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2017-13-03: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD requires adding an identification number to life-limited rod ends that do not have a serial number (S/N). The actions of this AD are intended to address an unsafe condition on these products.
2017-13-04: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 (including configuration C-2e) and MBB-BK 117 D-2 helicopters. This AD requires replacing the main rotor (M/R) blade vibration absorbers. This AD was prompted by a report of strong M/R blade vibrations on a Model MBB-BK 117 C-2 helicopter. The actions of this AD are intended to prevent an unsafe condition on these products.
98-09-19: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires modification of certain non-regulating shutoff valves on the engine starter, or installation of a pressure relief valve in the pneumatic supply line to the starter air shutoff valve on engines 1 and 2. This amendment is prompted by reports of uncontained failures of engine starters during flight and maintenance, which resulted from the application of excessive pressure on the engine starter that was associated with the installation of non-regulating shutoff valves on the starter. The actions specified by this AD are intended to prevent such uncontained failures of the engine starters, which could create a fire hazard in the engine nacelle.
61-23-02: 61-23-02 CANADAIR: Amdt. 362 Part 507 Federal Register November 3, 1961. Applies to all CL-44D4 aircraft. Compliance required as indicated. To preclude failure of the elevator tab tension rods, P/N 28-90031, the life of each rod is limited to 450 hours' time in service. Every 450 hours' time in service, all eight tension rods of the elevator tab system must be replaced with similar parts supplied by Canadair or FAA approved equivalent. For those aircraft with more than 450 hours' time in service on the effective date of this AD, rods must be replaced within the next 25 hours' time in service. When the rods are replaced and detuned in accordance with the procedures in Canadair Service Bulletin No. CL44D4-201 Issue 2, the replacement time is increased to 10,000 hours' time in service. (Canadair Service Bulletins Nos. CL44D4-190, and CL44D4-201 Issue 2 apply to this subject.) This directive effective November 3, 1961. Revised June 23, 1962.
79-08-05: 79-08-05 PIPER (TED SMITH): Amendment 39-3449. Applies to Aerostar Model 600, 601, and 601P Airplanes certificated in all categories. Compliance required as indicated. To prevent possible fire or explosion in the area aft of the fire wall in the engine nacelles, accomplish the following: (a) Within 10 hours time in service from the effective date of this AD, prior to engine start for each flight, check the lower engine nacelle cowling and the lower wing surface just outboard of the engine nacelle for wetting or other indications of fuel leakage. The checks required by this AD may be performed by the pilot. NOTE 1. Removal of the engine or nacelle cowling is not required to perform this check. NOTE 2. For the requirements regarding the listing of compliance and method of compliance with this AD in the airplane's permanent maintenance record, see FAR 91.173. (b) If fuel stains, discoloration or any other signs of leakage are observed, the source of leakage must be determined and the leak repaired prior to further flight. (c) Within the next ninety (90) days from the effective date of this AD or by the next annual inspection after the effective date of this AD, whichever occurs later, rework the aft nacelle and fire wall area to provide sealing, drainage, and ventilation per Part II of Piper Aerostar Service Bulletin 600-80, dated April 6, 1979. (d) Pre-flight inspections required by (a) may be discontinued after rework per (c) is accomplished. (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 repairs required by this AD. (f) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective May 24, 1979.
98-09-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model L-1011 series airplanes, that currently requires various modifications and corrective actions to prevent a potential fire hazard caused by heat damage to the flex fuel feed line from an undetected gearbox fire. In lieu of the various modifications and corrective actions, that AD also provides for an optional terminating action (i.e., installation of a vent air tube in the gear compartment and thickened gearbox housings) for another existing AD. For airplanes on which that optional terminating action has been accomplished, this amendment requires accomplishment of the various modifications and corrective actions. This amendment is prompted by a report indicating that, due to bearing failure, an in-flight fire occurred on an airplane on which a thickened gearbox housing was installed. The actions specified by this AD are intended to detect and correct bearing failure, which could lead to a fire in the gearbox.
98-09-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly known as Beech Aircraft Corporation Model 1900D airplanes). This AD requires inspecting and repairing the radio switching panel relay printed circuit board (PCB) and the nose avionics wire harnesses, and replacing the existing A017 component PCB with a new A017 component PCB that has internal overcurrent protection fuses. Several reported incidents of lost use of the pilot/co-pilot intercom system, VHF communication system, and public address system while in flight prompted this action. The actions specified by this AD are intended to prevent the loss of the pilot and co-pilot intercom, VHF communications, and passenger address system, which could result in loss of all communication during critical phases of flight.
98-09-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-200F and -200C series airplanes. This action requires repetitive inspections or a one-time inspection to detect cracking of certain areas of the upper deck floor beams; and corrective actions, if necessary. This amendment is prompted by reports indicating that fatigue cracks were found in the upper chord and web of upper deck floor beams. The actions specified in this AD are intended to prevent such fatigue cracking and the resultant failure of such floor beams. Failure of the floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent reduced controllability of the airplane; failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane.
2005-20-29: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks in various areas of the upper deck floor beams, and repair if necessary. This AD results from fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. We are issuing this AD to detect and correct cracking in the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. \n\nDATES: This AD becomes effective November 16, 2005. \n\n\tThe Director of the Federal Register approved the incorporation by reference ofBoeing Service Bulletin 747-53A2349, Revision 2, dated April 3, 2003; and Boeing Alert Service Bulletin 747-53A2452, dated April 3, 2003; as of November 16, 2005. \n\n\tOn June 27, 2002 (67 FR 36081, May 23, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2349, Revision 1, dated October 12, 2000. \n\n\tOn June 11, 1993 (58 FR 27927, May 12, 1993), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747-53-2349, dated June 27, 1991.
60-06-03: 60-06-03 BRANTLY: Amdt. 112 Part 507 Federal Register March 10, 1960. Applies to all Brantly B-2 helicopters Serial Numbers 1 through 29 with tail rotor guard upper fitting, P/N B2-416-2 installed. Compliance required within the next 10 hours' time in service and at each 10 hours' time in service thereafter. A fatigue crack has been found around the forward end of the weld joining the tail rotor guard to the sheet metal bracket at the upper tail rotor gear box. To preclude the possibility of the tail rotor loss because of entanglement with the tail rotor guard, the following shall be accomplished: (a) Remove paint in the area of the weld joining the upper guard fitting P/N B2-416- 2 and the tail rotor guard P/N B2-416-3 and inspect the weld area for cracks using a dye penetrant method or equivalent. (b) If a crack is found the defective parts must be replaced or repaired prior to further flight. The fitting may be repaired by stop drilling the crack and adding a reinforcing plate of 0.035 inch by 1 inch by 1 inch SAE 4130 steel over the crack, welding all four edges to P/N B2- 416-2. The reinforcing plate may be located under the head of the screw attaching the guard fitting to the tail rotor gear box, provided the plate is drilled for this screw and extends completely under the screw head. (c) When an improved upper fitting as specified in Brantly Service Bulletin No. 1 is incorporated, the provisions of this directive no longer apply.