Results
90-21-06: 90-21-06 DORNIER: Amendment 39-6755. Docket No. 90-CE-24-AD. Applicability: Models Do28D and Do28D-1 (all serial numbers) airplanes, certificated in any category. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent engine mount failure, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD visually inspect the riveted connections between the L-section and formed sheet of the right-hand and left-hand engine mounts. (1) If no loose or damaged rivets are found, reinspect the connections at intervals of 100 hours TIS thereafter. (2) If any loose or damaged rivets are found, prior to further flight remove and replace any damaged rivets, and replace all universal and Huck blind rivets having a diameter of 3.2mm (.126 in) with steel blind rivets having a diameter of 4.0mm in accordance with the instructions contained in Dornier Service Bulletin No. 1131-1613, dated August 2, 1989. Reinspect the connections at intervals of 100 hours TIS thereafter. (b) Airplanes may be flown in accordance with FAR 21.197 to a location were this AD may be accomplished. (c) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. All persons affected by this directive may obtain copies of the document referred to herein upon request to Dornier Luftfahrt GmbH, P.O. Box D-8031 Wessling, Federal Republic of Germany; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6755, AD 90-21-06) becomes effective on November 13, 1990.
78-21-02: 78-21-02 BELL: Amendment 39-3317. Applies to all Bell Helicopter Models 204B, 205A, 205A-1, and 212 modified by Chadwick, Inc., STC's SH149WE or SH17NW. Prior to further flight involving external-load operations over congested or densely populated areas, replace Chadwick, Inc., load cell link assembly P/N 47-40200-19 with parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Northwest Region. This amendment is effective October 12, 1978, and was effective earlier for all recipients of the airmail letter dated September 18, 1978, which contained this amendment.
90-24-01: 90-24-01 TEXTRON LYCOMING: Amendment 39-6760. Docket No. 89-ANE-13. Applicability: ALF502R series turbofan engines installed on, but not limited to British Aerospace BAE146 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent complete loss of engine power, uncontained disk failure, and possible damage to the aircraft, accomplish the following: (a) Inspect and recoat with "Sermetel W", "ALSEAL-518" or aluminum paint, third stage high compressor (HC) disks in accordance with Textron Lycoming Service Bulletin (SB) ALF502R-72-203, Revision 2, dated August 8, 1990, as follows: (1) For those third stage HC disks with 7,000 cycles since new (CSN) or greater on the effective date of this AD, within the next 500 cycles in service (CIS) not to exceed 8,500 CSN. (2) For those third stage HC disks with less than 7,000 CSN on the effective date of this AD, at or prior to accumulating a total of 7,500 CSN. (b) Reinspect third stage HC disksrecoated with aluminum paint as follows: (1) For disks inspected in accordance with Textron Lycoming SB ALF502R 72-203, Revision 2, dated August 8, 1990, at intervals not to exceed 6,000 CIS from last inspection. (2) For disks inspected in accordance with Textron Lycoming SB ALF502R 72-218, Revision 1, dated December 1, 1989, at intervals not to exceed 1,500 CIS from last inspection. Remove the modified second stage compressor spacer, Part Number 2-100-047R10, from service prior to accumulating 5,000 additional CIS since modification, not to exceed 16,600 CSN. (3) For disks inspected in accordance with Textron Lycoming SB ALF502R 72-237, dated November 30, 1989, at intervals not to exceed 1,000 CIS from last inspection. Remove the modified second stage compressor spacer, Part Number 2-100-047R10, from service prior to accumulating 5,000 additional CIS since modification, not to exceed 16,600 CSN. (c) No reinspection is required for those third stage HC disks recoatedwith "SERMETEL W" or "ALSEAL-518" surface finish in accordance with Textron Lycoming SB ALF502R 72-203, Revision 2, dated August 8, 1990. (d) Actions accomplished in accordance with SB ALF502R 72-203, dated January 31, 1989; SB ALF502R 72-203, Revision 1, dated June 16, 1989; or with SB ALF502R 72-218, dated May 26, 1989, in complying with Telegraphic Airworthiness Directive T89-13-52 dated June 22, 1989, are considered to be in compliance with the corresponding requirements of this AD, if applicable. (e) 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. (f) 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 (schedule) times specified 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 Executive Park, Burlington, Massachusetts 01803. The inspection procedures shall be done in accordance with the following Textron Lycoming Service Bulletins: Service Bulletin No. Page No. Issue/Revision Date ALF502R 72-203 1-4, 6 2 August 8, 1990 ALF502R 72-203 5 1 June 16, 1989 ALF502R 72-218 1, 2, 3, 4, 5, 6, 9 1 December 1, 1989 ALF502R 72-218 7, 8 original May 26, 1989 ALF502R 72-237 1-12 original November 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 Textron Lycoming, 550 Main Street, Stratford, Connecticut 06497. 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, NW, Room 8301, Washington, DC 20591. Airworthiness Directive 90-24-01 supersedes TAD T89-13-52 dated June 22, 1989. This amendment (39-6760, AD 90-24-01) becomes effective on November 13, 1990.
2017-12-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 series airplanes. This AD requires repetitive inspections for damage of a certain drive arm assembly, and related investigative and corrective actions if necessary. This AD was prompted by a report indicating that during an inspection associated with a flap, the extend overtravel stops on an actuator crank arm assembly were making contact with an adjacent drive arm assembly when the flaps were retracted. We are issuing this AD to address the unsafe condition on these products.
75-11-02: 75-11-02 MAULE AIRCRAFT CORPORATION: Amendment 39-2199. Applies to the Models M-4-210 serial numbers 1001 through 1045; M-4-210C serial numbers 1001C through 1117C; M-5-210C serial numbers 6001C through 6069C, 6072C, 6076C, 6077C, 6079C, 6080C, 6084C, and 6087C, certificated in all categories. Compliance required within the next 30 hours' time in service after the effective date of this AD unless already accomplished. To prevent fuel leakage in the cabin area and allow fuel line flexibility, accomplish the following or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region: 1. Turn the fuel tank selector valve to off position. 2. Remove the engine fuel injector return line from the firewall to the fuel header tank. (Line located in cabin wall to left of pilots feet.) 3. Short line inspection - Inspect the short line connected at the firewall to the check valve for cracking around the flares. If cracks are found,replace line with a serviceable line in accordance with Advisory Circular 43.13. 4. Long line replacement - Remove existing long line and install an 8-inch long, 1/4 inch diameter aluminum tube, between the return check valve and the header tank, using appropriate tube and fittings. This line is to incorporate a 1.5 to 2.0 inch diameter loop in the middle. Use caution when bending the tubing to prevent kinking. This looped tubing must be installed with the plane of the loop horizontal so that no low undrainable spots exist. 5. The check valve must be reinstalled with the arrow pointing aft. 6. Functional check the return line for leaks and repair as necessary. Maule Aircraft Corporation Service Letter 31 covers the same subject. This amendment becomes effective May 19, 1975.
75-09-09: 75-09-09 BELL: Amendment 39-2179. Applies to Model 206A and 206B helicopters, serial numbers 4 through 497, certificated in all categories. To prevent possible failure of the tail rotor control tube assembly, P/N 206-010-743-13, compliance with items 1 through 5 of Bell Helicopter Company Service Bulletin 206-75-2, dated February 18, 1975, or later FAA approved revision, is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. 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 Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, 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 Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective April 23, 1975.
75-18-02: 75-18-02 CAPRONI VIZZOLA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39-2340 as amended by Amendment 39-2430 is further amended by Amendment 39-2726. Applies to Caproni Calif A-21 series glider, serial numbers 201, 202, and 204 and subsequent, certificated in all categories. Compliance is required as indicated. To prevent aileron flutter, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished: (1) Install an operating limitations placard near the airspeed indicator reading - "DO NOT EXCEED 124 MPH - 108 KNOTS". (2) Inspect the aileron control driving cones for cleanliness. NOTE: To gain access to the driving cones, located in the fuselage under the central segment of the wing, disassemble the wing from the fuselage. Avoid entry of solid foreign material and dirt particles in driving cones upon reassembly. (3) Inspect the aileron system for free play by holding thetrailing edge of one aileron at the wing tip end and measuring the distance through which the trailing edge of the other aileron at wing tip end travels from upward to downward position when moved by hand without causing elastic deflection of the aileron. If the free play exceeds 3 MM (0.118 inch), rerig the aileron system. (b) Inspect the aileron system for cleanliness and free play, and rerig as necessary, in accordance with paragraphs (a)(2) and (a)(3) of this AD, at intervals not to exceed 50 hours time in service from the last inspection. (CAPRONI VIZZOLA COSTRUZIONI AERONAUTICHE S.p.A. Mandatory Technical Service Bulletin T.B. No. 75.05 R.A.I. dated July 29, 1975, refers in part to this subject.) (c) The placard required by paragraph (a) of this AD may be removed and the inspections required by paragraph (b) of this AD may be discontinued upon the incorporation of the following applicable modification: (1) For gliders with serial numbers 201, 202, 204 through208, 210, and 212 through 214, replace the fiberglass ailerons with metal ailerons, P/N A24A2, in accordance with paragraph (a) of the Instruction section of Caproni Vizzola Costruzioni Aeronautiche Technical Bulletin No. 76.08, undated, or an FAA-approved equivalent. (2) For gliders with serial numbers 211 and 215 through 218, replace the metal ailerons with modified metal ailerons, P/N A24Al, in accordance with paragraph (b) of the Instruction section of Caproni Vizzola Costruzioni Aeronautiche Technical Bulletin No. 76.08, undated, or an FAA-approved equivalent. (3) For glider serial number 209, replace the metal ailerons with modified metal ailerons, P/N A24B1, in accordance with paragraph (c) of the Instruction section of Caproni Vizzola Costruzioni Aeronautiche Technical Bulletin 76.08, undated, or an FAA-approved equivalent. (4) For gliders with serial numbers 219 through 228, replace the existing metal ailerons with modified metal ailerons, P/N A24B1, in accordance with the Instruction section of Caproni Vizzola Costruzioni Aeronautiche Technical Service Bulletin 76.07. undated, or an FAA-approved equivalent. Amendment 39-2340 became effective August 22, 1975. Amendment 39-2430 became effective November 28, 1975. This amendment, 39-2726, becomes effective September 30, 1976.
2017-11-13: We are superseding Airworthiness Directive (AD) 98-13-14, for certain Airbus Model A320-211, -212, and -231 airplanes. AD 98-13-14 required repetitive inspections of certain fastener holes of the aft fuselage, and corrective action if necessary. This new AD continues to require the actions in AD 98-13-14, with revised inspection compliance times. This AD was prompted by identification of cracks in the fastener holes of the former junction of the aft fuselage, which occurred during a fatigue test; and a determination that certain compliance times specified in AD 98-13-14 must be reduced. We are issuing this AD to address the unsafe condition on these products.
2017-10-13: We are superseding airworthiness directive (AD) 2015-17-19 for all Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. AD 2015-17-19 required inspection of the fan case low-pressure (LP) fuel tubes and associated clips and the fuel oil heat exchanger (FOHE) mounts and associated hardware. This AD requires an engine modification, which terminates the repetitive inspections. This AD was prompted by fractures on the LP fuel return tube at mid-span locations that were found with resulting fuel leaks. We are issuing this AD to correct the unsafe condition on these products.
70-06-07: 70-06-07 AVIONS MARCEL DASSAULT/SUD-AVIATION: Amdt. 39-958. Applies to all series Fan Jet Falcon airplanes with Microturbo Saphir I and II APU's installed. Compliance is required within the next 75 hours of APU operation, unless already accomplished. To prevent a fire hazard due to continued operation of the APU oil pump motor after APU shutdown, replace Equipment Construction Electrique (ECE) relay P/N 1475-7 with ECE contactor P/N 100CC01-A in accordance with Microturbo Saphir I Service Bulletin 49.10.39, dated September 30, 1969; or Microturbo Saphir II Service Bulletin 49.11.08, Revision No. 1, dated September 30, 1969, as applicable, or later SGAC-approved issues, or FAA-approved equivalents. This amendment becomes effective April 18, 1970.