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2018-11-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A350-941 airplanes. This AD requires a detailed inspection of the four retaining pins in the main landing gear support structure (MLGSS) trunnion block, left- and right-hand sides, and related investigative and corrective actions if necessary. This AD was prompted by a determination that short retaining pins may have been installed at the incorrect location of the MLGSS forward pintle. We are issuing this AD to address the unsafe condition on these products.
2005-17-15: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arrius 2F turboshaft engines. This AD requires a one-time removal and inspection of the fuel filter-holder assembly to determine that the fuel control unit (FCU) filter is dimensionally correct. The AD also requires updating the Engine Maintenance Manuals to include a dimensional check of the fuel filter-holder assembly every time the FCU filter element is removed from the fuel filter-holder assembly. This AD results from reports of restricted fuel flow caused by a dimensionally incorrect FCU filter. Ground run testing may not detect the fuel flow limitation. We are issuing this AD to detect a dimensionally incorrect FCU filter that could lead to an undetected limitation of fuel flow, limiting the maximum power available in-flight, which could result in the inability to continue safe flight, avoid obstacles or land safely.
2000-22-02 R1: This document corrects information in an existing airworthiness directive (AD) that applies to all Boeing Model 737 series airplanes. That AD supersedes AD 99-05-15, amendment 39-11063, to require revising the FAA-approved Airplane Flight Manual (AFM) procedure in the existing AD to simplify the instructions for correcting a jammed or restricted flight control condition. This document corrects the format for certain AFM material described in that AD. This correction is necessary to ensure that the flightcrew is aware of certain critical recall items in the AFM procedure that are necessary to address a condition involving a jammed or restricted rudder.
64-17-04: 64-17-04 CHAMPION: Amdt. 774 Part 507 Federal Register July 28, 1964. Applies to Model 402 Aircraft. Compliance required as indicated. There have been instances of cracking of exhaust stack extension at the clamp which attaches it to the main exhaust manifold. This allows hot exhaust gases to discharge into the engine compartment. There have also been failures of the exhaust stack extension rear support hanger. To correct this condition, accomplish the following: (a) Before each flight after the effective date of this AD, check by grasping and shaking for movement each exhaust stack extension to determine whether the exhaust stack extension connection to the manifold is loose or the rear support hanger has failed and make an appropriate entry in the aircraft record. The pilot may perform the check set forth in this paragraph. (b) Repair or replace loose or failed components before further flight. (c) Within 25 hours' time in service after the effective date of this AD, and within every 50 hours' time in service thereafter, accomplish the following: (1) Remove the attachment clamp which attaches the exhaust stack extension to the manifold on the right and left sides of both engines and visually inspect for cracks in the joining area of the exhaust stack extension and the exhaust manifold. Also visually inspect for elongated locating pin holes and for sheared or worn clamp positioning pins. (2) Check the edge distances of the clamp locating pin holes in the manifold. The minimum allowable edge distance is one-half inch. If the edge distance is less than one-half inch, reinstall the exhaust stack extension in accordance with the reinstallation instructions in Champion Service Letter No. 66. (3) Visually inspect stack extension rear support hanger for failure. (4) Replace or repair any failed or worn parts. (d) The repetitive inspections in paragraphs (a) and (c) may be discontinued when an improvedexhaust stack extension attachment clamp and flexible rear stack hangar have been installed on right and left sides of both engines in accordance with Champion Kit No. 224. (Champion Service Letter No. 66 and Champion Kit No. 224 cover this same subject.) This directive effective July 28, 1964. Revised October 15, 1964.
46-17-01: 46-17-01\tNORTH AMERICAN: (Was Mandatory Note 5 of AD-2-575-3.) Applies to Army BC-1A, AT-6, -6A, -6B, -6C; Navy SNJ-2, -3, -4 Aircraft. \n\n\tTo be accomplished prior to original certification or at first periodic inspection thereafter. \n\n\tInspect the universal joint pins in the flap control push-pull tubes, P/N 19-152642, connecting the outer and inner flap for broken pins. Replace all broken pins with new pins and install a close fitting rubber hose over each universal joint to hold in place any pins which may break in the future. \n\n\t(North American Service Bulletin dated March 6, 1947, covers this subject also.)
2018-11-15: We are adopting a new airworthiness directive (AD) for all Airbus Model A320-271N airplanes, and Model A321-271N, -271NX, -272N and -272NX airplanes. This AD requires replacing certain full authority digital engine control (FADEC) electronic engine controllers (EECs); or installing software standard FCS4.4 and re-identifying the FADEC EECs. This AD was prompted by a report that, when operated at low speed and high engine thrust, an engine did not restart following a fuel interruption shorter than five seconds. We are issuing this AD to address the unsafe condition on these products.
99-10-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-145 series airplanes. This action requires replacement of certain flexible joints and O-rings of the rear fuselage with improved flexible joints and new O-rings. This action also requires installation of new support assemblies to attach to the engine bleed line tubing in the area of the rear fuselage to improve the engine bleed line tubing alignment. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of certain flexible joints that attach to the engine bleed lines in the area of the rear fuselage. Failure of these flexible joints could cause damage to the fuel lines leading to the auxiliary power unit, which could result in an increased risk of fire to occur in the rear baggage compartment during flight.
49-11-02: 49-11-02 AERONCA: Applies to Serial Numbers S7AC and 7AC-1 to 7AC-7170, Inclusive; 7BCM-1 to 7BCM-339, Inclusive; 11CC-1 to -150, Inclusive; and All S11AC, 11AC and 11BC Serial Numbers. Compliance required at next periodic inspection but not later than May 1, 1949. To prevent failure of the rear fuselage-wing attachment fitting, reinforcement is to be accomplished by either of the following methods: 1. Cut on both sides of the rear spar fuselage carry through tube, at each end, a vertical slot 1/4 inch long. Insert a 5/8 inch by 0.083 (or heavier wall) 4130 steel, square or round tube having a minimum length of 2 1/2 inches and weld both sides of slot top and bottom of tube. Drill and ream bolt hole 0.250 plus or minus .001. 2. Insert in each rear spar fuselage wing attachment fitting, on both sides of airplane, a 5/8 inch by 0.083 (or heavier wall) 4130 steel tube having a minimum length of 4 5/8 inches. The insert tube should have a 0.250 plus or minus .001hole drilled 9/16 inch from outer end of tube, and reamed prior to installation. Bolt insert tube in fitting, then drill two vertical 0.250 plus or minus .001 holes through the fuselage carry through tube and the insert tube at 3 and 4 inches, respectively, from end of fitting. Four AN 4-11A bolts and AN 365/428 nuts or equivalent are required to bolt in the two insert tubes. 3. Insert through the entire length of the rear spar fuselage carry through tube a 5/8 inch by 0.083 (or heavier wall) 4130 round or square tube. The insert tube should have a hole drilled and reamed 0.250 plus or minus .001, 9/16 inch from each end of the tube to line up with the original bolt holes. The insert tube should be secured to the fuselage carry through tube by means of one AN 4-11A bolt and AN 365-428 nut or equivalent through both tubes anywhere between the longerons (drill and ream 0.250, plus or minus .001) or by welding both ends of the tubes together. Airplanes having the 5/8 inch by .065 reinforcement tube installed prior to the issuance of this revision need not change to the .083 wall tube. (Aeronca Service Helps and Hints No. 43 covers this same subject.) This supersedes AD's 47-50-01 and 49-02-03.
47-49-05: 47-49-05 LOCKHEED: (Was Mandatory Note 38 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required prior to February 15, 1948. Replace quick-disconnect fasteners used to attach aileron control cable housing on radio operator's floor (LAC P/N 28717-8) with screws and AN 366F8-32 nut plates. (LAC Service Bulletin 49/SB-300 covers this same subject.)
64-16-06: 64-16-06 PIPER: Amdt. 767 Part 507 Federal Register July 21, 1964. Applies to Model PA-30 Aircraft, Serial Numbers 30-41, 30-82, 30-83, 30-104 and 30-123. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished. Because of the possible presence of welds with inadequate penetration in the nose gear retraction tube, replace the present tube with a redesigned nose gear retraction tube, Piper P/N 21109-05. NOTE: The new tube can be identified by the two bead weld slots on each end of the tube. (Piper Service Letter No. 409, dated October 9, 1963, provides replacement method instructions.) This directive effective August 20, 1964.