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99-12-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T99-12-52 that was sent previously to all known U.S. owners and operators of all Boeing Model 727 series airplanes by individual telegrams. This AD requires a boost pump dry bay inspection to detect leakage of fuel through an arced-through conduit, and corrective action, as necessary. This AD also requires repetitive detailed visual inspections of the in-tank fuel boost pump wiring to detect chafing of the wire insulation, evidence of electrical arcing, or arc-through of the conduit wall on Model 727 series airplanes, and applicable corrective action; and installation of sleeving over the in- tank fuel boost pump wires as a method to protect the wiring from chafing. This action is prompted by reports of severe wear of in-tank fuel boost pump wiring, and arc-through of the surrounding conduit on two Model 727 series airplanes. The actions specified by this AD are intended toprevent fuel tank explosion resulting from arc-through of the fuel boost pump wiring conduits.
99-13-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires repetitive inspections to detect cracking of the upper cutout and lower flange of the outboard support assembly of the flaperons on the wings; and corrective actions, if necessary. This amendment also provides an optional terminating action for the repetitive inspections. This amendment is prompted by results of flight testing conducted by the manufacturer indicating that high engine thrust conditions during takeoff cause excessive cyclic loads and could lead to fatigue cracking of the outboard support of the flaperon. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in fracture of the flaperon support structure, loss of the flaperon, and consequent reduced controllability of the airplane.
2013-20-13: We are adopting a new airworthiness directive (AD) for certain Bell Model 206B and 206L helicopters. This AD requires installing a placard beneath the engine power dual tachometer and revising the operating limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady- state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.
99-13-02: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters, that currently requires conducting a filter clogging warning test, and, if necessary, replacing a jammed valve with an airworthy valve. This amendment requires the same corrective actions required by the existing AD; however, the applicability is reduced to encompass only certain part-numbered fuel filters. This amendment is prompted by jammed fuel filter by-pass valves and new information that justifies a reduction in the applicability of the superseded priority letter AD. The actions specified by this AD are intended to prevent engine power loss due to fuel starvation, which could cause one or both engines to flameout and a subsequent forced landing.
89-22-07: 89-22-07 PRATT & WHITNEY: Amendment 39-6344. Applicability: Pratt & Whitney (PW) JT3D-3B and JT3D-7 turbofan engines approved for return to service by Jet Power, Inc (JPI), FAA Repair Station No. 705-70, located at 4275 Northwest 77th Avenue, Miami, Florida, identified by serial number (S/N) as follows: 630197 631540 631996 632276 632282 632285 632339 632340 632346 632351 632408 632478 632481 632487 632749 632842 632846 632852 632962 632966 632968 632973 633040 633495 633541 633558 633564 633607 633609 633615 633669 633732 633742 633744 634616 642390 642490 642512 642901 642910 642914 643332 643471 642715 643803 643812 643899 643904 643973 644047 644071 644131 644200 644218 644306 644359 644667 644756 644953 644973 645017 645030 645051 645088 645128 645145 645177 645214 645294 645370 645401 645407 645570 645675 645753 645769 645785 645854 645865 645913 645915 645977 645999 646001 667054 667677 667736 667792 667879 667932 667979 668042 668103 668229 668312 668331 668373 668430 668557 668594 668603 668609 668658 668678 668827 668877 669156 669252 669324 669360 669375 669377 669411 669425 669484 669564 669583 669644 669690 669793 669797 669801 670744 671102 671133 671141 671233 671254 671340 671391 671425 675803 678988 678994 678999 688430 Compliance: Required within the next 30 calendar days after the effective date of this AD, unless already accomplished. To ensure the continuing structural integrity and certificated performance capabilities of JT3D-3B and JT3D-7 turbofan engines, accomplish the following: (a) Remove from service those engines identified above. (b) Engines removed from service in accordance with paragraph (a) above may be returned to revenue service by accomplishing either one of the two following requirements: (1) Accomplish the overhaul manual requirements on all parts, sub-assemblies, accessories, and components installed on the engine and, if any of the engines or components of the engines referred in paragraph (a) have been in an accident, accomplish the pertinent overhaul manual special check and inspection requirements. The engine overhaul and special inspection requirement must be accomplished in accordance with the requirements of Pratt & Whitney JT3D-3B Overhaul Manual, Part Number (P/N) 411568, Revision 78, dated December 15, 1988, or Pratt & Whitney JT3D-7 Overhaul Manual P/N 615105, Revision 50, dated December 15, 1988, as applicable. NOTE: The Light Overhaul Manual requirements, included in the above overhaul manuals, are not applicable in this case. (2) Submit to the FAA, Manager, Engine Certification Office, through the cognizant FAA Airworthiness Inspector, all the pertinent records identified below for review, and obtain a written FAA approval prior to returning an engine to service: (i) If the parts, sub-assemblies, accessories, or other components of an engine approved for return to service by JPI were subjected to overhaul or maintenance activities during the last shop visit at JPI, provide records establishing the origin and/or the prior service history of the subject parts. If the determination of the origin of such parts leads to other engines, the records for reason of removal from service, and if available, trend monitoring data for those engines must also be included. Provide records of accomplishment of the required inspections, checks, tests, as applicable in accordance with engine manual requirements that establish the components' airworthiness. (ii) A list of all life limited components by S/N, service history, and current status as required by FAR Part 121, Section 380, or FAR Part 91, Section 173, as appropriate. (iii) All repair or overhaul records, concerning the last shop visit at JPI, as required by FAR Part 121, Section 380, or FAR Part 91, Section 173, as appropriate. (iv) Substantiating evidence that the work performed during the last shop visit at JPI was done in accordance with FAA approved data as required by the FAR's. (v) Engine acceptance test data or engine "on-wing" test data, accomplish after repair or overhaul, whichever is applicable. (vi) Engine operation trend monitoring data, if available, for the current engine installation. (vii) A list by P/N or S/N of any engine, part, sub-assembly, accessory, or component acquired from JPI that has been known to have been involved in an accident. NOTE: If engine owners, operators, or cognizant Civil Aviation Authorities outside the United States wish to have the FAA's assistance in this effort, they may contact the FAA at the following address: Federal Aviation Administration, Engine and Propeller Directorate, Aircraft Certification Service, Attention: Manager, Engine Certification Office, ANE-140, 12 New England Executive Park, Burlington, Massachusetts 01803. Information collection requirements contained in the amendment to Section 39.13 have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96-511) and have been assigned OMB Control No. 2120-0056. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times in this AD, may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England ExecutivePark, Burlington, Massachusetts 01803. The engine overhaul and special inspection requirements shall be done in accordance with PW JT3D-3B Overhaul Manual P/N 411568, Revision 78, dated December 15, 1988, or JT3D-7 Overhaul Manual P/N 615105, Revision 50, dated December 15, 1988, as applicable. The sections of these manuals pertinent to Light Overhaul are not applicable. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Pratt & Whitney, Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803. This amendment (39-6344, AD 89-22-07) becomes effective on October 31, 1989.
99-12-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-200C series airplanes, that currently requires a one-time external detailed visual inspection to detect cracks of the fuselage skin in the lower lobe cargo compartment; repetitive internal detailed visual inspections to detect cracks of the frames in the lower lobe cargo compartment; and repair of cracked parts. That AD also provides for an optional preventative modification that constitutes terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating modification. This amendment is prompted by reports of cracking in the body frames between stringers 19 left and 25 left and at body stations 360 to 500B. The actions specified by this AD are intended to prevent opening or loss of the cargo door during flight, and consequent rapid decompression of the airplane.
83-07-12 R1: 83-07-12 R1 PILATUS BRITTEN-NORMAN LTD.: Amendment 39-4615. Applies to BN-2, BN2A, and BN-2B Islander Series equipped with wing tip fuel tanks and BN-2A MK. III Trislander Series (all Serial Numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To detect erosion of the wing tip tank fuel transmitter floats, which could restrict fuel flow and result in the loss of power, accomplish the following: a) Within the next 100 hours time-in-service after the effective date of this Airworthiness Directive (AD) and thereafter at intervals not to exceed 100 hours time-in-service: 1) Remove and visually inspect the wing tip tank fuel transmitter floats for evidence of cracking, fretting, or erosion in accordance with the instructions provided in the "Inspection and Rectification" section of Pilatus Britten-Norman Service Bulletin (SB) No. BN- 2/SB.154, Issue 1, dated February 12, 1982, (hereinafter referred to as the SB) or an FAA approved equivalent. 2) If any fuel transmitter float is found with cracks, fretting, or erosion during the accomplishment of the visual inspection in accordance with paragraph a)1) of this AD, prior to further flight, replace the float with a serviceable unit of the same part number and continue the repetitive visual inspections in accordance with paragraph a)1) of this AD. 3) If any fuel transmitter float is found with excessive erosion during accomplishment of the visual inspection in accordance with paragraph a)1) of this AD, prior to further flight, drain the affected tank and clean the filters, including also the fuel supply system, through the auxiliary pumps, to the engine together with all fuel filters enroute. 4) Reinstall wing tip tank fuel transmitters in accordance with instructions provided in the "Inspection and Rectification" section of the SB. b) The intervals between repetitive inspections required by this AD may be adjustedup to 10 percent of the specified inspection intervals to allow them to be accomplished concurrent with other scheduled maintenance on these airplanes. c) Aircraft may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 11, 1983.
88-04-03: 88-04-03 AEROSPATIALE: Amendment 39-5846. Applies to Model ATR-42 series airplanes, as listed in Service Bulletin ATR42-23-0002, Revision No. 1, dated March 11, 1987, certificated in any category. Compliance is required within one year of the effective date of this AD, unless previously accomplished. To prevent the loss of recorded information by continued operation of the Digital Flight Data Recorder (DFDR) and Cockpit Voice Recorder (CVR) after an accident, accomplish the following: A. Modify the DFDR and CVR power supply logic in accordance with Aerospatiale Service Bulletin ATR42-23-0002, Revision No. 1, dated March 11, 1987. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued inaccordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 21, 1988.
2013-21-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1, P2, P2+, T1, T2, and T2+ helicopters. This AD requires inspecting each linear transducer bearing (bearing) for freedom of movement and replacing the bearing if there is binding or rough turning or if there is chafing or damage on the lower side of the floor. Also, this AD requires modifying and re-identifying a certain rod. This AD was prompted by an incident involving limited control of a tail rotor because of the binding of a bearing. The actions of this AD are intended to detect and replace each bearing subject to binding, which could lead to subsequent loss of control of the helicopter.
99-12-04: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that requires revisions to the engine manufacturer's Time Limits Section (TLS) of the JT8D-200 Turbofan Engine Manual to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
93-25-15: 93-25-15 BEECH AIRCRAFT CORPORATION: Amendment 39-8779. Docket 93-NM-136-AD. Applicability: Model 400A airplanes having serial numbers RK-1 through RK-57 inclusive, RK-59, RK-60, and RK-62 through RK-66 inclusive; and Model 400T airplanes having serial numbers TT-02 through TT-30 inclusive, and TT-32; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural capability of the airframe, accomplish the following: (a) Within 200 hours time-in-service after the effective date of this AD, inspect the rivets in the escape hatch substructure to verify that the proper rivets are installed in accordance with Beechcraft Service Bulletin 2509, dated July 1993. (1) If the rivet is part number (P/N) MS20470E6, no further action is required by this AD. (2) If the rivet is not P/N MS20470E6, prior to further flight, replace the rivet with a new Cherry Max rivet or a HI-LOK fastener, in accordance with Beechcraft Service Bulletin 2509, dated July 1993. (b) As of the effective date of this AD, no person shall install any rivet having P/N MS20470AD5 in the location shown in Figure 1 of Beechcraft Service Bulletin 2509, dated July 1993, on any airplane. (c) 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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, 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. (d) 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. (e) The inspection and replacement shall be done in accordance with Beechcraft Service Bulletin 2509, dated July 1993. (NOTE: The issue date of Service Bulletin 2509 is indicated only on page 1 of the document; no other page of this document is dated.) 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on February 14, 1994.
99-11-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Model 402C airplanes. This AD requires inspecting the forward, aft, and auxiliary wing spars for cracks; repairing any cracks found; and reporting the results of the inspection to the Federal Aviation Administration (FAA). This AD is the result of an accident of one of the affected airplanes where the right-hand wing failed just inboard of the nacelle at Wing Station (WS) 87. Investigation of this accident revealed fatigue cracking of the forward main spar that initiated at the edge of the front spar forward lower spar cap. The actions specified by this AD are intended to detect and correct any cracks in the forward, aft, and auxiliary wing spars, which could result in reduced or loss of control of the airplane.
95-17-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ airplanes. This action requires modification of the left- and right-hand elevators to improve water drainage. This amendment is prompted by reports that elevator oscillations and resultant airplane pitch oscillations have occurred due to the elevator balance changes as a result of accumulation of water in the elevators. The actions specified in this AD are intended to minimize accumulation of water in the elevators, which could lead to elevator and airplane pitch oscillations with a subsequent reduction of controllability of the airplane and damage to the tail surface structure.
2022-14-01: The FAA is superseding Airworthiness Directive (AD) 2019-03- 25, which applied to certain Airbus SAS Model Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-03-25 required repetitive inspections of the center and outer wing box lower stiffeners and panels at a certain junction on the left- and right-hand sides for any cracking, and repair if necessary. AD 2019-03-25 also provided an optional modification, which would terminate the repetitive inspections. This AD was prompted by a determination that, for certain airplanes, the compliance time for the initial inspection is inadequate and must be revised. This AD continues to require the actions specified in AD 2019-03-25 with revised compliance times for certain airplanes and additional actions for certain airplanes, and expands the applicability, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-03-08: 91-03-08 LEARJET (FORMERLY GATES LEARJET): Amendment 39-6876. Docket No. 90-NM-285-AD. Applicability: Model 31 series airplanes, Serial Numbers (S/N) 001 through 023; Model 35/35A series airplanes, S/N 001 through 661; Model 36/36A series airplanes, S/N 001 through 059, 062, and 063; and Model 55/55B/55C series airplanes, S/N 001 through 144; equipped with Aerospace Lighting Corporation (ALC) inverters, Part Number (P/N) 18.95(); or Instrument and Flight Research (IFR) inverters, P/N 25-415-3-0L or 250001-240G; or Precision Winding, Incorporated inverters, P/N 6900092 or 6900054-54; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent electromagnetic interference, and smoke and/or fire in the cabin, accomplish the following: A. Within 25 hours time-in-service after the effective date of this AD, deactivate the cabinet and overhead fluorescent lighting systems, and fabricate and install placards on the deactivated circuit breakers in accordance with the accomplishment instructions specified in the following Learjet Alert Service Bulletins, all dated December 21, 1990: Model Service Bulletin 31 31-33-2A 35, 35A, 36, 36A 35/36-33-5A 55, 55B, 55C 55-33-3A NOTE: This AD applies only to airplanes with the following inverters: ALC inverters, Part Number (P/N) 18.95(); or IFR inverters, P/N 25-415-3-0L or 250001-240G; or Precision Winding, Incorporated inverters, P/N 6900092 or 6900054-54. Inverters having a different part number do not have to be deactivated. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Wichita Aircraft Certification Office (ACO), ACE-115W, FAA, Central Region, 1801 Airport Road, Room 100, Wichita, Kansas 67209. NOTE: The request should be submitted directly to the Manager, Wichita ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Wichita ACO. 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Learjet Corporation, Customer Services, P.O. Box 7707, Wichita, Kansas 67277-7707. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas. This amendment (39-6876, AD 91-03-08) becomes effective on February 12, 1991.
99-11-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires detailed visual inspections to detect corrosion or chrome plating cracks on the fuse pins of the outboard support of the main landing gear (MLG) beam. This AD also would require either installation of the existing fuse pins and repetitive inspections; or installation of newer-type fuse pins, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report indicating that corrosion was found on a fuse pin in the outboard support of the MLG beam. The actions specified by this AD are intended to detect and correct such corrosion and cracking, which could result in the failure of a fuse pin and, consequently, lead to collapse of the MLG.
80-01-07 R1: 80-01-07 R1 ROCKWELL INTERNATIONAL: Amendment 39-3658 as amended by Amendment 39-3774. Applies to Rockwell Model NA 265-60 and NA 265-80 airplanes equipped with the Raisbeck Mark Five modification in accordance with STC SA687NW or STC SA847NW. To prevent failure of the wing flap support structure accomplish the following: A. On or before 430 landings after modification by The Raisbeck Group STC SA687NW, unless already accomplished, replace the outboard flap track support plates in accordance with FAA approved Raisbeck Group Service Bulletin No. 17. B. If the flap system was previously affected by AD 79-13-02, the number of landings specified in Paragraph A may be increased by the total number of landings accomplished with inoperative flaps. C. On or before 10 further landings, unless previously accomplished, perform an eddy current inspection of the flap track support structure in accordance with FAA approved Raisbeck Service Bulletin No. 18, Rev. B, on airplanes having the following serial numbers: 306- 005, 006, 012, 024, 050, 071, 109, 116, 119, 122, 380-025. For all other serial numbers, perform the above inspection prior to 100 landings after modification by Raisbeck STC SA687NW or STC SA847NW. If cracks are found, immediately inform William M. Perrella, Engineering and Manufacturing Branch, FAA Northwest Region, telephone (206) 767-2516. Before further flight, repair cracks in accordance with a method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. D. Effective before further flight, the full flap extension speed is reduced from 180 knots IAS to 160 knots IAS and the 20 degree flap extension speed is reduced from 225 knots IAS to 180 knots IAS. Install a placard in full view of the flight crew which specifies these speeds. E. The life of the flap track support structure after modification by the Raisbeck Group STC SA687NW or STC SA847NW is limited to 900 landings, except for airplane S/N 306-116 which is limited to 450 landings. F. Reinspect the flap track support structure for cracks in accordance with FAA approved Raisbeck Service Bulletin No. 18, Rev. B, or methods approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, at intervals not to exceed 100 landings. G. Alternate modifications which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. H. Modification of the flap support structure per FAA approved Raisbeck Service Bulletins 17, dated October 5, 1979; 19, Rev. B, dated April 28, 1980; and 23, dated November 30, 1979, constitutes terminating action under the provisions of this AD. Equivalent modifications are acceptable if approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. If the optional bolts listed in Paragraph III of Raisbeck Service Bulletin 23 are used, they must be replaced at intervals not exceeding 900 landings. 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 The Raisbeck Group, 7777 Perimeter Road, Seattle, Washington 98108. Amendment 39-3658 became effective upon publication in the Federal Register and was effective earlier to all recipients of the emergency AD dated October 26, 1979. This Amendment 39-3774 becomes effective June 3, 1980.
2013-22-01: We are adopting a new airworthiness directive (AD) for Bell Model 206L-4 and 407 helicopters. This AD requires replacing or reworking certain aft bearing caps. This AD was [[Page 65179]] prompted by the manufacture of certain freewheel aft bearing caps without a lubrication channel to allow oil flow into the aft bearing support assembly. The actions of this AD are intended to prevent failure of the freewheel unit and subsequent loss of control of the helicopter.
2010-14-18: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Model 767-200, -300, and -300F series airplanes. The existing AD currently requires repetitive inspections to detect discrepancies of the 8 aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions if necessary. The existing AD also requires repetitive inspections for cracks of the closeout angle that covers the 2 aft-most fasteners in the lower tang of the midspar fitting, and related investigative and corrective actions if necessary. The existing AD also provides an optional terminating action for the repetitive inspections. This new AD reduces the compliance times for doing the inspections. This AD results from reports of cracks in the midspar fitting tangs. We are issuing this AD to detect and correct fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine.
93-11-09: 93-11-09 DE HAVILLAND, INC.: Amendment 39-8599. Docket 92-NM-205-AD. Applicability: All Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent degradation of the structural capabilities of the affected airplanes, accomplish the following: (a) For all affected airplanes: Within 6 months after the effective date of this AD, replace the six MS rivets with hi-strength Hi-Lok fasteners, Modification 7/2572, in the drag strut attachment fitting of the nose landing gear, in accordance with de Havilland Service Bulletin S.B. 7-53-32, dated March 15, 1991. (b) For airplanes having serial numbers 3 through 27, inclusive: Installation of a new outer drag strut attachment fitting, Modification 7/1328, in accordance with de Havilland Service Bulletin 7-53-31, dated December 15, 1989, as revised by Notice of Status Change 7-53-31-1, dated April 20, 1990, constitutes an acceptable alternative method of compliance with the requirements of this AD. (c) 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), ANE-170, 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. (d) 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. (e) The replacement shall be done in accordance with de Havilland Service Bulletin S.B. 7-53-32, dated March 15, 1991. The installation shall be done in accordance withde Havilland Service Bulletin 7-53-31, dated December 15, 1989; and Notice of Status Change 7-53-31-1, dated April 20, 1990, for de Havilland Service Bulletin 7-53-51, dated December 15, 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 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, New York Aircraft Certification Office, Engine and Propeller Directorate, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on July 22, 1993.
99-11-11: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France Model SA-365N, N1 and SA-366G1 helicopters, that currently requires repetitive inspections of the main gearbox (MGB) magnetic chip plug and oil filter if certain part number/modification level MGB's are installed. This new action expands the helicopter model and MGB applicability to include the SA-365N2 and N3 helicopters and all variants of the MGB. It also requires installing a MGB planetary gear shaft (gear shaft) vibration level monitoring unit (VLMU); inserting procedures into the Rotorcraft Flight Manual (RFM) for a preflight vibration check using the VLMU and inserting a related emergency procedure and limitation for an inoperative VLMU into the RFM. This action is prompted by two occurrences of gear shaft cracks. The actions specified by this AD are intended to detect cracks in the MGB planetary gear shaft, which could lead to failure of the MGB and subsequent lossof control of the helicopter.
95-01-03: 95-01-03 DASSAULT AVIATION: Amendment 39-9114. Docket 94-NM-227-AD. Applicability: Model Mystere-Falcon 50 series airplanes having serial numbers 2 through 232 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case doesthe presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent an electrical fire due to damage of the electrical wire bundles, accomplish the following: (a) Within 20 days after the effective date of this AD, measure the clearance between the electrical bundles in the left-hand cabinet and the counterbalancing actuator of the passenger door, in accordance with Dassault Aviation Alert Service Bulletin F50-A243 (F50-A39-1), Revision 1, dated November 10, 1994. (1) If the clearances are within the limits specified in the alert service bulletin, no further action is required by this AD. (2) If the clearances are outside the limits specified in the alert service bulletin, prior to further flight, reroute and clamp the wire bundles in accordance with the alert service bulletin. (b) An alternative method of compliance or adjustment ofthe 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, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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) The measuring, rerouting, and clamping shall be done in accordance with Dassault Aviation Alert Service Bulletin F50-A243 (F50-A39-1), Revision 1, dated November 10, 1994. This incorporation by referencewas 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 Falcon Jet Corporation, P.O. Box 967, Little Rock, Arkansas 72203-0967. 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. (e) This amendment becomes effective on January 18, 1995.
2022-14-08: The FAA is superseding Airworthiness Directive (AD) 2008-16- 06, which applied to all BAE Systems (Operations) Limited Model 4101 airplanes. AD 2008-16-06 required the installation of additional bonding leads, inspection of existing bonding leads for defects, inspection of fuel system pipe runs in the wings to ensure appropriate clearances are maintained, and corrective actions. This AD continues to require the actions in AD 2008-16-06, and adds a requirement to install additional bonding leads around the crossfeed valve and accomplish a resistance check. This AD was prompted by a report that there is insufficient bonding of the crossfeed valve in the fuel tank area. The FAA is issuing this AD to address the unsafe condition on these products.
99-11-05: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires repetitive displacement tests of the secondary slide in the dual concentric servo valve of the power control unit (PCU) for the rudder, and replacement of the valve assembly with a modified valve assembly, if necessary. This amendment is prompted by reports of cracking found in PCU secondary servo valve slides. The actions specified by this AD are intended to prevent failure of the secondary slide and consequent rudder hardover and reduced controllability of the airplane.
91-11-12: 91-11-12 BRITISH AEROSPACE: Amendment 39-7010. Docket No. 91-NM-16-AD. Applicability: All Viscount Model 810 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent in-flight separation of an entrance or emergency door from the airplane and subsequent decompression of the passenger cabin, accomplish the following: A. Within 90 days after the effective date of this AD, perform a non-destructive testing (NDT) X-ray inspection of the forward passenger door, and of the rear entrance and rear emergency doors, for incorrectly machined door operating torque shaft coupling sleeves, in accordance with Viscount Preliminary Technical Leaflet (PTL) No. 194, Revision 1, dated December 1989. B. If incorrectly machined door operating torque shaft coupling sleeves are found, prior to further flight, replace the sleeves with correctly machined serviceable parts in accordance with Viscount PTL No. 194, Revision 1, dated December 1989. C. 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 Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7010, AD 91-11-12) becomes effective on July 1, 1991.