Results
2015-17-22: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-243, A330-243F, A330-341, A330-342, and A330-343 airplanes. This AD was prompted by reports indicating that certain hinge sleeves on the cowl doors of the thrust reverser units (TRUs) were not heat treated. This AD requires replacing the sleeves of certain hinges on the cowl doors of the TRUs with new parts. We are issuing this AD to prevent, in the event of a fan-blade-off event due to high vibration, in-flight loss of TRU heavy components, which might damage airplane structure or control surfaces and consequently reduce controllability of the airplane.
2000-14-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires installation of placards on the P3-1 panel. This action is necessary to prevent loss of communication between the flight crew and Air Traffic Control; this situation could result in the flight crew being unaware of an unsafe scenario when the airplane is on the ground. This action is intended to address the identified unsafe condition.
96-05-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires replacement of the inlet filter in the spoiler servo-controls and installation of a lockwire. This amendment is prompted by reports of leakage of hydraulic fluid at the inlet filter plug of the spoiler actuator as a result of inadequate torque of the filter plug, and reports of broken lockwires. The actions specified in this AD are intended to prevent loss of hydraulic fluid to the extent that a complete failure of the associated hydraulic system could occur. Such a loss, when combined with other hydraulic system failures, could reduce the controllability of the airplane.
2000-14-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that currently requires repetitive inspections to detect cracking of the rear spar web or fuel leakage of the wing center section, and repair, if necessary. That action also provides for an optional modification of the rear spar web that constitutes terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent cracking of the rear spar web, which could permit fuel leakage into the airflow multiplier, and could result in an electrical short that could cause a fire.
2000-14-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires replacing the smoke detectors in the cargo compartment with new, improved smoke detectors. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent false smoke warnings from the cargo compartment smoke detectors, which could result in aborted takeoffs, diversions of flight routes, and emergency evacuation of flight crew and passengers.
2000-13-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires repetitive detailed visual and dye penetrant inspections of the backup struts in the left and right nacelles to detect discrepancies; and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the backup struts in the left and right nacelles due to fatigue cracking, which could result in loss of fail-safe redundancy in the design of the nacelle in terms of load capability.
2015-17-20: We are adopting a new airworthiness directive (AD) for certain serial number (S/N) GE Aviation Czech s.r.o. M601E-11, M601E-11A, and M601F turboprop engines with certain part number (P/N) gas generator turbine (GGT) blades, installed. This AD requires removing from service any affected engine with certain GGT blades installed. This AD was prompted by the determination that certain GGT blades are susceptible to blade failure. We are issuing this AD to prevent GGT blade failure, which could lead to engine failure and loss of the airplane.
74-14-03: 74-14-03 DETROIT DIESEL ALLISON: Amendment 39-1891. Applies to Detroit Diesel Allison Model 250-C20 Engines equipped with Chandler Evans Fuel Controls. Compliance required as indicated. To prevent after fires resulting from incomplete fuel cut-off at engine shutdown, unless already accomplished: A. Within the next 25 hours' flight time, and at each subsequent change of the fuel control or the associated linkage system inspect the fuel control rigging to assure that the fuel control quadrant reads minus 2 degrees with the throttle lever against the minimum stop when the twist grip is in the "Fuel Off" position. Minus 2 degrees is 1/32 inch to the left of the 0 degree mark. If the reading is not minus 2 degrees, readjust the minimum stop on the fuel control to obtain minus 2 degrees on the fuel control quadrant as follows: 1. Turn the minimum stop screw to obtain 0 degrees on the quadrant with the throttle against the stop. 2. Turn the minimum stop screw out (counterclockwise) one half turn. 3. Recheck to be sure the pointer is at minus 2 degrees when the twist grip is in the "Fuel off" position. NOTE: If after accomplishing the above, limitations of the aircraft engine control system linkage prevent reaching minus 2 degrees, set the minimum stop at 0 degrees. B. In addition to Part A, within the next 25 hours' flight time, accomplish the following on Model 250- C20 Engines equipped with Chandler Evans fuel controls, Part Numbers 6875653, 6876967, 6876797, 6877542, 6851386, and 6851506 only. This is a one time adjustment and test. 1. Adjust the cut-off lever link as follows: a. If the minimum stop is adjusted to minus 2 degrees, turn the nut closest to the throttle shaft four flats in the direction to shorten the effective length of the link. b. If the minimum stop is adjusted to 0 degrees, turn the nut closest to the throttle shaft eight flats in the direction to shorten the effective length of the link. c. Tightenthe nut on the opposite side of the cut-off lever bushing to 8-12 in. lb. so that the lever bushing is tight between the locknuts. d. Paint the locknuts and thread area around the nuts with red Glyptol or equivalent to identify the control as having been adjusted. 2. Start the engine and make a short ground run; then check the rigging for repeatability of the setting (0 degrees or -2 degrees) with the twist grip at "Fuel Off". 3. Check the fuel control cut-off valve for leakage as follows: a. Disconnect the fuel hose from the fuel nozzle and place the free end in an open container. b. Turn on the aircraft switches required to provide fuel boost pump pressure to the engine and pull the ignition circuit breaker or remove the primary wire to the ignition exciter to deactivate the ignition system. (Insulate the terminal of the primary wire.) c. Motor the engine to 10% N(1) RPM using the starter. d. If fuel flows from the open line in excess of 20 drops perminute with the twist grip at "Fuel Off", replace the fuel control and repeat the check before accepting the control. e. Reconnect the fuel hose and tighten the coupling to 80-120 in. lb. Detroit Diesel Allison Commercial Service Letter 250-C20-CSL-1023 pertains to this subject. This amendment is effective July 10, 1974.
2000-09-01 R1: This document corrects and clarifies information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-8 series airplanes. That AD currently requires a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; repetitive inspections of the wire bundle and door latch rollers to detect damage; and repair or replacement of damaged components. That AD also requires, among other actions, modification of the indication and hydraulic systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. This document corrects two errors that resulted in the incorrect references of two paragraphs. This correction is necessary to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of thedoor, flight control, or severe structural damage.
2022-21-01: The FAA is superseding Airworthiness Directive (AD) 2021-06- 07, which applied to certain Airbus SAS Model A330-200 series and A330- 300 series airplanes. AD 2021-06-07 required repetitive detailed inspections of the courier area oxygen system (CAOS) and replacement of affected parts if necessary. Since the FAA issued AD 2021-06-07, improved flexible oxygen hoses have been developed. This AD continues to require repetitive detailed inspections of the CAOS and replacement of affected parts if necessary. This AD also requires replacing each affected part with an improved serviceable part, which is terminating action for the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.