Results
2003-04-14: This amendment adopts a new airworthiness directive (AD) for the specified Bell model helicopters that requires replacing the hydraulic solenoid tee fitting (tee fitting) and tubes. This amendment is prompted by the manufacturer's discovery that tee fittings may be installed improperly and restrict hydraulic fluid flow. The actions specified by this AD are intended to prevent restricted flow of hydraulic fluid to the flight control hydraulic actuators resulting in loss of hydraulic control, excessive stiffness in the flight controls, and a subsequent forced landing of the helicopter.
2023-03-09: The FAA is superseding Airworthiness Directive (AD) 2021-20- 09, which applied to certain ATR--GIE Avions de Transport R[eacute]gional Model ATR72 airplanes. AD 2021-20-09 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive tasks and airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-20-09 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive tasks and airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
67-19-02: 67-19-02 BRITISH AIRCRAFT: Amdt. 39-434, Part 39, Federal Register June 10, 1967. Applies to British Aircraft Corporation Model BAC 1-11, 200 and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To detect honeycomb delamination on all moveable control surfaces and tabs, accomplish the following: (a) Within the next 600 hours' time in service after the effective date of this AD for airplanes with 1000 or more hours' time in service, or for airplanes with less than 1000 hours' time in service as of the effective date of this AD before the accumulation of 1500 hours' time in service, tap test all control surfaces and tabs for evidence of delamination of the skin from the honeycomb structure in accordance with British Aircraft Corporation Alert Service Bulletin No. 55/57-A-PM 2597, dated September 19, 1966, or later ARB-approved issue. (b) If the control surfaces with delamination are within the permissible limits specified in BAC Structural Repair Manual, they may remain in service, but must be inspected in accordance with paragraph (a) at intervals not to exceed 300 hours' time in service from the date of the last inspection. (c) Control surfaces with delaminations exceeding the permissible limits as specified in BAC Structural Repair Manual, must be repaired or replaced, before further flight, in accordance with this Structural Repair Manual, or later ARB-approved issue, or FAA-approved equivalent. This amendment effective July 10, 1967.
2016-04-10: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport Regional Model ATR42-500 airplanes, and Model ATR72-102, -202, -212, and -212A airplanes. This AD was prompted by a report of chafed wires between electrical harnesses. This AD requires inspections for wire discrepancies, and corrective actions if necessary. We are issuing this AD to detect and correct damaged wiring and incorrect installation of the wiring harness and adjacent air ducts that could lead to wire harness chafing and arcing, possibly resulting in an on-board fire.
2018-23-02: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 and A319 series airplanes; Model A320-211, A320- 212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes. This AD was prompted by reports of missing assembly hardware on the trimmable horizontal stabilizer actuator (THSA). This AD requires repetitive inspections and checks of the lower and upper THSA attachments and applicable related investigative and corrective actions; a one-time inspection of the THSA lower attachment and [[Page 59279]] replacement as applicable; and, for certain airplanes, activation of the electrical load sensing device (ELSD) and concurrent modifications. We are issuing this AD to address the unsafe condition on these products.
2003-16-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections to detect cracking of the front spar web of the wing, and corrective action if necessary. This amendment adds one airplane to the applicability, changes certain compliance times, adds certain new requirements, and provides an optional modification. This action is necessary to detect and correct fatigue cracking of the front spar web, which could result in fuel leaking onto an engine and a consequent fire. This action is intended to address the identified unsafe condition. \n\nDATES: Effective September 22, 2003.\n \n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 22, 2003.\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-57A2311, dated January 27, 2000, as listed in the regulations, was approvedpreviously by the Director of the Federal Register as of January 30, 2001 (65 FR 81331, December 26, 2000).
47-41-08: 47-41-08 BELL: (Was Mandatory Note 20 of AD-1H-2.) Applies to All Models of 47B Series, Through Serial Number 78. Compliance required at next 100-hour inspection. The stabilizer bar mixing levers should be reworked by cutting away the lower inboard edge of a 2-inch radius from a center position 1 1/2 inches from the vertical centerline of the center hole. The cut should not be more than 1/8 inch at its deepest point and the sharp corners, resulting from the removal of this segment, should be rounded by a 1/2-inch radius. This reworking will eliminate the interference between those levers and the stabilizer bar damper, which may exist when the stabilizer bar is depressed 5 degrees. (Complete instructions are carried by Bell Service Bulletin 47C52, dated July 9, 1947.)
48-19-02: 48-19-02 LOCKHEED: Applies to Models 49-46, 149-46, 649-79 and 749-79 Aircraft. Compliance required at next No. 1 inspection, and thereafter at periods not to exceed 550 hours of operation. Inspect the two fittings, P/N 256019, "Lever-Cockpit Torque Tube", in the elevator control system for the presence of cracks or other signs of failure at the rivet attachment points, particularly at the base of the arm. Remove and replace any defective parts. The periodic inspection may be discontinued if the two levers are replaced with new parts, LAC No. 302349, or are reinforced with additional fittings, LAC No. 302337, or their equivalents. (LAC Service Bulletin 49/SB-456 covers the lever substitution or reinforcement.)
46-39-04: 46-39-04 DOUGLAS: (Was Mandatory Note 7 of AD-762-7.) Applies to C-54 Series Aircraft. \n\n\tTo be accomplished not later than November 15, 1946. \n\n\tInstances of valve freezing, due to ice forming in the detent chamber, have been reported on fuel tank selector and crossfeed valves. To prevent valve freezing, the Parker and Hydro Aire valves must be reworked by filling the detent chamber with Dow Corning compound No. 4 and installing a washer to retain the compound and to act as a water shield. \n\n\t(Douglas Drawings 4331597 and 2331524 cover this same subject.)
47-50-02: 47-50-02 CESSNA: Applies to 120 and 140 Aircraft Serial Numbers Up to and Including 14289. Inspection required upon each 100 hours of operation until fuselage rear bulkhead (tail post) has been reinforced. Inspect the lower right-hand corner of the cutout in the fuselage rear bulkhead for cracks which usually extend down to the rivet holes at the nearest anchor nut. If cracks are found, install the new type bulkhead with reinforcement channel added per Cessna Drawing No. 0412169. (Cessna Service Letter No. 46 dated July 31, 1947, covers this same subject.)
47-50-13: 47-50-13 DOWNER (BELLANCA and UNIVERSAL (Stinson): Applies Only to Aircraft Equipped With Koppers Model Aeromatic F200 Propellers. Compliance required no later than the next 25-hour propeller lubrication and at 25 hours of operation thereafter. Inspect propeller hub as follows: Remove balancing band from both ends of hub barrel after index marking each to facilitate proper reassembly. Examine the other surfaces of the hub completely for indications of line cracks or fractures. The areas of primary concern are (1) those beneath the balancing bands, (2) the weld joint where hub barrel and mounting tube meet, and (3) the weld joint where mounting tube and mounting flange meet. Defective hubs should be removed from service. (Koppers Service Bulletin No. 12, dated October 9, 1947, covers this same subject.)
76-19-05: 76-19-05 AVIONS MARCEL DASSAULT (AMD): Amendment 39-2730. Applies to all Model Fan Jet Falcon airplanes, all Series, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent the possible inability of the emergency fuel shut-off valves to shut down the engines, accomplish the following: (a) Within the next 20 hours time in service after the effective date of this AD, unless already accomplished, inspect the fuel shut-off control in accordance with AMD Service Bulletin No. 551, dated March 3, 1976, or FAA-approved equivalent, for each engine to determine the time for the engine to flame-out after actuation of the emergency fuel shut-off control with the engine operating initially at ground idle rpm. If flame-out time is found to exceed 15 seconds, prior to further flight, except that the airplane may be flown in accordance with FARs 21.197 and 21.199 to a base where the repair can be performed, readjust the emergency fuel shut-off control in accordance with Fan Jet Falcon Maintenance Manual Chapter 76-20-2, pages 501 through 503, or an FAA-approved equivalent. (b) Within the next 150 hours time in service or 60 days after the effective date of this AD, whichever occurs later, unless already accomplished, inspect for proper assembly and repair, as necessary, the fuel shut-off valves, Zenith P/N B99-26203 and B99-26204, in accordance with AMD Service Bulletin No. 550, dated March 3, 1976, or an FAA-approved equivalent. This amendment becomes effective October 7, 1976.
2016-04-11: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 turbofan engine models. This AD was prompted by reports of two separate, single engine in-flight shutdowns [[Page 9752]] (IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade failure. This AD requires inspection and conditional removal of affected HPT rotor stage 1 blades. We are issuing this AD to prevent failure of the HPT rotor stage 1 blades, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.
2003-03-13: This amendment adopts a new airworthiness directive (AD) that applies to all MORAVAN a.s. (Moravan) Model Z-242L airplanes. This AD establishes a technical service life for these airplanes by restricting Acrobatic and Utility category operations and requiring replacement of the wings after a certain operational time period. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to prevent structural failure of the wing due to fatigue cracking. Such failure could result in a wing separating from the airplane with consequent loss of airplane control.
2018-18-09: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes; and certain Model C-295 airplanes. This AD was prompted by a report that cracks were found on the stabilizer-to- fuselage rear attachment fitting. This AD requires a detailed inspection of the upper and lower lugs of each horizontal stabilizer- to-fuselage rear attachment fitting, repair if necessary, and a report of findings. We are issuing this AD to address the unsafe condition on these products.
2008-22-12: We are adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires repetitive inspections for any crack in the area of the elevator side fitting/hinge fitting joint and for any crack or elongation inside and outside of the holes in the clevis and in the lug, corrective actions if necessary, and other specified actions. This AD results from reports of elongated holes and cracks found in the lugs of the attachment fittings of the elevator quadrant upper support assembly at the tip of the vertical fin. We are issuing this AD to detect and correct damage to the aft attachment lugs of the elevator quadrant support assembly that could lead to failure of the lugs. This condition could accelerate wear elsewhere in the elevator control system, which could reduce the crew's ability to maintain safe flight.
75-06-09: 75-06-09 BEECH: Amendment 39-2129. Applies to Models 60 and A60 (Serial Numbers P-3 through P-200) airplanes with more than 150 hours' time in service. Compliance: Required as indicated, unless already accomplished. To prevent malfunctions of the elevator inboard hinge supports, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: Remove the left and right elevator inboard hinge supports (P/N 60-524078-1 and 60- 524078-2) and install improved supports in accordance with Beech Kit No. 60-4005 or any equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instruction No. 0342-132, Revision III, or later revision refers to this subject. This amendment supersedes Amendment 39-1463, AD 72-13-01. This amendment becomes effective March 20, 1975.
2003-12-05: This amendment supersedes an existing airworthiness directive (AD), that is applicable to McCauley Propeller Systems 1A103/TCM series propellers. That AD currently requires an initial inspection for cracks in the propeller hub in accordance with a dye penetrant inspection procedure, replacement of propellers with cracks that do not meet acceptable limits, rework of propellers with cracks that meet acceptable limits, and repetitive inspections of all affected propellers. This amendment allows additional rework operations to be performed at more than one bolt hole location. This amendment is prompted by the need to clarify the requirement to use a steel backing plate and Mylar gasket during installation of the propeller, and to relax the replacement requirements. The actions specified in the proposed AD are intended to prevent propeller separation due to hub fatigue cracking, which can result in loss of control of the airplane.
2003-03-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires replacement of the screws in the aileron, rudder, and elevator trim tabs with new screws; and removal and re-installation of screws in the aileron, elevator, and rudder trim tabs and the rudder spring tab; as applicable. This action is necessary to prevent reduced structural integrity of the screws in the aileron, elevator, and rudder trim tabs and the rudder spring tab, due to countersinks that were not manufactured correctly, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-02-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2003-02-51 that was sent previously to all known U.S. owners and operators of Bombardier Model CL-600-2C10 (Regional Jet Series 700 and 701) series airplanes by individual notices. This AD requires an airplane flight manual (AFM) revision to introduce new quantity limitations for the center fuel tank and associated procedures; to limit flight to within 30 minutes of a suitable alternative airport; and to limit the center tank fuel quantity to 1,500 lbs. (680 kgs.) maximum at takeoff. This action is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. The actions specified by this AD are intended to detect and correct discrepancies in the fuel distribution system, which could cause the center tank to overfill and fuel to leak from the center tank vent system or to become inaccessible, and could result in engine fuel starvation.
47-27-01: 47-27-01 WACO: (Was Mandatory Note 4 of AD-648-1.) Applies to Models UKS-7, VKS-7, VKS-7F Aircraft. Compliance required not later than next periodic inspection. Inspect tank area in wings for damage to plywood tank support and wing spars caused by collection of moisture in the boxed area of the fuel tank. 1. Remove the left and right fuel tanks and inspect the condition of the plywood tank support and the front and rear spars. 2. If the plywood supports are found to be in poor condition they should be replaced using new plywood. 3. If the spars have been affected by the accumulated moisture, repairs should be made in accordance with FAA requirements or in extreme cases the spar should be replaced. 4. In order to provide drainage of the tank compartment three holes 3/16 inch in diameter should be drilled through the plywood support at the extreme rear of the support as close to the rear spar as possible without damaging the spar. These drain holes should, of course, extend through the fabric covering. 5. The drain holes should be drilled in all tank compartments at the time the fuel tanks are removed for this inspection. (The above inspection and recommended remedial measures also covered by Waco Aircraft Co. Service Letter No. 3.)
47-06-04: 47-06-04 GLOBE: (Was Mandatory Note 7 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 408 Inclusive; 1004 to 1224 Inclusive; and 2001 to 2324 Inclusive. Compliance required prior to April 1, 1947. Replace the AN 960-616 washers under the nuts at the attachment of the main landing gear retraction links to the shock struts with AN 940-616 washers. This is necessary for proper retention of the bushings in the retraction links. (Globe Customer Service Maintenance Bulletin No. 10 covers this same subject.)
2009-01-09: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A310 series airplanes. That AD currently requires repetitive detailed inspections to detect cracks propagating from the fastener holes that attach the left- and right- hand pick-up angles at frame 40 to the wing lower skin and fuselage panel, and corrective actions if necessary. This new AD revises the intervals for accomplishing the repetitive detailed inspections and provides for an optional terminating modification for the repetitive inspections. This new AD also revises the applicability of the AD to remove certain airplanes. This AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent reduced structural integrity of the airplane due to fatigue damage, and consequent cracking of the pick-up angles at frame 40.DATES: This AD is effective April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of February 9, 2001 (66 FR 1031, January 5, 2001).
2016-04-15: We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI), Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with a certain part-numbered main rotor blade attach pin (pin) installed. This AD requires ensuring the life limit of the pin as listed in the Airworthiness Limitations section of aircraft maintenance records and Instructions for Continued Airworthiness (ICA). If the hours time-in-service (TIS) of a pin is unknown, or if a pin has exceeded its life limit, this AD requires removing the affected pin from service. This AD was prompted by a report from an operator who purchased pins that did not have life limit documentation. These actions are intended to document the life limit to prevent a pin remaining in service beyond its fatigue life, which could result in failure of a pin, failure of a main rotor blade, and subsequent loss of control of the helicopter.
70-17-03: 70-17-03 HUGHES: Amdt. 39-1070. Applies to Model 269 Series helicopters certificated in all categories, which incorporate lead-lag and flapping hinge bolts, P/N HS 1446- 10-68, (only the lead-lag bolts are affected on Model 269C) with vendor identification BM (stylized) impression stamped on top of the bolt heads hereinafter referred to a BM bolts. Compliance required as indicated. To detect cracks in the BM bolts, P/N HS 1446-10-68, accomplish the following: Within 50 hours time in service after the effective date of this AD, unless already accomplished, remove all BM bolts in accordance with Hughes Handbook of Maintenance Instruction (BM bolts with the head dyed green or a white dot painted in the recessed head have been inspected and are not affected by this AD. The white dot was used in instances where the green dye application was not effective.) Perform a magnaflux inspection of the BM bolts for evidence of cracking. (a) Replace any BM bolt which shows evidence of cracking, with a serviceable bolt prior to further flight. Efface the part number of any cracked bolts sufficiently to prevent their inadvertent return to service. (b) Any BM bolt which shows no evidence of cracking may be returned to service after it has been identified with a white dot painted in the recessed head of the bolt. NOTE: (Hughes Service Information Notice No. N-78, dated July 31, 1970, pertains to the same subject.) This amendment becomes effective August 20, 1970.