Results
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.
2000-24-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Beech Models A36, B36TC, and 58 airplanes. This AD requires you to inspect for misrouted rudder control cables; replace any worn or damaged guard pins; replace any pulley brackets that are damaged or worn; and replace any misrouted rudder control cables. Three reports of misrouted cables prompted this action. The actions specified by this AD are intended to correct the misrouted rudder control cable and consequent guard pin wear or fraying of the cables with loss of rudder control.
2019-08-11: We are superseding Airworthiness Directive (AD) 2008-24-14, which applied to all Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008-24-14 required revising the instructions for continued airworthiness to incorporate certain airworthiness limitations for the main landing gear (MLG) trunnion fitting assembly. This AD requires revising the maintenance or inspection program, as applicable, to incorporate certain airworthiness limitations (AWLs). This AD also requires reworking the trunnion fitting in order to meet new structural safe-life limits. This AD was prompted by reports of cracks on the MLG trunnion fitting during fatigue testing; the introduction of new AWL tasks with revised inspection, modification, and safe-life requirements; and a determination that the trunnion fitting lower flange and both forward and aft bore holes are also subject to fatigue cracking. We are issuing this AD to address the unsafe condition on these products.
78-09-07 R3: 78-09-07 R3 BENDIX: Amendment 39-3205 as amended by Amendments 39-3252 and 39-3963 is further amended by Amendment 39-4538. Applies to Bendix S-20 series, S-1200 series, D-2000 series, and D-3000 series magnetos incorporating impulse couplings. Compliance required as indicated unless previously accomplished. To preclude magneto or engine failure resulting from magneto impulse coupling failure, accomplish the following: a. On magnetos having less than 475 hours time in service since new or overhaul, accomplish the provisions of paragraphs "c" and "d" of this AD prior to 500 hours time in service and thereafter at intervals not to exceed 500 hours time in service from the last inspection. b. On magnetos having 475 or more hours in service since new or overhaul, accomplish the provisions of paragraphs "c" and "d" of this AD within the next 25 hours time in service and thereafter at intervals not to exceed 500 hours time in service from the last inspection. c. Inspect and replace, if necessary, impulse coupling components in accordance with the paragraph titled "Detailed Instructions" contained in Bendix Engine Products Division Service Bulletin Number 599B or an FAA approved equivalent. d. After accomplishing paragraph "c" of this AD, make a logbook entry showing the compliance time. Include the magneto make, model, and serial number. (Note: Except for new or zero time overhauled magnetos, any magneto not accompanied by a record of operating time must be in compliance with paragraph "c" upon installation on an approved engine.) e. Equivalent inspections and procedures must be approved by the Manager, New York Aircraft Certification Office, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. f. As permitted by Federal Aviation Regulations (FARs) 21.197 and 21.199, aircraft may be flown to a base where maintenance required by this AD can be accomplished. Amendment 39-3205 was effective May 9, 1978. Amendment 39-3252 amended Amendment 39-3205 effective July 3, 1978. Amendment 39-3963 amended Amendments 39-3205 and 39-3252 effective November 3, 1980. This Amendment 39-4538 is effective on January 17, 1983.
97-24-08: This amendment adopts a new airworthiness directive (AD) that applies to Burkhart Grob, Luft-und Raumfahrt, GmbH. (Grob) Model G102 Astir CS sailplanes. This action requires replacing the elevator control lever with an improved elevator control lever. The discovery of cracks in the elevator control lever during a routine inspection of a Grob Model G102 Astir CS sailplane prompted this action. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the elevator control lever, which could result in loss of control of the sailplane.
94-03-08: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes, that currently requires certain structural modifications and inspections. This amendment requires additional structural modifications and inspections. This amendment is prompted by an evaluation by the Model DC-10 Task Group, which identified additional modifications for mandatory action. The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes. This action also reflects the FAA's decision that long-term continued operational safety should be assured by actual modification of the airframe, where feasible, rather than only repetitive inspections for known service problems.
2019-10-04: We are adopting a new airworthiness directive (AD) for certain BRP-Rotax GmbH & Co KG (Rotax) 912 and 914 model engines. This AD was prompted by power loss and engine revolutions per minute (RPM) drop on certain Rotax 912 and 914 model engines due to a quality control deficiency in the manufacturing process of certain valve push-rod assemblies resulting in partial wear on the rocker arm ball socket and possible malfunction of the valve. This AD requires one-time inspection and, depending on the findings, replacement of the affected parts with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products.
98-16-06: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires inspections of the lower door surrounding structure to detect cracks and corrosion, and repair, if necessary. This amendment also requires inspections to detect cracking of the holes of the corner doublers, the fail-safe ring, and the door frames of the door structures; and repair, if necessary. In addition, this amendment provides for optional terminating action for certain inspections. This amendment is prompted by reports indicating that corrosion was found between the scuff plates at exit and cargo doors, and fatigue cracks originated from certain fastener holes located in adjacent structure. The actions specified by this AD are intended to detect and correct such corrosion and fatigue cracking, which could result in reduced structural integrity of the door surroundings.