36 Airworthiness Directives: 22 airplane, 7 rotorcraft, 3 engine, 2 propeller, 2 glider.
AD 95-09-09 · published May 1, 1995, effective May 16, 1995
McDonnell Douglas Model DC-8-60 Series Airplanes Equipped With Engines Modified by Burbank Aeronautical Corporation II (BAC II) in Accordance With Supplemental Type Certificate (STC) SA4892NM or SA5455NM
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.
AD 74-08-09 R1 · published May 2, 1995, effective Jun 1, 1995
Transport Category Airplanes
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 [[Page 21430]] 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.
AD 95-08-08 · published May 2, 1995, effective May 2, 1995
The Boeing Company Airplanes
AD 95-08-09 · published May 2, 1995, effective May 2, 1995
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires modification of the support structure of the cargo liner. This amendment is prompted by a report of chafing and arcing in the vacuum waste exhaust heater that caused a spark to ignite the surrounding insulation blankets. The actions specified in this AD are intended to prevent fire and/or smoke due to chafing and arcing of the vacuum waste exhaust port heater.
AD 95-09-13 · published May 8, 1995, effective Jun 14, 1995
Cessna Aircraft Company Models T303, 402C, 404, 414A, and 421C Airplanes
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.
AD 95-07-05 · published May 10, 1995, effective May 10, 1995
Airbus Industrie, Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment is prompted by the discovery of fatigue cracks that emanated from the bolt holes inboard and outboard of rib 9 in the bottom booms of the front and rear wing spars. The actions specified by this AD are intended to prevent reduced structural integrity of a wing spar as a result of fatigue cracks in the bolt holes.
AD 95-07-06 · published May 10, 1995, effective May 10, 1995
Airbus SAS Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires inspections of the bearings of the aileron control system, and correction of discrepancies. This amendment is prompted by a report indicating that an operator experienced difficulties wherein considerable pressure was required to manually input roll control due to seized bearings in the aileron control system. The actions specified by this AD are intended to prevent such seizure of bearings, which could reduce the pilot's ability to initiate roll control during critical phases of flight.
AD 95-08-01 · published May 10, 1995, effective May 10, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires modification of the spoiler system. This amendment is prompted by reports of fatigue failures of the tee fittings of the spoiler bleed nipples. The actions specified by this AD are intended to ensure that the tee fittings do not fail, and subsequently lead to loss of the main system hydraulics.
AD 95-10-02 · published May 12, 1995, effective Jun 12, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas MD-11 series airplanes, that requires the installation of an electrically controlled slat system. This amendment is prompted by numerous incidents of inadvertent deployment of the slats while the airplane was in flight at cruise altitude. The actions specified by this AD are intended to prevent inadvertent deployment of the slats during flight, which could result in an abrupt pitch up of the airplane and consequent injury to crew and passengers; it could also result in significant vibrations and cause damage to the elevators.
AD 95-10-03 · published May 12, 1995, effective Jun 12, 1995
Airbus Industrie Model A300, A300-600, and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that requires inspections to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, and repair, if necessary. This amendment is prompted by a report indicating that fatigue cracks have been found on the lower spar of the pylon. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
AD 95-10-05 · published May 12, 1995, effective Jun 12, 1995
The Boeing Company Airplanes
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.
AD 95-10-13 · published May 16, 1995, effective Jun 15, 1995
Boeing Model 757 Series Airplanes Equipped With Rolls Royce Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires inspections to detect fatigue-related cracking or breakage of the hydraulic tubing support brackets located on the upper spar web in the engine struts; further inspection to detect related damage of the upper spar web, the fuel lines, and the hydraulic lines, as necessary; and repair or replacement of cracked or damaged parts. That AD was prompted by reports of fatigue-related cracks in the hydraulic tubing support brackets located on the upper spar web in the engine struts. The actions specified by that AD are intended to prevent such fatigue-related cracking, which could result in fuel or hydraulic fluid leakage into the interior of the engine strut and cause a fire. This amendment requires installation of a previously optional terminating action.
AD 95-10-17 · published May 18, 1995, effective May 23, 1995
Lockheed Model L-1011-385 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed Model L-1011-385 series airplanes. This action requires inspections to detect cracking or severing of the fuselage frames, and an additional inspection or repair, if necessary. This amendment is prompted by reports indicating that fatigue cracking was found on certain fuselage frames on these airplanes. The actions specified in this AD are intended to prevent reduced structural integrity of the fuselage shell due to the problems associated with fatigue cracking.
AD 95-09-10 · published May 19, 1995, effective May 19, 1995
McDonnell Douglas Corporation Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes. This action requires an inspection to detect chafing of or damage to the wire bundle in the overhead switch panel of the cockpit, application of spiral wrap to the wire bundle, and corrective actions, if necessary. This amendment is prompted by reports of chafed and shorted wires that resulted in smoke emanating from the overhead switch panel of the cockpit. The actions specified in this AD are intended to prevent the potential for fire and uncontrolled smoke throughout the cockpit as a result of chafing and shorting in the electrical wire bundles.
AD 95-10-14 · published May 22, 1995, effective Jun 21, 1995
Airbus Model A300, A310, and A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive mechanical and electrical inspections to detect chafing of electrical wiring; and repair or replacement of discrepant parts, and repositioning the looms. This amendment is prompted by reports of wire chafing in the forward avionic compartment. The actions specified by this AD are intended to prevent such chafing, which may lead to a short in the electrical circuits at the 104VU panel; this condition could result in unwanted depressurization, loss of wing de-icing, and loss of in-flight engine restart capability.
AD 95-10-15 · published May 22, 1995, effective Jun 21, 1995
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, -300A and Model Avro 146-RJ70A, -RJ85A, and -RJ100A airplanes, that requires repetitive inspections to verify proper deployment of the evacuation slide at each door position, and various follow-on actions to correct discrepancies. This amendment is prompted by a report that, during operational checks of evacuation slides on in- service airplanes, the inflation valves failed to deploy the evacuation slide properly. The actions specified by this AD are intended to prevent failure of the evacuation slide to deploy automatically on demand, which would necessitate the flightcrew to manually deploy the slide; this situation could delay or impede the evacuation of passengers during an emergency.
AD 95-10-16 · published May 22, 1995, effective Jun 21, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires modification of the nacelle strut and wing structure, inspections and checks to detect discrepancies, and correction of discrepancies. This amendment is prompted by the development of a modification of the strut and wing structure that improves the damage tolerance capability and durability of the strut-to-wing attachments, and reduces reliance on inspections of those attachments. The actions specified by this AD are intended to prevent failure of the strut and subsequent loss of the engine.
AD 95-11-02 · published May 22, 1995, effective Jun 21, 1995
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes and certain Model MD-11 series airplanes, that currently requires inspections to detect defects in the upper and lower lock links on the nose landing gear (NLG), and rework or replacement of any defective link with a serviceable link. The actions specified by that AD are intended to prevent collapse of the NLG. This amendment requires accomplishment of a certain inspection that constitutes terminating action for the currently required inspections.
AD 95-11-03 · published May 24, 1995, effective Jun 23, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires replacement of the existing pressure relief valve in the potable water system with a non-adjustable, single setting valve. This amendment is prompted by reports of potable water tanks that ruptured and resulted in damage to the passenger compartment. The actions specified by this AD are intended to prevent injury to the crew and passengers and damage to the passenger compartment due to an explosive failure of the potable water tank.
AD 95-11-04 · published May 24, 1995, effective Jun 23, 1995
Aerospatiale Model ATR42-200, -300, and -320 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-200, -300, and -320 series airplanes, that requires modification of the wiring in the elevator controls and the pitch trim dissymmetry monitoring equipment. This amendment is prompted by a report of loss of a propeller and engine gearbox, which resulted in damage to the fuselage. There has also been a report that a modification was implemented in the elevator control cables during manufacture, which reduced the maximum physical separation between the elevator controls and the monitoring equipment. The actions specified by this AD are intended to prevent reduced controllability of the airplane in the event that debris from an engine burst or propeller failure were to strike the fuselage and sever the elevator flight controls.
AD 95-09-03 · published May 30, 1995, effective Jun 14, 1995
Jetstream Model 4101 Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 95-09-03, that was sent previously to all known U.S. owners and operators of Jetstream Model 4101 airplanes by individual letters. This AD requires inspection to determine the number of hours time-in-service on the landing gear control unit, and modification of the cable (electrical wiring circuit) of the landing gear control unit. This amendment is prompted by a report of failure of a micro-switch in the landing gear control unit. The actions specified by this AD are intended to prevent uncommanded retraction of a landing gear, which could adversely affect airplane controllability.
AD 95-11-07 · published May 30, 1995, effective Jun 29, 1995
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that requires inspections to detect cracking of H-11 attach bolts of the upper vertical stabilizer and replacement of these bolts and associated nuts with Inconel bolts and nuts. This amendment is prompted by failure of the attach bolts of the upper vertical stabilizer due to stress corrosion. The actions specified by this AD are intended to prevent undetected cracked or failed attach bolts that may lead to reduced structural integrity of the vertical stabilizer.
AD 95-09-06 · published May 4, 1995, effective Jun 8, 1995
Bell Helicopter Textron, Inc. Model 206A, 206B, 206L, 206L-1, and 206L-3 Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, that requires installing a protective mechanical fuel valve switch guard on the fuel valve switch. This amendment is prompted by reports of airmen inadvertently placing the fuel valve switch to the ``OFF'' position. The actions specified by this AD are intended to prevent the fuel valve switch from being inadvertently placed in the ``OFF'' position, which could result in an engine failure and a subsequent power-off landing.
AD 95-09-07 · published May 9, 1995, effective May 24, 1995
Robinson Helicopter Company Model R44 Helicopters
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.
AD 95-10-07 · published May 11, 1995, effective May 26, 1995
Bell Helicopter Textron, Inc. Model 205A, 205A-1, and 204B Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI) Model 205A, 205A- 1, and 204B helicopters. This action requires verification that the tail rotor control system is rigged in accordance with the applicable maintenance manual; a fluorescent penetrant inspection for cracks at the roots of the gear teeth on the pinion and gear of affected 42- degree tail rotor drive gearbox assemblies (42-degree gearboxes) and replacement of the 42-degree gearbox pinion or gear if cracks are found, and creation of a component history card to track the numbers of torque events. A torque event is defined as a takeoff or a lift (internal or external). This amendment is prompted by 14 accidents reported in the United States and Canada related to failure of the 42- degree gearbox. The actions specified in this AD are intended to prevent failure of the 42-degree gearbox, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 95-10-08 · published May 11, 1995, effective May 26, 1995
Arrow Falcon Exporters, Inc., AST, Inc, Bell Helicopter Textron, Inc., California Department of Forestry, Global Helicopter Technology, Inc., Hagglund Helicopters, LLC, International Helicopters, Inc., Overseas Aircraft Support Inc, Richards Heavylift Helo, Inc., Robinson Air Crane, Inc., Rotorcraft Development Corporation, San Joaquin Helicopters, Smith Helicopters, Sout
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured restricted category Model UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, UH-1P, TH-1F, and TH-1L helicopters. This action requires verification that the tail rotor control system is rigged in accordance with the applicable maintenance manual; a fluorescent penetrant inspection for cracks at the roots of the gear teeth on the pinion and gear of affected 42-degree tail rotor drive gearbox assemblies (42-degree gearboxes), and replacement of the 42-degree gearbox pinion or gear if cracks are found; and, creation of a component history card to track numbers of torque events. A torque event is defined as a takeoff or a lift (internal or external). This amendment is prompted by 14 accidents reported since 1979 in the United States and Canada related to failure of the 42-degree gearbox. The actions specified in this AD are intended to prevent failure of the 42-degree gearbox, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 95-08-12 · published May 23, 1995, effective May 23, 1995
Airbus Helicopters Deutschland GmbH Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters, that requires a modification of the latches on the transmission and engine cowling access doors. This amendment is prompted by five occurrences of an engine or transmission cowling access door becoming loose in flight. The actions specified by this AD are intended to prevent the transmission and engine cowling access doors from opening in flight, being struck by the main rotor blade, and subsequently, separating from the helicopter and being ingested by the main rotor or tail rotor system resulting in a loss of control of the helicopter.
AD 95-11-05 · published May 25, 1995, effective Jun 9, 1995
Societe Nationale Industrielle Aerospatiale and Eurocopter France Model AS-355 E, F, F1, F2, and N Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Societe Nationale Industrielle Aerospatiale and Eurocopter France (Eurocopter France) Model AS-355 E, F, F1, F2, and N helicopters. This action requires a check to ensure that the main gearbox (MGB) oil pressure warning light illuminates during each shutdown of the helicopter engine until the MGB oil pressure switch (switch) is removed and replaced. This amendment is prompted by a malfunction of the MGB switch. This condition, if not corrected, could result in failure to detect a loss of oil pressure, loss of the MGB, loss of power to the main rotor system, and subsequent loss of control of the helicopter.
AD 95-11-06 · published May 25, 1995, effective Jun 9, 1995
Airbus Helicopters Helicopters
AD 95-10-04 · published May 10, 1995, effective May 25, 1995
AlliedSignal Inc. (Formerly Textron Lycoming and Avco Lycoming) Model T5313B and T5317 Series Turboshaft Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming and Avco Lycoming) Model T5313B and T5317 series turboshaft engines, that currently requires initial and repetitive dye penetrant inspections of the centrifugal compressor impeller for cracks, and if necessary, removal from service. This amendment requires the use of a new, more conservative minor cycle counting factors table, introduces a method for prorating past centrifugal compressor impeller usage based on the new cycle counting factors, provides an enhanced centrifugal compressor impeller inspection procedure, and eliminates flyback criteria based on crack size. For those centrifugal compressor impellers that exceed their published life limit, this amendment implements a schedule for safe removal of time-expired parts. This amendment is prompted by a report of an uncontained centrifugal compressor impeller failure and subsequent rotorcraft accident. The actions specified by this AD are intended to prevent centrifugal compressor impeller failure, which can result in an uncontained engine failure, inflight engine shutdown, or damage to the rotorcraft.
AD 95-10-11 · published May 16, 1995, effective May 31, 1995
General Electric Company Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This action requires an initial and repetitive brake holding torque check of the fan reverser center drive unit (CDU), visual inspection of the translating cowl inner bondment seal, and functional check of the translating cowl auto re-stow system. This action also requires removal and replacement of certain CDU's as a terminating action to the repetitive check and inspection program. This amendment is prompted by a report of a CDU not able to hold the fan reverser translating cowl at the required position when manually driven to its stow position during routine maintenance. The actions specified in this AD are intended to prevent the loss of the CDU's brake holding feature, which could result in possible movement of the fan reverser translating cowl towards the deploy position in flight.
AD 95-11-01 · published May 22, 1995, effective Jun 21, 1995
Turbomeca S.A. Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Turbomeca Arriel 1 series turboshaft engines, that currently requires repetitive checks for engine rubbing noise during gas generator shutdown, and for free rotation of the gas generator by rotating the compressor manually after the last flight of the day. This amendment continues to require these checks, but eliminates the reference to the Turbomeca service bulletin, allows the pilot to perform all the checks required in this AD, clarifies the inspection interval requirement for daily checks, and specifies terminating action for the repetitive checks required by this AD. In addition, this AD allows the check for engine rubbing noise to be performed during engine motoring, and specifies that the engine turbine (T4) temperature must be below 150 degrees Centigrade when performing the check for free rotation. This amendment is prompted by comments submitted by operators of the affected enginesin response to the existing AD and the availability of an improved design 2nd stage nozzle guide vane. The actions specified by this AD are intended to prevent engine failure due to rubbing of the 2nd stage turbine disk on the 2nd stage turbine nozzle guide vane, which could result in complete engine failure and damage to the aircraft.
AD 95-09-08 · published May 4, 1995, effective May 19, 1995
McCauley Propeller Systems Propellers
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.
AD 95-11-08 · published May 26, 1995, effective Jun 12, 1995
Hartzell Propeller Inc. Models HC-92WK- ( ) and HC-92ZK-( ) Propellers
This amendment supersedes airworthiness directive (AD) 73-02- 01, applicable to Hartzell Propeller Inc. Models HC-92WK-( ) and HC- 92ZK-( ) propellers, that currently requires visual and penetrant inspections of the propeller blade shank area for corrosion at 1,000 hour time in service (TIS) intervals and shotpeening after inspection. This amendment requires a one-time inspection of the blade clamp screws, then a dye penetrant inspection, compressive rolling of the blade shank, and replacement of blade clamp screws, all to be accomplished at intervals of 500 hours TIS. This amendment is prompted by reports of two recent propeller blade separations that occurred at less than 1,000 hours TIS since last inspection. The actions specified by this AD are intended to prevent propeller blade separation, which could result in loss of control of the aircraft.
AD 95-09-11 · published May 8, 1995, effective Jun 9, 1995
Schempp-Hirth Flugzeugbau GmbH Gliders
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.
AD 95-09-12 · published May 8, 1995, effective Jun 9, 1995
Alexander Schleicher GmbH & Co. Gliders
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.
