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83-24-10 R1: 83-24-10 R1 BRITISH AEROSPACE: Amendment 39-4780 as amended by Amendment 39- 5053. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated unless already accomplished. To detect cracking and corrosion and to prevent structural failure of the fuselage pressure vessel with the resultant cabin depressurization, accomplish the following: A. Within the next 12 months after the effective date of this AD, unless accomplished within the last 2 years, and thereafter at intervals not to exceed 3 years from the last inspection, visually inspect for corrosion and cracks the interior of the lower fuselage skin between stations 416-456 and stringers 32(LH) and 32(RH) and the interior of the lower fuselage skin between stations 630-690 and stringers 32(LH) and 32(RH), and ensure that drain paths in these areas are unobstructed, in accordance with paragraphs 2.1.1 and 2.1.2 of British Aerospace Alert Service Bulletin 53-A-PM5632, dated August 18, 1978. B. On airplanes having long range fuel tanks or water injection tanks installed, accomplish the instructions of paragraph 2.1.3 of the service bulletin. C. If cracks or corrosion are found during any inspection required by this AD, before further flight, rework or repair in accordance with Structural Repair Manual, Chapters 53-01-0 or 53-02-0 as appropriate, and continue the repetitive inspections at the intervals specified in paragraph A. of this AD. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. 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 inspections and/or modifications required by this AD. Amendment 39-4780 became effective January 15, 1984. This Amendment 39-5053 becomes effective June 4, 1985.
2016-11-11: We are adopting a new airworthiness directive (AD) for EVEKTOR, spol. s.r.o. Models L 13 SEH VIVAT and L 13 SDM VIVAT gliders (type certificate previously held by AEROTECHNIK s.r.o.). This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as lack of distinct color marking of the elevator drive. We are issuing this AD to require actions to address the unsafe condition on these products.
83-15-04: 83-15-04 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 4695. Applies to Models P68, P68B, P68C, P68C-TC and P68 Observer (all serial numbers (S/N) up to S/N 289, excluding S/Ns 234, 256, 259, 269, and 288) airplanes certificated in any category. Compliance: Required within 50 hours time-in-service from the effective date of this AD, unless already accomplished. To preclude loosening of the stabilator support brackets, accomplish the following: a) Check and correct, if necessary, the torque of the AN4-6A bolts which attach the horizontal stabilator torque tube support brackets to the fuselage frame (ref. Parts Catalog P68B, Figure No. 5.2, Item No. 33; or Parts Catalog P68C, Figure No. 5.3, Item No. 36). NOTE: The correct torque value for these bolts is 0.9 to 0.950 Kpm; 78 to 83 in. lbs. b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. c) 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. Partenavia Service Bulletin No. 57 dated March 7, 1983, covers the subject matter of this AD. This amendment becomes effective on August 4, 1983.
2016-11-09: We are adopting a new airworthiness directive (AD) for Turbomeca S.A. Arriel 1D and 1D1 turboshaft engines with a pre- modification (mod) TU357 gas generator module (M03), installed. This AD requires removing the pre-modification (mod) TU357 gas generator module (M03) and replacing with a part eligible for installation. This AD was prompted by reports of divergent rubbing between the piston shaft small diameter labyrinth and the rear bearing support. We are issuing this AD to prevent failure of the labyrinth seal and engine, in-flight shutdown, and loss of control of the helicopter.
82-03-03: 82-03-03 McDONNELL DOUGLAS: Amendment 39-4306. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, and -40 series airplanes certificated in all categories. \n\nTo assure that the DC-10 wing slats remain extended even if the slat control system sustains severe damage, accomplish the following: \n\nUnless already accomplished, compliance is required with paragraphs A and B on or before January 31, 1983, or in accordance with a schedule of accomplishment approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\nA.\tModify the leading edge slat servo system and replace the outboard slat system follow-up cables as outlined in the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 27-187, original issue, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\nB.\tInstall balanced pressure relief valves in hydraulic systems No. 1 and No. 3slat extend lines, left and right wing, as outlined in the Accomplishment Instructions of McDonnell Douglas DC-10 Service Bulletin 27-189, original issue, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\nC.\tWithin the next 2000 flight hours after accomplishment of the modifications noted in paragraph A above, and at intervals not to exceed 4000 flight hours thereafter, visually inspect the balance spring assemblies and outboard slat follow-up cables, left and right wing, for integrity of installation. \n\nD.\tWithin the next 4,000 flight hours after accomplishment of the modifications noted in paragraph B above, and at intervals not to exceed 4,000 flight hours thereafter, functionally check for proper operation of the outboard slat relief valves as outlined in the Accomplishment Instructions, paragraph (E) of McDonnell Douglas DC-10 Service Bulletin 27-189, original issue, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\nE.\tUpon the request of an operator, an FAA maintenance inspector, subject to prior approval by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region, may adjust the repetitive intervals specified in paragraphs C and D of this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator. \n\nF.\tAlternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Mountain Region. \n\nG.\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\nThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\nAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle Washington 98108, or 4344 Donald Douglas Drive, Long Beach, California 90808. \n\nThis amendment becomes effective February 25, 1982.
52-12-02: 52-12-02 CURTISS-WRIGHT: Applies to all Model C-46 Series aircraft operated under CAR Part 42. Compliance required as indicated. In accordance with CAR 42.11 and to comply with air carrier standards, the main passenger cabin door locking means on all C-46 aircraft used for air carrier passenger operation must be equipped with both internal and external handles so that the door can be opened from either inside or outside in case of emergency. Aircraft not so equipped must be modified to comply by September 1, 1952.
2016-10-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a determination that the network interface installed between the Information Management System (IMS) 6000 unit and the Cabin Entertainment System (CES) network could affect the Aircraft Control Domain (ACD), and result in the transmission of misleading navigational information to the flightcrew. This AD requires inspecting the network interface installation between the IMS and the CES, and disconnecting the installation, if necessary. We are issuing this AD to prevent the transmission of misleading navigational information, which could adversely affect the ability of the flightcrew to maintain the safe flight and landing of the airplane.
2016-10-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by a report of cracking in the fuselage frame. This AD requires inspections for cracking in the fuselage frame, left and right sides, and repair if necessary. We are issuing this AD to detect and correct fuselage frame fatigue cracking. Such cracking could result in loss of structural integrity and the inability to sustain loading conditions.
2010-14-16: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Several cases have been reported where a loss of fluid in the No.2 hydraulic system has caused the power transfer unit (PTU) to overspeed, resulting in pressure fluctuations and increased fluid flow within the No. 1 hydraulic system. In one case, the hydraulic system control logic did not shut down the PTU and the overspeed condition persisted, resulting in the illumination of the No.1 HYD FLUID HOT caution light. * * * * * The unsafe condition is possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 17, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 17, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 2, 2008 (73 FR 47818, August 15, 2008). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of July 10, 2007 (72 FR 30968, June 5, 2007).
82-06-03: 82-06-03 CANADAIR: Amendment 39-4343. Applies to Canadair Model CL-600-1A11 airplanes, serial numbers 1005 thru 1008 and 1010 thru 1037 certificated in all categories. Compliance is required as indicated unless already accomplished: 1. Within the next 25 hours time in service after the effective date of this AD replace the antiskid control unit P/N 600-87000-23 with P/N 600-87000-27 in accordance with paragraph 2A of Canadair Alert Service Bulletin A600-0094 dated November 20, 1981. Within the next 75 hours time in service after the effective date of this AD perform wiring system modifications to introduce a second power source for the antiskid system per paragraph 2B of the service bulletin. 2. Until such time as both the above requirements are accomplished, the takeoff distances derived from Section 4, page 4-44, or Supplement No. 2, page S2-73, and the landing distances derived from Section 4, page 4-63, or Supplement No. 2, page S2-94 of the FAA approved Airplane Flight Manual, shall be increased by 50 percent for all operations. If any suspected braking deficiency occurs during the brake operation, immediately switch off the antiskid system and control the brakes manually as described in paragraph 35.3 of Section 2 of the Airplane Flight Manual. 3. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for accomplishment of the inspection required by this AD. 4. Alternate methods of compliance with this AD may be used when they provide an equivalent level of safety and are approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 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 addresses listed above. These documents may also be examined at the FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective March 22, 1982.