Results
2016-13-01: We are superseding Airworthiness Directive (AD) 2016-08-05 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. AD 2016-08-05 required replacement of affected angle of attack (AOA) transducers. This new AD requires the same actions as AD 2016-08-05. This new AD was prompted by a report of a typographical error in the regulatory text of AD 2016-08-05. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
47-49-09: 47-49-09 LOCKHEED: (Was Service Note 9 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088 and to Models 649 and 749 Serials 2501 Through 2513, Inclusive. At each engine change period, inspect the wing attaching pins at Station 80 to determine whether any of these pins are working upward through the fittings. If any pin has worked up until only the lower chamfered portion protrudes, replace the Station 80 cover strip with a new 0.064 24ST alclad strip. When this strip has been replaced the periodic inspection of that joint may be discontinued. (LAC Service Bulletin 49/SB-151 covers this same subject.)
2003-26-05: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8C1 series and CF34-8C5 series turbofan engines, with certain serial number (SN) master variable geometry (VG) actuators installed. This AD requires initial and repetitive reviews of the airplane Maintenance Data Computer (MDC) for master VG actuator fault messages, and if the MDC is inoperative, reviews of the Engine Indication and Crew Alerting System (EICAS) for fault messages. This AD also requires replacement of actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This AD results from nine reports of master VG actuator electrical signal faults, one report of which was a dual-channel fault, resulting in the FADEC commanding the engine power to idle. We are issuing this AD to prevent VG master actuator dual-channel electrical signal faults: Which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle; and Could result in a multi-engine loss of thrust if dual-channel faults occur on more than one engine simultaneously.
74-25-10: 74-25-10 BELL: Amendment 39-2039. Applies to Model 206A and 206B helicopters certificated in all categories and equipped with Rotor Brake Kit, P/N 206-706-032-1. Compliance required within the next ten hours' time in service after the effective date of this airworthiness directive unless already accomplished. To prevent failure of the rotor brake disc which could cause serious damage to critical components of the helicopter, accomplish the following: a. Remove the engine to transmission driveshaft and aft coupling. (Refer to Section VI of the Maintenance and Overhaul Manual.) b. Remove the Rotor Brake Disc Assembly P/N 4000071 or 4000071-1, attachment bolts and gasket from the coupling and discard. c. Reinstall the coupling and driveshaft as described in the Maintenance and Overhaul Manual. d. Disable the brake by removing the P/N 156F538-4S-0061 hose assembly between the rotor brake and firewall and capping the AN833-4C elbows with AN929-4J caps or equivalent. e. Bell Service Bulletin No. 206-50-74-1, Revision A, dated October 29, 1974 or later FAA/DER Approved Revision, includes equivalent instructions for these procedures and lists alternate FAA approved rotor brake configurations. f. Equivalent methods of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective December 16, 1974.
2016-12-07: We are superseding airworthiness directive (AD) 2010-11-10 for all Turbomeca S.A. Astazou XIV B and XIV H turboshaft engines. AD 2010- 11-10 requires inspection of certain third stage turbine wheels and removal of any damaged wheel. This AD requires expanding the population and frequency of repetitive inspections. This AD was prompted by a report of a third stage turbine wheel crack detected during engine overhaul. We are issuing this AD to prevent uncontained failure of the third stage turbine wheel, which could result in damage to the engine and damage to the helicopter.
2024-19-13: The FAA is superseding Airworthiness Directive (AD) 2023-04-06 and AD 2024-04-07, which applied to certain Airbus SAS Model A318, A319, A320 and A321 series airplanes. AD 2023-04-06 and AD 2024-04-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023-04-06 and AD 2024-04-07 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in the European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-03-16: 91-03-16 BOEING: Amendment 39-6875. Docket No. 90-NM-175-AD. \n\n\tApplicability: Model 747-400 series airplanes, as listed in Boeing Alert Service Bulletin 747-25A2862, Revision 1, dated December 13, 1990, certificated in any category. \n\n\tCompliance: Required within the next 9 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent smoking material from dropping behind the sidewall lining at the second observers station, accomplish the following: \n\n\tA.\tInstall a housing on the outboard side of the second observer's ashtray in accordance with Boeing Alert Service Bulletin 747-25A2862, Revision 1, dated December 13, 1990. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, SeattleACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6875, AD 91-03-16) becomes effective on March 4, 1991.
2016-11-19: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of chafing of the feeder cable at the pylon- wing junction due to vibration; one report revealed that the cable loom plastic support bracket of the G-route was broken due to vibration; and another report revealed wire chafing due to clamp damage. This AD requires modifying the cable loom support bracket of the G-route of the inboard pylons at the pylon-wing junction. We are issuing this AD to prevent chafing of the wiring in the pylon-wing area, which could result in an electrical short circuit near a flammable fluid vapor zone, and consequent fire or fuel tank explosion.
77-12-05: 77-12-05 CHAMPION SPARK PLUG COMPANY: Amendment 39-2923 as amended by Amendment 39-3208. Applies to Part Numbers CH48108 and CH48109 oil filters as installed in aircraft certified in all categories, identified by the following manufacturing date codes, 1A7E and 2A7C for the Part Number CH48108 filters, and 1A7G and 1A7I for the Part Number CH48109 oil filters, except for those affected filters which are identified with the symbol "Insp OK 5G7A" stamped adjacent to the manufacturing date code. The manufacturing date code is located on the outside of the filter housing adjacent to the filter installation instructions. Champion Spark Plug Company Aviation Sales Bulletin No. 77-13 also pertains to this subject. Compliance required before further flight, unless already accomplished, except that the airplane may be flown in accordance with FAR 21.197 to a base where the removal can be performed. To preclude possible oil filter malfunction resulting from internal bypass valve failure, remove all applicable filters from service. Amendment 39-2923 became effective June 24, 1977. This amendment 39-3208 becomes effective May 12, 1978.
2003-26-02: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; that requires either a review of airplane maintenance or delivery records, or one-time inspection of the hydraulic actuators located in the pivot doors of both thrust reversers to identify the part number, and eventual replacement of certain actuators with modified or new actuators. This action is necessary to prevent jamming of a thrust reverser door during operation, or inadvertent deployment of a thrust reverser door in-flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.