Results
2006-18-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-400, 747-400D, and 747- 400F series airplanes. The existing AD currently requires reviewing airplane maintenance records; inspecting the yaw damper actuator portion of the upper and lower rudder power control modules (PCMs) for cracking, and replacing the PCMs if necessary; and reporting all airplane maintenance records review and inspection results to the manufacturer. This new AD expands the applicability and discontinues certain requirements of the existing AD. This AD adds repetitive inspections of the PCMs, and replacement of the PCMs if necessary. This AD results from manufacturer findings that the inspections required by the existing AD must be performed at regular intervals. We are issuing this AD to detect and correct cracking in the yaw damper actuator portion of the upper and lower rudder PCMs, which could result in an uncommanded left rudder hardover, consequent increased pilot workload, and possible runway departure upon landing.
2018-18-16: We are superseding Airworthiness Directive (AD) 2018-12-08, which applied to certain Airbus SAS Model A330-200 and -300 series airplanes, and Model A340-212, -213, -312, and -313 airplanes. AD 2018- 12-08 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This new AD corrects certain compliance time references. This AD was prompted by a report of cracking at fastener holes located at a certain frame (FR) on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products.
87-13-11: 87-13-11 FAIRCHILD AIRCRAFT CORPORATION: Amendment 39-5668. Applies to Model SA26-T, SA26-AT, SA226-T, SA226-T(B), SA226-AT, SA226-TC (All serial numbers) except SA226-T(B), S/N T-276, T-283 through T-297, SA226-AT, S/N AT-062E through AT-069 and SA226-TC, S/N TC-247 through TC-279; airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent inadvertent landing gear selector movement, accomplish the following: (a) On or before December 1, 1987, accomplish the following: (1) Visually inspect the sides and end of the center pedestal for installation of brackets, holders, or any sort of provision for the storage of maps, charts, and approach charts and, prior to further flight, remove any such devices. (2) Modify the landing gear selector lever in accordance with Fairchild Aircraft Corporation S/B 26-32-30-39, dated February 13, 1987 (for the Model SA26 airplanes), or S/B 226-32-048, revision dated February 13, 1987 (for the Model SA226 airplanes), as applicable. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Regional Office, Fort Worth, Texas 76193-0150, Telephone (817) 624-5150. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Fairchild Aircraft Corporation, P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Effective on August 10, 1987.
2006-18-16: We are adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Model 390 airplanes. This AD requires you to inspect the spigot bearing, part number (P/N) MS14104-16, for the proper position in the spigot fitting assembly and to install the wing spigot bearing retainer kit, P/N 390-4304-0001. We are issuing this AD to detect spigot bearings that are not positioned flush with the fitting assembly. This condition could result in the spigot bearing becoming disengaged from the fitting assembly, which could cause motion between the wing and the fuselage and degrade the structural integrity of the wing attachment to the fuselage. This could lead to wing separation and loss of control of the airplane.
2000-09-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211-535 series turbofan engines. This AD will require removal from service of suspect radial drive steady bearings with certain serial number prefixes and replacement with serviceable parts. This amendment was prompted by reports of a number of radial drive steady bearing failures from distinct batches of parts. The actions specified by this AD are intended to prevent radial drive steady bearing failure, which could result in an in-flight engine shutdown and smoke and fumes in the cabin.
2018-17-12: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with full authority digital engine control (FADEC) software, version 9.3.2.4 or earlier, installed. This AD requires upgrading the FADEC software to a software version eligible for installation. This AD was prompted by an ice-crystal icing (ICI) event that caused damage to both engines, a single engine stall, and subsequent engine shutdown. We are issuing this AD to address the unsafe condition on these products.
2005-24-11: The FAA is superseding an existing airworthiness directive (AD) that applies to certain EMBRAER Model EMB-135 and Model EMB-145 series airplanes. The existing AD currently requires repetitive inspections of the spring cartridges of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, and corrective action if necessary. The existing AD also provides for optional terminating action for the repetitive inspections for certain airplanes. This AD retains the requirements of the existing AD and adds a requirement for final terminating action for all affected airplanes. This AD results from reports of an improperly fitting lock washer causing the clevis of the spring cartridge in the electromechanical elevator gust lock system to become unscrewed. We are issuing this AD to prevent the unscrewing of the spring cartridge clevis from jamming the elevator, which could lead to reduced controllability of the airplane.
88-01-03: 88-01-03 BOEING: Amendment 39-5810. Applies to Model 757 series airplanes equipped with Rolls Royce RB 211-535C or -535E4 engines, specified in Boeing Alert Service Bulletin 757-71A0026, Revision 1, dated September 24, 1987, certificated in any category. Compliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the potential for total thrust loss in both engines due to a lightning strike, accomplish the following: \n\n\tA.\tModify engine electrical and electronic control unit wiring in accordance with Boeing Alert Service Bulletin 757-71A0026, Revision 1, dated September 24, 1987, or later FAA-approved revision. \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, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197and 21.199 to operate airplanes to a base for the accomplishment of the modification required by 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 the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington, 98124. These documents 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. \n\n\tThis amendment becomes effective February 16, 1988.
2006-18-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-541 and -642 airplanes. This AD requires a one-time inspection of the anti-stall valve sleeve of the ram air turbine (RAT) for proper installation, determining the part number of the modification plate on the hydraulic pump of the RAT, and follow-on corrective actions if necessary. This AD results from reports of failure of the anti-stall valve on the hydraulic pump of the RAT during scheduled ground tests. We are issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation.
2021-06-09: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a report indicating that a passenger door opened under residual cabin pressure during taxiing after landing, and following the display of the CAB PRESS CTL alert. This AD requires revising the existing airplane flight manual (AFM) to update the Cabin Pressurization Control Fault procedure, as specified in a 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.