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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.
2019-05-07: We are superseding Airworthiness Directive (AD) 2017-20-01 for certain Honeywell International Inc. (Honeywell) TFE731-20 and TFE731- 40 turbofan engines. AD 2017-20-01 required removing the affected fan disk and replacing it with a fan disk eligible for installation. Since we issued AD 2017-20-01, we determined that some turbofan engine models were omitted from the applicability of AD 2017-20-01. This AD adds turbofan engine models to the applicability and removes the Honeywell TFE731-20 turbofan engine model from the applicability. This AD requires removal of affected fan disks and replacement with parts eligible for installation. This AD was prompted by two fan disks found with surface rollovers in the dovetail slot area. We are issuing this AD to address the unsafe condition on these products.
87-05-08: 87-05-08 MCDONNELL DOUGLAS: Amendment 39-5559. Applies to McDonnell Douglas Model DC-9-81, -82, and -83 series airplanes, certificated in any category, equipped with Air Cruiser Company emergency exit evacuation slide part numbers D29984-103 and -109 having serial numbers prior to 0093. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent jamming during deployment of the emergency evacuation slide, accomplish the following: \n\n\tA.\tWithin 6 months after the effective date of this AD, modify the emergency evacuation slide deployment strap clip in accordance with Air Cruiser Service Bulletin 304-25-3, dated January 21, 1986, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719-0180. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective March 25, 1987.
2006-14-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200 and A330-300 series airplanes; and Airbus Model A340-200 and A340-300 series airplanes. This AD requires lubrication of the upper and lower shortening mechanism (SM) link of the main landing gear, and consequent detection of resistance or blockage of the greaseway. Depending upon the resistance finding and upon whether or not the airplane has a certain modification, this AD also requires various other actions including unblocking the greaseway; accomplishing all necessary repairs; performing various inspections; and accomplishing the eventual replacement of the SM8 pin, if necessary. This action is necessary to prevent failure of the landing gear lengthening system, which could result in reduced controllability of the airplane on the ground during landing. This action is intended to address the identified unsafe condition.
2006-05-01: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 500, 700, and 800 series turbofan engines. This AD requires inspecting all engines to determine those that are equipped with a suspect oil filler cap assembly. This AD also requires, within seven days of the effective date of this AD, an initial and repetitive check of oil cap security following oil servicing of multiple-engine airplanes having more than one suspect oil filler cap assembly installed. Finally, this AD requires replacing affected oil filler cap assemblies. This AD results from four in- service oil loss events since March 2005, following failures to properly install the oil tank filler cap after oil servicing. We are issuing this AD to prevent oil loss that could result in multiple engine in-flight shutdowns during a flight.
2019-05-09: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-251N and -271N airplanes, and Model A321-253N airplanes. This AD was prompted by reports of low clearance between the electrical harness and nearby hydraulic pipes in the inboard trailing edge of the wing. This AD requires repetitive detailed inspections of certain electrical harnesses for discrepancies and corrective actions, if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. We are issuing this AD to address the unsafe condition on these products.