplanes, Serial Numbers 160 through 199; certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless previously accomplished. To prevent an electrical fire and smoke in the cockpit, accomplish the following: A. Replace the FD 574-24 wire from terminal block 301VT BH:C to connector 203VU P33:A1 in the autopilot electrical system with a 20 AWG size wire, in accordance with SAAB Service Bulletin 340-34-068, dated November 9, 1990. 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. NOTE: The request should be forwarded through an FAA Principal Avionics Inspector, who may concur or comment then send it to the Manager, Standardization Branch, ANM-113. 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. D. The replacement requirements shall be done in accordance with SAAB Service Bulletin 340-34-068, dated November 9, 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 SAAB- Scania AB, Product Support, S-581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7058, AD 91-14-17) becomes effective on August 6, 1991.
76-20-05: 76-20-05 ARMSTRONG WHITWORTH: Amendment 39-2737. Applies to Model AW-650 Series 101 airplanes, certificated in all categories. Compliance is required as indicated. To prevent failure of main landing gear due to cracks in the main undercarriage auxiliary jack attach pin, accomplish the following: (a) For airplanes with attach pins which have accumulated more than 6,000 landings but less than 10,000 landings on the effective date of this AD, within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the last three calendar months, and thereafter at intervals not to exceed three calendar months from the last inspection, inspect the pin attaching the auxiliary jack to the drag stay for cracks, in accordance with Accomplishment Instructions 2A(1) through 2A(6) of Dowty Rotol Service Bulletin No. 32-50D, dated February 23, 1976, or an FAA-approved equivalent. (b) If a crack is found as a result of any inspection required by this AD, before further flight, comply with paragraph (d) of this AD. (c) For airplanes with attach pins which have accumulated 10,000 or more landings on the effective date 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 for the performance of the work required by this AD, and for other airplanes before the accumulation of 10,000 landings on the attach pin, comply with paragraph (d) of this AD. (d) Remove the pin attaching the auxiliary jack to the drag stay, install a new attach pin, Dowty Rotol P/N 100402604 in place thereof, and thereafter inspect in accordance with the repetitive inspection cycle set forth in paragraph (a) of this AD upon the accumulation of 6,000 landings on the new attach pin. This amendment becomes effective October 14, 1976.
76-17-01: 76-17-01 GENERAL ELECTRIC: Amendment 39-2696. Applies to Models CF6-50A, CF6-50C, CF6- 50D, CF6-50E, CF6-50E1, and CF6-50H Turbofan Engines. Compliance required by June 1, 1977, unless previously accomplished. To prevent excessive overpressure in the high pressure compressor, accomplish the following in accordance with General Electric Service Bulletin (CF6-50) 72-412, Revision 1, or subsequent FAA Approved Revision thereto: (a) Remove the fan stator stages 1, 2 and 3 inner shrouds, stage 2 outer shroud and stages 2 and 3 cases with abradable epoxy resin. (b) Replace with new or reworked parts incorporating aluminum honeycomb material. 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 General ElectricCompany, Cincinnati, Ohio 45215. These documents may also be examined at the FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018 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 Great Lakes Region. This amendment becomes effective August 20, 1976.
94-05-08: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that requires modification of the electrical power supply system. This amendment is prompted by a report that a single phase fault current can cause sequential failure of all onboard main electrical generators. The actions specified by this AD are intended to prevent such failures and subsequent loss of electrical power sources onboard the airplane.
94-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes. This action requires inspections to detect cracking in the ventral aft pressure bulkhead, and repair, if necessary. This amendment is prompted by reports of cracking found in the ventral aft pressure bulkhead on several airplanes. The actions specified in this AD are intended to prevent the propagation of cracks in the ventral aft pressure bulkhead, which could lead to failure of the bulkhead and subsequent rapid decompression of the airplane.
78-14-05: 78-14-05 CONSOLIDATED AERONAUTICS: Amendment 39-3260. Applies to Lake Model LA-4-200 airplanes, Serial Nos. 769 through 830, inclusive. Compliance is required as indicated, unless already accomplished. To prevent operation with flawed (material defect) wing main beam attachment fittings, accomplish the following: 1. Prior to further flight and thereafter prior to the first flight of each day until paragraph 3 is accomplished, visually inspect the outboard portion of the four (4) wing main beam attachment fittings (steel fittings), P/N 1-3214-3, for flaws which appear as spanwise cracks. 2. Flawed fittings found as a result of the inspections of paragraphs 1 above or 3a below, must be replaced prior to further flight with serviceable fittings, P/N 1-3214-3, in accordance with paragraph 4. 3. Within the next 15 hours time in service after the effective date of this AD, visually inspect the outboard end of the four steel wing main beam attachment fittings, P/N 1- 3214-3,for the impression stamped bar stock heat treat lot number. These fittings are visible through the main gear wheel wells. If the fitting impression stamped lot number is 741 or 741R, either: a. Ultrasonic inspect the steel wing main beam attachment fitting(s), P/N 1- 3214-3, for flaws in accordance with Lake Aircraft Division of Consolidated Aeronautics, Inc., Service Bulletin B60, or b. Replace the steel wing main beam attachment fitting(s), P/N 1-3214-3, with serviceable fitting(s), P/N 1-3214-3, in accordance with paragraph 4. NOTE: This paragraph applies whether or not an "H" is impression stamped on the outboard end of the fitting opposite "741" or "741R". 4. Replacement serviceable fittings must be installed in accordance with Lake Aircraft Division of Consolidated Aeronautics, Inc., Service Bulletin B60. 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 Lake 4 Sales Corporation, P.O. Box 399, Tomball, Texas 77375. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, 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 FAA New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective July 19, 1978.
99-06-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that requires replacement of the rivets that attach the pressurized floor panel to gantries 4 and 5 with new titanium alloy bolts. This amendment also requires, for certain airplanes, repetitive inspections to detect discrepancies of the rivets; and corrective actions, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the rivets that attach the pressurized floor panel to gantries 4 and 5, which could result in the loss of the floor panel and consequent rapid decompression of the airplane.
97-16-09: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires modification of the hydraulic system, and a revision to the Airplane Flight Manual (AFM) to include revised procedures for lowering the landing gear. This amendment is prompted by a report of uncommanded application of the brakes when the direct current (DC) hydraulic pump was selected ON with the main hydraulic system operative; this situation was caused by build-up of back pressure in the brake supply and hydraulic return systems. The actions specified by this AD are intended to prevent uncommanded application of the brakes during landing, as a result of the build-up of back pressure.
97-16-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the existing fire, tailpipe, and bleed-air overheat detector control units with new, improved units. This amendment is prompted by reports indicating that false engine and auxiliary power unit (APU) fire warnings were issued from the fire detector control units due to moisture or induced voltages of the detector control unit. The actions specified by this AD are intended to prevent such false fire warnings, which could result in unnecessary diversion of the airplane, and resultant increased risks to the airplane, passengers, and crew, and the potential for an overweight landing.
47-10-24: 47-10-24 LOCKHEED: (Was Mandatory Note 27 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required prior to June 1, 1947. Install thermal relief valve and bypass line in fuel crossfeed line adjacent to No. 4 cross transfer valve. (LAC Service Bulletin 49/SB-48 covers this same subject.)
48-07-02: 48-07-02 DOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43024; 43035 through 43064; and 43105 Through 43110. \n\n\tTo be accomplished not later than the first engine change after March 1, 1948, but in any event not later than June 1, 1948. \n\n\tTo prevent failure in the engine supercharger control actuator when shifting from low to high blower and vice versa, it is necessary to provide overtravel in the engine supercharger control linkage by installing a new Geneva-Loc supercharger actuator lever, a new Bendix link-supercharger actuating link and a new four-hole mounting support bracket. \n\n\t(Douglas Service Bulletin DC-6 No. 127 covers this same subject.)
94-09-03: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 series airplanes, that requires that the brake wear limits prescribed in this proposal be incorporated into the FAA-approved maintenance inspection program. This amendment is prompted by an accident in which a transport category airplane executed a rejected takeoff (RTO) and was unable to stop on the runway due to worn brakes; and the subsequent review of allowable brake wear limits for all transport category airplanes. The actions specified by this AD are intended to prevent the loss of brake effectiveness during a high energy RTO.
94-07-02: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires modification of the cavity vent drain tube assembly at the center wing lower auxiliary fuel tank cavity. This amendment is prompted by a report that the cavity vent tube, if not properly grounded, could act as an electrical path in the event of a lightning strike. The actions specified by this AD are intended to prevent arcing in the tank cavity and possible resulting fire.
92-16-08: 92-16-08 BOEING: Amendment 39-8317. Docket No. 92-NM-08-AD. \n\n\tApplicability: Model 747 series airplanes; equipped with escape slides listed in Boeing Service Bulletin 747-25-2132, dated September 17, 1971; or equipped with escape systems installed in accordance with Supplemental Type Certificate SA574GL, SA575GL, SA744GL, SA745GL, or SA1215EA; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent jamming of an emergency exit door, accomplish the following: \n\n\t(a)\tFor airplanes equipped with escape slides listed in Boeing Service Bulletin 747-25-2132, dated September 17, 1971; and for airplanes equipped with escape systems installed in accordance with Supplemental Type Certificate (STC) SA574GL, SA575GL, SA744GL, or SA745GL: Within 20 months after the effective date of this AD, replace the plastic pulley guards on the emergency slide system packboard release mechanism, Boeing part number (P/N) 69B51507-1 and -2, with metal pulley guards, Boeing P/N 69B54562-1 and -2, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(b)\tFor airplanes equipped with escape systems installed in accordance with STC SA1215EA: Within 20 months after the effective date of this AD, replace the plastic pulley guards on the emergency slide system packboard release mechanism, Boeing part number (P/N) 69B51507-1 and -2, with metal pulley guards, Boeing P/N 69B54562-1 and -2, in accordance with Air Cruisers Service Bulletin 25-139, Revision 1, dated September 18, 1991; or in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\t(c)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThis amendment becomes effective on September 16, 1992.
92-02-17: 92-02-17 BOEING: Amendment 39-8154. Docket No. 91-NM-145-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-25- 2754, dated March 30, 1989, certificated in any category. \n\n\tCompliance: Required within the next 24 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the girt bar end fittings from disengaging the girt bar floor brackets, accomplish the following: \n\n\t(a)\tReplace the girt bar floor brackets with modified brackets, in accordance with Boeing Service Bulletin 747-25-2754, dated March 30, 1989. \n\n\t(b)\tAn 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. \n\n\tNOTE: The request should 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)\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\t(d)\tThe replacement requirements of this AD shall be done in accordance with Boeing Service Bulletin 747-25-2754, dated March 30, 1989. 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 S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(e)\tThis amendment (39-8154, AD 92-02-17) becomes effective on March 2, 1992.
93-09-07: 93-09-07 PACIFIC SCIENTIFIC COMPANY, HTL/KIN-TECH DIVISION: Amendment 39-8573. Docket 93-NM-37-AD. This AD supersedes AD 93-08-06, Amendment 39-8553. \n\n\tApplicability: Fire extinguishers, as listed in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993; as installed on, but not limited to, Airbus Industrie Model A300, A310, and A320 series airplanes, Boeing Model 757-200 series airplanes equipped with Rolls Royce engines, and McDonnell Douglas Model DC-9-80 (MD-80) and MD-11 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of a fire extinguisher to discharge extinguishant in the event of a fire, accomplish the following: \n\n\t(a)\tPrior to the accumulation of 500 hours time-in-service or within 60 days after the effective date of this AD, whichever occurs first, unless accomplished within the last 8 months prior to the effective date of this AD, perform a test ofthe low pressure indicating circuit to monitor actuation of the pressure switch on the fire extinguisher in accordance with the Accomplishment Instructions in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. \n\n\t\t(1)\tIf the switch passes the test, no further action is required by this AD. \n\n\t\t(2)\tIf the switch fails this test, prior to further flight, replace the fire extinguisher with a serviceable extinguisher. This replacement extinguisher must have been inspected previously in accordance with paragraph 3 of the Accomplishment Instructions in the service bulletin. \n\n\t(b)\tAs of the effective date of this AD, no person shall install, on any airplane, a Pacific Scientific fire extinguisher having a part number listed in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993, that has not been inspected previously in accordance with paragraph 3 of the Accomplishment Instructions in Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. \n\n\t(c)\tFor switches that fail to pass the test required by paragraph (a) of this AD: Within 30 days after accomplishing the test, submit a report of the results of the test to the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or fax to (310) 988-5210. The report must include the following information: \n\n\t\t(1)\tWhen was the inspection performed? \n\n\t\t(2)\tWhat is the part number of the fire extinguisher? \n\n\t\t(3)\tWhat is the airplane model and series from which the extinguisher was removed? \n\n\t\t(4)\tWhere was the extinguisher installed (e.g., Position/Location: left engine, right engine, auxiliary power unit (APU) compartment, etc.)? \n\n\t\t(5)\tWhen was the last hydrostatic check performed on that extinguisher? \n\n\t\t(6)\tWho performed the last hydrostatic check on that extinguisher? \n\n\t\t(7)\tWhen was the last hex key check (low pressure indicating circuit test) performed onthat extinguisher? \n\n\t\t(8)\tWas the extinguisher guard tack welded, completely welded, or not welded to the switch housing? The information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(d)\tAn 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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. \n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. \n\n\t(e)\tSpecial 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. \n\n\t(f)\tThe testing and replacement shall be done in accordance with Pacific Scientific Alert Service Bulletin 26A1106, dated March 10, 1993. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51, as of May 11, 1993 (58 FR 21912, April 26, 1993). Copies may be obtained from Pacific Scientific Company, HTL/Kin-Tech Division, Attention: Product Support Department, 1800 Highland Avenue, Duarte, California 91010. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or at the Office of the Federal Register, 800 North Capitol Street,NW., suite 700, Washington, DC. \n\n\tThis AD supersedes AD 93-08-06, Amendment 39-8553. \n\n\t(g)\tThis amendment is effective May 11, 1993.
91-08-03: 91-08-03 SIKORSKY AIRCRAFT: Amendment 39-6958. Docket No. 91-ASW-05. Applicability: All Sikorsky Aircraft Model S-76A helicopters, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent fatigue failure of the vertical pylon forward spar, which could result in loss of the helicopter, accomplish the following: (a) Within the next 25 hours time in service determine if forward spar cap angles, part numbers (P/N's) 76201-05001-103 and 76201-05001-104, are installed and if it is equipped with Sikorsky Modification Kit 76070-20086, then-- (1) If the affected helicopter has Sikorsky Modification Kit 76070-20086 installed, no further action is necessary; however (2) If the affected helicopter has the original unmodified forward spar cap angles with 1,395 or more hours time in service after the effective date of this AD, comply with paragraph (c), unless already accomplished, and thereafter at intervals notto exceed 1,420 hours time in service. NOTE: Information pertaining to Kit 76070-20086 is contained in Sikorsky Alert Service Bulletin No. 76-55-12. (b) For those helicopters with the original unmodified forward spar cap angles specified in paragraph (a)(2) with less than 1,395 hours time in service after the effective date of this AD, compliance with paragraph (c) is required prior to accumulation of 1,420 hours time in service, unless already accomplished, and thereafter at intervals not to exceed 1,420 hours time in service. (c) Remove and replace the forward spar cap angles with new parts of the same part numbers. (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance with the AD may be accomplished. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance or adjustment of the compliance times, which provides an equivalent level of safety, may be used if approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. This Amendment (39-6958, AD 91-08-03) becomes effective on May 3, 1991.
89-26-01: 89-26-01 BOEING: Amendment 39-6416. Docket No. 89-NM-139-AD. \n\n\tApplicability: Model 767 series airplanes listed in Boeing Service Bulletin 767-32-0081, dated April 27, 1989, certificated in any category. \n\n\tCompliance: Required within the next 750 landings after the effective date of this AD or prior to the accumulation of 15,000 landings, whichever occurs later, unless previously accomplished. \n\n\tTo prevent partial loss of braking and, potentially, the complete loss of braking, accomplish the following: \n\n\tA.\tReplace aluminum brake metering valve module shafts with steel shafts, in accordance with Boeing Service Bulletin 767-32-0081, dated April 27, 1989. \n\n\tB.\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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal MaintenanceInspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\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 documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6416, AD 89-26-01) becomes effective on January 12, 1990.
77-23-05: 77-23-05 SCOTTISH AVIATION, LTD. (Formerly BEAGLE AVIATION, LTD.): Amendment 39-3076. Applies to Beagle Model B206 Series 1 and Series 2 airplanes, certificated in all categories. Compliance is required as indicated. To prevent possible fatigue failure of the outer wing, wing center section, and empennage assemblies, accomplish the following: (a) Prior to the accumulation of 11,000 hours total time in service on the outer wing, wing center section, or empennage assemblies, replace the affected assembly with an assembly of the same part number, or a part number approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, which has accumulated less than 11,000 hours total time in service. (b) Operators who have not kept records of hours of time in service on any assembly to which a provision of this AD applies shall substitute airplane hours time in service in lieu thereof. (Scottish Aviation, Limited, Mandatory Service Bulletin No. B206/54, dated October 21, 1975, covers the same subject.) This amendment becomes effective December 10, 1977.
75-19-03: 75-19-03 BOEING: Amendment 39-2366. Applies to all Boeing Model 747 series aircraft certificated in all categories. Compliance required as indicated unless already accomplished. \n\tTo prevent possible lavatory fire, accomplish the following: Within 300 hours time in service from the effective date of this AD, unless already accomplished, remove capacitor assembly from toilet flush motor and cap exposed wires in accordance with Boeing Service Bulletin 747-38-2021, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe 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). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 19, 1975.
59-06-07: 59-06-07 VICKERS: Applies to All Viscount Model 745D Aircraft. Compliance required by April 1, 1960. In order to preclude the possibility of foreign object jamming primary flight controls in the cockpit floor, cover plates must be installed over all openings, in accordance with Vickers- Armstrongs Modification Bulletin NR.D.2146 Parts (B), (C), (D), (E), (F), and (P), or equivalent. Modifications D.1185 and D.2272 also cover sealing openings in the cockpit floor area.
54-19-02: 54-19-02 SIKORSKY: Applies to All Model S-55 Helicopters. Compliance required before October 1, 1954. To insure against the loosening of the servo pilot valve locknut and subsequent improper servo operation, safety clips, Sikorsky P/N S-14-40-5194, should be installed and safetied to P/N S14-40-3227-24 lockwasher. (Sikorsky Service Information Circular 1440-458 covers this same subject.)