Results
2010-07-09: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc RB211-Trent 700 series turbofan engines. That AD currently requires initial and repetitive borescope inspections of the high-pressure-and-intermediate pressure (HP-IP) turbine internal and external oil vent tubes for coking and carbon buildup, and cleaning or replacing the vent tubes if necessary. This AD requires the same actions, but adds additional inspections of the vent flow restrictor. This AD results from further analysis that the cleaning of the vent tubes required by AD 2007-02-05 could lead to loosened carbon fragments, causing a blockage downstream in the vent flow restrictor. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup that could cause uncontained engine failure and damage to the airplane.
96-14-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-301, -311, and -315 series airplanes, that currently requires modification of the airspeed limitations placard and revision of the Airplane Flight Manual to specify operating at lower airspeeds when the airplane is operating at full flaps. That action also provides for the optional termination of the requirements of the AD for certain airplanes. That action was prompted by a report that incorrect rivets were installed on the outboard flaps assemblies of these airplanes. The actions specified by that AD are intended to prevent structural failure of the outboard flaps of the wings due to the installation of incorrect rivets in the flap assemblies, which could result in reduced controllability of the airplane. This new amendment requires the installation of the previously optional terminating modification on certain airplanes.
2011-09-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: There have been several in-service reports of finding trapped water on the bottom of the cockpit windshield frames (or lower windshield frames) that resulted in either corrosion or water ingress into the cockpit. In one occurrence, the trapped water caused severe corrosion of numerous anchor nuts that secure the windshield to the lower windshield frame, such that the intended fastening function was seriously compromised. Corrosion of the lower windshield frames, including the anchor nuts that secure the windshield to the aircraft structure, can result in a serious structural degradation possibly leading to the loss of the windshield during flight. Also, water could leak into the cockpit and cause either a malfunction or failure of the electrical and electronics systems in the area of the cockpit instrument panels. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2011-09-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Further to accomplishment of A340 ALI tasks 545104, which require a rototest inspection as per Non Destructive Testing Manual (NTM) 54-51-04 of engine pylon pyramid attachment areas at aft end of lower arms between Rib 1 and Rib 2 (2 fastener locations/pylon), four findings have been reported and repaired. * * * * * The unsafe condition is cracking, which might impact the structural integrity of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
74-08-09 R2: This amendment revises an existing airworthiness directive (AD), applicable to all transport category airplanes, that currently requires installation of placards prohibiting smoking in the lavatory and disposal of cigarettes in the lavatory waste receptacles; establishment of a procedure to announce to airplane occupants that smoking is prohibited in the lavatories; installation of ashtrays at certain locations; and repetitive inspections to ensure that lavatory waste receptacle doors operate correctly. That AD was prompted by fires occurring in lavatories, which were caused by, among other things, the improper disposal of smoking materials in lavatory waste receptacles. The actions specified by that AD are intended to prevent such fires. This amendment revises the existing AD to allow dispatch relief in the event a lavatory door ashtray is missing.
99-15-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes. This action requires repetitive detailed inspections to detect looseness or gap of the press fit bushing installation of the actuator fittings of the aileron trim tabs, and eventual replacement of the bushings with new, staked bushings. Accomplishment of such replacement terminates the repetitive inspections. This action also provides for an optional temporary preventive action, which, if accomplished, would terminate the repetitive inspections until the terminating action is accomplished. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent looseness or gap of the bushings. In the event of failure of the redundant trim tab actuator, such looseness or gap of the bushings could lead to trim tab flutter and consequent structural failure of the trim tab and reduced controllability of the airplane.
2011-09-03: We are adopting a new airworthiness directive (AD) for all Model 382, 382B, 382E, 382F, and 382G airplanes. This AD requires repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacements of rainbow fittings, which would extend the repetitive interval for the next inspection. This AD results from a report of fatigue cracking of the wing upper and lower rainbow fittings during durability testing and on in-service airplanes. Analysis of in- service cracking has shown that these rainbow fittings are susceptible to multiple site fatigue damage. We are issuing this AD to detect and correct such fatigue cracks, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing.
96-13-03: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-9 and C-9 (military) series airplanes, that currently requires the implementation of a program of structural inspections to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This amendment requires, among other things, revision of the existing program to require additional visual inspections of additional structure. This amendment is prompted by new data submitted by the manufacturer indicating that certain revisions to the program are necessary in order to increase the confidence level of the statistical program to ensure timely detection of cracks in various airplane structures. The actions specified by this AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes.
78-26-12: 78-26-12 CESSNA: Amendment 39-3382. Applies to Models 210G, H, J (Serial Number 21058819 through 21059199); 210M, N (Serial Numbers 21062274 through 21063025); T210G, H, J (Serial Number T210-0198 through T210-0454 and 21058140); T210M, N (Serial Numbers 21062274 through 21063025); and P210N (Serial Numbers P21000001 through P21000141) airplanes. COMPLIANCE: Required as indicated unless already accomplished. To detect binding of fuel quantity transmitter float arms and assure proper operation of the fuel quantity indicating system accomplish the following: A) On Models 210M, N and T210M, N (Serial Numbers 21062761 through 21063025) and P210N (Serial Numbers P21000063 through P21000141) airplanes, before next flight (except that the airplane may be flown to a location where this inspection may be accomplished, provided the pilot visually verifies through the fuel filler neck that adequate fuel is available to complete the flight), completely fill, then drain the leftand right fuel tanks with the engine inoperative and the airplane stationary in the level ground attitude. Observe the fuel quantity gauge during draining and upon completion of drainage, verify that the respective fuel quantity gauge indicates empty. Remove any Cessna P/N C668002-0101 or -0102 fuel quantity transmitter from which an erroneous fuel quantity reading is observed and check for binding of the float arm. Replace any fuel quantity transmitter found binding with an airworthy component. After replacement, check for fuel leaks and proper functioning of the fuel gauging system. B) For Models 210G, H, J, M (Serial Numbers 21058819 through 21059199 and 21062274 through 21062760), T210G, H, J, M (Serial Numbers T210-0198 through T210-0454, 21058140 and 21062274 through 21062760) and P210N (Serial Numbers P21000001 through P21000062) airplanes, before next flight, review the aircraft maintenance records to determine if a fuel quantity transmitter has been replaced since June7, 1978. 1. If a fuel quantity transmitter has not been replaced since June 7, 1978, make an entry in the aircraft maintenance records indicating that this Airworthiness Directive has been accomplished and the airplane may be returned to service. 2. If a fuel quantity transmitter has been replaced since June 7, 1978, comply with the requirements of Paragraph A). C) The review of the aircraft maintenance records required by Paragraph B) may be accomplished by the holder of a Pilot's Certificate issued under Part 61 of the Federal Aviation Regulations on any aircraft owned or operated by that person. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Cessna Service Letter SE 78-69, dated November 15, 1978, or later approved revisions pertains to the subject matter of this AD. This amendment becomes effective on January 4, 1979, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated November 15, 1978.
2011-09-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing an auto shutoff feature for the center override/jettison fuel pumps, and installing power control circuitry for the center override/jettison and main jettison fuel pumps. This AD also requires installing new software in the electrical load management system (ELMS) electronics units in certain power management panels; installing airplane information management system 2 (AIMS-2) software in the AIMS-2 hardware; and making certain wiring changes. This AD was prompted by results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.