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98-09-27: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 768 and 772 series turbofan engines. This action requires initial and repetitive visual inspections of thrust reverser hinge lugs and attachment ribs for cracks, and, if necessary, removal from service and replacement with serviceable parts. This amendment is prompted by aircraft certification testing which revealed that stresses on the thrust reverser hinge were higher than had been anticipated during engine certification. The actions specified in this AD are intended to prevent thrust reverser hinge failure, possibly resulting in liberation of the thrust reverser cowl duct from the engine nacelle, which could result in impact damage to other sections of the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 21, 1998. Comments for inclusion in the Rules Docket must be received on or before July 6, 1998.
60-02-02: 60-02-02\tBOEING: Amdt. 75 Part 507 Federal Register January 15, 1960. Applies to the following 707-100 Series Aircraft Only: Serial Numbers 17586 through 17591, 17609, 17610, 17628 through 17641, 17659 through 17666, 17925, 17926. \n\tCompliance required as indicated. \n\tService experience has shown that it is possible for the inboard aileron balance panel end seals to loosen and restrict movement of the aileron on some Boeing 707 aircraft. Therefore, certain inspection(s) or modification(s) are to be accomplished. \n\tPart I. Within the next 200 hours' time in service and at each 200 hours' time in service thereafter until Part II of this AD is accomplished, conduct the following inspection(s). \n\t(a)\tRemove the inboard aileron balance bay access panels on the wing lower surfaces. \n\t(b)\tInspect the fasteners retaining the felt end seals P/N 5-87140-8 and P/N 3-94377-1 at each end of the balance panel hinge and retorque as necessary. \n\t(c)\tReinstall access panels. \n\tPart II. ThePart I inspections may be discontinued after incorporating the following modification(s). \n\t(a)\tRemove the inboard aileron balance bay access panels on the wing lower surfaces. \n\t(b)\tDelete felt end seals 5-87140-8 and washer BAC-W10P-69S (8 places) and retaining screw NAS 514P-632-8, washer AN 960-6 and nut (16 places). Open holes are satisfactory. \n\t(c)\tDelete felt end seals 3-94377-1 (8 places). \n\t(d)\tInspect and replace any damaged nuts and nut plates from which bolts were removed. \n\t(e)\tDelete spacer washer AN 960D10 (8 places). \n\t(f)\tReassemble using shorter bolts to compensate for parts deleted or modified. \n\t(g)\tCheck for proper operation of inboard ailerons. \n\t(h)\tReinstall access panels. \n\t(Boeing Service Bulletin No. 245 pertains to this same subject.)
2002-09-09: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., Textron Lycoming, Avco Lycoming, and Lycoming) former military T53 series turboshaft engines. This amendment requires conducting a revised operating cycle count (prorate) and initial and repetitive inspections for cracks of centrifugal compressor impellers. This amendment is prompted by a report of a military surplus helicopter that experienced low-cycle fatigue failure of the centrifugal compressor impeller, resulting in an uncontained engine failure. The actions specified by this AD are intended to prevent centrifugal compressor impeller failure, which can result in an uncontained engine failure, in-flight engine shutdown, or damage to the helicopter.
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.