36 Airworthiness Directives: 28 airplane, 4 rotorcraft, 2 engine, 2 glider.
AD 2000-26-13 · published Jan 2, 2001, effective Jan 17, 2001
Dornier Model 328-300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-300 series airplanes. This action requires inspections of all three hydraulic accumulators for signs of leaks, corrective actions if necessary, and eventual installation of an additional locking device to secure the nuts in the hydraulic accumulators, which will terminate the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is necessary to prevent possible loss of one or more of the hydraulic accumulators, which could result in a complete loss of the hydraulic system and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2000-26-15 · published Jan 2, 2001, effective Jan 17, 2001
The Boeing Company Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires deactivation of the map light assemblies; or modification and reidentification of the insulation blankets adjacent to certain map light assemblies, if applicable, a general visual inspection to detect damage of the Captain, First Officer, and Right Observer map light assemblies, and follow-on actions. This amendment is prompted by the FAA's determination that certain airplanes equipped with reading light assemblies in the crew rest area are subject to the identified unsafe condition. For certain airplanes, this amendment requires deactivation of the reading light assemblies, or an inspection to detect damage of the reading light assemblies, and follow-on or corrective actions, as applicable. The actions specified in this AD are intended to detect any broken light bulb housing, which could expose the power contactor. An exposed power contactor could cause the Captain, First Officer, or Right Observer map light or reading light in the crew rest area to short or overheat, which could result in smoke or fire in the cockpit.
AD 2000-26-07 · published Jan 3, 2001, effective Feb 7, 2001
British Aerospace Model BAe 146 and Model Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the BAe/Avro 146 Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement actions. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-26-08 · published Jan 3, 2001, effective Feb 7, 2001
British Aerospace (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the British Aerospace J41 Aircraft Maintenance Manual. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-26-09 · published Jan 3, 2001, effective Feb 7, 2001
Dornier Model 328-100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of new revisions to the Dornier 328 Airworthiness Limitations Document. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-26-10 · published Jan 3, 2001, effective Feb 7, 2001
BAe Systems (Operations) Limited Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAe Systems (Operations) Limited Model ATP airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the British Aerospace ATP Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement action. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
AD 2000-26-14 · published Jan 5, 2001, effective Feb 9, 2001
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires repetitive detailed visual inspections to detect cracks propagating from the fastener holes that attach the left-and right-hand pick-up angles at frame 40 to the wing lower skin and fuselage panel, and corrective actions, if necessary. The actions specified by this AD are intended to prevent reduced structural integrity of the airplane due to fatigue damage and consequent cracking of the pick-up angles at frame 40. This action is intended to address the identified unsafe condition.
AD 2000-26-16 · published Jan 8, 2001, effective Feb 16, 2001
Raytheon Aircraft Company Beech Models A36, B36TC, and 58 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, and 58 airplanes. This AD requires you to inspect for missing rivets on the right hand side of the fuselage and, if necessary, install rivets. Raytheon has identified several instances of missing rivets on these airplanes. The actions specified by this AD are intended to install missing rivets in the right hand fuselage panel assembly in the area above the right wing and below the cabin door threshold. These rivets must be present for the fuselage to carry the ultimate load and prevent critical structural failure with loss of airplane control.
AD 2000-26-17 · published Jan 8, 2001, effective Feb 24, 2001
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with a certain windshield configuration. This AD requires you to incorporate pilot's operating handbook (POH) information that prohibits the operation of the windshield heating system in the "LIGHT" mode, and requires you to modify the windshield deicing system wiring and circuit breakers. You can remove the POH information after accomplishing the modification. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent loss of electrical power to the windshield deicing system due to operation in the "LIGHT" mode, which could result in icing of the windshield and loss of control of the airplane.
AD 2000-26-20 · published Jan 10, 2001, effective Feb 14, 2001
Gulfstream Model G-1159A (G-III) Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-1159A (G-III) series airplanes, that requires modification of the master caution panel by installing an additional legend labeled "BATT ON BUS" and associated wiring to indicate when the airplane batteries are powering the direct current (DC) essential bus. This action is necessary to ensure that the flight crew is aware that an electrical system failure has occurred and that the main airplane batteries are powering the essential DC bus. If the flight crew is unaware of this situation, action to stop the depletion of the airplane batteries will not be taken and critical equipment, such as communications and navigation equipment, could fail. This action is intended to address the identified unsafe condition.
AD 2000-26-19 · published Jan 11, 2001, effective Feb 2, 2001
SOCATA-Groupe AEROSPATIALE Model TBM 700 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA--Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires you to inspect for a low point in the fuel tank air vent valve hose; and reroute the hose as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent in-flight damage to the wing skins caused by abnormal venting conditions of the wing fuel tank, which could result in severe handling problems or reduced structural capability. Continued operation with such structural deformation or handling problems could result in loss of control of the airplane.
AD 2001-01-02 · published Jan 17, 2001, effective Mar 5, 2001
British Aerospace HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes that are equipped with certain nose landing gear units. This AD requires you to inspect the steering jack assembly to assure proper clearance between the bush heads on the steering plates and the shim on the steering jack trunnions and to assure that there is adequate lubrication at both trunnions and the eye end fitting. This AD also requires you to adjust the clearance and provide adequate lubrication, as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent cracked steering jack piston rods caused by inadequate clearance or inadequate lubrication of the steering jack pivot points. The condition could result in failure of the nose wheel steering system with consequent loss of airplane control.
AD 2001-01-03 · published Jan 18, 2001, effective Feb 24, 2001
British Aerospace HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires you to remove the nose landing gear steering actuator and install one that incorporates a modified piston rod. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the nose landing gear steering actuator because of problems with the current design piston rod. Continued operation with the current design piston rod could result in loss of nose wheel steering and possible loss of control of the airplane during takeoff, landing, and taxi operations.
AD 2001-01-05 · published Jan 18, 2001, effective Feb 22, 2001
Dassault Model Falcon 10 and Model Mystere-Falcon 50 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 10 and Model Mystere-Falcon 50 series airplanes. For certain airplanes, this amendment requires modification of the aircraft wiring to illuminate the "T/O CONFIG" red warning light on the cockpit warning panel. For certain other airplanes, this amendment requires installation of a "NO TAKEOFF" red light on each pilot's instrument panel; modification of the associated aircraft wiring to activate the lights whenever the aircraft is not in the proper configuration for takeoff; and a revision to the Airplane Flight Manual to check that the "NO TAKEOFF" lights are out prior to takeoff. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent takeoff with the parking brake engaged, which could result in an extended takeoff roll or a rejected takeoff, and consequent runway overrun.
AD 2001-01-06 · published Jan 18, 2001, effective Feb 22, 2001
Airbus Model A300 B2 and A300 B4 (A300); Model A300 B4-600, A300 B4-600R, and A300 F4-600R (A300-600); and Model A310 Series Airplanes; Equipped With Dowty Ram Air Turbines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes; equipped with Dowty ram air turbines (RAT). That AD currently requires repetitive deployment tests of the RAT and checks of the adjustment of the locking rod. This amendment also requires modification of the RAT, which terminates the repetitive tests and checks. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure the availability of the RAT in case of need.
AD 2001-01-08 · published Jan 18, 2001, effective Feb 22, 2001
BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires inspection for cracking of the mounting brackets of the hydraulic hand pump at the frame attachment flanges, replacement of any cracked bracket with a new bracket, replacement of all bolts and nuts with new bolts and nuts, and installation of a particular "D" packer. The actions specified by this AD are intended to prevent failure of these brackets, which could result in inability to extend the landing gear in an emergency situation where the main hydraulic system is lost. This action is intended to address the identified unsafe condition.
AD 2001-01-09 · published Jan 18, 2001, effective Feb 2, 2001
Airbus Model A330-301, -321, and -322 Series Airplanes; and Model A340-211, -212, -213, -311, -312, and -313 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A330-301, -321, and -322 series airplanes; and Model A340-211, -212, -213, -311, -312, and -313 series airplanes. The existing AD requires repetitive replacements of the yaw damper actuator installed on active position with a new or overhauled actuator. This action adds a requirement, for certain airplanes, to install upgraded flight control primary computers, which terminates the requirement for the repetitive actuator replacements for those airplanes. This action is necessary to prevent hydraulic leakage from the yaw damper actuator installed on active position, due to premature wear of the dynamic seals between the actuator piston and the piston bearing. Hydraulic leakage could lead to the complete loss of the green hydraulic circuit, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-01-10 · published Jan 22, 2001, effective Feb 6, 2001
Boeing Model 747-400, 747-400F, 767-200, and 767-300 Series Airplanes Equipped With Pratt & Whitney Model PW4000 Series Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-400, 747-400F, 767-200, and 767- 300 series airplanes equipped with Pratt & Whitney Model PW4000 series engines. This action requires revising the Airplane Flight Manual (AFM). This action is necessary to prevent reduced acceleration and climb performance relative to performance data 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 2001-02-02 · published Jan 22, 2001, effective Feb 6, 2001
Bombardier Model DHC-8-200, and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model DHC-8-200, and -300 series airplanes. This action requires repetitive inspections to detect chafing or arcing damage to the cable/wire and fuel tube assemblies on the right hand side of each engine, and replacement with new components, if necessary. This action also provides an optional terminating action for the repetitive inspections required by this AD. This action is necessary to prevent chafing of the cable/wire bundles against the fuel line, which could result in arcing and a consequent fire or explosion. This action is intended to address the identified unsafe condition.
AD 2001-01-12 · published Jan 24, 2001, effective Feb 28, 2001
Construcciones Aeronauticas, S.A. (CASA), Model CN-235, CN-235-100, and CN-235-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to to all CASA Model CN-235, CN-235-100, and CN-235-200 series airplanes, that requires replacing the upper brackets in frames 33, 34, and 35, with improved brackets that are more fatigue resistant, and reinforcing frame 35. The actions specified by this AD are intended to prevent fatigue cracking in the zone of the fittings connecting the fuselage to stiffener rods located in frames 33, 34, and 35, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-01-13 · published Jan 24, 2001, effective Feb 28, 2001
Boeing Model 737-300, -400, and -500 Series Airplanes
This amendment adopts a new airworthiness directive (AD); applicable to all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires, among other actions, a one-time detailed visual inspection of the fuel quantity indicating system (FQIS) wiring and fuel tubing on the inboard side of the right wing rib wing buttock line (WBL) 227 and on the aft side of stringer No. 13 to determine if clearance exists between the FQIS wire harness and the refuel tube and tube coupling, and to detect any loose or broken refuel tube clamp or bracket or chafing of the FQIS wire harness; and corrective actions, if necessary. This action is necessary to detect and correct chafing and to prevent electrical contact between the FQIS wiring and the surrounding structure, which, in conjunction with another wiring failure outside the fuel tank, could result in fire or explosion of the fuel tank. This action is intended to address the identified unsafe condition.
AD 2001-02-01 · published Jan 24, 2001, effective Feb 28, 2001
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, that requires repetitive inspections to detect cracking of certain areas of the forward pressure bulkhead, and repair, if necessary. This amendment also requires certain preventive modifications, which, when accomplished, terminate the repetitive inspections for the affected areas. This action is necessary to prevent fatigue cracking on critical areas of the forward pressure bulkhead, which could result in rapid decompression of the airplane fuselage. This action is intended to address the identified unsafe condition.
AD 2001-02-04 · published Jan 29, 2001, effective Mar 13, 2001
Pilatus Aircraft LTD Model PC-6 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft LTD (Pilatus) Model PC-6 airplanes that are equipped with a certain stabilizer trim actuator. This AD requires you to inspect the lower lug of the actuator for cracks, damage, or distortion; verify that the staked bearing is correctly installed in the bore of the lug; and repair any cracked, damaged, or distorted parts and reassemble any incorrectly installed staked bearing, as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to detect and correct damage, distortion, or cracks in the lower lug assembly, which could result in failure of the lower lug. Such failure could lead to loss of the stabilizer trim actuator with consequent loss of control of the airplane.
AD 2001-02-05 · published Jan 29, 2001, effective Mar 5, 2001
CL-604 Variant of Bombardier Model Canadair CL-600-2B16 Series Airplanes Modified in Accordance With Supplemental Type Certificate SA8060NM-D, SA8072NM-D, or SA8086NM-D
This amendment supersedes an existing airworthiness directive (AD), applicable to Model CL-604 variant of Bombardier Model Canadair CL-600-2B16 series airplanes modified in accordance with certain Supplemental Type Certificates, that currently requires that the fuel service panel maintenance light on the fuel service panel be disconnected. This amendment requires modification of the wiring of the fuel port flood light (which is the name given to the fuel service panel maintenance light in the service bulletin that describes the wiring modification). This amendment is prompted by a report indicating that an electrical spark was noted when the fuel cap chain contacted the fuel port flood light housing of the fuel service panel. The actions specified by this AD are intended to prevent electrical sparks from a grounded object from coming into contact with the fuel port flood light housing of the fuel service panel, which could result in a fuel fire due to the proximity of the fuel service panel to the fuel port.
AD 2001-02-06 · published Jan 29, 2001, effective Mar 5, 2001
Empresa Brasileira de Aeronautica, S.A. (EMBRAER), Model EMB-120 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the ice protection systems and to add information regarding operation in icing conditions; installing an ice detector system; and revising the AFM to include procedures for testing system integrity. This amendment requires installing the ice detector system in accordance with revised procedures. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to ensure that the flightcrew is able to recognize the formation of significant ice accretion and take appropriate action; such formation of ice could result in reduced controllability of the airplane in normal icing conditions.
AD 2001-02-07 · published Jan 29, 2001, effective Mar 5, 2001
Boeing Model 767 Series Airplanes Powered by Pratt & Whitney Engines
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by Pratt & Whitney engines, that requires modification of the nacelle strut and wing structure. The actions specified by this AD are intended to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut.
AD 2001-02-09 · published Jan 29, 2001, effective Mar 5, 2001
Boeing Model 757-200 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently 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. That AD also provides for an optional terminating action for the repetitive inspections. This amendment adds inspections to detect additional cracking of the fastener holes in the lower spar chord. This amendment also adds an optional terminating modification. This amendment is prompted by the issuance of new service information. The actions specified by this AD are intended to detect and correct fatigue cracking in the lower spar chord, which could result in reduced structural integrity of the engine strut.
AD 2001-02-08 · published Jan 30, 2001, effective Feb 20, 2001
Short Brothers Model SD3-60 SHERPA, SD3-SHERPA, SD3-30, and SD3-60 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA, SD3-SHERPA, SD3- 30, and SD3-60 series airplanes, that requires replacement of the existing pneumatic de-icing boot pressure indicator switch with a newly designed switch. This amendment is prompted by an occurrence on a similar airplane model in which the pneumatic de-icing boot indication light may have provided the flightcrew with misleading information as to the proper functioning of the de-icing boots. The actions specified by this AD are intended to prevent ice accumulation on the airplane leading edges, which could reduce controllability of the airplane.
AD 2000-26-12 · published Jan 2, 2001, effective Feb 6, 2001
Eurocopter Deutschland GmbH Model EC135 P1 and EC135 T1 Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and EC135 T1 helicopters that requires inspecting the hydraulic line shielding hose (hose), replacing any unairworthy hose with an airworthy hose, and installing a nylon cable tie. This amendment is prompted by the tail rotor drive shaft Thomas coupling contacting and chafing the hose that shields the fenestron tail rotor hydraulic lines. The actions specified by this AD are intended to prevent damage to the hose, leaking of accumulated hydraulic fluid to an area with an ignition source, inflight fire, and subsequent loss of control of the helicopter.
AD 2001-01-04 · published Jan 18, 2001, effective Feb 2, 2001
Sikorsky Aircraft Corporation Model S-76A, S-76B, and S-76C Helicopters
This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters. This AD requires initial and repetitive inspections of the main landing gear positioning rod assembly (rod assembly) and the side brace rod end (rod end) for corrosion. If any corrosion is found, this AD requires replacing any part that is corroded with an airworthy part before further flight. This amendment is prompted by a landing gear collapse caused by corrosion due to dissimilar metals in the landing gear rod end. The actions specified in this AD are intended to detect corrosion of the threaded joint in the rod assembly to prevent a collapse of the landing gear, and subsequent loss of control of the helicopter during landing.
AD 2000-25-52 · published Jan 22, 2001, effective Feb 6, 2001
MD Helicopters, Inc. Model 369A, H, HE, HM, HS, D, E, FF, and 500N Helicopters
This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2000-25-52 which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model 369A, H, HE, HM, HS, D, E, FF, and 500N helicopters. This amendment supersedes an existing emergency AD that requires, before further flight, performing a tap inspection on both the upper and lower surfaces of each main rotor blade (blade). If any voids are detected that exceed specified inspection requirements, the emergency AD also requires replacing the unairworthy blade with an airworthy blade before further flight. This amendment requires the same actions as the emergency AD and corrects the applicability to include the appropriate serial numbers. This amendment is prompted by the discovery of an error in the emergency AD. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
AD 2000-26-06 · published Jan 22, 2001, effective Feb 26, 2001
Eurocopter Deutschland GMBH Model MBB-BK 117 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopters. That AD currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The actions specified by this AD are intended to prevent fatigue failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
AD 2001-01-01 · published Jan 16, 2001, effective Jan 31, 2001
BMW Rolls-Royce GmbH Models BR700-710A1-10 and BR700-710A2-20 Turbofan Engines.
This amendment adopts a new airworthiness directive (AD) that is applicable to BMW Rolls-Royce (RR) GmbH models BR700-710A1-10 and BR700-710A2-20 turbofan engines with oil filter differential pressure switch part number (P/N) 21SN04-419 or P/N 21SN04-431 installed. This action requires inspections of oil filter differential pressure switches, and replacement if necessary, in accordance with Rolls-Royce Service Bulletin No. SB-BR700-79-900215, Revision 2, dated August 2, 2000. This amendment is prompted by a report of severe engine oil loss, caused by oil leakage from a defective oil filter differential pressure switch. The actions specified in this AD are intended to prevent defective oil filter differential pressure switches from causing severe engine oil loss, resulting in in-flight shutdowns.
AD 2001-02-12 · published Jan 30, 2001, effective Feb 14, 2001
CFM International (CFMI) Model CFM56-7B Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFMI model CFM56-7B turbofan engines. This action requires a one-time on-wing torque inspection, and torque if needed, of all the PS3 pressure line fittings to insure proper torque. This amendment is prompted by service events which resulted in two in-flight shutdowns (IFSD's) and an aborted takeoff due to the disconnection of one of the PS3 line fittings. The actions specified in this AD are intended to prevent air leakage from incorrectly torqued fittings of the PS3 line, which could result in engine power loss.
AD 2000-26-18 · published Jan 10, 2001, effective Feb 2, 2001
Stemme GmbH & Co. KG Models S10 and S10-V Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires you to replace the eyebolts on the airbrake, inspect the airbrake sheets for proper clearance and adjust as necessary, and inspect for damage to the landing gear doors and replace any damaged parts. 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 prevent aerodynamic flutter of the upper covering straps on the airbrake cover caused by the current design airbrake eyebolts, which could result in damage to the airbrake system and landing gear doors. Continued operation with such damaged components could result in loss of control of the sailplane.
AD 2001-01-11 · published Jan 22, 2001, effective Mar 9, 2001
Rolladen Schneider Flugzeugbau GmbH Models LS 4 and LS 4a Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Rolladen Schneider Flugzeugbau GmbH (Rolladen Schneider) Models LS 4 and LS 4a sailplanes. This AD requires you to inspect the airbrake system for damage and proper rigging, with correction, repair, or replacement, as necessary. This AD also requires you to report any damage found to the Federal Aviation Administration (FAA). 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 damage to the airbrake locking bracket caused by asymmetric loads. This condition could result in the pilot's inability to operate the airbrake controls, with consequent loss of sailplane control.
