Results
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.
2007-14-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It was detected by the STC holder that in earlier installations of the ACASII system there were no isolation diodes installed in the Heading and Attitude Valid lines. The absence of an isolation diode in the valid lines can prevent the valid flag to come up even if a gyro fault exists. The problem has only been detected for Heading Valid lines but could equally affect the Attitude Valid lines. With installation of the ACASII, the heading and attitude valid lines have to be connected to the TPU67A. On valid state, the signals are +28VDC. On invalid, the signals are open. This condition of direct connection (without an isolation diode installed) of the valid lines to the TPU67A, if not corrected, could cause the TPU67A to feed current into the open stated valid lines. This prevents the flag to appear even if the gyro is invalid, providing the flight crew with erroneous navigation information. We are issuing this AD to require actions to correct the unsafe condition on these products.
87-10-08: 87-10-08 CASA: Amendment 39-5622. Applies to CASA Model C-212 series airplanes, serial numbers as listed in CASA Service Bulletin 212-52-16, dated October 23, 1985, certificated in any category. Compliance is required within 9 months after the effective date of this AD. To prevent inadvertent opening of the crew door, accomplish the following, unless previously accomplished: A. Install a protective cover over the crew door internal handle in accordance with CASA Service Bulletin 212-52-16, dated October 23, 1985. B. 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. C. Special flight permits may be issued in accordance with FAR 21.197 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 Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. 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 39-5622 becomes effective June 19, 1987.
2008-10-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD also requires the initial inspection of a certain repetitive AWL inspection to phase in that inspection, and repair if necessary. This AD results from a design review of the fuel tank system. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2008-10-03: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron (Bell) model helicopters. This action requires certain checks and inspections of each tail rotor blade assembly (T/R blade) at specified intervals and repairing or replacing, as applicable, any unairworthy T/R blade. This amendment is prompted by three failures of a T/R blade occurring during flight and a recent incident of a cracked T/R blade discovered during a scheduled visual inspection. The actions specified in this AD are intended to detect damage to a T/R blade that could lead to cracking of a T/R blade and subsequent loss of control of the helicopter.