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84-03-03: 84-03-03 BRITISH AEROSPACE: Amendment 39-4812. Applies to Model HS 125 airplanes series 1A with modifications 251867 and 252605, series 400A with modification 252550, series 600A with modification 252468, and series 700A, certificated in all categories. The serial numbers of the affected airplanes are listed in the Planning Information section of British Aerospace 125 series Service Bulletin 24-225-(2747), dated October 17, 1980. Compliance is required as indicated, unless already accomplished. To prevent loss of power to both engine fuel computers by a single fuse failure, accomplish the following: A. Modify the engine fuel computers' direct current power supply electrical circuits within the next 500 hours time in service or one year, whichever occurs first after the effective date of this AD, in accordance with paragraph 2, Accomplishment Instructions, of British Aerospace, HS 125 series Service Bulletin 24-225-(2747), dated October 17, 1980. B. Alternate means ofcompliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, 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 inspections and/or modifications required by this AD. This amendment becomes effective March 22, 1984.
81-21-05: 81-21-05 ARTEX AIRCRAFT SUPPLIES, INC.: Amendment 39-4231. Applies to Artex replacement battery packs, P/N 00-21-006, which are designed for use in the Emergency Beacon Corporation Emergency Locator Transmitter. Within 30 calendar days after the effective date of this AD, inspect the ELT and if the battery is an Artex Battery Pack, P/N 00-21-006, replace it with a battery pack with a different part number which is approved under TSO-C91 for use in this ELT. Note: If no replacement battery pack is immediately available, placard the ELT "Not to be used in salt water." The airplane may be operated for up to 90 days with a placarded ELT. Alternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. This amendment becomes effective October 19, 1981.
82-09-51 R1: 82-09-51 R1 CANADAIR: Amendment 39-4452. Applies to all Canadair CL-600 airplanes certificated in all categories. Because of the possible loss of normal braking, accomplish the following unless already accomplished. 1. Revise flight manual operating procedures as follows before further flight: A. The critical engine failure recognition speed V1 shown in Section 4, page 4-39; Supplement 2, page S2-69; or Supplement 6, page S6-74 of the airplane flight manual shall be reduced by 10 KIAS but shall not be lower than 105 KIAS (VMCG). B. The takeoff distances derived from Section 4, page 4-44; Supplement 2, page S2-73; or Supplement 6, page S6-80 of the airplane flight manual shall be increased by a factor of 1.2 (20 percent). C. The landing distances derived from Section 4, page 4-63; Supplement 2, page S2-94; or Supplement 6, page S6-101 of the airplane flight manual shall be increased by a factor of 1.65 (65 percent). 2. If any suspected braking deficiencyoccurs during the brake operation, immediately release brakes, switch off the anti-skid system, and control the brakes manually as described in paragraph 35.3 of Section 2 of the airplane flight manual. 3. Within the next 50 flights after the effective date of this AD, modify the anti-skid system in accordance with Canadair Service Bulletin A600-0212 dated May 1, 1982. Accomplishment of this modification constitutes terminating action for this AD and authorizes removal of the airplane Flight Manual revisions imposed by item 1. above. 4. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 5. 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. 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). This amendment becomes effective September 9, 1982, and was effective earlier to all recipients of telegraphic AD T82-09-51 dated April 14, 1982.
2017-10-10: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires installing an engine flame detector bracket assembly and harness assembly. This AD was prompted by reports of false fire warnings. The actions of this AD are intended to prevent an unsafe condition on these products.
2017-15-03: We are superseding Airworthiness Directive (AD) 2014-08-02 which applied to certain Airbus Model A300 B4-600 and A300 B4-600R series airplanes. AD 2014-08-02 required modifying the profile of stringer run-outs of both wings, including a high frequency eddy current (HFEC) inspection of the fastener holes for defects, and repairs if necessary. This new AD retains the actions required by AD 2014-08-02 and revises the compliance times. This AD was prompted by further analysis in the context of widespread fatigue damage (WFD), which concluded that shorter compliance times are necessary to meet specified requirements to address WFD. We are issuing this AD to address the unsafe condition on these products.
61-15-04: 61-15-04 LOCKHEED: Amdt. 309 Part 507 Federal Register July 21, 1961. Applies to All 188 Series Aircraft Incorporating A Lounge Using Hardman Seats. Compliance required as indicated. Reports have been received that grommets are missing in some of the aft lounge safety belt cable guide brackets. Grommets are required in these brackets to permit the cable to withstand the design load. Within the next 100 hours' time in service inspect the safety belt cable guide bracket, Hardman P/N 5072-1, of the left and right aft lounge seats for presence of nylon grommets. If the nylon grommets are missing, install nylon grommets, P/N 295957-10A (United Carr Fastener Corp.), or equivalent, or restrict occupancy of the left and right aft lounge seats during takeoff and landing until such time as grommets are installed. (Lockheed Service Bulletin 88/SB-541 refers to the same subject.) This directive effective August 2, 1961.
2003-17-05: This amendment adopts a new airworthiness directive (AD) that applies to all Short Brothers and Harland Ltd. (Shorts) Models SC-7 Series 2 and SC-7 Series 3 airplanes. This AD establishes a technical service life for these airplanes and allows you to incorporate modifications, inspections, and replacements of certain life limited items to extend the life limits of these airplanes. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of critical structure of the aircraft caused by fatigue.
2017-14-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of an aborted takeoff because the rudder pedals were not operating correctly. Investigation revealed a protruding screw in the rudder pedal heel rest adjacent to the pedals. This AD requires a torque check of the screws in the cover assembly of the heel rest for both the Captain and the First Officer's rudder pedals, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-14-11: We are superseding Airworthiness Directive (AD) 2007-13-08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007-13-08 required repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake; and applicable corrective actions. This AD expands the applicability of AD 2007-13-08, and includes an optional terminating installation for the repetitive actions. This AD was prompted by a determination that the unsafe condition could occur on additional airplanes. We are issuing this AD to address the unsafe condition on these products.
60-11-03: 60-11-03 LOCKHEED: Amdt. 159 Part 507 Federal Register May 24, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. Due to loose attachments and cracked quick engine change upper cowl panel longerons the following inspections are required. Prior to dispatch from a terminal where inspection facilities are available, unless already accomplished within the last 300 hours' time in service, and thereafter at every 300 hours' time in service, inspect the top cowl panel upper longerons and the attachments at the rear fittings for cracks or loose attachments. (a) Replace loose attachments in the longeron fittings. Acceptable replacements are: (1) One-sixty-fourths-inch diameter oversize Hi-Lok (P/N HL 56-6 pin, P/N HL 64-6-5 pin, P/N HL 85-6 collar). (2) Thirteen-sixty-fourths-inch diameter NAS type close tolerance screw, minimum heat treat 160,000 p.s.i. Ream to oversize hole limits of 0.212-0.2192-inch diameter. (3) Seven-thirty-seconds-inch diameter NAS type close tolerance screws; minimum heat treat 160,000 p.s.i.; minimum edge distance, 1 1/2 diameters. Ream to oversize hole limits of 0.2181-0.2192-inch diameter. (4) It is satisfactory to mix Huck bolts and Hi-Lok fasteners, but it is not acceptable to mix NAS type screws with Huck bolts or Hi-Lok fasteners. (b) Cracked longerons must be replaced or an FAA approved repair incorporated before next flight. The preceding inspections may be discontinued after the incorporation of the modifications contained in Lockheed Service Bulletin 88/SB-500. (Lockheed Alert Service Bulletin No. 467 covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 29, 1960. Revised September 29, 1960. Revised May 13, 1961.