33 Airworthiness Directives: 22 airplane, 3 rotorcraft, 5 engine, 2 appliance, 1 glider.
AD 2001-09-01 · published May 2, 2001, effective Jun 6, 2001
Boeing Model 757-200 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -300 series airplanes, that requires repetitive clearing of the drain passage at the aft end of the main landing gear (MLG) truck beam to ensure moisture and contaminants within the truck beam can properly drain; and, for certain airplanes, an internal inspection of the truck beam to detect discrepancies, and follow-on actions. This amendment is prompted by reports of fracture of MLG truck beams. The actions specified by this AD are intended to prevent stress corrosion cracking, leading to fracture of a MLG truck beam during ground operations, which could result in either reduced controllability of the airplane or a fire.
AD 2001-09-02 · published May 2, 2001, effective Jun 6, 2001
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires replacement of certain existing bushings of the aft trunnion of the outer cylinder of the main landing gear (MLG) with new bushings, and replacement of grease in an undercut on the aft trunnion, if necessary. The actions specified by this AD are intended to prevent stress corrosion cracking and consequent fracture of the aft trunnion of the outer cylinder of the MLG, which could result in collapse of the MLG. This action is intended to address the identified unsafe condition.
AD 2001-09-03 · published May 2, 2001, effective May 17, 2001
Airbus Model A330 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Model A330 series airplanes. This action requires repetitive inspections of the spars, rib, and stringers in the vertical stabilizer spar box for failure of the bonds to the skin, and repair, if necessary. It also requires modification of the vertical stabilizer spar box by installation of fasteners to reinforce the bonds to the skin, which terminates the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information. This action is necessary to prevent failure of the bonds of the vertical stabilizer spar box to the skin, which could lead to reduced structural integrity of the spar box. It is intended to address the identified unsafe condition.
AD 2001-09-10 · published May 2, 2001, effective May 17, 2001
McDonnell Douglas Model MD-11 Series Airplanes Equipped With Pratt & Whitney Model PW4400 Series Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes equipped with Pratt & Whitney Model PW4400 series engines, that currently requires revising the Airplane Flight Manual (AFM) to advise the flight crew of applicable operational limits. This amendment corrects a typographical error in one paragraph of the existing AD that resulted in a reference to an incorrect engine fan blade which is not subject to the requirements of that paragraph. The actions specified in this AD are intended to ensure that the flight crew is informed of applicable limitations in airplane performance, and to prevent reduced acceleration and climb performance relative to performance data in the AFM, which could result in the airplane overrunning the end of the runway during takeoff or landing, or impacting obstacles or terrain. This action is intended to address the identified unsafe condition.
AD 2001-09-09 · published May 4, 2001, effective May 21, 2001
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to verify the proper configuration of the drive assemblies for the low-pressure and, for certain airplanes, the cross-feed fuel valves; and corrective action, if necessary. This action is necessary to prevent failure of the low- pressure and/or cross-feed fuel valves, which could result in the inability to shut off the fuel supply to the engine and exacerbate an engine fire, or the inability to cross-feed fuel when required. This action is intended to address the identified unsafe condition.
AD 2001-09-05 · published May 7, 2001, effective May 22, 2001
Airbus Model A310-324, A310-325, and A300 B4-622R Series Airplanes Equipped with Pratt & Whitney PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310-324, A310-325, and A300 B4- 622R series airplanes equipped with Pratt & Whitney PW4000 series engines. This action requires revising the Airplane Flight Manuals (AFM) for the Model A310 and Model A300-600 series airplanes. This action is necessary to prevent acceleration and climb performance less than that specified in the AFM, which could result in runway overruns or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.
AD 2001-09-08 · published May 7, 2001, effective Jun 11, 2001
Construcciones Aeronauticas, S.A. (CASA), Model CN-235 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires installing a second electrical connector in the electrical Master Central Unit. The actions specified by this AD are intended to prevent the loss of electrical power, other than that provided by the emergency system, in the event of disconnection of the single electrical connector within the electrical Master Central Unit. This action is intended to address the identified unsafe condition.
AD 2001-09-12 · published May 7, 2001, effective Jun 11, 2001
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100, -100C, and -200 series airplanes, that, for certain airplanes, requires a one-time inspection of certain fuselage circumferential skin joints to determine the type of fasteners installed, and replacement of any aluminum fasteners with steel fasteners, if necessary; or modification of certain fuselage circumferential skin joints; as applicable. For certain other airplanes, this amendment also requires repetitive inspections to detect corrosion, sealant deterioration, cracking, or disbonding; repair, if necessary; and modification of certain fuselage circumferential skin joints. This amendment is prompted by reports of corrosion between the body skins and cold-bonded doublers at the fuselage circumferential skin joints. The actions specified by this AD are intended to prevent delamination of the cold-bonded doublers, which could result in corrosion of the body skins and doublers, and consequent reduced structural capability of the fuselage circumferential skin joints.
AD 2001-09-13 · published May 9, 2001, effective May 24, 2001
Boeing Model 767-200, -300, and -300F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires inspections for fatigue cracking of the horizontal stabilizer pivot bulkhead, and repetitive inspections or other follow-on actions. This action also provides a permanent repair, which is optional for airplanes with no cracks, and, if accomplished, ends the repetitive inspections. This action is necessary to find and fix fatigue cracking of the horizontal stabilizer pivot bulkhead and adjacent structure, which could result in loss of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
AD 2001-09-14 · published May 10, 2001, effective May 25, 2001
Airbus Model A330-243, -341, -342, and -343 Series Airplanes Equipped With Rolls Royce Trent 700 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Airbus Model A330-243, -341, -342, and -343 series airplanes equipped with Rolls Royce Trent 700 series engines. This action requires repetitive inspections of certain components, and corrective action, if necessary. This action is necessary to detect and correct fatigue cracking of the hinge assemblies and the 12 o'clock beam structure of the thrust reverser C-duct, which could cause failure of the thrust reverser hinge, resulting in separation of the thrust reverser from the airplane. This action is intended to address the identified unsafe condition.
AD 2001-09-15 · published May 10, 2001, effective Jun 14, 2001
Boeing Model 737-200 and -300 Series Airplanes Equipped with Cargo Doors Installed in Accordance With Supplemental Type Certificate (STC) SA2969SO
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -300 series airplanes, that currently requires repetitive inspections to detect cracking in the radii on the support angles on the lower jamb (latch lug fittings) of the main deck cargo door, and replacement of cracked parts. This amendment adds a requirement for installation of redesigned lower jamb latch support angles in the main cargo door surround structure, which would terminate the repetitive inspections. This amendment is prompted by the development of a modification that will provide better protection of the subject area against effects of structural fatigue. The actions specified by this AD are intended to prevent in-flight separation of the main deck cargo door from the airplane due to fatigue cracking on the support angles on the lower door jamb.
AD 2001-09-16 · published May 10, 2001, effective Jun 29, 2001
Eagle Aircraft Pty. Ltd. Model 150B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Eagle Aircraft Pty. Ltd. (Eagle) Model 150B airplanes. This AD requires you to inspect the rudder cables for fraying, broken strands, etc. (referred to as damage), and replace any damaged cables. This AD also requires you to replace the rudder cable pulleys with larger diameter pulleys to eliminate the possibility of further damage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The actions specified by this AD are intended to detect and correct damaged rudder cables caused by chafing of the cable against the pulleys. Continued airplane operation with damaged cables could result in rudder cable system failure with possible loss of airplane control.
AD 2001-09-18 · published May 10, 2001, effective Jun 14, 2001
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires a one-time inspection to detect cracking of the main landing gear (MLG) pistons, and repair or replacement of the pistons with new or serviceable parts, if necessary. This amendment requires, among other actions, repetitive dye penetrant and magnetic particle inspections to detect cracks of the MLG pistons; repair and replacement of discrepant parts; and installation of a preventative modification; as applicable. This amendment also provides for an optional terminating action for certain MLG pistons. This amendment is prompted by additional reports of failure of the MLG pistons during towing of the airplanes. The actions specified by this AD are intended to prevent fatigue cracking of the MLG pistons, which could result in failure of the pistons and subsequent damage to the airplane structure or injury to airplane occupants.
AD 2001-10-01 · published May 11, 2001, effective May 29, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 series airplanes. This action requires revising the FAA-approved Airplane Flight Manual to prohibit in-flight auxiliary power unit (APU) starts, and installing a placard on or near the APU start/stop switch panel to provide such instructions to the flight crew. This action is necessary to prevent flame backflow into the APU compartment through the eductor during in-flight APU starts, which could result in fire in the APU compartment. This action is intended to address the identified unsafe condition.
AD 2001-10-02 · published May 15, 2001, effective May 30, 2001
Empresa Brasileira de Aeronautica, S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires applying torque to certain tubing fittings of the fire extinguishing systems of various areas of the airplane, and applying torque paint to the fittings. This action is necessary to ensure that certain tubing fittings of the fire extinguishing systems are properly torqued. Improperly torqued tubing fittings of the fire extinguishing systems of the baggage compartment, auxiliary power units (APU), and engines, if not corrected, could become loose and cause the fire extinguisher to inadvertently discharge. Inadvertent discharge of a fire extinguisher could result in reduced fire protection or the inability to extinguish a fire in the baggage compartment, APU, or engine. This action is intended to address the identified unsafe condition.
AD 2001-10-04 · published May 16, 2001, effective Jun 8, 2001
Air Tractor, Inc. AT-400, AT-500, and AT-800 Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 2000- 14-51, which requires inspection of the wing lower spar cap for cracks on Air Tractor, Inc. (Air Tractor) Models AT-501, AT-502, and AT-502A airplanes, and modification or replacement of any cracked wing lower spar cap. This AD lowers the safe life for the wing lower spar cap on Air Tractor AT-400, AT-500, and AT-800 series airplanes. This AD is the result of numerous reports of cracks in the \3/8\-inch bolthole of the wing lower spar cap on the affected airplanes. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the originally established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight.
AD 2001-10-05 · published May 18, 2001, effective Jun 22, 2001
Bombardier Model DHC-8-100, -200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires removing certain foam filters from the cabin ducting installation located below the dado panels on the left- and right-hand sides of the airplane. The actions specified by this AD are intended to prevent an increased risk of spreading a fire or failure of the cabin to pressurize adequately if certain foam filters are installed. This action is intended to address the identified unsafe condition.
AD 2001-10-10 · published May 24, 2001, effective Jun 8, 2001
McDonnell Douglas Model DC-9-81, -82, -83, and -87 Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, and Model MD-88 airplanes. This action requires an inspection of the wiring of the primary and alternate static port heaters for chafing, loose connections, and evidence of arcing, and to determine what type of insulation blanket is installed in the area of the static port heaters; and corrective actions, if necessary. This action is necessary to ensure that insulation blankets constructed of metallized Mylar<SUP>TM</SUP> are removed or protected from the area of the static port heater. Such insulation blankets could propagate a small fire that is the result of an electrical short of the static port heater and could lead to a much larger fire and smoke in the cabin. This action is intended to address the identified unsafe condition.
AD 2001-10-11 · published May 24, 2001, effective Jun 8, 2001
McDonnell Douglas Model MD-90-30 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-90-30 series airplanes. This action requires an inspection of the wiring of the primary and alternate static port heaters for chafing, loose connections, and evidence of arcing, and to determine what type of insulation blanket is installed in the area of the static port heaters; and corrective actions, if necessary. This action is necessary to ensure that insulation blankets constructed of metallized Mylar<SUP>TM</SUP> are removed or protected from the area of the static port heater. Such insulation blankets could propagate a small fire that is the result of an electrical short of the static port heater and could lead to a much larger fire and smoke in the cabin. This action is intended to address the identified unsafe condition.
AD 2001-10-14 · published May 24, 2001, effective Jun 8, 2001
Boeing Model 737, 747, 757, 767, and 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737, 747, 757, 767, and 777 series airplanes. This action requires repetitive inspections of any chemical oxygen generators and/or passenger, attendant, or lavatory service unit assemblies of the passenger oxygen system that have been replaced, to verify correct installation of the release pin in the generator firing mechanism of the oxygen generator; and corrective action, if necessary. This action is necessary to find and fix incorrect installation of the release pin in the generator firing mechanism, which could result in the unavailability of supplemental oxygen and possible incapacitation of passengers and cabin crew during an in-flight decompression. This action is intended to address the identified unsafe condition.
AD 2001-10-15 · published May 24, 2001, effective Jun 8, 2001
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 Series Airplanes
This document adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires a one-time inspection to detect incorrect wiring of electrical connectors to the pressure switches and cartridges on the fire extinguisher bottles for the engines and the auxiliary power unit (APU); disconnection and reconnection of the wiring, as necessary; and adjustment of the length of the harnesses on the fire extinguisher bottles to avoid future misconnections. This action is prompted by the issuance of mandatory continuing airworthiness information issued by a foreign civil airworthiness authority. This action is necessary to prevent the issuance of erroneous commands or the receipt of erroneous information pertaining to the fire extinguisher system for the engines and the APU, which could result in the inability to put out a fire in an engine or in the APU. This action is intended to address the identified unsafe condition.
AD 2001-11-01 · published May 31, 2001, effective Jul 5, 2001
McDonnell Douglas Model DC-9-32 Series Airplanes Modified Per Supplemental Type Certificate SA4371NM
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-32 series airplanes modified per Supplemental Type Certificate SA4371NM, that requires an inspection to determine if certain ground wires on the water heater of each lavatory are installed, and corrective action, if necessary. The actions specified by this AD are intended to detect improper grounding of a water heater, which, coupled with an internal short in the water heater, could result in heat or smoke damage or a fire on the airplane. This action is intended to address the identified unsafe condition.
AD 94-14-20 R1 · published May 4, 2001, effective Jun 8, 2001
Sikorsky Aircraft Corporation Model S-76A Helicopters
This amendment revises an existing airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A helicopters. That AD currently requires a one-time inspection of the tail rotor blade (blade) spar elliptical centering plug (centering plug) for disbonding and the addition of a retaining pad on the pitch change shaft between the output tail rotor gearbox flange and the inboard tail rotor spar. This amendment contains the same requirements as the existing AD but clarifies that the 500-hour time-in-service (TIS) repetitive inspections, which could cause inadvertent damage, are not required. This AD also incorporates by reference a revised alert service bulletin (ASB) that does not include the 500-hour TIS repetitive inspections. This amendment is prompted by operator confusion about whether the current AD continues to require the 500- hour TIS repetitive inspections. The actions specified by this AD are intended to verify that the FAA has determined that the 500-hour TIS repetitive inspections are not required to prevent the centering plug from disbonding and moving out of position, loss of tail rotor control, and subsequent loss of control of the helicopter.
AD 2001-09-11 · published May 7, 2001, effective Jun 11, 2001
Bell Helicopter Textron, Inc. Model 412 Helicopters and Agusta S.p.A. Model AB412 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to certain serial-numbered Bell Helicopter Textron, Inc. (Bell) Model 412 helicopters and Agusta S.p.A. (Agusta) Model AB412 helicopters. That AD currently requires a temporary reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required. This amendment requires the same actions as the previous AD but expands the applicability of the AD to all Bell Model 412, 412CF, 412EP, and Agusta Model AB412 helicopters. This amendment is prompted by the determination that the unsafe condition exists on all Bell Model 412 and all Agusta Model AB412 helicopters, regardless of serial number. The actions specified by this AD are intended to prevent static and dynamic overload damage to the yoke that could result in loss of the tail rotor and subsequent loss of control of the helicopter.
AD 2001-10-06 · published May 17, 2001
Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Sikorsky Aircraft Corporation (Sikorsky) Model S- 76A, S-76B, and S-76C helicopters and currently requires, before further flight, performing a fluorescent penetrant inspection (FPI) of the main rotor shaft assembly (shaft). Also, a recurring FPI and visual inspection for a cracked shaft are required by that AD. That AD also requires replacing the shaft with an airworthy shaft before further flight if a crack is found. This amendment requires replacing certain serial numbered shafts with an airworthy shaft before further flight. This amendment is prompted by further investigation and a determination that the inspections can be safely eliminated if certain serial- numbered shafts are removed from service before further flight. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
AD 2001-09-17 · published May 9, 2001, effective May 14, 2001
CFM International (CFMI) CFM56-5C Turbofan Engines
This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of CFMI CFM56-5C turbofan engines by individual letters. That action required within 10 days after receipt of that emergency AD, an initial inspection of the fuel manifold for wear or chafing; and an initial inspection of the CJ9L harness for correct installation, for clamp wear and to verify a minimum clearance between the CJ9L harness and the fuel manifold. That action also required repetitive inspections of the fuel manifold, clamps, and the CJ9L harness within every 500 hours time in service until new configuration clamps are installed on the harness. This amendment requires the same inspections, and adds inspection requirements for the manifold, clamps, and the CJ10L harness, and clamps on the other side of the engine. The actions specified in this AD are intended to prevent fuel leakage on the hot section or in the primary fire zone of the engine which may result in an engine fire and subsequent damage to the airplane.
AD 2000-03-03 R1 · published May 15, 2001, effective Jun 19, 2001
General Electric Company CF34 Series Turbofan Engines
This amendment revises an existing airworthiness directive (AD), applicable to General Electric Company CF34 series turbofan engines, that currently requires revisions to the Engine Maintenance Program specified in the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF34 series turbofan engines. Those revisions require enhanced inspection of selected critical life-limited parts at each piece-part exposure. The existing AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment removes inspection requirements for parts removed from engines mounted on-wing. This amendment is prompted by the high removal rate and subsequent piece-part exposure of fan disks due to certain maintenance procedures. This additional exposure has resulted in fan disk focused inspection rates that exceed the intent of the focused inspection initiative. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
AD 2001-10-03 · published May 16, 2001, effective May 31, 2001
General Electric Company CF34 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF34-1A, -3A, -3A1, - 3A2, -3B, and -3B1 turbofan engines. This action requires a one-time inspection, and if necessary replacement of certain fan disks for electrical arc-out indications, and assigns a reduction in the life limit of certain fan disks. This amendment is prompted by a report of a crack that was found during a visual inspection as part of routine engine maintenance. The actions specified in this AD are intended to prevent rupture of the fan disk due to cracks that initiate at an electrical arc-out, which could result in an uncontained failure of the engine.
AD 2001-10-07 · published May 18, 2001, effective Jun 18, 2001
General Electric Co. CF6-80C2 Turbofan Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Co. (GE) CF6-80C2 turbofan engines with certain stage 1 high pressure turbine (HPT) rotor disks installed. This amendment requires initial and repetitive inspections of certain HPT rotor disks for cracks in the bottom of the dovetail slot. This amendment is prompted by a report of an uncontained failure of an engine during a high-power ground run for maintenance. The actions specified by this AD are intended to detect cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.
AD 2001-10-12 · published May 23, 2001, effective Jun 7, 2001
General Electric Company Engines
This amendment supersedes an existing airworthiness directive (AD) that is applicable to GE Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines that currently requires removal of certain unapproved parts before further flight. This amendment requires removal of additional unapproved parts. This amendment is prompted by the discovery by the FAA of additional unapproved parts not listed in the original AD that have been introduced into the field and might be installed on the affected engines. The actions specified in this AD are intended to prevent the use of unapproved parts which could lead to an uncontained engine failure and damage to the airplane.
AD 2001-10-09 · published May 23, 2001, effective Jun 15, 2001
Honeywell KC 225 Automatic Flight Control Systems
This amendment adopts a new airworthiness directive (AD) that applies to certain Honeywell KC 225 automatic flight control systems (AFCS) that are installed on airplanes. This AD requires you to inspect the KC 225 AFCS to determine the computer modifications (Mods) that are incorporated, deactivate any units with only Mods 1 and/or 2 incorporated, and fabricate and install an appropriate placard if the unit is deactivated/inoperative. The AD would provide, as an alternative method of compliance, the option of installing a unit that incorporated MOD 3 or higher. This AD is the result of several reports that the AFCS is disconnecting without warning in a gross mistrim configuration. The actions specified by this AD are intended to prevent an undesirable autotrim command that the autopilot cannot detect in the required time. The airplane could then deviate from the selected altitude or the autopilot could disconnect without warning, which could result in heavy loads at the control column. Such loads in the pitch axis could result in loss of control of the airplane.
AD 2001-10-13 · published May 31, 2001, effective Jun 15, 2001
Britax Sell Gmbh & Co. OHG Water Boilers, Coffee Makers, and Beverage Makers
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Britax Sell Gmbh & Co. OHG water boilers, coffee makers, and beverage makers. This action requires inspecting the wiring for indications of overheating or electrical arcing, and if indications are found, replacing the wiring. This amendment is prompted by reports of discolored and partially melted wires. The actions specified in this amendment are intended to prevent a fire in the galley compartment due to inadequate crimping of the electrical terminal contact pins, which could result in smoke in the cockpit and cabin and loss of control of the airplane.
AD 2001-10-08 · published May 21, 2001, effective Jul 13, 2001
Rolladen Schneider Flugzeugbau GmbH Models LS 3, LS 4, and LS 6c Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Rolladen Schneider Flugzeugbau GmbH (Rolladen Schneider) Models LS 3, LS 4, and LS 6c sailplanes. This AD requires you to inspect the airbrake levers in the wing for lower end corrosion and for play in flight direction when fully extended and retracting under load; replace the bearings if there is jamming under load or if corrosion is found; and adjust the lower lever member (only for the Model LS 3). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct corrosion damage to the airbrake levers and bearings caused by collection of water in the airbrake boxes, not detected during postflight checks. This condition could result in the airbrakes locking in the extended position and a consequent off-field or short landing.
