Results
2019-01-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200, -200F, and -300 series airplanes. This AD was prompted by a revision of the airworthiness limitations section (ALS), which provides new and more restrictive maintenance requirements and airworthiness limitations for airplane structures and systems. This AD requires revising the existing maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2018-19-30: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. This AD was prompted by a report of an improperly installed spacer around the electrical pins in the cartridge connector for the fire bottle extinguisher cartridge. This AD requires repetitive inspections for excessive or missing spacers, and applicable corrective actions. We are issuing this AD to address the unsafe condition on these products.
63-23-01: 63-23-01 DOUGLAS: Amdt. 638 as amended by Amendment 39-973. Applies to all DC-3 series aircraft including military type C-41, C-41A, C-47, C-47A, C-47B, C-48, C-48A, C-49, C-49A, C-49B, C-49C, C-49D, C-49J, C-49K, C-50, C-50A, C-50B, C-50C, C-50D, C-51, C-52, C-52A, C-52B, C-52C, C-53, C-53B, C-53C, C-53D, C-68, C-117A and R4D series except R4D-8 aircraft, certificated in all categories. \n\n\tCompliance required as indicated. \n\n\t(a) Unless already accomplished within the last 400 hours' time in service after the next 50 hours' time in service after the effective date of this AD, inspect the wing upper attach angles on both the outer wing and center section between the front and rear spars for cracks. Use at least a 4-power magnifying glass. Reinspect at periods not to exceed 450 hours' time in service from the last inspection. Replace cracked attach angles before further flight. \n\n\t(b) At the next wing removal, inspect all wings in the manner specified in (c), and reinspectat intervals not to exceed 8,000 hours thereafter. \n\n\t(c) At the time specified in (b), the removed wings shall be thoroughly cleaned and inspected as follows: \n\n\t\t(1) Inspect the center and outer wing upper attach angle doubler for cracks along the radius of the bent-up flange at the wing attachment point. Conduct the inspection with a 6-power magnifying glass or dye penetrant. \n\n\t\t(2) Inspect the center and outer wing upper attach angles including the areas between the attaching bolt holes for evidence of cracks. Remove all paint to permit inspection with a 6-power magnifying glass or by dye penetrant. \n\n\t(d) Replace, before further flight, any cracked parts found during the inspection set forth in paragraph (c) with new parts per Douglas Service Bulletin DC-3 No. 262, Reissue No. 1 June 14, 1963, or later FAA-approved revisions. \n\n\t(e) The proper installation alignment of the attach angles and doublers described in (d) shall be maintained. This shall be accomplished by the use of satisfactory jigs or by FAA approved equivalent means. Douglas jig fixtures P/N's A652-5110506-1-1F2 and A652-5110506-1F2 or P/N's C652-5110500-101-1-1F1 and C652-5110500-101-1F1 or those that meet the criteria of Advisory Circular AC 39-1, are considered to be satisfactory for alignment purposes. \n\n\t(f) The parts replaced in accordance with paragraph (d) shall be inspected in accordance with the requirements of paragraphs (b) and (c). All uncracked parts which are not replaced shall continue to be inspected per the inspection procedure of (c) with adherence to the previously established inspection schedules for these parts. \n\n\t(g) Whenever wings are being replaced after modification per (d); whenever spar butt plates on the center and outer wing, the compression angles on the center wing or the waffle plates on the outer wing are being reworked or replaced; or whenever one outer wing is substituted for another, the following tolerances shall be maintained:(1) Compression angles attached to the corrugations and stringers and the spar cap butt plates of the center wing must be held in plane with the wrap around doublers on the attach angle to within plus 0.004 inch/minus 0.000 inch. \n\n\t\t(2) Waffle plates attached to the stringers and the spar cap butt plates of the outer wing must be held in plane with the wrap around doublers on the attach angle to within plus 0.006 inch/minus 0.000 inch. \n\n\tNOTE-The tolerances ranges set forth in (g)(1) and (g)(2) will allow a flush to 0.010 interference between the compression angles and plates when the wing is installed. This interference fit assures the most effective distribution of loads across the joint and the maximum service life. \n\n\t(Douglas Service Bulletin No. 262, Reissue No. 1, June 14, 1963, or later FAA-approved revisions, covers this same subject.) \n\n\tAmendment 638 effective December 6, 1963. \n\n\tThis Amendment (39-973) becomes effective April 16, 1970.
2014-05-06 R2: We are removing Airworthiness Directive (AD) 2014-05-06 R1, which applied to Airbus Helicopters Deutschland GmbH (type certificate previously held by Eurocopter Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters. AD 2014-05-06 R1 required installing bushings and washers on the flight controls. This action is prompted by an error in the issuance of 2014-05-06 R1. Accordingly, AD 2014-05-06 R1 is removed.
81-01-06: 81-01-06 BENDIX AVIONICS: Amendment 39-4008. Applies to M-4 (A, B, C, D) Autopilot Primary Servo Models 3013E, 3013F, 3013G, 3013H, 3013J and 3013K and YD-4 Yaw Damper Primary Servos Models 3013J and 3013K having magnetic clutch, P/N 717503-0001, Serial Numbers 16750 through 18396, installed, repaired or overhauled after January 1, 1979, that do not contain Modification Number 4, as defined in Bendix Service Bulletin M-4D-060. PRIMARY SERVO PRIMARY SERVO PRIMARY SERVO MODEL NUMBER PART NUMBER SERIAL NUMBER *3013E 1U014-01 *3013F 1U014-02 *3013G 1U014-03 Any primary servo that has had magnetic clutches installed after January 1, 1979. 3013H 4000523-8501 9530 through 9925 and any primary servo that has been repaired or overhauled after January 1, 1979 3013J 4009506-8501 1775 through 1792 and any primary servo that has been repaired or overhauled after January 1, 1979. 3013K 4009506-8502 2067 through 2110 and any primary servo that has been repaired or overhauled after January 1, 1979. *Older model primary servos which may contain magnetic clutches manufactured by Bendix. Compliance is required as indicated below unless already accomplished. To prevent the possible failure of the primary servo due to seizure of the magnetic clutches (P/N 717503-0001, Serial Numbers 16750 through 18396), accomplish the following: Within the next 50 hours time in service after the effective date of this AD, inspect and modify the affected primary servos in accordance with Bendix Service Bulletin M-4D-060, dated November 1980 or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment is effective January 12, 1981.
2018-25-08: We are superseding Airworthiness Directive (AD) 2017-22-07, which applied to certain Airbus SAS Model A319 series airplanes; Model A320-211,-212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2017- 22-07 required repetitive inspections of the frame forks, and corrective actions if necessary. AD 2017-22-07 also included optional modifications that constituted terminating action. This AD requires modifying certain forward and aft cargo compartment doors, and related investigative and corrective actions. This AD was prompted by an evaluation done by the design approval holder indicating that certain areas of certain cargo compartment doors are subject to widespread fatigue damage, and a determination was made that a modification of the frame forks must be done. We are issuing this AD to address the unsafe condition on these products.
87-05-03: 87-05-03 AVIONS MARCEL DASSAULT - BREGUET AVIATION (AMD-BA): Amendment 39-5563. Applies to Model Mystere Falcon 200 series airplanes, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent malfunction of the fuel system crossfeed valve actuator, accomplish the following: A. Install a fuel system booster crossfeed valve actuator, AVIAC P/N 2778-1 (ZENITH P/N D97C00-215), in accordance with AMD-BA Service Bulletin No. AMD-BA F200- 64, dated March 3, 1986. B. Install a placard on the fuel distributor block in accordance with AMD-BA Service Bulletin No. AMD-BA F200-64, dated March 3, 1986. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. All persons affected by this directive, who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to Avions Marcel Dassault-Breguet Aviation, 40 JFC, Teherboro Airport, Teterboro, New Jersey 07608. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 25, 1987.
2018-25-18: We are adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by reports of cracking in main landing gear (MLG) universal joints (U-joints). This AD requires repetitive detailed inspections of the affected U-joints for cracks, and replacement if necessary. This AD also provides an optional terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
79-14-01: 79-14-01 De HAVILLAND: Amendment 39-3509. Applies to DeHavilland Aircraft of Canada, Limited, Model DHC-6 Series Twin Otter Aircraft, certificated in all categories, S/N 331 through 563 inclusive, 565 through 587 inclusive, 589 through 598 inclusive, 600, 601, 603 and 604. Compliance is required as indicated. To preclude loss of elevator control and ensure proper operation of the elevator control system: (a) Within the next 100 hours in service after the effective date of this airworthiness directive, unless previously accomplished, inspect the four bolts on the aft elevator cable control quadrant for correct torque and alter, as necessary, in accordance with the INSPECTION and RECTIFICATION paragraphs of ACCOMPLISHMENT INSTRUCTIONS in DeHavilland S/B No. 6/379 dated December 11, 1978, or an approved equivalent. (b) Within 600 hours in service after the effective date of this airworthiness directive, unless already accomplished, alter in accordance with Modification No. 6/1679, noted in S/B No. 6/379, or an approved equivalent. (c) Equivalent inspections, alterations and replacement parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) Upon submission of substantiating data by an owner, or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time specified in this AD. This amendment is effective July 6, 1979.
2018-25-01: We are superseding airworthiness directive (AD) 2018-13-07 for all Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H turbofan engine models. AD 2018-13-07 required initial inspections of the intermediate-pressure compressor (IPC) stage 1 rotor blades, IPC stage 2 rotor blades, and IPC shaft stage 2 dovetail posts, and removing any cracked parts from service. This AD requires initial inspections and adds repetitive inspections of the IPC stage 1 rotor blades, IPC stage 2 rotor blades, and IPC shaft stage 2 dovetail posts, and removing any cracked parts from service. This AD was prompted by the manufacturer determining the need for repetitive inspections of the IPC stage 1 rotor blades, IPC stage 2 rotor blades, and IPC shaft stage 2 dovetail posts. We are issuing this AD to address the unsafe condition on these products.