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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.)