Results
2014-15-16: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -231, and -232 airplanes. This AD requires a detailed inspection for missing fasteners on the frame between certain stringers; for certain airplanes, a rototest inspection of the fastener holes for cracking; and corrective actions if necessary. This AD was prompted by a report that when the cabin lining was removed during a cabin conversion it was discovered that fasteners were missing on the frame. We are issuing this AD to detect and correct missing fasteners which, if not corrected, could affect the structural integrity of the airframe and could result in rapid decompression.
2000-01-10: This amendment supersedes Airworthiness Directive (AD) 98-08-07, which currently requires replacing the rudder and elevator pivot arms with parts of improved design on certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires replacing the rudder and elevator pivot arms with parts that have been improved since issuance of AD 98-08-07. 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 failure of the elevator and rudder caused by fatigue cracking of the pivot arms, which could result in reduced airplane controllability and possible loss of control of the airplane.
2000-01-02: This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Model BAe.125 series 1000A and 1000B airplanes and Model Hawker 1000 series airplanes, that requires an inspection to determine the integrity of the duct connection on both ends of the turbine air discharge duct in the air conditioning system; an inspection to measure the bead height on the ends of the turbine air discharge duct; and corrective actions, if necessary. This amendment is prompted by reports indicating that the turbine air discharge duct disconnected from the cold air unit (CAU) or water separator due to insufficient bead height on the ends of the turbine air discharge duct. The actions specified by this AD are intended to prevent such disconnection from the CAU or water separator, which could result in cabin depressurization.
48-51-02: 48-51-02 CONVAIR: Applies to All Model 240 Aircraft. Recently reported difficulties concerning the horizontal tail surfaces for Convair Model 240 aircraft have indicated the necessity of conducting thorough and frequent inspections of all critical items to detect any fatigue cracks and to minimize the development of hazardous conditions. The several reported difficulties appear to result from tail vibrations induced by the engines and/or propellers at certain r.p.m.'s. Pending completion of the necessary investigations and determination of adequate remedial measures, the following must be accomplished: A. To be accomplished daily on the left horizontal surfaces. (NOTE: Time limit may be extended to each No. 3 operation upon incorporation of AD 49-44-02 and CVAC Service Bulletins 240-219 and 240-247). Utilizing available inspection openings but without removing any surfaces, conduct a close, visual inspection of the following: 1. Horizontal stabilizer skin, rearspar and hinge brackets. 2. Elevator skin, leading edge ribs, spars, hinge brackets and balance weight installations. 3. Tab skin, spar, hinge brackets and balance weight installations. Particular care should be taken to detect any evidence of loose balance weights, sheared rivets or cracked hinge brackets. Any failed parts should be adequately repaired or replaced prior to the next flight. NOTE: Inspection procedures which have been satisfactorily demonstrated to the CAA Agent to provide equivalent safety may be accepted in lieu of the inspection procedures outlined above. NOTE: The following static balance tolerances about the respective hinge lines must be retained after rework of any surface: 1. Left elevator, including flight tab; 72-87 inch-pounds tail heavy with the seal curtain removed. 2. Right elevator, including trim tab: 0-15 inch-pounds nose heavy with the seal curtain removed. 3. Elevator flight tab: 6-8 inch-pounds nose heavy. B. To be accomplished at periods not to exceed 50 hours until close tolerance bolts and bushings have been installed in elevator tab hinges in accordance with CVAC Service Bulletin 240-205. Remove all elevator flight tab hinge pins and inspect the pins, bushings and bearings for sign of wear. Worn parts should be replaced. This supersedes AD 48-47-01.
2014-15-09: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200 and -300, and A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reassessment of an unsafe condition related to MZ-type spoiler servo-controls (SSCs) that did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. This reassessment resulted in the determination that performing repetitive operational tests of all SSC types is necessary. This AD requires repetitive operational tests of the hydraulic locking function on each SSC installed on the blue or yellow hydraulic circuits, and replacing any affected SSC with a serviceable SSC. We are issuing this AD to detect and correct loss of the hydraulic locking function during take-off, which, in combination with one inoperative engine, could result in reduced controllability of the airplane.
2000-01-05: This amendment supersedes an existing airworthiness directive (AD) applicable to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections and tests of the thrust reverser control and indication system on each engine, and corrective actions, if necessary; installation of a terminating modification; and repetitive operational checks of that installation, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in significant reduction in airplane controllability. The actions specified in this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane. This action identifies certain repetitive operational checks that were inadvertently omitted from the existing AD, and revises certain procedures for accomplishment of the operational checks and certain follow-on corrective actions.
82-19-02: 82-19-02 GENERAL DYNAMICS: Amendment 39-4458. Applies to Model 340, 440, and military models eligible or to be made eligible for civil use under Type Certificate 6A6, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent possible loss of a horizontal stabilizer due to failure of the stabilizer attachment fittings (P/Ns 340-8510150 and 340-8510151) caused by fatigue cracks, accomplish the following: A. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 450 hours of time in service, conduct a visual inspection of the upper and lower, forward and aft, horizontal stabilizer attachment fitting lugs in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions," General Dynamics Convair Division Service Bulletin 640 (340D)55-3A, Revision 1, dated June 12, 1981. If cracks are found, replace with a new part before further flight. B. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 1150 hours of time in service, conduct an ultrasonic inspection of the upper and lower, forward and aft, horizontal stabilizer attachment fitting lugs in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-3A. If cracks are found, replace with a new part before further flight. C. Repeat the visual inspection required by paragraph A of this AD at intervals not to exceed 700 hours time in service from the last such inspection and repeat the ultrasonic inspection required by paragraph B of this AD at intervals not to exceed 1400 hours time in service from the last such inspection. D. Within 10,000 hours time in service from the effective dateof this AD, unless already accomplished, install bushings in the horizontal stabilizer attachment fitting lug holes in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-3A. Continue to visually inspect at 700 hour intervals per paragraph A and to inspect by ultrasonic procedures at 1400 hour intervals per paragraph B of this AD. E. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 450 hours time in service, conduct an internal visual inspection for cracks in the horizontal stabilizer attachment fittings, upper, lower, forward and aft, and associated structure outboard of the lugs and butt rib in the area surrounding the fasteners, in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of General Dynamics Convair Division Service Bulletin 640 (340D) 55-4, Revision 1, dated March 24, 1982. Inspect for evidence of loose rivets or fasteners in the stabilizer attachment fittings with particular attention given to those just outboard of the butt rib which fasten the upper forward fittings to the spar web and rail. If cracks are found in the stabilizer attachment fittings or associated structure, and/or if loose fasteners are detected in the stabilizer attachment fitting: replace fitting with a new part, repair structure, and/or replace the fasteners, in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-4 before further flight. F. Within 250 hours time in service or within 90 days from the effective date of this AD, whichever occurs first, unless previously accomplished within the last 1150 hours time in service, conduct an x-ray inspection for cracks in the upper forward and upper aft horizontal stabilizer attachment fittings in the area outboard of the lugs in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-4. Only the four (4) upper fittings are required to be x-ray inspected as they are the most highly loaded in tension and therefore most susceptible to fatigue cracking. If cracks are found, replace with a new part before further flight. G. Repeat the visual inspection required by paragraph E of this AD at intervals not to exceed 700 hours time in service from the last such inspection and repeat the x-ray inspection required by paragraph F of this AD at intervals not to exceed 1400 hours time in service from the last such inspection. H. Within 10,000 hours time in service from the effective date of this AD, unless already accomplished, replace the first three (3) steel rivets outboard of the butt rib through the two (2) forward upper horizontal stabilizer attachment fittings in accordance with the applicable provisions of paragraph 2 entitled, "Accomplishment Instructions" of SB 640 (340D) 55-4. Continue to visually inspect at 700 hour intervals per paragraph E and x-ray inspect at 1400 hour intervals per paragraph F of this AD. I. Prior to issuance of a Certificate of Airworthiness for military aircraft being converted for civil certification, and prior to further flight for any aircraft that has been out of service for one (1) year or more, the airplane must be inspected in accordance with paragraphs A, B, E, and F of this AD. J. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections or modifications required by this AD. K. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Dynamics, Convair Division, P.O. Box 80877, San Diego, California 92138. These documents also may be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168; or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California. This supersedes AD 81-16-07, Amendment 39-4180 (46 FR 39431), issued July 24, 1981, and AD 80-11-01, Amendment 39-3775 (45 FR 35309), issued May 13, 1980. This Amendment becomes effective September 16, 1982.
74-10-10: 74-10-10 AIRESEARCH MANUFACTURING COMPANY OF ARIZONA: Amendment 39-1842 as amended by Amendment 39-1868 is further amended by Amendment 39-2253. Applies to Model TPE331-1-151B, -2-201C, -3U-307G, -5-251C, -5-251K and -6-251M engines. Compliance required as indicated. To detect, correct and prevent loosening of the fuel control assembly mounting and support bracket fasteners, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless previously accomplished, replace the fuel control assembly support bracket with a new bracket in accordance with instructions contained in paragraph 2.B. of AiResearch Service Bulletin TPE331-73-0028, dated April 29, 1974, or later FAA-approved revisions. (b) Within 100 hours time in service after accomplishment of paragraph (a), above, or 25 hours additional time in service after the effective date of this AD, whichever occurs later, and intervals not to exceed 100 hours time in service thereafter, inspect and retorque the fuel control assembly and support bracket mounting fasteners in accordance with the procedures contained in paragraph 2.C. of AiResearch Service Bulletin TPE331- 73-0028, dated April 29, 1974, or later FAA-approved revisions. (c) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. Note: AiResearch Operating Information Letter OI-331-3, Revision A, dated April 19, 1974, provides pertinent operational information. Flight crews are urged to obtain a copy of this letter and acquaint themselves with the information presented therein. (d) Unless previously accomplished, within the next 1000 hours time in service, or within one year after the effective date of this AD, whichever occurs earlier, the fuel control assembly support bracket attachment lug and fastener must be modified in accordance with AiResearch Service Bulletin TPE331-73-0029, dated May 27, 1974, or later FAA-approved revisions. This change has been incorporated in production engines by model and serial number as defined in paragraph 1.A. of the above referenced service bulletin. (e) The recurring inspection required in (b), above, may be discontinued when the modification prescribed in (d), above, have been accomplished. (f) If the replacement of the support bracket required by paragraph (a), above, has not already been accomplished on the effective date of this amendment to the AD, this modification, when accomplished, must be done in accordance with the instructions contained in paragraph 2.B. of AiResearch Service Bulletin TPE331-73- 0028, Revision 2, dated June 20, 1975, or later FAA-approved revisions. (g) If the replacement of the support bracket required by paragraph (a), above, has already been accomplished, at the next inspection required by paragraph (b), above, install the three (3) washers, P/N 960C10, and bolts, P/N MS21379-14, as required, per paragraph 2.B. of AiResearch Service Bulletin TPE331-73-0028, Revision 2, dated June 20, 1975, or later FAA-approved revisions. (h) If the modification described in paragraph (d), above, has already been accomplished, before exceeding an additional 100 hours time in service after the effective date of this AD, as amended, unless already accomplished; or, when accomplishing paragraph (d), install the three (3) washers, P/N 960C10 and bolts, P/N MS21279-14, as required, per paragraph 2.B. of AiResearch Service Bulletin TPE331-73-0028, Revision 2, dated June 20, 1975, or later FAA-approved revisions. Amendment 39-1842 became effective May 13, 1974. Amendment 39-1868 became effective June 14, 1974. This amendment 39-2253 becomes effective July 11, 1975.
2014-15-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD requires revising the airplane flight manual to incorporate temporary revisions that introduce additional limitations for operation of taxi and landing lights. This AD was prompted by a determination that there is a potential for fuel leakage from auxiliary power unit (APU) boost pump component installations in the right-hand landing lights compartment. We are issuing this AD to advise the flightcrew of the limitations for taxi lights and landing lights to prevent heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, which could potentially ignite any fuel or fumes present in the right-hand landing lights compartment.
2014-15-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A310-304, -322, -324, and -325 airplanes. This AD was prompted by reports of insufficient clearance between the fuel quantity indicator (FQI) probes and the adjacent structure and metallic components in the wing fuel tanks. This AD requires a one-time detailed visual inspection for sufficient clearance between FQI probes on both the left-hand side and right-hand side of the trim horizontal stabilizer and the adjacent structure and metallic components in the fuel tanks, and modification if necessary. We are issuing this AD to detect and correct insufficient clearance, which could lead to electrical arcing in a fuel tank during a lightning strike, which could result in ignition and consequent fire or explosion in the fuel tank.