33 Airworthiness Directives: 18 airplane, 6 rotorcraft, 6 engine, 1 propeller, 2 glider.
AD 2001-04-08 · published Mar 5, 2001, effective Mar 20, 2001
Boeing Model 737-600, -700, -800, and -700C Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, -800, and -700C series airplanes. This action requires initial and repetitive inspections of the elevator tab assembly to detect any damage or discrepancy; and corrective actions, if necessary. This action is necessary to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-04-09 · published Mar 5, 2001, effective Mar 20, 2001
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires repetitive testing of the elevator control system to determine if an elevator power control actuator (PCA) is rigged incorrectly due to yielded or failed shear rivets in a bellcrank assembly for the elevator PCA, and follow-on actions, if necessary. This action is necessary to prevent continued operation with yielded or failed shear rivets in a bellcrank assembly for the elevator PCA, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-04-15 · published Mar 6, 2001, effective Mar 21, 2001
McDonnell Douglas Model DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8F-54, and DC-8F-55 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-8-31, DC-8-32, DC- 8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8F-54, and DC-8F-55 series airplanes. This action requires modification of the flow control system by rerouting the bleed air ducts to warm the pitot tube lines. This action is necessary to prevent the pitot lines from freezing, which could result in erroneous or total loss of airspeed indications to the flight crew, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-05-05 · published Mar 6, 2001, effective Mar 21, 2001
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires repetitive detailed visual inspections to find discrepancies of the installation of the midspar fuse pins of the inboard and outboard struts, and follow-on actions, if necessary. This action also provides for an optional terminating modification for the repetitive inspections. This action is necessary to find and fix discrepancies of the installation of the midspar fuse pins, which could result in loss of the secondary retention capability of the fuse pins, migration of the fuse pins, and consequent loss of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
AD 2001-05-02 · published Mar 12, 2001, effective Apr 27, 2001
Pilatus Aircraft Ltd. Model PC-7 Airplanes
This amendment supersedes Airworthiness Directive (AD) 98-08- 22, which currently requires inspecting the elevator and rudder attachment brackets for cracks and corrosion on certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes and replacing any cracked or corrosion-damaged parts. Since the issuance of AD 98-08-22, Pilatus has redesigned the brackets. Installation of these brackets should inhibit corrosion, which resulted in cracks or corrosion damage. This AD requires you to replace the elevator and rudder attachment brackets with parts of improved design. 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 failure of the elevator and rudder attachment brackets because of cracks or corrosion damage. Such failure could result in the elevator or rudder separating from the airplane with consequent loss of airplane control.
AD 2001-05-03 · published Mar 12, 2001, effective Apr 27, 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 apply Loctite on attaching bolt/ screw threads of inboard, central, and outboard carriages; increase tightening torques of associated hardware; and replace central carriage attaching bolts. 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 loose, or the loss of, flap attaching bolts/screws, which could cause rough or irregular control. Such rough or irregular control could lead to the loss of control of the airplane.
AD 2001-05-04 · published Mar 12, 2001, effective Apr 27, 2001
Piaggio Aero Industries S.p.A Model P-180 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Piaggio Aero Industries S.p.A (PIAGGIO) Model P-180 airplanes. This AD requires you to inspect the flap actuators for incorrect maneuvering and evidence of grease and oxidation around the gear box (actuators with any of these conditions are referred to as problem actuators). If you find a problem actuator, this AD requires you to immediately replace the flap actuators with improved design actuators or repair the existing actuators to the improved design level. If you do not find a problem actuator, this AD requires you to repeat the inspection until the installed actuators are of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to detect and remove problem flap actuators from service. Continued operation with problem actuators could result in flap system failure, with consequent reduction in, or loss of, control of the airplane.
AD 2001-05-10 · published Mar 21, 2001, effective Apr 25, 2001
McDonnell Douglas Model DC-10 and MD-11 Series Airplanes, and KC-10A (Military) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 and MD-11 series airplanes, and KC-10A (military) airplanes, that requires installation of thrust reverser interlocks on certain airplanes, inspections of the thrust reverser systems to detect discrepancies on certain other airplanes, and corrective actions, if necessary. This amendment is prompted by a determination that the current thrust reverser systems do not adequately preclude unwanted deployment of a thrust reverser. The actions specified by this AD are intended to prevent unwanted deployment of a thrust reverser, which could result in reduced controllability of the airplane.
AD 2001-06-02 · published Mar 23, 2001, effective Apr 27, 2001
McDonnell Douglas Model DC-8 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series -10 through -50, -61, -61F, -71, -71F airplanes, that currently requires a visual or eddy current inspection(s) of the left and right wing front spar lower caps to detect cracks migrating from attachment holes; and repair, if necessary. That AD also provides for an optional terminating modification of the front spar lower cap. This amendment is prompted by a report that additional cracking was found in the front spar lower cap of a wing. This amendment requires accomplishment of the previously optional terminating action. This amendment also expands the applicability of the existing AD to include additional airplanes and increases the interval for the repetitive eddy current inspections. The actions specified by this AD are intended to prevent reduced structural integrity of the left or right wing due to metal fatigue failure of the front spar lower cap.
AD 2001-06-03 · published Mar 23, 2001, effective Apr 9, 2001
Airbus Model A330-301, -321, -322 Series Airplanes; and Model A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330-301, -321, and -322 series airplanes, and all Model A340 series airplanes. This action requires replacing, with oversize fasteners, the interference fit fasteners between ribs 2 and 7 and between ribs 9 and 11; and reinforcing the cover plate of the torsion box of the aft passenger/crew doors. This action is necessary to prevent propagation of fatigue cracking of the top wing skin and the torsion box of the aft passenger/crew doors, which could lead to reduced structural capability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-06-04 · published Mar 23, 2001, effective Apr 9, 2001
McDonnell Douglas Model DC-8-33, -42, -55, and -61 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Model DC-8-33, -42, -55, and -61 series airplanes. This action requires detailed visual and eddy current inspections of the lower wing skin at the 3 outboard fasteners of stringer 64 end fitting to detect cracks; and corrective actions, if necessary. This action is necessary to prevent fatigue cracking of the lower wing skin, which could reduce structural integrity and loss of fail-safe capability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-06-07 · published Mar 23, 2001, effective Apr 9, 2001
Bombardier Model CL-600-2B19 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires a one-time inspection to find chafing or damage of the integrated drive generator cables of the cable harness assembly of the engines, and follow-on actions. This action is necessary to prevent such chafing or damage, which could result in electrical arcing between the cable and an engine cowl door, creating a possible ignition source and consequent fire and/or loss of electrical power on the airplane. This action is intended to address the identified unsafe condition.
AD 2001-06-08 · published Mar 23, 2001, effective Apr 9, 2001
Boeing Model 737-600, -700, and -800 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-600, -700, and -800 series airplanes. This action requires repetitive inspections of certain elevator hinge plates, and corrective action, if necessary. This action also provides for an optional replacement of the elevator hinge plates with new, improved hinge plates, which would end the repetitive inspections. This action is necessary to detect and correct fatigue cracking of the elevator hinge plates, which could lead to the loss of the attachment of the elevator to the horizontal stabilizer, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-06-05 · published Mar 28, 2001, effective May 11, 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 equipped with Option No. OPT 70-35-001 (gaseous oxygen system). This AD requires you to incorporate a modification that relocates the oil breather vent location. 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 oil from entering the gaseous oxygen system service compartment. Such oil contamination could result in a fire or explosion.
AD 2001-06-06 · published Mar 28, 2001, effective May 14, 2001
Cessna Aircraft Company Model 172RG Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Model 172 airplanes. This AD requires you to inspect the main landing gear pivot assemblies for cracks, replace any cracked main landing gear pivot assemblies, and install new bushings on the pivot assembly shaft. This AD is the result of many service difficulty reports of cracked main landing gear pivot assemblies on the affected airplanes. The actions specified by this AD are intended to detect, correct, and prevent future cracks on the original design landing gear pivots. Cracked main landing gear pivots could fail resulting in gear-up landings or loss of braking.
AD 2001-06-01 · published Mar 30, 2001, effective May 8, 2001
The New Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, PA-31-350, PA-31P, PA-31T, PA-31T1, PA-31T2, PA-31T3, and PA-31P-350 Airplanes
This amendment supersedes three existing airworthiness directives (AD's) that apply to certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31P, PA-31T, and PA-31T1 airplanes. These AD's currently require you to repetitively inspect and/or modify the elevator structure. This AD initially retains the inspection and modification requirements that are currently required; adds certain other airplane models to the AD applicability; and requires a modification at a certain time period, as terminating action for the currently required repetitive inspections. This action coincides with the Federal Aviation Administration's (FAA) policy of incorporating modifications, when available, that will terminate the need for repetitive inspections. The actions specified by this AD are intended to continue to detect and correct damage to the elevator structure. A damaged elevator structure could lead to reduced or loss of control of the airplane.
AD 2001-06-17 · published Mar 30, 2001, effective Apr 20, 2001
Cessna Aircraft Company Models 172R and 172S Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Models 172R and 172S airplanes. This AD requires a one-time inspection for proper engine idle speed and fuel control mixture setting and adjustment, as necessary. This AD also requires incorporating engine operating procedures into the pilots operating handbook (POH) and FAA-approved airplane flight manual (AFM). This AD is the result of reports of rough engine operation because of an over-rich fuel mixture (improper fuel flow settings). The actions specified by this AD are intended to detect and correct such improper fuel flow settings, which could result in rough engine operation or engine stoppage. This over-rich fuel mixture also contributes to the engine not restarting during flight when using published in-flight restart procedures.
AD 2001-06-18 · published Mar 30, 2001, effective Apr 16, 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. That AD also requires installing the ice detector system in accordance with revised procedures. That amendment was prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This amendment corrects and clarifies certain AFM procedures, and provides for an alternative AFM revision. 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 2001-04-12 · published Mar 5, 2001, effective Mar 20, 2001
Eurocopter France Model EC120B Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France Model EC120B helicopters. This action requires visually checking the engine to main gearbox coupling tube assembly (tube) for a crack and replacing any cracked tube. This amendment is prompted by a report of a crack detected on a tube. The actions specified by this AD are intended to prevent a tube failure, loss of engine drive, and a subsequent forced landing.
AD 2001-03-51 · published Mar 6, 2001, effective Mar 21, 2001
Sikorsky Aircraft Corporation Model S-76B and S-76C Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-03-51, which was sent previously to all known U.S. owners and operators of Sikorsky Aircraft Corporation (Sikorsky) Model S-76B and S-76C helicopters by individual letters. This AD requires, for certain main rotor shafts, initial and recurring fluorescent penetrant inspections. Replacing each affected main rotor shaft (shaft) on or before reaching 1,000 hours time-in- service (TIS) is also required. This amendment is prompted by four reports of shaft cracks. The actions specified by this AD are intended to prevent failure of the shaft and subsequent loss of control of the helicopter.
AD 2001-04-14 · published Mar 6, 2001
Eurocopter France Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Societe Nationale Industrielle Aerospatiale (currently Eurocopter France) Model AS350 and AS355 series helicopters that currently requires inspecting the fuselage frame (frame) for a crack at the fuselage-to-tailboom interface and replacing or repairing, as necessary. That AD also requires a fastener torque check and retorquing, as necessary. This amendment retains the requirements of the existing AD but would increase the inspection interval from 1,200 hours time-in-service (TIS) to 2,500 hours or 6 years TIS, whichever occurs first. This amendment revises the time interval for inspecting the frame at the fuselage-to-tailboom interface to coincide with the inspection interval specified in the maintenance manual. The actions specified by this AD are intended to eliminate confusion and unnecessary costs and to prevent a cracked frame, tailboom failure, and subsequent loss of control of the helicopter.
AD 2001-04-13 · published Mar 12, 2001, effective Apr 16, 2001
Eurocopter France Model SA.315B, SA.316B, SA.316C, SE.3160, and SA.319B Helicopters
This amendment supersedes an existing airworthiness directive (AD) for Eurocopter France (ECF) Model SA.315B, SA.316B, SA.316C, SE.3160, and SA.319B helicopters. That AD requires initial and recurring inspections of the main rotor blade (blade) spar for cracks. This amendment requires initial and recurring dye penetrant or eddy current inspections for a cracked blade spar at 100-hour time-in- service (TIS) intervals or 600 cycles, whichever occurs first, rather than the 25-hour TIS intervals currently required. This amendment is prompted by an accident in which an ECF Model SA.315B helicopter blade failed due to fatigue cracking. The actions specified by this AD are intended to prevent separation of a blade and subsequent loss of control of the helicopter.
AD 2000-25-08 · published Mar 20, 2001, effective Apr 24, 2001
Eurocopter France Model AS-350B, BA, B1, B2, and D; and AS-355E, F, F1, F2, and N Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model AS-350B, BA, B1, B2, and D; and AS-355E, F, F1, F2, and N helicopters. That AD currently requires inspecting the main gearbox suspension bi-directional cross beam (cross beam) for cracks, replacing the cross beam if a crack is found, and adding time intervals for repetitive dye-penetrant inspections on cross beams with 5,000 or more hours time-in-service (TIS). This amendment requires the same inspections as the existing AD but would delete repetitive dye-penetrant inspections on cross beams with 5,000 or more hours TIS. This amendment is prompted by the discovery that repetitive dye-penetrant inspections were erroneously required in the existing AD. The actions specified by this AD are intended to prevent failure of the cross beam that could lead to rotation of the main gearbox, severe vibrations, and a subsequent forced landing.
AD 2001-05-09 · published Mar 20, 2001, effective Apr 24, 2001
Bell Helicopter Textron Canada Model 430 Helicopters
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires modifying the electrical system. This amendment is prompted by the loss of electrical power due to design deficiencies discovered during single-pilot Instrument Flight Rules (IFR) flight testing. The actions specified by this AD are intended to prevent loss of electrical power and subsequent loss of control of the helicopter.
AD 2001-04-10 · published Mar 2, 2001, effective Apr 6, 2001
Pratt & Whitney Canada (PWC) Model PW305 and PW305A Turbofan Engines
This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney Canada (PWC) Models PW305 and PW305A turbofan engines, that requires removing stage 4 low pressure turbine (LPT) disks from service before exceeding new, lower cyclic life limits. This amendment is prompted by the results of a spin pit test analysis which indicate that the stage 4 LPT disk does not have full published life. The actions specified by this AD are intended to prevent LPT disk failure resulting from premature cracking of the LPT disks, which could result in an uncontained engine failure and damage to the airplane.
AD 2001-04-11 · published Mar 6, 2001, effective May 7, 2001
Pratt & Whitney Division Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney (PW) JT9D series turbofan engines. This amendment requires initial and repetitive detailed eddy current inspections for cracks in 1st stage high pressure turbine (HPT) disks, and, if necessary, replacement with serviceable parts. This amendment is prompted by the discovery of a crack in the web of one cooling air hole on a 1st stage HPT disk. The actions specified by this AD are intended to prevent 1st stage HPT disk cracking, which could result in an uncontained engine failure and damage to the aircraft.
AD 2001-04-16 · published Mar 6, 2001, effective Mar 21, 2001
General Electric Company CF6-50 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6-50 series turbofan engines. That AD currently requires visual inspection of the stage 2 low pressure turbine (LPT) nozzle lock assemblies, and replacement of the borescope plug with a new design plug. This amendment is prompted by a report of an uncontained engine failure on an engine that had complied with the current AD. This amendment requires additional inspections and provides interim and terminating corrective actions. The actions specified in this AD are intended to detect cracked, loose or missing stage 2 LPT nozzle lock assembly studs that could lead to failure of the locks, nozzle segment rotation, LPT case machining, and subsequent uncontained failure of the engine. The actions also provide for modifications of nozzle lock assemblies if the nozzle lock studs are found cracked, loose, or missing.
AD 2001-05-06 · published Mar 14, 2001, effective Mar 29, 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 turbofan engines with fan disk part numbers (P/N's) BRR18803, BRR19248, or BRR20791 installed, and BR700-710A2-20 turbofan engines with fan disks P/N's BRR19248 or BRR20791 installed. This action requires initial and repetitive inspections of these fan disks for cracks, and if necessary replacement with serviceable parts. This amendment is prompted by reports of cracks in several fan disks in the dovetail area. The actions specified in this AD are intended to detect cracks in the fan disk, that could result in an uncontained engine failure and damage to the airplane.
AD 2001-05-07 · published Mar 15, 2001, effective Mar 30, 2001
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment supersedes airworthiness directive (AD) 2000- 25-06, dated December 5, 2000, that is applicable to certain Pratt & Whitney (PW) PW4000 turbofan engines with the current design low pressure turbine (LPT) 4th stage air seal installed. That AD currently requires, based on engine model, replacement of the current design seal with a new design seal, or with a modified seal. This amendment adds the listing of certain engine serial numbers, to correct an error in the applicability section of AD 2000-25-06, for engines affected by PW Service Bulletin (SB) PW4 ENG 72-657, Revision 1, dated July, 19, 2000. This correction is prompted by comments received on AD 2000-25-06. The actions specified by this AD are intended to reduce stresses that could lead to LPT 4th stage air seal cracking, resulting in seal fracture, uncontained engine failure, and damage to the airplane.
AD 2001-06-09 · published Mar 27, 2001, effective May 1, 2001
General Electric Company CF6-80A3 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80A3 series turbofan engines, that currently requires initial and repetitive on- wing borescope inspections of the left hand aft engine mount link assembly for cracks, bearing migration, and bearing race rotation, and if necessary, replacement with serviceable parts. This AD requires initial and repetitive visual inspections of both left hand and right hand aft engine mount link assemblies for separations, cracks, and bearing race migration. Cracked or separated parts will have to be replaced prior to further flight. If spherical bearing race migration is discovered, a borescope inspection for cracks is also required. If no cracks are discovered by the additional borescope inspection, assemblies would have a 75-cycle grace period for remaining in service before replacement. Finally, installation of improved aft engine mount link assemblies will constitute terminating action to the inspections of this AD. This amendment is prompted by a recent analysis of internal bearing friction and bearing migration and inspections, which revealed migrated spherical bearing races on two CF6-80A3 series and ten CF6- 80C2 series aft engine mount links. The actions specified by this AD are intended to prevent aft engine mount link failure, which can result in adverse redistribution of the aft engine mount loads and possible aft engine mount system failure.
AD 99-18-18 R1 · published Mar 15, 2001, effective Apr 19, 2001
Dowty Aerospace Propellers Model R381/6-123-F/5 Propellers
This amendment revises an existing airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Model R381/6-123- F/5 propellers, that requires initial and repetitive visual and ultrasonic inspections of propeller blades for cracks across the camber face, and, if blades are found cracked, replacement with serviceable blades. This amendment is prompted by an engineering analysis of field service data and certification testing that indicate that the repetitive visual inspection interval can be safely increased and that the ultrasonic inspections can be eliminated. The actions specified in this proposed AD are intended to detect propeller blade cracks and propagation, which if not detected could result in propeller blade separation and possible aircraft loss of control.
AD 2001-05-01 · published Mar 12, 2001, effective Apr 27, 2001
DG Flugzeugbau GmbH Model DG-500MB Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain DG Flugzeugbau GmbH (DG Flugzeugbau) Model DG-500MB sailplanes equipped with a SOLO 2625 02 engine. This AD requires you to install additional access holes in the propeller mount and modify the engine. This AD also requires you to do a ground test run and replace the digital engine indicator circuit breaker. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Federal Republic of Germany. The actions specified by this AD are intended to correct an inadequate circuit breaker and unsatisfactory drive belt tension that could cause damage to the engine crankshaft. Such damage could lead to engine failure and loss of control of the sailplane.
AD 2001-05-08 · published Mar 23, 2001, effective Apr 13, 2001
VALENTIN GmbH Model 17E Sailplanes
This amendment adopts a new airworthiness directive (AD) that applies to all VALENTIN GmbH (Valentin) Model 17E sailplanes. This AD requires you to inspect for, and correct, cracked or improperly installed central wing bolts; install a stronger central bolt if not already installed; and inspect for, and replace, problem telescopic rods. 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 correct improperly installed or cracked central bolts and damaged, deformed, or loose telescopic rods. This condition, if not corrected, could cause the wing to separate from the sailplane, which could cause result in control of the sailplane.
