Results
2020-16-05: The FAA is adopting a new airworthiness directive (AD) for all Blanik Aircraft CZ s.r.o. Model L 23 Super-Blanik gliders. This AD requires a one-time inspection of the rudder control cable attachment screws and hinge bolts, replacement of the cable attachment screws and hinge bolts if a crack is found, and reporting the inspection results to the manufacturer. This AD was prompted by reports of cracked rudder cable attachment screws. The FAA is issuing this AD to address the unsafe condition on these products.
2008-09-18: The FAA adopts a new airworthiness directive (AD) for certain Taylorcraft, Inc. Models A, B, and F series airplanes. This AD requires you to inspect the wing strut attach fittings for corrosion or cracks and requires repair or replacement if corrosion or cracks are found. This AD results from data collected from an accident involving a Taylorcraft Model BF12-65 airplane. The wing separated from the airplane after the wing strut attach fitting failed due to corrosion. We are issuing this AD to detect and correct corrosion or cracks in the wing strut attach fittings, which could result in failure of the wing strut attach fittings and lead to wing separation and loss of control.
2001-17-03: This amendment adopts a new airworthiness directive (AD) that is applicable to all EMBRAER Model EMB-135 and -145 series airplanes. This action requires repetitive inspections of the engine thrust reverser stow/transit switches, and corrective action, if necessary. This action is necessary to prevent erroneous signals in the Engine Indicating and Crew Alerting System (EICAS) caused by internal corrosion of the thrust reverser stow/transit switches, which could result in uncommanded loss of engine power in flight, or unnecessary aborted takeoffs on the ground. This action is intended to address the identified unsafe condition.
95-10-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that requires replacement of the horizontal stabilizer trim electric actuator. This amendment is prompted by reports of a binding condition in the clutch disk in the horizontal stabilizer trim electric actuator. The actions specified by this AD are intended to prevent reduced controllability of the airplane due to binding of a clutch disk in the horizontal stabilizer trim electric actuator.
2008-09-17: We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, and MD-10-10F airplanes. This AD requires repetitive inspections for the presence of stray nickel or chrome plating deposits on the air filler valve bore of certain main landing gear (MLG) shock strut cylinders, and if necessary, related investigative and corrective actions. Doing the corrective action terminates the repetitive inspections. This AD results from a report of a left MLG collapse during landing rollout. We are issuing this AD to detect and correct stray nickel and chrome plating deposits, corrosion, and cracking of the air filler valve bore on the MLG cylinder, which could result in landing gear failure, significant damage to the airplane, and injury to personnel.
2001-16-11: This amendment adopts a new airworthiness directive (AD); applicable to certain Boeing Model 737-100, -200, and -200C series airplanes; that requires a one-time inspection of the carriage spindles on the outboard midflap for circumferential score marks; and rework of the carriage spindles or replacement with new or serviceable spindles, if necessary. This action is necessary to prevent severe flap asymmetry due to fractures of both carriage spindles at an outboard midflap, which could result in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
95-09-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company Model R44 helicopters. This action requires removal of the push-pull tube sleeve guide assembly (sleeve guide) and replacement with a push-pull tube roller guide assembly (roller guide); and, inspections of the push-pull tube sleeves for signs of wear and replacement as necessary. This amendment is prompted by a report of an operator experiencing binding in the cyclic control system caused by torn heat-shrink material (material) on the cyclic push-pull tubes binding in the sleeve guide. The actions specified in this AD are intended to prevent binding in the cyclic control system and subsequent loss of control of the helicopter.
2008-09-08: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: On the pre-flight check of a SZD-50-3 glider, the Right Hand (RH) wing airbrake was found impossible to retract. Investigation revealed that the occurrence was caused by a loose bolt of the "V'' shape airbrake bellcrank, named hereafter intermediate control lever. The Left Hand (LH) wing lever also presented, to a lesser extent, a loose bolt. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 5, 2008. As of February 1, 2008 (73 FR 3623), the Director of the Federal Register approved the incorporation by reference of Allstar PZL Glider Sp. z o. o. Service Bulletin No. BE-059/SZD-50-3/2007 "PUCHACZ,'' dated October 15, 2007, listed in this AD.
2018-18-15: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211- Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. This AD was prompted by low-pressure compressor (LPC) case A-frame hollow locating pins that may have reduced integrity due to incorrect heat treatment. This AD requires replacement of the LPC case A-frame hollow locating pins. We are issuing this AD to address the unsafe condition on these products.
2001-17-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires repetitive inspections for corrosion or cracking of the keel beam splices, and corrective action, if necessary. This action also provides an optional terminating action for the repetitive inspections. This action is necessary to find and fix corrosion or cracking of the keel beam splices, which could result in failure of the keel beam and consequent failure of the forward fuselage of the airplane. This action is intended to address the identified unsafe condition.
95-09-13: This amendment supersedes AD 93-05-03, which currently requires repetitively inspecting each fuel inlet float valve in accordance with certain test procedures on Cessna Aircraft Company (Cessna) Models T303, 402C, 404, 414A, and 421C airplanes, and replacing any valve that does not pass this test. The manufacturer has developed fuel inlet float valves of improved design, and the Federal Aviation Administration (FAA) has determined that the improved valves should be installed to reduce the number of repetitive tests currently required by AD 93-05-03. This action requires installing these fuel inlet float valves of improved design. The actions specified by this AD are intended to prevent possible loss of engine power caused by failure of a fuel inlet float valve.
84-22-01: 84-22-01 VICKERS-SLINGSBY: Amendment 39-4941. Applies to Model T65A gliders, all serial numbers certificated in any category. Compliance required as indicated. To prevent possible malfunction of the elevator, accomplish the following: 1. Within the next 10 hours time in service, after the effective date of this AD, unless already accomplished, inspect the following in accordance with Slingsby Engineering Ltd. (S.E.L.) Technical Instruction (TI) No. 104/T65, Issue 1, Section 1, dated September 22, 1982 (hereinafter referred to as TI): A. The pivot bearing (P/N 04DU04) for the elevator rocker arm assembly on top of the fin for wear, B. The glass reinforced plastic operating tongue of the elevator which projects forward into the tailplane for cracks, damage, or lack of stiffness, and, C. The tailplane center hinge pin mounting rib at the section just forward of the hinge pin for cracks and/or damage. 2. Prior to further flight: A. If wear is found in excess of 0.01 inches in the forward and aft direction as a result of the inspection of Item 1A above, repair in accordance with Section 3 of the TI described in Item 1. B. If cracks, damage or lack of stiffness are found as a result of the inspection of Item 1B above, repair in accordance with Section 2 of the TI described in Item 1. C. If cracks or damage are found as a result of the inspection of Item 1C above, replace with a new reinforced rib in accordance with Section 4 of the TI described in Item 1. 3. Within the next 100 hours time in service, if cracks or damage are not found, unless already accomplished, reinforce the elevator in accordance with Section 5 of the TI described in Item 1. 4. Alternate inspections, adjustment of the inspection interval, or other actions which provide an equivalent level of safety must be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium, telephone 513.38.30 Ext. 2710. The Slingsby Engineering Ltd. (S.E.L.) Technical Instruction (TI) No. 104/T65, Issue 1, dated September 22, 1982, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request from Slingsby Engineering Limited, Ings Lane, Kirbymoorside, York Y066EZ, England. This document may also be examined at the Office of Regional Counsel, 12 New England Executive Part, Burlington, Massachusetts 01803. This amendment becomes effective November 7, 1984.
95-09-11: This amendment adopts a new airworthiness directive (AD) that applies to Schempp-Hirth Cirrus and Cirrus VTC sailplanes. This action requires modifying the airbrake actuating lever and replacing the airbrake system coupling balls. Reports of the coupling balls on the airbrake actuating lever breaking at the threaded end on several of the affected sailplanes prompted this action. The actions specified by this AD are intended to prevent airbrake system failure caused by the above condition, which, if not detected and corrected, could result in sailplane controllability problems.
2008-09-03: We are adopting a new airworthiness directive (AD) for the specified Agusta S.p.A. (Agusta) model helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The European Aviation Safety Agency (EASA), the Technical Agent for Italy, with which we have a bilateral agreement, states in the MCAI: It has been reported, on an A109A helicopter, a case of failure of the grooved clamp fixing the engine exhaust duct, with the consequent loss of the duct. The duct has hit the main and tail rotor producing the loss of the tail rotor and the emergency landing of the helicopter. The fracture of the grooved clamp was due to excessive loads and corrosion around the attaching rivets. This AD requires actions that are intended to address this unsafe condition.
2001-16-09: This amendment supersedes an existing airworthiness directive (AD), which is applicable to all Model A320 series airplanes, that currently requires repetitive measurements of the deflection of the elevator trailing edge; inspections of the elevator servo controls and their attachments; and replacement of worn or damaged parts, if necessary. This amendment requires periodic inspection of the elevators for excessive freeplay, repair of worn parts if excessive freeplay is detected, and modification of the elevator neutral setting. It also revises the applicability to include additional airplane models. This amendment is prompted by additional reports of severe vibration in the aft cabin of Model A320 series airplanes and studies that indicate that the primary cause is excessive freeplay in the elevator attachments. The actions specified by this AD are intended to prevent excessive vibration of the elevators, which could result in reduced structural integrity and reduced controllability of the airplane.
2020-16-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of low halon concentration in the forward and aft cargo compartments due to air leakage through cargo door seals. This AD requires repetitive cleaning and greasing of affected cargo door seals, 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.
95-09-12: This amendment supersedes Airworthiness Directive (AD) 88-11-05, which currently requires repetitively inspecting the wing spar of Alexander Schleicher Models ASW-15 and ASW-15B gliders for wood rot, and replacing any wing spar where wood rot is found. Alexander Schleicher Models ASW-12 and ASW-17 gliders are of a similar type design to Models ASW-15 and ASW-15B gliders, and the Federal Aviation Administration (FAA), in working with the Civil Aviation Authority of Germany, has decided that the actions referenced in AD 88-11-05 should also apply to Models ASW-12 and ASW-17 gliders. The actions specified by this AD are intended to prevent failure of the wing spar caused by wood rot, which, if not detected and corrected, could result in loss of control of the airplane.
2008-08-11: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD900 series helicopters that requires modifying the pilot and co-pilot dual-control directional pedal assemblies, or the pilot single-control directional pedal assembly (directional control pedal assembly). This amendment is prompted by an accident which has been attributed to loss of directional control due to failure of the welds in the directional control pedal assembly. The actions specified by this AD are intended to prevent fatigue cracking in the welds that connect the directional control pedal to the pedal shaft, resulting in loss of directional control and subsequent loss of control of the helicopter.
95-09-08: This amendment adopts a new airworthiness directive (AD) that is applicable to McCauley Model 2A37C223/90RB propellers. This action requires installation of internal steel components, replacement of a balance ring, replacement of cylinder mounting screws, and modification to an oil-filled configuration with red dye. Replacement of the identified components redistributes propeller weight while the red dye oil-filling provides an "on-condition" (in-service) means of early crack detection of the propeller assembly and also improves lubrication and corrosion protection. Any screw failures or cracks found during the accomplishment of this AD must be reported to the FAA. This amendment is prompted by a report of a propeller found with at least one cylinder screw that had failed due to fatigue. The actions specified in this AD are intended to prevent cylinder screw failure that could result in loss of propeller control and subsequent loss of aircraft control.
2001-16-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires initial and repetitive inspections of certain areas of the wing spars to detect cracking or corrosion; and follow-on corrective actions and repair, if necessary. This amendment is prompted by reports of cracks and corrosion in the upper chord of the front and rear spars of the wing and reports of cracks propagating from previously repaired areas. The actions specified by this AD are intended to detect and correct such cracking or corrosion of the upper and lower chords of the wing spars, which could result in reduced structural integrity of the wing.
74-08-09 R1: This amendment revises an existing airworthiness directive (AD) that is applicable to all transport category airplanes. The existing AD 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 action 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 the AD are intended to prevent such fires. This amendment provides for an alternative action regarding the current requirement to install specific placards at certain locations.
2008-09-10: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2003-06-01, which applies to all Air Tractor, Inc. (Air Tractor) Models AT-300, AT-301, AT-302, and AT-400A airplanes that have aluminum spar caps; certain Air Tractor Models AT-400 airplanes that have aluminum spar caps; and all Models AT-300 and AT-301 airplanes that have aluminum spar caps and are or have been converted to turbine power. AD 2003-06-01 requires replacing the wing spar lower caps at a specified safe life limit; allows extending the safe life limit on certain airplanes if a wing lower spar cap splice rework is done; allows a limited time of continued operation beyond the safe life limit provided parts are ordered, the replacement is scheduled, and repetitive inspections reveal no cracks; and requires a report of any cracks found during any inspection to the FAA. This AD results from a recent report of cracks found on a Model AT-301 airplane at hours below the modification time specified inAD 2003-06-01. Consequently, this AD retains the wing spar lower cap replacement and reporting requirements from AD 2003-06-01 and adds a repetitive eddy-current inspection. We are issuing this AD to detect and correct cracks in the wing centerline splice joint. If not detected and corrected, these cracks could result in the wing separating from the airplane during flight. \n\nDATES: This AD becomes effective on May 8, 2008. \n\tOn May 8, 2008, the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 55, revised October 4, 2004, listed in this AD. \n\tAs of April 4, 2003, (68 FR 13221, March 19, 2003), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Service Letter 55, revised October 23, 2002, and Snow Engineering Co. Process Specification Number 197, revised June 4, 2002, listed in this AD. \n\tWe must receive any comments on this AD by June 27, 2008.
2001-17-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes. This action requires measuring the gap between the bellcrank and the body of the rotary variable inductive transducers (RVITs) of the aileron and elevator, performing corrective action if necessary, and torquing the bolt that attaches the bellcrank to the RVIT shaft. This action is necessary to prevent restricted movement of the aileron or elevator, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2020-15-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports of improperly locked diagonal struts located in a certain section of the fuselage; the teeth of the lock washers were incorrectly engaged, which could lead to a loss of tightening torque of an affected strut. This AD requires inspecting the diagonal strut for correct installation and for correct locking of the lock washers, and corrective actions if necessary, 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.
95-09-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-8-60 series airplanes. This action requires inspection to determine the part number of the cone bolt on the right side of the forward mount of each engine, and replacement of the bolt, if necessary. This amendment is prompted by a report of failure of a cone bolt at that location on an engine of one airplane. The actions specified in this AD are intended to prevent failure of the cone bolt on the right side of the forward mount of the engine, which may lead to separation of the engine during a critical phase of flight.