Results
49-06-04: 49-06-04 BOEING: Applies to Model 377 Aircraft. The 11 convolution type altitude compensating bellows, Bendix P/N 390935, shall be replaced with new bellows after each 100 hours of operation until the 9 convolution type Bendix P/N 391003 is available and has been installed in the carburetor.
75-08-05: 75-08-05 ROCKWELL INTERNATIONAL CORP., GENERAL AVIATION DIVISION: Amendment 39-2158. Applies to Model 690A airplanes, Serial Numbers 11100 through 11196, 11198 through 11215, 11219 through 11227, and 11231 through 11233. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To assure correct battery disconnect, accomplish the following: (a) Check operation of the battery select switch in accordance with Rockwell International, General Aviation Division, Service Bulletin No. 149, dated February 20, 1975, or later approved revision or in accordance with an equivalent operational check approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. (b) If the check indicates incorrect connection, interchange Wires P42B22 and P53B22. This amendment becomes effective on April 5, 1975.
2015-11-01: We are adopting a new airworthiness directive (AD) for Slingsby Aviation Ltd. Models T67M260 and T67M260-T3A airplanes. 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 failure of a brake master cylinder pivot pin. We are issuing this AD to require actions to address the unsafe condition on these products.
2005-05-17: The FAA is adopting a new airworthiness directive (AD) for Boeing Model 737-300, -400, and -500 series airplanes modified in accordance with STC ST00127BO. This AD requires installation of bonding straps to the safe side harnesses of the digital transient suppression device of the fuel quantity indicating system. This AD is prompted by the results of fuel system reviews conducted by the STC holder. We are issuing this AD to prevent unsafe levels of current or energy from entering the fuel tank, due to hot short faults or threat conditions associated with the safe side harness assembly, which could result in a fire or explosion of the fuel tank.
2015-21-11: We are superseding Airworthiness Directive (AD) 2015-16-01 for certain The Boeing Company Model airplanes. AD 2015-16-01 required incorporating design changes to improve the reliability of the cabin altitude warning system by installing a redundant cabin altitude pressure switch, replacing the aural warning module (AWM) with a new or reworked AWM, and changing certain wire bundles or connecting certain previously capped and stowed wires as necessary. For certain airplanes, AD 2015-16-01 also required prior or concurrent incorporation of related design changes by modifying the instrument panels, installing light assemblies, modifying the wire bundles, and installing a new circuit breaker, as necessary. This AD retains all actions required by AD 2015-16-01. This AD was prompted by the discovery of a typographical error in AD 2015-16-01 that referred to a nonexistent paragraph. We are issuing this AD to prevent the loss of cabin altitude warning, which could delay flightcrew recognition of a lack of cabin pressurization, and could result in incapacitation of the flightcrew due to hypoxia (a lack of oxygen in the body), and consequent loss of control of the airplane.
75-18-03: 75-18-03 LOCKHEED: Amendment 39-2342 as amended by Amendment 39-2511 is further amended by Amendment 39-3157. Applies to all Model 382 series airplanes certificated in all categories. Compliance required within the next 50 hours time in service after the effective date of this Airworthiness Directive unless already accomplished, on airplane serial numbers 3946 and 4101 through 4298, with 6,300 hours or more total time in service, and serial numbers 4299 through 4541 with 9,450 hours or more total time in service on the effective date of Amendment 39-3157 and at intervals not to exceed 3,400 hours time in service from the last inspection until 20,000 hours (without ECP 954) or 24,000 hours (with ECP 954) at which time the interval is not to exceed l,700 hours from the last inspection. (A) To detect cracks in the outer wing lower forward spar caps at OWS 54 and 108, eddy current inspect in accordance with Hercules Airfreighter Inspection procedures SMP515-A Card No. SP-62, revised August 11, 1975. (B) If a crack or cracks are found, contact the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, Atlanta, Georgia 30320, telephone number 404-526-7428. Before the accumulation of more than 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-187, or later FAA-Approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspections required by this AD may be discontinued for those airplanes modified in accordance with the above paragraph. Amendment 39-2342 became effective August 27, 1975. Amendment 39-2511 became effective February 13, 1976. This Amendment 39-3157 becomes effective March 20, 1978.
2005-09-03: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to detect damage of certain wiring in the flight compartment, performing corrective actions if necessary, modifying certain wiring connections, and revising the airplane flight manual. This AD is prompted by reports of miswiring in the power distribution system. We are issuing this AD to ensure that the flightcrew is aware of the source of battery power for certain equipment, and to prevent damage to wiring and surrounding equipment that could result in smoke or fire on the airplane.
2015-21-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.27 Mark 200, 300, 400, 500, 600, and 700 airplanes. This AD was prompted by a design review, which revealed that no controlled bonding provisions are present on a number of critical locations inside the fuel tank or connected to the fuel tank wall; and no anti-spray cover is installed on the fuel shut-off valve (FSOV) in both wings. This AD requires installing additional bonding provisions in the fuel tank, installing an anti-spray cover on the FSOV, and revising the airplane maintenance program by incorporating fuel airworthiness limitation items and critical design configuration control limitations. We are issuing this AD to prevent an ignition source in the fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
2001-09-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Eagle Aircraft Pty. Ltd. (Eagle) Model 150B airplanes. This AD requires you to inspect the rudder cables for fraying, broken strands, etc. (referred to as damage), and replace any damaged cables. This AD also requires you to replace the rudder cable pulleys with larger diameter pulleys to eliminate the possibility of further damage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified by this AD are intended to detect and correct damaged rudder cables caused by chafing of the cable against the pulleys. Continued airplane operation with damaged cables could result in rudder cable system failure with possible loss of airplane control.
97-10-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time inspection to detect riding, chafing, or damage of the wire bundles adjacent to the disconnect panel bracket of the observer's station. This amendment also requires repair or replacement of damaged wires with new or serviceable wires; installation of anti-chafing sleeving on the wire bundles, if necessary; and installation of grommet along the entire upper aft edge of the disconnect panel bracket. This amendment is prompted by a report indicating that the circuit breakers tripped on a Model MD-11 series airplane due to inflight arcing behind the avionics circuit breaker panel as a result of chafing of the wire bundles adjacent to the disconnect panel bracket assembly. The actions specified by this AD are intended to detect and correct such chafing, which could result in a fire in the wire bundles and smoke in the cockpit.