36 Airworthiness Directives: 29 airplane, 2 rotorcraft, 4 engine, 1 glider.
AD 97-02-21 · published Mar 3, 1997, effective Mar 3, 1997
Embraer - Empresa Brasileira de Aeronautica S.A. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires repetitive inspections to detect cracks in the wing rib-to-skin support brackets (shear clips), and replacement of cracked brackets with new or serviceable brackets. This amendment also requires the eventual replacement of certain brackets with new brackets, which terminates the requirement for the inspections. This amendment is prompted by reports of cracks in certain wing rib-to-skin support brackets in both the lower and upper skin of the wings. The actions specified by this AD are intended to prevent cracking of those support brackets, which can subsequently lead to the loosening of the rivets in the wing skin, leakage of fuel through the rivet holes, and, ultimately, the reduction of the structural integrity of the wing.
AD 97-05-08 · published Mar 3, 1997, effective Mar 18, 1997
Boeing Model 727 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 727 series airplanes. This action requires repetitive pre-modification inspections to detect cracks in the forward support fitting of the number 1 and number 3 engines; and repair, if necessary. This AD also provides for an optional high frequency eddy current (HFEC) inspection, and, if possible, modification of the fastener holes; and various follow-on actions. Accomplishment of these optional actions would constitute terminating action for the repetitive pre-modification inspections. This amendment is prompted by reports indicating that fatigue cracks were found in the forward support fitting of the number 1 and number 3 engines. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in failure of the support fitting and consequent separation of the engine from the airplane.
AD 97-02-07 · published Mar 4, 1997, effective Mar 4, 1997
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to Airbus Model A300-600 and Model A310 series airplanes, that requires testing to verify if the smoke detection system can detect smoke within 60 seconds; and cleaning the installation and duct, if necessary. It also requires operators to submit a report of the test findings to the manufacturer. This amendment is prompted by a report that, during testing of the smoke detection system on in-service airplanes, the system failed to detect smoke within 60 seconds due to dust accumulation in the extraction ducts. The actions specified by this AD are intended to ensure that dust accumulation does not reduce the effectiveness of the smoke detection system and, consequently, lead to undetected smoke or fire in the lavatory of the airplane.
AD 97-02-18 · published Mar 4, 1997, effective Mar 4, 1997
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP airplanes, that requires repetitive inspections to detect damage of the antenna mounting reinforcing plates and surrounding fuselage skin. If any damage is detected, the AD requires replacement of the reinforcing plate with a new reinforcing plate and/or repair of the surrounding fuselage skin, which would terminate the repetitive inspection requirements. This amendment is prompted by reports of corrosion found at the antenna reinforcing plates, which was caused by the ingress of water at the plates. The actions specified by this AD are intended to prevent such corrosion, which could result in reduced structural integrity of the fuselage pressure vessel.
AD 97-02-20 · published Mar 4, 1997, effective Mar 4, 1997
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires a one-time inspection of the autopilot actuators on the pitch and yaw controls to ensure correct rigging, and re-rigging, if necessary. This amendment is prompted by a report of sudden pitch up of an airplane during cruise following disengagement of the autopilot; this condition was the result of incorrect rigging of the autopilot pitch actuator. The actions specified by this AD are intended to prevent incorrect rigging of the autopilot actuators on the pitch and yaw controls, which could result in reduced controllability of the airplane.
AD 97-05-10 · published Mar 4, 1997, effective Mar 19, 1997
Boeing Model 737 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737 series airplanes. This action requires removal of the main rudder power control unit (PCU) and replacement with a serviceable unit. This amendment is prompted by a report of the installation of an incorrect bolt on the main rudder PCU. The actions specified in this AD are intended to prevent cracking of the bearing of the main rudder PCU due to installation of an incorrect bolt; such cracking could result in seizure of the bearing and resultant uncommanded rudder movement.
AD 97-05-09 · published Mar 5, 1997, effective Apr 9, 1997
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires replacement of the flow restrictors of the aileron and elevator power control units (PCU's) with new flow restrictors. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent reduced roll and/or pitch rate control of the airplane and consequent increased pilot workload as a result of fragments from a deteriorated flow restrictor filter screen becoming lodged in the PCU.
AD 97-04-05 · published Mar 6, 1997, effective Mar 6, 1997
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires a one-time inspection of the airplane records to determine the modification status of the elevator trim servo, and, if necessary, inspections to determine the serial number of the servo, and repetitive inspections for looseness or movement of the motor housing of the servo. This action also requires replacement of certain elevator trim servos with a serviceable assembly. This amendment is prompted by reports of the motor housing separating from the elevator trim servo and the consequent release of certain component parts, due to inadequate locking of screws that were installed during assembly of the servos. The actions specified in this AD are intended to prevent the motor housing of the elevator trim servo from separating and releasing component parts that could lodge in and jam the elevator controls, and result in reduced pitch control of the airplane.
AD 97-04-02 · published Mar 10, 1997, effective Mar 10, 1997
Raytheon Aircraft Company Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-04-02, which was sent previously to known U.S. owners and operators of certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This AD requires installing new exterior operating instruction placards for the airstair door, cargo door, and emergency exits, as applicable. This AD results from an accident involving a Raytheon Model 1900C airplane that collided with another airplane while completing its landing roll. The ensuing fire destroyed both airplanes. The actions specified by this AD are intended to assure complete instructions are visible for opening the airstair door, cargo door, or emergency exits, which, if not visible or understandable, could result in the inability to open the airstair door, cargo door, or emergency exits during an emergency situation.
AD 97-04-14 · published Mar 10, 1997, effective Mar 10, 1997
ATR - GIE Avions de Transport R gional Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Aerospatiale Model ATR42-200, -300, and -320 series airplanes. This action requires modification of the electrical wiring of the stick pusher/shaker test function to reinforce system protection. This amendment is prompted by a report of at least one occurrence when the stick pusher self-activated during flight. The actions specified in this AD are intended to prevent inadvertent activation of the stick pusher, which could cause reduced controllability of the airplane, especially during takeoff or landing.
AD 97-03-08 · published Mar 11, 1997, effective Mar 11, 1997
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires repetitive inspections to detect cracking of the offset lightening hole on the drag brace of the left and right main landing gear (MLG); and replacement of these braces with braces having a centralized lightening hole. This replacement terminates the repetitive inspections. This amendment is prompted by a report indicating that fatigue cracking was detected on the upper link of a drag brace. The actions specified by this AD are intended to prevent fatigue cracking of the drag braces of the MLG, which, if not corrected, could cause the MLG to fail and, consequently, result in reduced controllability of the airplane during takeoff, landing, and taxiing.
AD 97-06-04 · published Mar 13, 1997, effective Mar 28, 1997
Boeing Model 757-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires inspections to detect cracking on the free edge of the tang, if necessary, and of the fastener holes in the lower spar chord; and various follow-on actions. This action also provides for optional terminating action for the requirements of this AD. This amendment is prompted by a report of fatigue cracking in the lower spar chord of two Model 757 series airplanes. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in reduced structural integrity of the engine strut.
AD 97-06-05 · published Mar 13, 1997, effective May 16, 1997
Alpha Aviation Concept Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Avions Pierre Robin Model R2160 airplanes. This action requires repetitively inspecting the weld area between the strut and the lower plate of the nose landing gear leg for cracks, and replacing the strut when cracks are found. The AD is the result of several reports of cracks in the weld securing the nose wheel steering bottom bracket to the nose landing gear leg on the affected airplanes. The actions specified by this AD are intended to prevent nose landing gear failure caused by cracks in the weld area between the strut and the lower plate of the nose landing gear leg, which could result in loss of control of the airplane during landing operations.
AD 97-06-06 · published Mar 13, 1997, effective May 9, 1997
Textron Aviation Inc. Airplanes
This amendment supersedes AD 92-27-10, which currently requires inspecting the pilot and copilot chairs to ensure that the locking pins will fully engage in the seat tracks on certain Raytheon Aircraft Company (Raytheon) 90, 99, 100, 200, and 1900 series airplanes (formerly referred to as Beech 90, 99, 100, 200, and 1900 series airplanes), and modifying any chair where the locking pin fails to fully engage or is misaligned. AD 92-27-10 resulted from reports of pilot and copilot chair locking pin malfunctions. Since issuance of that AD, the Federal Aviation Administration (FAA) has determined that additional airplanes should be subject to the pilot and copilot chair locking pin inspection and possible modification, and that the inspection should be accomplished in accordance with revised procedures. This AD retains the inspection and possible modification requirements of AD 92-27-10; incorporates additional airplanes into the applicability over that included in AD 92-27-10;and requires the inspection in accordance with revised service information. The actions specified by this AD are intended to prevent inadvertent movement of the pilot or copilot chair, which could result in loss of control of the airplane if it occurs during a critical flight maneuver.
AD 97-03-12 · published Mar 14, 1997, effective Mar 14, 1997
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires a one-time inspection for damage caused by arcing and overheating of the electrical ground posts ("earth posts") and ground cables for the direct current (DC) power generation and propeller de-icing systems of the left and right engines; and repair and replacement, if necessary. This amendment also requires the eventual replacement of earth posts with new posts. This amendment is prompted by reports indicating that earth posts on some airplanes have failed due to overheating. The actions specified by this AD are intended to prevent potential consequences of overheating, such as failure of the DC power generation and propeller de-icing systems.
AD 97-06-07 · published Mar 14, 1997, effective Apr 18, 1997
Dornier Model 328-100 Series Airplanes Equipped With Burns Aerospace Corporation Passenger Seats
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires modification of the restraining systems of certain passenger seats by replacing anchor point fasteners with fasteners that are able to withstand required 16g load conditions. This amendment is prompted by a report indicating that the restraining systems on these seats failed to meet 16g test load requirements during dynamic testing. The actions specified by this AD are intended to prevent the fasteners from failing, which could result in release of the seat restraint and consequent injury to passengers.
AD 97-06-08 · published Mar 17, 1997, effective Apr 21, 1997
de Havilland Model DHC-7 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires certain structural inspections, and repair, if necessary. This amendment is prompted by a structural re-evaluation, which identified certain significant structural items to inspect for fatigue cracking as these airplanes approach and exceed the manufacturer's original design life. The actions specified by this AD are intended to prevent fatigue cracking in these areas which, if not detected and corrected in a timely manner, could reduce the structural integrity of these airplanes.
AD 97-06-09 · published Mar 18, 1997, effective Apr 21, 1997
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes. This AD requires replacing certain aileron/rudder trim control modules with an improved module that contains an improved rudder trim switch that precludes the problems of sticking associated with the existing switch. This amendment is prompted by reports of sticking conditions in the rudder trim switch. The actions specified by this AD are intended to prevent such sticking, which could result in uncommanded movement of the rudder and consequent deviation of the airplane from its set course.
AD 97-06-12 · published Mar 18, 1997, effective Apr 21, 1997
BAE Systems (Operations) Limited Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that currently require inspections to detect cracking of the upper main fitting of the nose landing gear (NLG), and replacement or repair of cracked parts, if necessary. Those actions were prompted by reports of cracking in the main fittings of the NLG. This amendment requires that, for certain airplanes, the inspections be accomplished at reduced intervals. This amendment is prompted by the results of new analyses of the cracking that were conducted by the manufacturer of the NLG. The actions specified by this AD are intended to prevent failure of the main fitting, which could lead to collapse of the NLG during landing.
AD 97-03-09 · published Mar 19, 1997, effective Mar 19, 1997
Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires repetitive checks to detect backlash in the elevator mechanical control system, and various follow-on actions. This amendment also provides for an optional terminating action for the repetitive check requirements. This amendment is prompted by a report indicating that corrosion was found on the pivot bolts and bushings of the backlash remover lever mechanism on the elevator booster control unit (BCU) of a Model F28 Mark 0100 series airplane. The actions specified by this AD are intended to prevent such corrosion, which could result in backlash in the elevator controls and reduced elevator control authority in the manual mode.
AD 97-06-10 · published Mar 19, 1997, effective May 16, 1997
Raytheon Aircraft Company (Formerly Beech Aircraft Corporation) Model 76 Airplanes
This amendment supersedes Airworthiness Directive (AD) 91-14- 14, which currently requires repetitively inspecting the main landing gear (MLG) ``A'' frame assemblies for cracks on Raytheon Aircraft Company (Raytheon) Model 76 airplanes (formerly referred to as Beech Model 76 airplanes), and replacing any assembly found cracked. AD 91- 14-14 resulted from reports of fatigue cracks developing on the MLG ``A'' frame assemblies of the affected airplanes. Raytheon has developed improved design MLG ``A'' frame assemblies, and the Federal Aviation Administration (FAA) has determined that Model 76 airplanes with an improved design ``A'' frame assembly installed on both the left and right MLG should be exempt from AD 91-14-14. This action retains the requirement of repetitively inspecting the MLG ``A'' frame assemblies for cracks and replacing any cracked ``A'' frame assembly only for those Model 76 airplanes that do not have the improved design parts installed. The actions specified by this AD are intended to prevent MLG failure because of a cracked ``A'' frame assembly, which could result in loss of control of the airplane during landing operations.
AD 97-04-06 · published Mar 28, 1997, effective Mar 28, 1997
328 Support Services GmbH Airplanes
AD 97-04-07 · published Mar 28, 1997, effective Mar 28, 1997
Airbus Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that currently requires repetitive visual inspections and tap tests of the rudder skin panels to detect disbonding; and repairs, if necessary. That AD was prompted by reports of weakening of the bonding material between the core of the rudder and its inner and outer skin, and cracking of the core. This amendment adds repetitive elasticity laminate checker (ELCH) inspections of the rudder in place of the currently required tap tests. It also requires replacement of the rudder with a modified rudder, which will terminate the repetitive inspections. The actions specified by this AD are intended to detect and prevent disbonding of the rudder, which, if not corrected, could reduce the structural integrity of the rudder, and consequently lead to a reduction in its ability to sustain limit loads.
AD 97-04-08 · published Mar 28, 1997, effective Mar 28, 1997
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050, 100, 200, 300, 400, 600, and 700 series airplanes, that requires an ultrasonic inspection to determine if certain tubes are installed in the drag stay units of the main landing gear (MLG), and various follow-on actions. This amendment is prompted by a report that, due to fatigue cracking from an improperly machined radius of the inner tube, a drag stay broke, and, consequently, lead to the collapse of the MLG during landing. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity or collapse of the MLG.
AD 97-07-02 · published Mar 28, 1997, effective May 2, 1997
Airbus Model A300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. It requires a one-time template inspection of the rear pressure bulkhead to detect dents; repetitive eddy current inspections of dents greater than a certain depth to detect cracking; and repair, if necessary. This amendment is prompted by a report indicating that cracking has been found in the vicinity of a dent in the rear pressure bulkhead of one airplane. The actions specified by this amendment are intended to prevent fatigue cracking resulting from a dent in the rear pressure bulkhead; that condition, if not corrected, could reduce the structural integrity of the bulkhead and, consequently, lead to rapid depressurization of the airplane.
AD 97-07-03 · published Mar 28, 1997, effective May 15, 1997
Piper Aircraft Inc. Airplanes
This amendment supersedes Airworthiness Directive (AD) 81-11-04 that applies to The New Piper Aircraft, Inc. (Piper) Models PA31, PA31-300, PA31-325, and PA31-350 airplanes that have Cleveland nose wheel assembly part number (P/N) 40-76B installed. AD 81-11-04 currently requires inspecting the nose wheel flange for cracks. The repetitive inspections terminate by replacing the nose wheel assembly with Cleveland P/N 40-140, which is an improved design. This action is prompted by the lack of designation of Piper Model PA31P in the Applicability section of AD 81-11-04, and the subsequent failure of a nose wheel assembly on a Piper Model PA31P airplane during taxiing operations. The actions specified by this AD are intended to prevent the failure of the nose wheel, which if not corrected, could result in loss of control of the airplane during taxiing, take-off, or landing operations.
AD 97-04-17 · published Mar 31, 1997, effective Mar 31, 1997
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes, that requires inspections to detect leakage of hydraulic fluid from the lock jack assemblies of the main landing gear (MLG), and eventual replacement of those assemblies with new or serviceable assemblies. This amendment is prompted by reports of leakage of hydraulic fluid from lock jack assemblies due to a manufacturing forging defect that extends through the wall of the lock jack assembly. The actions specified by this AD are intended to prevent leakage of hydraulic fluid from the lock jack assemblies of the MLG, which, in conjunction with a hot brake, could cause a fire in the MLG bay.
AD 97-04-18 · published Mar 31, 1997, effective Mar 31, 1997
Fokker Services Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires repetitive x-ray inspections to detect cracks in stringers 4 through 7 of the lower skin of the wings, and modification or repair, if necessary. This amendment also requires modification of the stringers of the lower skin of the wings, which terminates the repetitive inspections. This amendment is prompted by reports of fatigue cracking found in stringers 4 through 7 of the lower skin of the wings. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the wings.
AD 97-05-06 · published Mar 3, 1997, effective Apr 7, 1997
Schweizer Aircraft Corporation Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269A-2, and 269B helicopters, that currently requires initial and repetitive inspections of the main rotor thrust bearing (bearing) for bearing rotational roughness, corrosion, inadequate lubrication, physical damage, or excessive zinc chromate paste or moisture. This amendment requires the same initial and repetitive inspections required by the existing AD, but would extend the retirement life for certain bearings, and would remove the Model 269A-2 helicopter from, and add the Model TH-55A helicopters to the applicability of this AD. This amendment is prompted by an FAA analysis of service information issued by the manufacturer that extends the retirement life for certain bearings. The actions specified by this AD are intended to prevent failure of the bearing, loss of the main rotor, and subsequent loss of control of the helicopter.
AD 97-06-02 · published Mar 12, 1997, effective Apr 16, 1997
Bell Helicopter Textron, Inc. Model 214B, 214B-1 and 214ST Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 214B-1, and 214ST helicopters, that currently establishes a retirement life of 40,000 high-power events for the lower planetary spider (spider). This amendment changes the method of calculating the retirement life for the spider from high-power events to a maximum accumulated Retirement Index Number (RIN) of 80,000, and makes this RIN applicable to an additional part-numbered spider. This amendment is prompted by fatigue analyses and tests that show certain spiders fail sooner than originally anticipated because of the unanticipated higher number of external load lifts and takeoffs (torque events) performed with those spiders, in addition to the time-in-service (TIS) accrued under other operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the spider, which could result in failure of the main transmission and subsequent loss of control of the helicopter.
AD 97-04-03 · published Mar 6, 1997, effective May 5, 1997
AlliedSignal Inc. TFE731 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that requires removal from service of certain first stage low pressure turbine (LPT) seal plates prior to accumulating the new, reduced cyclic life limit, and replacement with serviceable LPT seal plates. This amendment is prompted by a report that the machined LPT seal plate geometry did not meet the design intent due to drawing ambiguity. The actions specified by this AD are intended to prevent fatigue cracking and subsequent uncontained failure of an LPT seal plate.
AD 97-06-14 · published Mar 26, 1997, effective May 27, 1997
General Electric Aircraft Engines Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CF34 series turbofan engines, that reduces the allowable operating cyclic life limit for affected fan disks. This amendment is prompted by an updated stress and life analysis. The actions specified by this AD are intended to prevent fan disk rupture, engine failure, and damage to the aircraft.
AD 97-06-15 · published Mar 26, 1997, effective May 27, 1997
General Electric Company CF34 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CF34 series turbofan engines, that reduces the allowable operating cyclic life limit for affected high pressure compressor (HPC) stage 1 rotor disks. This amendment is prompted by an updated stress and life analysis. The actions specified by this AD are intended to prevent HPC stage 1 rotor disk rupture, engine failure, and damage to the aircraft.
AD 97-05-12 · published Mar 31, 1997, effective Apr 15, 1997
General Electric Aircraft Engines CT7 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Aircraft Engines (GE) CT7 series turboprop engines. This action requires eddy current inspection of disk holes of stage 1 and 2 gas generator turbine (GGT) disks for cracks, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a stage 2 GGT disk failure. The actions specified in this AD are intended to prevent a stage 1 or 2 GGT disk failure, which could result in an uncontained engine failure and damage to the aircraft.
AD 97-03-02 · published Mar 21, 1997, effective Mar 21, 1997
Glasflugel Gliders
This amendment adopts a new airworthiness directive (AD) that applies to Glasflugel Models H301 "Libelle", H301B "Libelle", Standard "Libelle", Standard Libelle 201B, Club Libelle 205, and Kestrel sailplanes. This AD requires measuring and adjusting the control surface weight and static moment, and inserting amendments into the Glasflugel Flight and Service Manual. This AD results from reports of considerable variation of the weight and static moment of the control surface on the affected sailplanes found during repair or repainting of the control surface. The actions specified by this AD are intended to prevent sailplane flutter because the weight and static moment of the control surface are not within certain limits, which could result in flutter and subsequent loss of control of the sailplane.
