Results
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.
97-09-14: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires an inspection of reworked aileron/elevator power control units (PCU's) and rudder PCU's to determine if reworked PCU manifold cylinder bores containing chrome plating are installed, and replacement of the cylinder bores with bores that have been reworked using the oversize method or the steel sleeve method, if necessary. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent a reduced rate of movement of the elevator, aileron, or rudder due to contamination of hydraulic fluid from chrome plating chips; such reduced rate of movement, if not corrected, could result in reduced controllability of the airplane.
2024-12-06: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of moisture in the wing- to-fuselage joint, between the mating front spar and rear spar frame segments. This AD requires a visual inspection of the fuselage front and rear spar frames, an ultrasonic test if applicable, other specified actions, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
56-27-01: 56-27-01 CONVAIR: Applies to All Models 340 and 440 Aircraft. Compliance required as noted below. A report has been received concerning the failure of the elevator servo tab rod on a version of the Model 340 aircraft. Since the tabs on the subject model aircraft are unbalanced, a serious flutter condition resulted and a critical accident was narrowly avoided. In view of the fact that the tab rods and tab rod ends on the subject models aircraft are identical in design, hence susceptible to a similar type of failure, the following inspections and tab rod replacements or equivalent measures are required. Compliance required at every 110 hours of operation or regular scheduled inspection closest thereto. 1. (a) Inspect the tab rods and rod ends on the elevator, for looseness in the rivets which attach the rod ends to the rods, and for any relative movement between the rod and the rod ends. Parts which exhibit these defects shall be replaced with satisfactory parts. Upon completion of the tab rod replacement program or equivalent noted in items 2 (a), and 2 (b) below, this 110-hour inspection may be discontinued. Compliance required not later than November 30, 1957. 2. (a) Model 340 replacement of all elevator tab rods with improved, heavier rods and rod ends, and replacement of the right-hand elevator tab idler link with symmetrical idler link. (Convair Service Bulletin Nos. 340-207 and 340-150A cover this same subject.) 2. (b) Model 440 replacement of the right-hand elevator tab rods and tab rod ends with improved heavier tab rods and tab rod ends. (Convair Service Bulletin No. 440-27A covers this same subject.)
2024-13-04: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a determination that non-conforming washers may have been installed in production on engine 1 and 3 forward yokes. This AD requires a one-time inspection for non-conforming washers and, depending on findings, related investigative and corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.