Results
2000-16-02: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney PW4164, PW4168, and PW4168A series turbofan engines. The current AD requires initial and repetitive torque checks for loose or broken bolts used to secure the engine to the airplane made from INCO 718 material (front pylon mount bolts). The current AD also requires the replacement of the bolts, if necessary, with new bolts, and establishes a new cyclic life limit for the front pylon mount bolt. This amendment adds requirements for initial and repetitive torque checks of front pylon mount bolts made from a new material, MP159, and initial and repetitive visual inspections of the primary mount thrust load path. This amendment is prompted by the use of front pylon mount bolts made from MP159 material and fatigue testing that shows that the forward engine mount bearing housings have insufficient fatigue life expectancy. The actions specified by this AD are intended to prevent frontpylon mount bolt and primary mount thrust load path failure, which could result in an engine separating from the airplane.
2005-03-03: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires examination of maintenance records to determine if Titanine JC5A (also known as Desoto 823E508) corrosion inhibiting compound ("C.I.C.") was ever used; inspection for cracks or corrosion and corrective action, if applicable; repetitive inspections and C.I.C. applications; and modification of the aft trunnion area of the outer cylinder, which terminates the need for the repetitive inspections and C.I.C. applications. This new AD also requires, for certain other airplanes, repetitive inspections for cracks or corrosion, corrective action if necessary, and repetitive C.I.C. applications. This AD is prompted by a report that JC5A was used on more airplanes during production than previously identified. We are issuing this AD to prevent severe corrosion in the main landing gear (MLG) outer cylinder at the aft trunnion, which could develop into stress corrosion cracking and consequent collapse of the MLG.
96-16-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, and Model F28 Mark 0100 series airplanes, that requires repetitive pre-load adjustments of the main landing gear (MLG) downlock-actuator. This AD also provides optional terminating action for the repetitive adjustments. This amendment is prompted by a report that, upon landing, the MLG of an airplane collapsed as a result of the lock toggle-links being pulled out of the over-center position by the downlock-actuator, which was due to the relative movement of the upper and lower side-stay members. The actions specified by this AD are intended to prevent collapse of the MLG, which could adversely affect the controllability of the airplane during landing.
2000-15-20: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A and A109A II helicopters. This AD requires radiographic inspections of the internal surface of each main rotor blade spar (spar) for corrosion. This AD is prompted by the discovery of corrosion on the internal surfaces of the spar in the area adjacent to the main rotor blade inertia balance weights. The actions specified by this AD are intended to prevent failure of a main rotor blade due to corrosion on the internal surface of the spar and subsequent loss of control of the helicopter.
2005-03-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes; and Model 757-200 and -200CB series airplanes, that requires inspection of the applicable body station frames for open body station frames and related investigative/corrective actions; and installation of lanyard hook brackets and lanyard assemblies under the air conditioning overhead ducts, as applicable. This action is necessary to prevent loosened or disconnected overhead ducts from causing ceiling panels to drop below the minimum height of the evacuation zone for the passenger cabin, which could result in inadequate height for safe exit in the event of an emergency evacuation. This action is intended to address the identified unsafe condition.
2014-23-08: We are superseding Airworthiness Directive (AD) 2012-06-19 for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340- 200 and -300 series airplanes. AD 2012-06-19 required repetitive inspections of the main fitting and sliding tube of the nose landing gear (NLG) for defects, damage, and cracks; and corrective actions if necessary. This new AD requires an inspection of the part number and serial number of the NLG main fitting and NLG sliding tube; for affected parts, this new AD requires a magnetic particle inspection (MPI) for cracks, and flap peening and replacement if necessary. This new AD also requires, for certain parts, additional inspections for damage and cracking. This new AD also adds airplanes to the applicability. This AD was prompted by reports of a cracked main fitting and sliding tube during NLG overhaul. We are issuing this AD to detect and correct cracks, defects, or damage ofthe main fitting or sliding tube, which could result in consequent NLG collapse.
97-06-06: This amendment supersedes AD 92-27-10, which currently requires inspecting the pilot and copilot chairs to ensure that the locking pins will fully engage in the seat tracks on certain Raytheon Aircraft Company (Raytheon) 90, 99, 100, 200, and 1900 series airplanes (formerly referred to as Beech 90, 99, 100, 200, and 1900 series airplanes), and modifying any chair where the locking pin fails to fully engage or is misaligned. AD 92-27-10 resulted from reports of pilot and copilot chair locking pin malfunctions. Since issuance of that AD, the Federal Aviation Administration (FAA) has determined that additional airplanes should be subject to the pilot and copilot chair locking pin inspection and possible modification, and that the inspection should be accomplished in accordance with revised procedures. This AD retains the inspection and possible modification requirements of AD 92-27-10; incorporates additional airplanes into the applicability over that included in AD 92-27-10;and requires the inspection in accordance with revised service information. The actions specified by this AD are intended to prevent inadvertent movement of the pilot or copilot chair, which could result in loss of control of the airplane if it occurs during a critical flight maneuver.
2005-03-04: The FAA adopts a new airworthiness directive (AD) for all Pacific Aerospace Corporation, Ltd. (Pacific Aerospace) Model 750XL airplanes. This AD requires you to replace any type TLP-D or TLED rivets on the aileron pushrod ends and elevator control pushrod ends. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to replace the above identified rivets on the aileron pushrod ends and elevator control pushrod ends, which, if not replaced, could result in loose mechanical elements in the control systems. This could lead to control anomalies and loss of airplane control.
76-10-09: 76-10-09 BEECH: Amendment 39-2616. Applies to Models B19 (Serial Numbers MB-732 through MB-788), C23 (Serial Numbers M-1600 thru M-1769) and B24R (Serial Numbers MC-305 thru MC-398) airplanes equipped with mechanical flaps. Compliance: Required as indicated, unless already accomplished. To prevent unscheduled retraction of wing flaps, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: A. Pursuant to the procedures and instructions outlined in Beechcraft Service Instructions No. 0831-161 or later approved revisions: (1) Using a flashlight and mirror, visually inspect the inside of the flap torque tube to determine if Beech P/N 169-524024-9 flap cable block is attached to the torque tube with rivets or with screws and nuts. (2) If the flap cable block is attached to the torque tube with the screws and nuts identified in Paragraph (3) below, no further action is required. (3) If a flap cable blockis attached to the torque tube with rivets, drill out the three rivets (one at a time in accordance with the aforementioned service instructions) and replace with three each MS24694S58 screws, AN960-10 washers and MS21042L3 locknuts or Beech P/N 130909N29 locknuts. B. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective May 28, 1976.
96-13-12: 96-13-12 DORNIER: Amendment 39-9681. Docket 95-NM-231-AD. Applicability: Model 328-100 series airplanes having serial numbers 3005 through 3024 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent abnormal functions of the bus power control units and the generator control units, which could result in electrical short circuits in the electrical power distribution systems and a subsequent fire, accomplish the following: (a) Within 3 months after the effective date of this AD, perform the requirements of paragraph (a)(l) and (a)(2) of this AD, in accordance with Dornier Service Bulletin SB-328-24-061, Revision 1, dated November 3, 1994. (1) Remove the generator control units 2PC and 12PC and replace them with new improved units having part number 118-000-1. And, (2) Remove bus power control unit 20PC and replace it with a new improved unit having part number 106-000-3. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The removals and replacements shall be done in accordance with Dornier Service Bulletin SB-328-24-061, Revision 1, dated November 3, 1994, which contains the following effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1,3 1 November 3, 1994 2 Original October 14, 1994 This incorporation by reference is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on August 2, 1996.