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2006-10-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-223, -321, -322, and -323 airplanes. This AD requires repetitive inspections of the firewall of the lower aft pylon fairing (LAPF), and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the LAPF firewall. We are issuing this AD to detect and correct this cracking, which could reduce the effectiveness of the firewall and result in an uncontrolled engine fire.
87-25-02: 87-25-02 SIKORSKY AIRCRAFT: Amendment 39-5778. Applies to all Model S-76A and S-76B series helicopters through and including serial number 760350, certified in any category. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of AC electrical power due to 26 VAC transformer single ground connection failure, provide separate ground connections for 26 VAC transformers 1 and 2. NOTE: Sikorsky Service Bulletin No. 76-24-5, AC Electrical Power System - AC Power Transformer Ground Wires Termination-Separation of, dated October 19, 1987, constitutes an acceptable means of compliance with this requirement. This amendment becomes effective December 31, 1987.
89-02-03: 89-02-03 BEECH: Amendment 39-6104. Applicability: Model 200 (Serial Numbers BB-2 through BB-161) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished per Beech Service Bulletin No. 2240, dated February 1988, or Beech Letter No. 52-83-0030, dated January 20, 1983, or Beech Letter No. 52-85-0049, dated April 17, 1985. To prevent possible failure of the wing main outboard spar, accomplish the following: (a) Within the next 200 hours time-in-service (TIS) after the effective date of this AD, or upon accumulating 10,000 hours TIS, whichever occurs later, replace both wing main outboard spars in accordance with Beech Service Bulletin No. 2240, dated February 1988. Only the left wing main spar need be replaced for Serial Nos. BB-149 through BB-161. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalentmeans of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6104, AD 89-02-03) becomes effective on February 8, 1989.
2019-05-13: We are removing AD 2007-22-05 and AD 2013-13-13 (referred to after this as ``the affected ADs''), which applied to Airbus SAS Model A300-600 and A310 series airplanes. The affected [[Page 10406]] ADs required certain actions to address various unsafe conditions. The affected ADs are no longer necessary because we have since issued other ADs to address these unsafe conditions. Accordingly, we are removing the affected ADs.
85-01-04: 85-01-04 PITTS: Amendment 39-4980. Applies to Model S-2A (S/N's 2001 through 2105) airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of normal aileron and elevator control: (a) Visually inspect the cockpit control tube assembly using a 10 power glass for cracks in the area of the welds attaching the P/N 2-5100-12 stick housings to the P/N 2-5100-11 tube. (1) If cracks are detected weld shut the cracks and install a P/N 2-5100-20 gusset at both the fore and aft stick housing locations in accordance with Pitts Service Letter No. 5, Revision B. (2) If cracks are not present, install P/N 2-5100-20 gussets in accordance with Pitts Service Letter No. 5, Revision B. (b) The aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) Installation of P/N 2-5100-19 gussets in accordance with Pitts Service Letter No. 5, Revision A, satisfies the requirements of this AD. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Denver Aircraft Certification Office, Federal Aviation Administration, Northwest Mountain Region, 10455 East 25th Avenue, Suite 307, Aurora, Colorado 80010; Telephone (303) 340-5594. This amendment becomes effective on January 21, 1985.
99-03-10: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-03-10 which was sent previously to all known U.S. owners and operators of Agusta Model A109E helicopters by individual letters. This AD requires, before further flight, inspections of the exhaust ejector locking system, clamp, and dampers for each engine. This AD also requires, at specified time intervals, verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment is prompted by an inflight incident in which a metallic clamp which secured the left-hand engine exhaust ejector to the ejector saddle became detached and subsequently separated from the helicopter. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, which could result in damage to the main or tail rotor system and subsequent loss of control of the helicopter.
2006-10-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action if necessary. This new AD requires new inspections for cracking or severe wear of the bearings of the link assembly, inspections of any link assembly not previously inspected for damage, and corrective actions if necessary. This AD also ends the existing repetitive inspections for certain airplanes, and extends the repetitive interval for the existing repetitive inspections and the compliance time for the corrective action on certain other airplanes. This AD also provides an optional terminating action. This AD results from additional reports indicating fractured bearings of the link assembly joint in the inboard and outboard flaps of the trailing edge. We are issuing this AD to prevent failure of the bearings in the link assembly joint, which could result in separation of the inboard or outboard flap and consequent loss of control of the airplane. \n\nDATES: This AD becomes effective June 19, 2006. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 19, 2006. \n\n\tOn February 14, 2002 (67 FR 4328, January 30, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000.