Results
2006-20-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires doing initial and repetitive detailed or high frequency eddy current inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repairing any crack found. This AD results from a report indicating that certain rivets were incorrectly installed in some areas of the skin lap splices during production because they were drilled with a countersink that was too deep. We are issuing this AD to detect and correct premature fatigue cracking at certain skin lap splice locations of the fuselage, and consequent rapid decompression of the airplane.
47-10-18: 47-10-18 LOCKHEED: (Was Mandatory Note 20 of AD-763-3.) Applies to All Model 49-46 Aircraft. Compliance required not later than 100 hours of operation after March 1, 1947, or during conversion of Model 49-51 aircraft to Model 49-46 aircraft, whichever occurs first. The hose connections in the fuel line between air metering chamber and fuel injection pump shall be changed to incorporate fire resistant hose and double hose clamps, using Wright Aeronautical Corporation P/N 856864 and 855403.
47-43-06: 47-43-06 CESSNA: (Was Service Note 4 of AD-768-5.) Applies to 120 and 140 Aircraft Serial Numbers 8001 to 10209, Inclusive. Inspection required whenever airplane is tied down in high winds without controls locked and upon each 100 hours of operation until Cessna parts 0422200-2 and 0422200-3 are installed. Inspect the aileron support ribs for indications of buckling or cracking, particularly in the narrow part of the web at the aft edge of the lightening hole and in the top flange just forward of the doubler plate. Any damaged support rib should be replaced with Cessna parts 0422200-2 (left) and 0422200-3 (right) which are made of 0.051-inch material and have a shorter lightening hole. (Cessna Service Letter No. 46 dated July 31, 1947, covers this same subject.)
2006-20-09: The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO-540, (L)TIO-540, IO-580, and IO-720 series reciprocating engines. This AD requires replacing certain crankshafts. This AD results from reports of 23 confirmed failures of similar crankshafts in Lycoming Engines 360 and 540 series reciprocating engines. We are issuing this AD to prevent failure of the crankshaft, which will result in total engine power loss, in-flight engine failure, and possible loss of the aircraft.
2006-20-05: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 airplanes. This AD requires repetitive inspections to measure the depth of chafing or scoring in the skin along the full length of the wing-to-fuselage fairing from forward to aft ends at the contact between the seal and fuselage, and related investigative/corrective actions if necessary. This AD results from a report of chafing in this area. We are issuing this AD to detect and correct such chafing or scoring, which could result in reduced structural integrity of the fuselage.
48-25-02: 48-25-02 CESSNA: Applies to All 120 and 140 Aircraft Equipped With Cessna Welded Exhaust Muffler Assemblies. Inspection required each 25 hours of operation. Remove the carburetor air heater muff and cabin heater muff and inspect the muffler assemblies for any evidence of cracks paying particular attention to the areas of the mufflers and stacks adjacent to where the exhaust stacks and tailpipe are welded to the muffler assembly. The present placard calling for inspection of the mufflers every 100 hours should be revised to call for this inspection every 25 hours. This directive is intended to apply to only those aircraft equipped with exhaust muffler assemblies that are fabricated by welding exhaust stacks to muffler.
47-30-07: 47-30-07 BEECH: (Was Mandatory Note 3 of AD-2-582-2.) Applies Only to AT-11 Aircraft Which Are Not Equipped With Generator Circuit Protective Devices. To be accomplished prior to certification or, if certificated, on next periodic inspection but not later than October 1, 1947. In accordance with Figure 1 install a 50-ampere trip-free circuit breaker, Spencer Thermostat Co. PLM-50 or equivalent, between the battery terminal of each generator cutout and its respective ammeter shunt. The circuit breakers should be accessible in flight and labeled respectively: "LEFT GEN. CIRCUIT" and "RIGHT GEN. CIRCUIT."
2006-19-09: We are adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) Model B300 airplanes. This AD requires you to modify the cabin passenger seats by installing a modification kit on each passenger seat, removing the existing technical standard order (TSO) label, and re-identifying each modified passenger seat assembly with a new part number. This AD results from the seats not meeting the ultimate load requirements of 14 CFR part 23 during structural testing of the seat with design changes. We are issuing this AD to prevent the passenger seats from failing during emergency landing conditions when high inertial loadings occur. Passenger seat failure may result in occupant injury.
2006-18-07: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires replacing the very high frequency (VHF) antenna located in position 1 of the fuselage with a new, improved VHF antenna. This AD results from a report of the loss of all voice communications due to a lightning strike damaging all the VHF antennas. We are issuing this AD to prevent the loss of voice communication, which, when combined with the complexity of the national airspace system, could result in reduced flightcrew situational awareness, increased flightcrew workload, and increased risk of human error, and consequent reduced ability to maintain safe flight and landing of the airplane.
57-14-02: 57-14-02 DAVIS AIRCRAFT PRODUCTS (Safety Belts): Applies to Model FDC-1650 Belts, P/N FDC-1650, FDC-1650-27, FDC-1650-27M1. \n\n\tCompliance required as soon as possible but not later than August 15, 1957. \n\n\tSome of the release fittings of the subject belt assemblies are so constructed as to require one particular side of the fitting UP when being inserted in the buckle. \n\n\tIt is possible to improperly fasten the belts effected so that the buckle may become unfastened under load. The unsatisfactory release fittings have a tab bent up to an angle of approximately 11 degrees with the plane of the fitting (See Figure 1). \n\n\tTo provide for securely assembling the buckle with the release fitting in either position, the tab area indicated in the sketch must be removed or bent flush with the plane of the adjoining metal. \n\n\tThis rework applies only to the release fitting shown in the sketch. Other portions of the buckle assembly than that shown should not be modified. This condition has been corrected on all assemblies of current manufacture.