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2001-26-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires you to inspect the landing-gear emergency-extension cable for damage and replace if necessary; verify the correct installation of the bowden-cable conduit clamp and correct if necessary; and modify the temperature-control lever mechanism. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the malfunction of the emergency landing-gear extension system. Insufficient clearance between the temperature-control lever mechanism and the landing-gear emergency-extension cable could result in damage to the emergency landing gear extension cable, or the cable could get caught on the temperature control lever. Damage to, or interference with, the landing-gear emergency-extension cable could lead to a malfunction of the emergency landing-gear extension system.
2001-26-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires a one-time inspection of the forward and aft lower bogies of the left- and right-hand sliding windows of the flightcrew compartment for the presence of a lock pin. If the lock pin is missing, this amendment requires corrective action. This action is necessary to prevent the inability of the flightcrew to open the left- or right-hand sliding window for evacuation in an emergency, due to a window jamming in the closed position. This action is intended to address the identified unsafe condition.
2003-14-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires installing brackets and ramps under floor panels between frames 23C and 23D and installing wire bundles on the ramps. The actions specified by this AD are intended to prevent chafing damage to the electrical wire cables, which could lead to an electrical short circuit and potential for a fire under the floor panels. This action is intended to address the identified unsafe condition.
2015-15-05: We are superseding Airworthiness Directive (AD) 98-22-10 for certain The Boeing Company Model 737-100, -200, -200C, and -300 series airplanes. AD 98-22-10 required repetitive inspections for cracking of the aft frame and frame support structure of the forward service doorway, and repair if necessary. AD 98-22-10 also provided an optional terminating action for the repetitive inspection requirements of that AD. This new AD requires new inspections and adds airplanes to the applicability; for certain airplanes, this new AD provides an optional preventive modification, which terminates the repetitive inspections. This AD was prompted by reports of fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, and a determination that inspections are needed in additional locations and that additional airplanes might be subject to the identified unsafe condition. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six \n\n((Page 43922)) \n\ndoorstop fittings, which could result in door deflection and loss of pressurization.
80-17-10: 80-17-10 AVCO LYCOMING: Amendment 39-3880. Applies to Lycoming Model TIO-540-S1AD engine with serial numbers thru S/N L-6991-61A except: S/Ns L-5253-61A L-6669-61A L-5616-61A L-6671-61A L-5641-61A L-6775-61A L-5691-61A L-6840-61A L-5808-61A L-6860-61A L-5823-61A L-6861-61A L-5878-61A L-6886-61A L-5909-61A L-6887-61A L-5967-61A L-6888-61A L-5970-61A L-6900-61A Thru L-6905-61A L-6160-61A L-6915-61A Thru L-6921-61A L-6183-61A L-6930-61A Thru L-6940-61A L-6451-61A L-6979-61A Thru L-6988-61A and L-6990-61A installed in Piper PA-32RT-300T and PA-32R-301T aircraft. Compliance is required prior to each flight after receipt of this directive until a new transition wastegate assembly P/N LW16858 is installed. To prevent loss of engine power control due to seized throttle movement, accomplish the following: 1. Prior to each flight check the throttle movement for stiffness or binding as follows: a. Release the throttle friction lock in the cockpit. b. Move the throttle from idle to full open and back to idle. c. If the throttle movement is stiff or binds, replace any wastegate valve or cable assembly with a new assembly in accordance with Lycoming S/B 448. 2. An alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. The checks in this AD may be accomplished by the pilot. Any corrective action required by this AD must be accomplished by a person authorized by FAR 43.3. Piper special advisory Telex SA-32RT-300T/32R-301-1 dated February 8, 1980, and Lycoming Service Bulletin No. 448 pertain to this subject. This AD is effective on August 18, 1980, and was effective upon receipt for all recipients of the letter dated March 17, 1980, which concerned this subject.
2001-25-11: This amendment supersedes two airworthiness directives (AD's), AD 99-17-16 and AD 2001-15-12. Those AD's both apply to Pratt and Whitney (PW) model PW4000 series turbofan engines. AD 99-17-16 generally requires that operators limit the number of PW4000 engines with potentially reduced stability margin to no more than one engine on each airplane, and requires initial and repetitive on-wing and test cell engine stability tests. It also establishes reporting requirements for stability testing data. AD 2001-15-12 also limits the number of PW4000 engines with potentially reduced stability on each airplane by applying rules based on airplane and engine configuration. In addition, AD 2001-15-12 also requires that engines that exceed high pressure compressor (HPC) cyclic limits based on cycles-since-overhaul (CSO) are removed from service, limits the number of engines with the HPC cutback stator (CBS) configuration to one on each airplane, and establishes a minimum rebuild standard for engines that are returned to service. These AD's were prompted by reports of surges during takeoff on airplanes equipped with PW4000 series turbofan engines. This amendment continues the limitation on the number of PW4000 engines with potentially reduced stability on each airplane to no more than one, and introduces a new cool engine fuel spike test to allow engines to be returned to service after having exceeded cyclic limits or undergone work in the shop. This AD also continues the limitation on the number of engines with HPC CBS configuration to one on each airplane, places a cyclic limit on how long a CBS engine may remain in service, and establishes a minimum rebuild standard for engines that are returned to service. This amendment is prompted by further analyses of compressor surges in PW4000 engines, and continuing reports of surges in the PW4000 fleet. The actions specified by this AD are intended to prevent engine power losses due to HPC surge.
98-18-01: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 214B-1, and 214ST helicopters, that currently establishes a retirement life of 60,000 high-power events for the main rotor trunnion (trunnion). This amendment requires changing the method of calculating the retirement life for the trunnion from high-power events to a maximum accumulated Retirement Index Number (RIN). This amendment is prompted by fatigue analyses and tests that show certain trunnions fail sooner than originally anticipated because of the unanticipated higher number of lifts or takeoffs (torque events) performed with those trunnions. The actions specified by this AD are intended to prevent fatigue failure of the trunnion, which could result in loss of the main rotor and subsequent loss of control of the helicopter.
2015-15-02: We are superseding Airworthiness Directive (AD) 2012-13-06, for all Airbus Model A300 series airplanes and all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2012-13-06 required a one-time detailed inspection to determine the length of the fire shut-off valve (FSOV) bonding leads and for contact or chafing of the wires, and corrective actions if necessary. This new AD requires a new one-time detailed inspection of the FSOV bonding leads to ensure that the correct bonding leads are inspected, and corrective action if necessary. This AD was prompted by a determination that the description of the inspection area specified in the service information was misleading; therefore, some operators might have inspected incorrect bonding leads. We are issuing this AD to detect and correct contact or chafing of wires and the bonding leads, which, if not detected, could be a sourceof sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.
81-01-52: 81-01-52 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4055. Applies to Models SA330F, G, and J series helicopters, certificated in all categories. Compliance required within five (5) hours' time in service after the effective date of this AD unless already accomplished since December 22, 1980. To prevent possible in-flight loss of the pilot or copilot doors or the copilot's jettisonable panel (if installed), accomplish the following: (a) Inspect the jettisonable pilot door in accordance with Aerospatiale SA330 work cards Nos. 52-10-601 and 52-10-401 of the SA330 Maintenance Manual (Document 8582), or an FAA approved equivalent, and (b) Inspect either - (1) The jettisonable copilot panel in accordance with Aerospatiale SA330 work cards Nos. 52-21-601 and 52-21-401 or an FAA-approved equivalent, or (2) The jettisonable copilot door (if fitted per Aerospatiale Modification No. OP-11-611 or OP-11-970) in accordance with Aerospatiale work cards Nos. 52-10-601 and 52- 10-401 of the maintenance manual, or an FAA-approved equivalent. (c) Rerig improperly rigged doors and panels before further flight. Use serviceable parts in accordance with the respective reference work cards or FAA-approved equivalents. This amendment becomes effective March 16, 1981, to all persons except those persons to whom it was made immediately effective by telegraphic AD T81-01-52, issued December 31, 1980, which contained this amendment.
2001-26-11: This amendment supersedes an existing airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of low pressure compressor (LPC) fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment requires initial inspections at modified thresholds and repetitive inspections at reduced intervals from the current AD using new LPC fan blade inspection criteria, and requires renewal of dry film lubricant on removed blades. This amendment is prompted by reports that an in-service engine experienced LPC fan blade root cracking at a lower life than previously forecast, and, the manufacturer's further investigation that has led to a better understanding of the causes of fan blade root cracking. The actions specified in this AD are intended to prevent LPC fan blade failure due to cracking, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the airplane.