Results
2000-23-31: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-82 (MD-82) and DC-9-83 (MD-83) series airplanes, and Model MD-88 airplanes. This action requires deactivating the left and right lower sidewall lights located in the passenger compartment. This action is necessary to prevent arcing and heat damage of the Luminator fluorescent lamp holders located outboard of the Passenger Service Unit panel, which could result in smoke and fire in the passenger compartment. This action is intended to address the identified unsafe condition.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 13, 2000.\n\n\tComments for inclusion in the Rules Docket must be received on or before January 29, 2001.
2008-12-01: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 525 airplanes. This AD requires you to inspect for missing firewall sealant between the aft firewall assembly and seal assembly; and, if you find that firewall sealant is missing, seal with firewall sealant between the aft firewall assembly and seal assembly. This AD results from a report that firewall sealant may not have been applied between the aft firewall assembly and seal assembly during manufacture of certain Model 525 airplanes. We are issuing this AD to detect and correct missing firewall sealant between the aft firewall assembly and seal assembly, which could result in failure of the fire extinguishing system to prevent the spread of fire through the firewall gap. This failure could lead to an uncontrolled fire.
82-01-01: 82-01-01 CANADAIR: Amendment 39-4288. Applies to Model CL-600 airplanes with serial number 1002 to 1050 inclusive. To prevent asymmetric spoiler deployment, accomplish the following within ten days after the effective date of this AD, unless already accomplished: 1. Visually inspect and adjust, if necessary, the left and right controlex cables (parts numbers 600-91305-5 and 600-91305-7) for compliance with the revised rigging procedure specified in Canadair Alert Service Bulletin A600-0024, Revision 1, dated November 6, 1981, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 2. Airplanes may be flown in accordance with FAR 21.197 to a maintenance base for accomplishment of the inspection required by this AD. 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 the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective January 4, 1982.
2008-11-20: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: AD 2007-0315-E was issued to address a possible fuel leakage in the gear compartment in front of the engine and mandated inspections and replacement of fuel plastic-made connectors by connectors made of metal. Since its publication, another fuel leakage has been reported on a S10-VT which had implemented the STEMME Service Bulletin (SB) A31-10-082 as required by AD 2007-0315-E. It has been determined that the fuel leak may have been caused by the deformation that the originally installed clamps created on the fuel hoses and thus preventing the new clamps from being sufficiently pinched to perform a correct tightening.This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective June 23, 2008. On June 23, 2008, the Director of the Federal Register approved the incorporation by reference of STEMME F & D Service Bulletin A31-10-083, Am-Index: 01.a, dated February 26, 2008, listed in this AD. As of February 20, 2008 (73 FR 5733, January 31, 2008), the Director of the Federal Register approved the incorporation by reference of STEMME F & D Service Bulletin A31-10-082, AM.-Index: 01.a, dated November 30, 2007, listed in this AD. We must receive comments on this AD by July 2, 2008.
2008-11-18: We are adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Model SR20 airplanes. This AD requires you to perform an inspection and replacement as necessary of the heat exchanger. This AD results from the discovery of engine exhaust fumes in the cabin of CDC Model SR20 airplanes. We are issuing this AD to detect and correct leaks in the exhaust system, which could result in exhaust gases leaking into the cabin heating system. This condition could lead to carbon monoxide in the cabin and incapacitation of the pilot.
86-12-01 L: 86-12-01 BELL HELICOPTER TEXTRON, INC.: Letter issued June 6, 1986. Applies to all Bell Model 214ST helicopters, certificated in all categories. Compliance is required prior to further flight after receipt of this AD, unless previously accomplished. To prevent loss of main rotor collective control, visually inspect locking plate, Part Number (P/N) 214-010-232-101, in accordance with Part I of Bell Helicopter, Textron, Inc., Alert Service Bulletin (ASB) 214ST-86-36, dated May 23, 1986. If the locking plate is defective, check the torque of the lower collective hub nut, Part Number 214-010-407-001, in accordance with Part IV of ASB 214ST-86-36. At the next "A" check, inspect the locking plate in accordance with Part II of ASB 214ST-86-36. At each subsequent "A" check, inspect the locking plate in accordance with Part III of ASB 214ST-86-36. At the next "B" check and each subsequent "B" check, check the torque of the lower collective hub nut, P/N 214-010-407-1, in accordance with Part IV of ASB 214ST-86-36. An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive becomes effective upon receipt.
2008-11-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires repetitive inspections for any cracking of or damage to the left side and right side flight deck No. 2, No. 4, and No. 5 windows, as necessary, and corrective actions if necessary. This AD results from reports of in-flight departure and separation of the flight deck windows. We are issuing this AD to detect and correct cracking in the vinyl interlayer or damage to the structural inner glass panes of the flight deck No. 2, No. 4, and No. 5 windows, which could result in loss of a window and rapid loss of cabin pressure. Loss of cabin pressure could cause crew communication difficulties or crew incapacitation.
2007-14-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 and A300-600 series airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness by incorporating new and revised certification maintenance requirements. This AD results from the manufacturer determining that additional and revised certification maintenance requirements are necessary in order to ensure continued operational safety of the affected airplanes. We are issuing this AD to prevent safety-significant latent failures that would, in combination with one or more other specific failures or events, result in a hazardous or catastrophic failure condition of avionics, hydraulic systems, fire detection systems, fuel systems, or other critical systems.
73-12-08: 73-12-08 GENERAL DYNAMICS: Amdt. 39-1659. Applies to Models 22 and 22M airplanes. Compliance, as indicated, required on all airplanes with 28,000 hours or more of total time in service, unless already accomplished. To prevent failures of the flap track support structure accomplish the following: a. Within the next 50 landings after the effective date of this A.D., unless already accomplished within the last 275 landings, and thereafter at intervals not to exceed 325 landings from the last inspection, (1) Visually inspect the right and left inboard flap at wing station 180.504 for cracks in the flap track support rails 22-17463-57, -58, -59, -60, in the fitting 22-18994-1, -3 or -5 and in the track supporting structure general vicinity. (2) If cracks are found in any fitting, it must be replaced before further flight. If cracks are found in the rails or supporting structure other than fittings, parts must be replaced or repaired, before further flight, in amanner approved by the Chief, Aircraft Engineering Division, FAA Western Region. Airplanes with minor cracks in fittings, rails or support structure may be flown per FAR 21.197 to a base where replacement or repair of parts can be accomplished. b. When parts are replaced or repaired per (a)(2) above, the repetitive inspections of (a) above, are no longer required for that part until it accumulates another 28000 hours' time in service from the last inspection. For the purpose of complying with this A.D., subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplanes hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This amendment becomes effective June 12, 1973.
2008-10-12: We are adopting a new airworthiness directive (AD) to supersede AD 2007-13-17, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-602, AT-802, and AT-802A airplanes. AD 2007-13- 17 currently requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. Since we issued AD 2007-13-17, Air Tractor has learned of a Model AT-502B with a crack located where the lower engine mount tube is welded to the engine mount ring. In addition, Air Tractor has developed gussets that, when installed according to their service letter, terminate the repetitive inspection requirement. Consequently, this AD would retain the inspection actions of AD 2007-13-17 for Model AT-602, AT-802, and AT-802A airplanes, including the compliance times and effective dates; establish new inspection actions for the AT-400 and AT-500 series airplanes; incorporate a mandatory terminating action for all airplanes; and terminate the reporting requirement of AD 2007- 13-17. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane. DATES: This AD becomes effective on June 12, 2008. On June 12, 2008, the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 253, Rev. C, dated April 17, 2008; Snow Engineering Co. Service Letter 253, Rev. B, dated November 30, 2007; and Snow Engineering Co. Service Letter 253 Rev. A, dated October 16, 2007, as listed in this AD. As of August 10, 2007 (72 FR 36863, July 6, 2007), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 253, revised January 22, 2007, as listed in this AD.