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86-16-01: 86-16-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-5364. Applies to Models N22B and N24A (all serial numbers) airplanes certificated in any category, unless Service Bulletin (S/B) No. NMD-27-34 (Mod N642) has been accomplished. Compliance: Required within 100 hours time-in-service after the effective date of this AD or one calendar year after the effective date of this AD, whichever occurs first, unless already accomplished. To prevent jamming of the rudder pedals accomplish the following: (a) Modify the airplane sidewall structure and rudder pedals in accordance with Paragraph 2. "Accomplishment Instructions" of GAF S/B No. NMD-27-34 dated October 21, 1985. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. (c) An equivalent method of compliance with this AD if used, must be approved by the Manager, Western Aircraft Certification Office, ANM-170W, Northwest Mountain Region, FAA, Post Office Box 92007, Worldway Postal Center, Los Angeles, California 90009-2007. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Government Aircraft Factories, 226 Lormier Street, Fisherman's Bend, Port Melbourne, Victoria, Australia 3207, or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106 or the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California 90009-2007. This amendment becomes effective August 28, 1986.
87-03-12: 87-03-12 DEHAVILLAND: Amendment 39-5549. Applies to DHC-6 Models 1, 100, 200, and 300 airplanes certificated in any category, when fitted with side folding cabin utility seats. Compliance: Required as indicated, unless already accomplished. To prevent disengagement of the utility seat forward legs from the floor mounting rail, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished within the last 25 hours TIS, and at subsequent intervals not to exceed 50 hours TIS thereafter, attempt to move the lower end of each forward leg sideways into the open part of the keyhole slot using as much force as can be exerted by hand. If the leg can be removed from the keyhole slot, remove the seat from service until Modification No. 6/1828 is incorporated in accordance with the ACCOMPLISHMENT INSTRUCTIONS of DeHavilland Service Bulletin (S/B) No. 6/447, Revision C, dated May 16, 1986. (b) Repeat thecheck in paragraph (a) of this AD each time the seats are moved from stowed to deployed position. (c) The check required by paragraph (b) of this AD may be accomplished by a flightcrew member, certificated under FAR 61 or FAR 63 rules, briefed on the procedure. (d) When Modification No. 6/1828 is incorporated in accordance with the ACCOMPLISHMENT INSTRUCTIONS of DeHavilland S/B No. 6/447, Revision C, on each seat, subsequent checks required by this AD are no longer required on that seat. (e) An equivalent means of compliance may be used when approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, ANE-170, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This AD supersedes AD 84-07-07, Amendment 39-4841. This amendment becomes effective on February 13, 1987.
88-26-51: 88-26-51 PRATT & WHITNEY CANADA: Amendment 39-6275. Final Rule of previously issued telegraphic AD. Applicability: Pratt & Whitney Canada (PWC) PW115/118/118A turboprop engines prior to Serial Number (S/N) PCE 115033, and PW120/120A/121 turboprop engines prior to S/N PCE 120174. Compliance: Required as indicated, unless already accomplished. To prevent an uncontained engine failure resulting from low cycle fatigue failure of certain high pressure turbine (HPT) components, accomplish the following: (a) Determine upon receipt of this AD the cyclic life accumulated on the HPT front cover, HPT rear cover, and HPT disk, in accordance with PWC Service Bulletin (SB) 20002, Revision 4, dated November 21, 1988, paragraph 2.D.(1), as follows: (1) For engines which have not incorporated PWC SB 20133, dated September 14, 1987, calculate the total cyclic life accumulated using a flight count factor (FCF) of 1.5 in accordance with the formula found in PWC SB 20002, Revision 4, paragraph 2.D.(1). (2) For engines which have incorporated PWC SB 20133, dated September 14, 1987, calculate the total cyclic life accumulated prior to the incorporation of PWC SB 20133 using an FCF of 1.5, plus the total cycles accumulated after the incorporation of PWC SB 20133 using an FCF of 1.0, in accordance with the note in PWC SB 20002, Revision 4, paragraph 2.D.(1). (b) Remove from service and replace with a serviceable part within 25 cycles in service (CIS) from the receipt of this AD, those HPT front covers, HPT rear covers, or HPT disks which have accumulated 14,975 CIS or greater upon receipt of this AD, as calculated in accordance with paragraph (a)(1) or (a)(2) of this AD. (c) Remove from service and replace with a serviceable part at or prior to accumulating 15,000 CIS, those HPT front covers, HPT rear covers, or HPT disks which have accumulated less than 14,975 CIS upon receipt of this AD, as calculated in accordance with paragraph (a)(1) or(a)(2) of this AD. (d) 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. (e) 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 adjustment to the compliance times specified in this AD, may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The determination of the cyclic life accumulated on the HPT front cover, HPT rear cover, and HPT disk shall be accomplished in accordance with PWC SB 20002, Revision 4, dated November 21, 1988. 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 Pratt& Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1. 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, or at the Office of the Federal Register, 1100 L Street, Room 8301, Washington, D.C. 20591. This amendment (39-6275, AD 88-26-51) becomes effective on September 22, 1989, as to all persons except those persons to whom it was made immediately effective by TAD T88-26-51, issued December 28, 1988, which contained this amendment.
2006-23-16: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD requires modifying the nose landing gear. This AD results from reports of loss of the nose wheel assembly. We are issuing this AD to prevent the nose wheel nut from loosening, and consequently, the nose wheel assembly detaching from the airplane; and to prevent the nose wheel clamping loads from applying to the machined radius at the root of the stub axle, which could result in damage to the nose landing gear.
2018-20-10: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by an inspection on the production line that revealed evidence of paint peeling on the forward and aft cargo frame forks around the hook bolt hole. This AD requires a detailed visual inspection for any deficiency of the frame forks around the hook bolt hole on certain forward and aft cargo doors and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
85-08-02: 85-08-02 TELEDYNE CONTINENTAL MOTORS: Amendment 39-5029. Applies to TCM new and rebuilt engines, IO-470-C, S/Ns 242071 through 242076; O-470-K, S/Ns 49390 through 49394; O-470-L, S/Ns 69640 through 69643; O-470-M, S/Ns 54141 and 54142; O-470-R, S/Ns 238170, 238171, 238176 through 238197, 238199 through 238211, 238213, 238215 through 238218, 238223, 238224, 466653 and 466654; O-470- S S/N 226443, 226444, 226446 through 226457; and all cylinder assemblies P/N 646680A4 and 646680A5 in inventory or installed on engines IO-470-C, O-470-G, -K, -L, -M, -R, -S since March 1984. After April 30, 1985, compliance is required as indicated unless already accomplished: (a) Compliance required within the next 10 hours time in service for the affected engines with cylinder assemblies having P/Ns 646680A4 and 646680A5 installed. (b) Compliance is required prior to installation on an engine for uninstalled cylinder assemblies with P/Ns 646680A4 and 646680A5. To prevent possible valve stemwear, oil contamination, valve seizure, and total loss of engine power, accomplish the following: (a) Inspect each specified engine and cylinder assembly for the P/N stamped on the base flange of the cylinder. NOTE: This AD applies only to the specified engines and cylinder assemblies having P/Ns 646680A4 and 646680A5. (1) If an inspection reveals no specified engines or cylinder assemblies in stock, no further action is required by this AD. (2) If inspection of any of the specified engines reveals no cylinder assemblies with P/Ns 646680A4 or 6466680A5, make appropriate engine log book entry stating in effect that this engine has been inspected in accordance with this AD. Return engine to service. No further action is required by this AD. (3) If inspection of any of the specified engines or aftermarket stock reveals cylinder assemblies having P/Ns 646680A4 or 646680A5, comply with paragraphs (b), (c), (d), (e), and (f). (b) Remove the cylinder assemblies (P/N 646680A4 and/or P/N 646680A5) from stock or from the engine, as applicable, and replace the exhaust valve, P/N 626540, with P/N 637781 exhaust valve. NOTE: The exhaust valves, gaskets, and seals necessary to accomplish this modification are listed by P/N in TCM SB M85-3, dated February 4, 1985, and can be purchased through TCM distributors. (c) Inspect the valve guide for any metal transferred from the valve stem. If present, remove using a 1/4- inch diameter by approximately 8-inch long mandrel wrapped with 180 grit crocus paper. Polish the guide only enough to remove the transferred material. After polishing, the guide inside diameter must not exceed the service limit of 0.4405 inch. (d) Restamp the cylinder assemblies with P/N 646680A7 after replacing the valves and polishing the valve guides, if required. (e) Return the cylinder assemblies to stock or reinstall on the engine, as applicable. NOTE: Reinstall cylinder assemblies using the procedures outlined in the Maintenance and Overhaul Manual for O-470 and IO-470 Series Aircraft Engines published by TCM under Form No. X30022A. (f) Make appropriate maintenance record entry showing compliance with this AD. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337. 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 this document from the manufacturer may obtain copies upon request to Teledyne Continental Motors, Aircraft Products Division, P.O. Box 90, Mobile, Alabama 36601. These documents also may be examined at the Office of the Regional Counsel, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and in the Central File Room of the Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337, weekdays, except Federal Holidays, between the hours of 8:00 a.m. and 4:30 p.m. This amendment becomes effective on April 15, 1985.
2006-23-11: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce, plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires initial and repetitive on-wing or in-shop inspections of the high pressure (HP)/intermediate pressure (IP) turbine bearing oil feed tube heat shield. This AD results from a report that a damaged outer heat shield caused fretting of the oil feed tubes. We are issuing this AD to prevent an uncontained failure of the HP turbine disc and damage to the airplane.
2018-19-22: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF34-10A16, CF34-10E2A1, CF34-10E5, CF34- 10E5A1, CF34-10E6, CF34-10E6A1, CF34-10E7, and CF34-10E7-B turbofan engines with certain high-pressure turbine (HPT) front rotating air seals. This AD requires replacement of the affected HPT front rotating air seal. This AD was prompted by cracks found in the HPT front rotating air seal. We are issuing this AD to address the unsafe condition on these products.
2006-23-13: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 airplanes. This AD requires inspecting the three-phase circuit breakers and three-phase circuit breaker panels for discrepancies; and fixing any discrepancy and replacing unserviceable units with new units, if necessary. This AD results from reports of three-phase circuit breakers overheating on in- service airplanes. We are issuing this AD to prevent failure of a three-phase circuit breaker. Such failure could prevent an electrical load from being isolated from its electrical supply, which could result in smoke or fire in the flight deck.
2000-11-15: This amendment adopts a new airworthiness directive (AD), that requires revisions to Chapter 5, Airworthiness Limitations section, of the Honeywell International Inc. ALF502R and LF507 series Engine Manuals to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This action 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, which 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 enginefailure and damage to the airplane.
89-02-04: 89-02-04 BOEING: Amendment 39-6101. Applicability: Model 737 series airplanes, line numbers 1 through 446, certificated in any category. \n\n\tCompliance: Required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent collapse of the nose landing gear, accomplish the following: \n\n\tA.\tReplace the aluminum nose landing gear actuator support fitting with a steel fitting, in accordance with Boeing Service Bulletin 737-53-1119, dated September 22, 1988. \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 Maintenance Inspector (PMI), who may add any comments 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, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6101, AD 89-02-04) becomes effective February 8, 1989.
2004-03-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727-100C, 727-200F, and 727C series airplanes, that requires repetitive open-hole high frequency eddy current inspections for cracks in the fuselage skin, strap (bearstrap), and doubler at the forward and aft hinge fittings for the main deck cargo door, and repair of any cracks found. This action is necessary to detect and correct such cracks, which could reach critical crack length and result in rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
58-07-06: 58-07-06 VICKERS: Applies to All Viscount 700 Series Aircraft Fitted With Heavy- Duty Wing Root Terminals and Aluminum Cables, Incorporating Modification D.1255. Compliance required as indicated. Cases have occurred of heavy-duty wing root terminals with their associated aluminum cables overheating as a result of poor electrical contact between the aluminum cable lug and the wing root terminal assembly. The poor electrical contact is attributed to the relaxation of the connection and the spreading and indentation of the aluminum cable lug by repetitive torque loading. To prevent the possibility of damage to the cable lug, a special washer, 80236 Part 3043, has been introduced by Mod. D.2628 to replace the existing washer 72436 Part 2069. The new washer is of increased thickness with an electro-tinned finish and has an outside diameter equal to the width of the cable lug. Vickers-Armstrong has issued the following corrective measures which the British Air registration Board considers mandatory. The FAA concurs and considers compliance therewith mandatory. Inspect all wing root connections for signs of looseness and overheated condition within the next 135 flying hours and take the following action: 1. Where signs of overheat are apparent the wing root terminal and cable lug assembly should be dismantled, and the overheated cable and components renewed. 2. Where loose connections are found these should be retightened after first inspecting the cable lug to ensure that the faces of the lug are clean, flat and free from signs of burning. 3. If signs of burning or damage are found on either face of the lug when complying with the recommendations in paragraphs 1 and 2, the lug and its associated cable should be replaced. 4. Where no signs of overheated or loose connections are found, existing terminal connections may be considered serviceable. All wing root connections should, however, be further inspected within every subsequent 135 flying hours until the new washer 80236 Part 3043 is fitted in place of washer 72436 Part 2069. 5. All wing root connections must have washer 80236 Part 3043 installed within 800 flying hours. (Vickers-Armstrong PTL No. 186, Issue 1, dated February 11, 1958, and Modification Bulletin No. D.2628 covers the same subject.)
2018-19-15: We are adopting a new airworthiness directive (AD) for certain GEVEN S.p.A. (Geven) Type D1-02 and D1-03 seat assemblies. This AD was prompted by a report that seat belt attachment bolts were found detached or partially detached from the seat. This AD requires inspection, torque verification, and modification of certain model seats. We are issuing this AD to address the unsafe condition on these products.
2018-19-27: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000EX airplanes. This AD was \n\n((Page 50480)) \n\nprompted by the manufacturer revising the airplane maintenance manual (AMM) maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2006-23-03: The FAA adopts a new airworthiness directive (AD) for all B-N Group Ltd. BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R series (all individual models included in Type Certificate Data Sheet (TCDS) A17EU, Revision 16, dated December 9, 2002) airplanes. This AD requires you to inspect the horizontal stabilizer attachment bolts and anchor nuts for damage and wear and replace damaged and/or worn parts with new, modified parts. If no damaged or worn parts are found during the inspection, this AD requires you to replace the horizontal stabilizer attachment bolts and anchor nuts at a specified time with new, modified parts. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. We are issuing this AD to detect and correct damaged and/or worn horizontal stabilizer attachment bolts and anchor nuts, which could result in failure of the horizontal stabilizer. This failure could result in loss of control.
2006-23-01: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to do repetitive eddy-current, non-destructive inspections of the nose skin and adjacent structure above the left and right main landing gear bay and repetitive visual inspections of the forward support structure of the floor panel for crack damage. If you find any crack damage, this AD requires you to contact Pilatus to obtain a repair solution and incorporate the repair. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct cracks in the nose skin and adjacent structure above the left and right main landing gear bay and in the forward support structure of the floor panel. Crack propagation in certain areas could lead to failure of the main wing torsion box, which could result in loss of control.
2018-19-07: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by a report of yellow hydraulic system failure, including both braking accumulators, due to failure of the parking brake operated valve (PBOV). This AD requires replacement of a certain PBOV with a different PBOV. We are issuing this AD to address the unsafe condition on these products.
2006-23-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as during production installation of the Garmin G1000 supplemental type certificate (STC) some parts of the installed fuel system indicating system were contaminated with particles from the manufacturing process. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 28, 2006. The Director of the Federal Register approved the incorporation by reference of Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB-40-048/2, Revision 2, dated September 26, 2006; and Work Instruction WI-MSB-40.048/2, Revision 2, dated September 26, 2006, listed in this AD as of November 28, 2006. We must receive comments on this AD by December 8, 2006.
2006-23-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 airplanes. This AD requires modifying the airplane and the engine/nacelle to install a third line of defense against inadvertent deployment of the thrust reverser in flight. This AD also requires two other actions that must be accomplished before or concurrently with the modification: installing a structural change in the fan cowl to avoid interference; and installing a dedicated, shielded electrical circuit. This AD results from a report that the manufacturer has developed a third line of defense against the inadvertent deployment of the thrust reverser of Model A300 airplanes that are equipped with General Electric CF6-50 series engines (in accordance with FAA guidelines). We are issuing this AD to prevent inadvertent deployment of the thrust reverser in flight, which could result in reduced controllability of the airplane.
86-17-04: 86-17-04 BOEING: Amendment 39-5369. Applies to all Model 757-200 series airplanes listed in Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, certificated in any category. \n\n\tTo detect nuts that have insufficient self-locking torque characteristics, installed on the nose gear door actuator attachment, main landing gear jury brace support attachment, main landing gear forward trunnion drag fitting aft attachment, and the P&W 2037 engine front evener bar attachment, accomplish the following, unless already accomplished: \n\n\tA.\tWithin the next 90 days after the effective date of this AD, check the Category II self-locking nuts, P/N BACN10JC12CM or BACN10JC12CD, except the rudder pedal adjustment cable retainer self-locking nut, for proper self-locking torque in accordance with Paragraph II of Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, or later FAA- approved revision. If any self-locking nut is found not to meet the self-locking torque criteria of Boeing Service Letter 757-SL-27-24-B, dated June 2, 1986, or later FAA-approved revision, it must be replaced prior to further flight with a nut which meets the self-locking torque criteria. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provide an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle AircraftCertification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 5, 1986.
2018-19-23: We are superseding Airworthiness Directive (AD) 2013-01-02, which applied to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and Model 757-200, 757- 200PF, and 757-300 series airplanes. AD 2013-01-02 required replacing the control switches of certain cargo doors. This AD requires replacement of certain cargo door control switches with a new, improved switch; installation of an arm switch in certain cargo doors; operational and functional tests; and applicable on-condition actions. This AD also adds airplanes to the applicability. This AD was prompted by reports of uncommanded cargo door operation. We are issuing this AD to address the unsafe condition on these products.
87-20-01: 87-20-01 AEROSPATIALE: Amendment 39-5727. Applies to Model SN601 Corvette airplanes, certificated in any category, except those airplanes on which Modification No. 1390 (Service Bulletin 73-1, replacement of fuel anti-ice additive system by a fuel heating system), has been accomplished. Compliance is required as indicated, unless previously accomplished. To prevent loss of power due to ice clogging of low pressure fuel filters, accomplish the following: A. Within six months after the effective date of this AD, replace the low pressure fuel filters (P/N 433-E25-2) with modified filters (P/N 433-E25-21), in accordance with Aerospatiale Service Bulletin No. 28-10, dated April 25, 1986. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective October 19, 1987.
2006-23-07: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removing from service certain sets of fan blade annulus fillers at a new life limit. This AD results from six reports of fan annulus filler release into the engine. We are issuing this AD to prevent a dual-engine shutdown on twin-engine airplanes.
2006-22-05: The FAA is superseding an existing airworthiness directive (AD), which applies to various aircraft equipped with certain Honeywell Primus II RNZ-850( )/-851( ) integrated navigation units (INUs). That AD, as one alternative for compliance, provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV-850 navigation receiver module (NRM), which is part of the INU. In lieu of accomplishing this inspection, and for aircraft found to have an affected NRM, the existing AD provides for revising the aircraft flight manual to include new limitations for instrument landing system approaches. This new AD requires inspecting to determine whether certain modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable; as well as further modifications to address additional anomalies. This AD results from reports indicating that erroneous glideslope indicationshave occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has an accurate glideslope deviation indication. An erroneous glideslope deviation indication could lead to the aircraft making an approach off the glideslope, which could result in impact with an obstacle or terrain.