Results
2006-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD requires repetitive inspections for discrepancies of the grease and gear teeth of the radial variable differential transducer of the nose wheel steering gearbox; or repetitive inspections for damage of the chrome on the bearing surface of the nose landing gear (NLG) main fitting barrel; as applicable. And, for airplanes with any discrepancy or damage, this AD requires an additional inspection or corrective actions. This AD also adds a terminating action. The actions specified by this AD are intended to prevent incorrect operation or jamming of the nose wheel steering, which could cause reduced controllability of the airplane on the ground. This action is intended to address the identified unsafe condition.
2019-11-03: The FAA is adopting an airworthiness directive (AD) for certain The Boeing Company Model 737-700C, -800, and -900ER series airplanes. This AD requires a maintenance records check to determine if any main slat track assembly has been removed, an inspection of the main slat track assemblies for a suspect lot number or a lot number that cannot be determined, and applicable on-condition actions. This AD was prompted by a report that certain main slat track assemblies were manufactured incorrectly and are affected by hydrogen embrittlement. The FAA is issuing this AD to address the unsafe condition on these products.
2019-11-05: We are superseding Airworthiness Directive (AD) 2015-22-02 for certain Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. AD 2015-22-02 required inspecting the tail rotor (TR) pitch link assemblies. This AD retains the inspections of AD 2015-22-02 and requires replacing certain pitch link bearings. This AD was prompted by a new design bearing introduced by Bell. We are issuing this AD to address the unsafe condition on these products.
98-18-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect cracking in the inner flange of door frame 66, and corrective actions, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to correct fatigue cracking in the inner flange of door frame 66, which could result in reduced structural integrity of the airplane.
98-19-14: This amendment adopts a new airworthiness directive (AD) that applies to all S.N. Centrair (Centrair) 101 series sailplanes. This AD requires replacing the airbrake control system with one of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent loss of the airbrake control system caused by cracks in the original design airbrake control system, which could result in an inadvertent forced landing with consequent sailplane damage and/or passenger injury.
87-10-02: 87-10-02 BOEING: Amendment 39-5620. Applies to Model 767 series airplanes, as listed in Boeing Alert Service Bulletin 767-27A0074, dated March 20, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent lateral control system restriction or jamming resulting from improper installation of a trailing edge flap drive vapor seal, accomplish the following: \n\n\tA.\tWithin the next 100 landings or 30 days after the effective date of this AD, whichever occurs first, inspect the trailing edge flap drive vapor seals for correct installation in accordance with Boeing Alert Service Bulletin 767-27A0074, dated March 20, 1987, or later FAA-approved revision. Vapor seals found to be installed incorrectly must be reworked to correct the installation before further flight in accordance with the instructions contained in the aforementioned alert service bulletin. \n\n\tNOTE: At the time of issuance of this AD, the Boeing 767 IllustratedParts Catalog, the Boeing 767 Maintenance Manual, and the Boeing 767 Maintenance Planning Data document all contained illustrations depicting a trailing edge flap drive vapor seal installed incorrectly, with the vapor seal flanges aligned vertically. The FAA-approved airplane maintenance program should be revised to take account of these errors. \n\n\tB.\tAn alternate means of compliance 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 21.197 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 information from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This information may be examinedat FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment 39-5620 becomes effective May 22, 1987.
2019-11-04: We are adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 D-2 helicopters. This AD requires replacing the rescue hoist cable cut pushbutton flip guard (flip guard). This AD was prompted by reports of unintended lifting of several flip guards. [[Page 26557]] We are issuing this AD to address the unsafe condition on these products.
98-16-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Cessna Model 750 Citation X series airplanes. This action requires repetitive in-flight functional tests to verify proper operation of the secondary horizontal stabilizer pitch trim system, and repair, if necessary. This amendment is prompted by reports of simultaneous failures of the primary and secondary horizontal stabilizer pitch trim system during flight, due to internal water contamination and corrosion damage in the system actuator. The actions specified in this AD are intended to detect and correct such contamination and damage, which could result in simultaneous failure of both primary and secondary pitch trim systems, and consequent reduced controllability of the airplane.
2006-23-12: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes equipped with certain hydraulic accumulators. This AD requires inspecting the hydraulic accumulators to identify certain serial numbers, and replacing any affected accumulator with a new or serviceable accumulator. Operators may delay doing the replacement by doing repetitive inspections of the affected hydraulic accumulators for signs of failure (leaking or cracking), and replacing any failed accumulator with a new or serviceable unit. This AD results from a report that one hydraulic accumulator failed in service, which caused the loss of the yellow hydraulic system when the airplane was configured for landing. We are issuing this AD to prevent damage to the pressure skin, failure of certain hydraulic systems, contamination of the cabin with hydraulic mist, increased workload for the flightcrew associated with the loss of one or more hydraulic circuits, and consequent reduced controllability of the airplane.
2006-22-13: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, PW4090-3, and PW4098 turbofan engines, with certain front turbine hub part numbers installed. This AD requires a onetime visual inspection of the anti-rotation slots in the front turbine hub, for a machining nonconformance, and its replacement if the inspection failed. This AD results from a report of a crack found in an anti-rotation slot of a front turbine hub, during overhaul shop inspection. The anti-rotation slot geometry was not machined in conformance with the design drawing during manufacture. We are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.