Results
2018-18-12: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, and AS350BA helicopters with a Pall Aerospace Corporation inlet barrier filter (IBF) element. This AD requires revising the Rotorcraft Flight Manual Supplement to [[Page 45546]] prohibit operating a helicopter with an IBF element in wet weather and replacing the IBF element if wet. This AD is prompted by a forced landing after an engine flameout. The actions of this AD are intended to address an unsafe condition on these products.
89-02-06: 89-02-06 AEROSPATIALE: Amendment 39-6114. Applicability: Model ATR42 series airplanes, as listed in Aerospatiale Service Bulletin ATR42-27-0027, Revision 2, dated June 27, 1988, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of rudder control, accomplish the following: A. Within 60 days after the effective date of this AD, install screws and nuts having two separate locking devices in the forward and aft quadrant cable stops in the rudder control system, in accordance with Aerospatiale Service Bulletin ATR42-27-0027, Revision 2, dated June 27, 1988. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. 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 documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6114, AD 89-02-06) becomes effective February 22, 1989.
2006-19-05: This amendment adopts a new airworthiness directive (AD) for the specified restricted category type-certificated helicopters. The AD requires a review of the helicopter records to determine the Commercial and Government Entity (CAGE) code of the tail rotor (T/R) slider. If the T/R slider is FAA approved or has a certain legible CAGE code, this AD requires no further action. If you cannot determine whether the T/R slider is FAA approved and it has no stamped CAGE code, an illegible stamped CAGE code, or an affected CAGE code, the AD also requires, before further flight and at specified intervals, magnaflux inspecting the T/R slider for a crack. If a crack is found, the AD requires, before further flight, replacing the T/R slider with an airworthy T/R slider. The AD also requires replacing the T/R slider with an airworthy T/R slider on or before accumulating 1,000 hours time-in-service (TIS) or on or before 12 months, whichever occurs first. This amendment is prompted by two accidents attributed to sub-standard T/R sliders that failed during flight. The actions specified by this AD are intended to prevent failure of a T/R slider, loss of T/R control, and subsequent loss of control of the helicopter.
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.