Results
98-26-17: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Jetstream Model 3201 airplanes. This AD requires accomplishing both a routine visual inspection and either a detailed visual inspection or x-ray inspection of the main landing gear (MLG) bay auxiliary spar booms for cracks or fuel leaks on both the left and right sides of the airplane. This AD also requires obtaining and incorporating repair procedures for the MLG bay auxiliary spar where fuel leaks or cracks are found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent wing failure caused by cracks or fuel leaks in the area of the MLG bay auxiliary spar booms, which could result in loss of control of the airplane.
75-17-32: 75-17-32 DETROIT DIESEL ALLISON: Amendment 39-2336. Applies to Detroit Diesel Allison Model 501-D13 series engines which incorporate P/N 6829072 second stage turbine wheels with the following serial numbers: KK14208 KK14421 KK14443 KK14460 KK15456 KK15484 KK14210 KK14422 KK14445 KK14461 KK15457 KK15485 KK14211 KK14423 KK14446 KK14463 KK15471 KK15486 KK14403 KK14424 KK14447 KK14464 KK15472 KK15487 KK14405 KK14427 KK14448 KK14465 KK15473 KK15489 KK14406 KK14428 KK14449 KK14817 KK15474 KK15490 KK14407 KK14430 KK14450 KK14819 KK15475 KK15492 KK14408 KK14431 KK14451 KK14821 KK15476 KK15493 KK14409 KK14432 KK14452 KK14822 KK15477 KK15494 KK14413 KK14434 KK14453 KK14823 KK15478 KK15495 KK14414 KK14435 KK14454 KK14825 KK15479 KK15496 KK14416 KK14436 KK14455 KK15451 KK15480 KK15497 KK14417 KK14437 KK14456 KK15452 KK15481 KK15498 KK14418 KK14440 KK14457 KK15453 KK15483 KK15500KK14420 KK14442 KK14459 KK15454 Note: At time of overhaul, some wheels have R1, R2, R3, R4 or R5 added as a suffix to the wheel serial number. The suffix should be disregarded in determining the applicability of this airworthiness directive. Compliance required as indicated. I. Remove from service wheels which have not been inspected since installation as new wheels, according to the following schedule: (a) Remove from service within 100 cycles from the effective date of this Airworthiness Directive, wheels with more than 6900 cycles. (b) Remove from service prior to exceeding 7000 cycles, wheels with not more than 6900 cycles, on the effective date of this Airworthiness Directive. II. Remove from service wheels which have been inspected by fluorescent penetrant method FP- 30A/ZL-30A at last inspection, according to the following schedule: (a) Remove from service within 100 cycles from the effective date of this Airworthiness Directive, wheels with more than 3900 cycles since last inspection or more than 9400 total cycles, whichever occurs first. (b) Remove from service prior to exceeding 4000 cycles since last inspection or 9500 total cycles, whichever occurs first, wheels with not more than 3900 cycles since last inspection or not more than 9400 total cycles on the effective date of this Airworthiness Directive. Note: If the method of fluorescent penetrant inspection used at last inspection cannot be determined, it must be assumed that FP-30A/ZL-30A was not used. III. Remove from service wheels which have been inspected by a fluorescent penetrant method other than FP-30A/ZL-30A at last inspection, according to the following schedule: (a) Remove from service within 100 cycles from the effective date of this Airworthiness Directive, wheels with more than 2400 cycles since last inspection, or more than 9400 total cycles, whichever occurs first. (b) Remove from service prior to exceeding2500 cycles since last inspection or 9500 total cycles, whichever occurs first, wheels with not more than 2400 cycles since last inspection or not more than 9400 total cycles on the effective date of this Airworthiness Directive. IV. or the purposes of this airworthiness directive, a cycle is defined as one takeoff. V. Detroit Diesel Allison Commercial Service Letter 501D13 CSL-234 pertains to this subject. This amendment is effective August 14, 1975.
2005-17-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. This AD requires doing a one-time general visual inspection of the axle nut on each main landing gear (MLG) wheel for the presence of locking bolts and associated hardware; doing any related investigative and corrective actions as applicable; and submitting an inspection report to the manufacturer. This AD results from a report that an axle nut had separated from an axle on a main landing gear (MLG) wheel, due to missing locking bolts. We are issuing this AD to detect and correct missing locking bolts on the axle nuts of the MLG wheels. Absence of the locking bolts could result in separation of a wheel(s) from the axle and consequent reduced controllability of the airplane during takeoff and landing, and possible injury to people on the ground.
47-20-03: 47-20-03 ERCO: (Was Mandatory Note 11 of AD-718-6.) Applies to All 415 Series Aircraft Ercoupes Up to and Including Serial Number 3642 Which Incorporate Fuel Pumps With a Metal Filter Bowl, and Bearing AC P/N 1539076 on the Pump Mounting Flange. Inspection to be accomplished immediately, alteration to be made not later than the next periodic inspection. Inspect immediately and at each 25 hours thereafter until the following alteration is completed, the fuel pump lines near the pump for failure and leakage due to chafing. Alter fuel pump lines not later than next periodic inspection as follows: Remove the fuel pump top and rotate it 120 degrees clockwise (two screwholes from the original position). Replace the pump inlet port fittings with AN 842-4D elbow and the outlet port fittings with (415-48101-40) elbow having 1/16-inch restriction. Drill two 3/4-inch diameter holes in right front engine cooling baffle and install grommets (AN 931-9-13). Route fuel pump hoses through respective holes; shorten outlet hose (415-48101-2) and install fuel pump hose (415-48101-2 and 415-48101-3) onto respective elbows securing them with two hose clamps (AN 746-4). Safety-wire clamps. Close extra unused hole in baffle with button plug (415-40589-1) or equivalent. (Erco Service Department Memorandum No. 42 dated January 9, 1947, covers this same subject.)
2005-13-35: The FAA is superseding an existing airworthiness directive (AD), which applies to all Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. That AD currently requires installation of a placard on the instrument panel of the cockpit to advise the flightcrew that positioning of the power levers below the flight idle stop during flight is prohibited. Additionally, the existing AD requires eventual installation of an FAA-approved system that would prevent such positioning of the power levers during flight. Installation of that system terminates the requirement for installation of a placard. This new AD requires operators who have incorporated a certain Bombardier service bulletin to perform repetitive operational checks of the beta lockout system and to revise the Airworthiness Limitations document. This AD is prompted by in-service issues reported by operators who incorporated Bombardier Service Bulletin 8-76-24 as an alternative method of compliance to the existing AD. We are issuing this AD to prevent the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability of the airplane.
48-39-01: 48-39-01 AERONCA: Applies to All Model 7 Series Aircraft. To be accomplished as soon as possible but not later than November 1, 1948. Inspect front and rear control stick socket castings, P/N 2-705, for cracks at the ears to which the push-pull tube attaches. If found cracked, the castings should be replaced. To prevent future failures the bolt, nut and washer now installed are to be replaced with a clevis bolt, AN 24- 16 (11/16 grip) and an AN 320-4 shear nut so that excessive loads cannot be placed on the socket ears.
47-49-07: 47-49-07 LOCKHEED: (Was Mandatory Note 40 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088, Unless Equipped With MLG Drag Strut Dampers. Compliance required prior to February 1, 1948. (a) Replace the NAS 58A65 bolt used to connect the two halves of each MLG upper drag link assembly, LAC P/N 283418 and 288983, with a 5/8-inch diameter high strength bolt, LAC P/N 297902. (LAC Service Bulletin 49/SB-368 covers installation of MLG shock strut dampers.) (b) Reduce MLG shock strut inflation pressures to provide a static extension of 2 inches at maximum landing weight.
48-05-01: 48-05-01 DOUGLAS: Applies to All DC3 Aircraft Equipped With Pacific Aviation Oil Shutoff Valves. \n\n\tCompliance required at first engine change after March 1, 1948, but not later than May 1, 1948. \n\n\tReplace the present "O" rings in the oil shutoff valves with rings of H222-90 high temperature material or AMS-3228B material. There has been reported leakage attributed to the fact that the material in the "O" rings is not capable of withstanding the operating temperature of the oil. \n\n\t(Douglas Service Bulletin DC3 No. 256 covers this same subject.)
2005-16-12: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH) model BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This AD requires a onetime inspection of the Independent Overspeed Protection (IOP) unit, part number (P/N) 112E9321G2, for 19 specific serial numbers (SNs), and removal from service of those units. This AD results from a report that incorrect capacitors were installed in 19 IOP units. The incorrect capacitor in the IOP unit can lead to an inadvertent IOP command resulting in an in-flight engine shutdown. We are issuing this AD to prevent inadvertent dual-engine in-flight shutdown.
46-23-05: 46-23-05 NOORDUYN: (Was Mandatory Note 1 of AD-2-578-1.) Applies to Army UC- 64, -64A, and -64B Aircraft. Required at next periodic inspection. Inspect the trailing edge of the horizontal stabilizer to determine whether or not drain holes are present in the metal trailing edge cover. If the holes are not present, it will be necessary to remove enough fabric to permit inspection of the ribs. Defective or deteriorated wood must be replaced and drain holes, approximately 1/16-inch diameter, spaced to drain all pockets must be drilled.