Boeing DHC-7-102

Service difficulty reports · 246

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duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
  FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
  WHERE aircraft_model_key = 'DHC7102'
  ORDER BY difficulty_date DESC"

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SDR CA060504002Drive Assy · failedCLIMB TO FL 120, AT FL 085 COMMUNICATION ESTABLISHED WITH APPROACH, AND INSTRUCTED TO MAINTAIN FL 080. CAPT TOLD GO TO DESCENT AND MAINTAIN 080, AUTOPILOT WAS ENGAGED, CAPT REALIZED A/C WAS STILL CLIMBING AND THE WHEEL TRIM WAS TRIMMING FULL NOSE-UP, FO PUSHIMar 27, 2006 · Dhav DHC7102 · Elevator Control SystemSDR 2005FA0001475Engine · seizedENGINE INSTALLED ON AIRCRAFT AFTER RETURN FROM REPAIR FACILITY. DURING INITIAL GROUND RUN OF ENGINE THE POWER LEVER SEIZED AND VERY HARD TO MOVE. ENGINE TEMPERATURE AND PRESSURE WERE NORMAL. FEATHERED THE PROPELLER AND SHUTDOWN ENGINE. POST INSPECTION SHOWOct 25, 2005 · N34HG · Dhav DHC7102 · Engine (Turbine/Turboprop)SDR CA051027006Windshield · cracked(CAN) AC, WHILE IN LIGHT ICING CONDITIONS, ENCOUNTERED A MALFUNCTION OF CAPTAIN'S (LT SIDE) WINDSHIELD. ENTERING ICING CONDITIONS, NORMAL MODE WAS SELECTED. CAPTAIN NOTICED DISCOLORATION IN LWR PORTION OF WINDSHIELD, VERBALIZED IT TO F/O. CAPTAIN OBSERVED DISCOct 7, 2005 · Dhav DHC7102 · Flight Compartment WindowsSDR CA050120005Strut · broken(CAN) NLG HAD SEVERE SHIMMY, STEERING SYSTEM FAILURE UNCONTROLLED. B- MAINTENANCE FINDINGS: THE STEERING ACTUATOR MOUNTING PIN INTEGRATED ON THE INNER CYLINDER BODY FOUND COMPLETELY SHEARED OR RUPTURED. THE STEERING ACTUATOR FOUND LEAKING . TJan 18, 2005 · Dhav DHC7102 · Nose/Tail Landing GearSDR CA050527014Fuel Control · failedIN DESCENT, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUT DOWN IN FLIGHT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.Jan 17, 2005 · Dhav DHC7102 · Fuel Control/Turbine EnginesSDR CA041130003Bearing · failed(CAN) THE AIRCRAFT ON DEPARTURE RETRACT, THE GEAR WOULD NOT RETRACT. POSITION INDICATION LIGHTS REMAINED GREEN AND THE GEAR SELECTOR LEVER WAS ILLUMINATED AND REMAINED SO. NO CIRCUIT BREAKERS WERE TRIPPED ON THE FLIGHT DECK. THE AIRCRAFT LANDED WITHOUT INCIDENNov 12, 2004 · Dhav DHC7102 · Nose/Tail Landing Gear Strut/AxleSDR CA041013008Pump · failed(CAN) WHILE THE AIRCRAFT WAS IN CRUISE AT 15,000 FEET, NR 4 HYDRAULIC PUMP CAUTION LIGHT ILLUMINATED, FOLLOWED 5 MINUTES LATER BY NR 3 HYDRAULIC PUMP CAUTION LIGHT COMING ON. ALL HYDRAULIC PRESSURE WAS LOST ON NR 2 HYDRAULIC SYSTEM AND ALTERNATE LANDING GEAROct 5, 2004 · Dhav DHC7102 · Hydraulic Pump (Electric/Engine), MainSDR CA040713006Fcu · failed(CAN) AT CRUISE ALTITUDE AT FL110 ON A MEDEVAC FLIGHT DESCENT CHECKS WERE CARRIED OUT. AS TURBULENCE WAS EXPECTED A RATE OF 500 RPM AND SPEED OF 170 KIAS WAS BRIEFED AFTER DESCENT. CLEARANCE RECEIVED POWER LEVERS WERE PULLED BACK TO APPROX 3000 TORQUE. NR 3 EJun 20, 2004 · Dhav DHC7102 · Fuel Controlling SystemSDR CA040614008Circuit Breaker · failed(CAN) IN ORDER TO INSTALL A LIGHT ASSEMBLY IN THE NOSE COMPARTMENT THE L4 (CB) WAS PULLED IN THE COCKPIT. AFTER INSTALLATION WAS COMPLETED, CB WAS PUSHED BACK IN TO TEST SYSTEM, BY THE TIME THE INDIVIDUAL WALKED FROM THE COCKPIT BACK TO THE NOSE COMPARTMENT THJun 7, 2004 · Dhav DHC7102 · DC Power Distribution SystemSDR CA040316007Coupler · burned(CAN) HF SYS FAILED, SMOKE AND BURN SMELL CAME FROM HF PWR AMP/COUPLER. UNIT WAS REMOVED AND SENT FOR INSP. FOUND THAT HARDWARE ATTACHING COVER ON CONNECTOR J9524 TO FACEPLATE OF UNIT HAD CONTACTED PRINTED CIRCUIT BD AND SHORTED +28 VDC SUPPLY TO GROUND. ELEMar 4, 2004 · Dhav DHC7102 · HF Communications SystemSDR CA040302002Blade · separated(CAN) ON 2ND FLIGHT OF THE DAY, A SUDDEN PARTIAL POWER LOSS OCCURRED ON NR 1 ENGINE, A STRONG SMELL ACCOMPANIED THE POWER LOSS. ENGINE NR 1 WAS SUBSEQUENTLY SHUT DOWN. THE AIRCRAFT COMPLETED AN UNEVENTFUL UNSCHEDULED LANDING. UPON SUBSEQUENT INSPECTION IT WAFeb 21, 2004 · Dhav DHC7102 · Turbine Engine Compressor SectionSDR CA031223003Shaft · sheared(CAN) AFTER FLIGHT MAINTENANCE NOTICED AN OIL LEAK FROM THE NR 2 NACELLE, FURTHER INVESTIGATION FOUND THE NR 2 AC GENERATOR SHAFT SHEARED. THE FLIGHT CREW HAD NOT NOTICED ANY FAILURES SINCE IN THE NORMAL OPERATION MODE THIS AC GEN IS IN STANDBY AND ONLY WORKS Dec 22, 2003 · Dhav DHC7102 · AC Generator-AlternatorSDR CA031210003Oil Runner · loose(CAN) DURING THE UNSCHEDULED REMOVAL OF NR 2 PROP DUE TO OIL LEAKING FROM THE PROP SHAFT, IT WAS NOTICED THAT THE PROP SHAFT OIL RUNNER (PART OF THE POWER SECTION) WOULD ROTATE WITHOUT THE PROP SHAFT MOVING. INFORMED US THAT THIS IS AN INDICATION THAT BEARING Dec 6, 2003 · Dhav DHC7102 · Turbine SectionSDR CA031015015Brake Assy · leaking(CAN) BRAKE WAS SENT TO SHOP FOR WARRANTY REPAIR. SNAGGED AS LEAKING FROM PIN ON OCT 02, 2002. THE UNIT WAS REPAIRED AND RETURNED. BRAKE WAS INSTALLED ON 13 AUG 03, IT WORKED FOR 132.1 HOURS AND THEN STARTED TO LEAK FROM ONE OF THE PISTONS. THIS IS NOT THE FIROct 9, 2003 · Dhav DHC7102 · BrakeSDR CA030908008Shaft · sheared(CAN) SHORTLY AFTER TAKEOFF THE NR 3 DC GEN LIGHT CAME ON, THE SYSTEM WAS DEACTIVATED. AFTER ABOUT FIVE MINUTES THE NR 3 DC GEN HOT LIGHT CAME ON FOR ABOUT 20 SECONDS. FOR TROUBLESHOOTING WE ATTEMPTED TO START THE NR 3 ENG, WHICH KNOCKED THE GROUND POWER UNIT Sep 3, 2003 · Dhav DHC7102 · Starter-GeneratorSDR CA030908007Bearing · failed(CAN) TWO MIN AFTER TAKEOFF THE NR 3 DC STARTER-GEN FAILED, THE GENERATING SYSTEM WAS SHUTDOWN. MAINTENANCE FOUND THAT THE STARTER MODE FUNCTIONING OK. AFTER TROUBLESHOOTING THE STARTER-GENERATOR WAS REPLACED DUE TO HEAVY BRUSH WEAR AND THE BEARING WAS FAILINSep 3, 2003 · Dhav DHC7102 · Starter-GeneratorSDR CA030616004Solenoid · failed(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN ALL THREE GEAR STAYED UP AND LOCKED. AN EMERGENCY GEAR EXTENSION WAS COMPLETED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE JACKED THE AIRCRAFT AND ATTEMPTED TO COMPLETE GEAR SWINGS WHEN THEJun 13, 2003 · Dhav DHC7102 · Landing Gear SelectorSDR CA030609002Seal · swollen(CAN) WHILE REMOVING FUEL LIDS TO ACCESS FUEL TANKS FOR SNAG RECERTIFICATION FOLLOWING MAJOR INSPECTION, IT WAS NOTICED THAT THE NEW LIGHTNING SEAL P/N CVR 67 THAT WAS INSTALLED IN THE LAST WEEK OR TWO HAD SWOLLEN ALMOST 50 PERCENT LARGER THEN ITS NORMAL SIZE May 27, 2003 · Dhav DHC7102 · Wing, Plate/SkinSDR CA030514008Wire · broken(CAN) DURING HEAVY MAINT INSPECT FOUND TWO WIRES CHAFED & BROKEN AT DETERIORATED CLAMPS IN LOWER AFT FIREWALL AREA. RUBBER CUSHION HAD TORN AWAY ALLOWING METAL CLAMP TO WEAR WIRES. THESE WIRES ARE FOR FIRE LOOP SYSTEM ON NR 3 ENGINE, WHICH WAS WORKING WHEN AIRMay 13, 2003 · Dhav DHC7102 · Fire DetectionSDR CA030320001Line · chafed(CAN) AFTER FINDING THIS LINE CHAFED ON AN OTHER AIRCRAFT WE COMPLETED A SPECIAL INSPECTION. WE FOUND THAT THE DE-ICE LINE HAD BEEN CHAFING ON A HYDRAULIC LINE. THIS LINE IS LOCATED UNDER PANEL 419AT (NR 1 ENG BATMAN PANEL). THE LINE IS HIDDEN UNDER NUMEROUS Mar 18, 2003 · Dhav DHC7102 · Airfoil Anti/De-ice SystemSDR CA030314005Line · chafed(CAN) DURING TROUBLESHOOTING A DE-ICE SNAG, ( NR 1 ENG DE-ICE BOOT WILL NOT INFLATE ) IT WAS FOUND THAT THE DE-ICE LINE P/N 73010033-147 HAD BEEN CHAFFING ON A HYDRAULIC LINE. THIS LINE IS LOCATED UNDER PANEL 419AT (NR 1 ENG BATMAN PANEL). THE LINE IS HIDDEN UFeb 12, 2003 · Dhav DHC7102 · Airfoil Anti/De-ice SystemSDR CA020104020Spar Cap · chafed(CAN) DURING "C" CHECK AND CORROSION INSPECTION THE LT REAR SPAR CAP AND SPAR AREA ABOVE THE SPAR CAP WAS FOUND CHAFED. THE CHAFING WAS CAUSED BY SPIRAL WRAP WOUND AROUND A WIRE BUNDLE THAT RUNS ACROSS THE FACE OF THE REAR SPAR.Jan 4, 2002 · Dhav DHC7102 · Wing SparSDR CA011217015Boot · dislodged(CAN) THE AIRCRAFT WAS FERRYING BACK TO BASE. IN CRUISE THE FLT MECHANIC WHILE STANDING AT THE BACK BETWEEN THE GALLEY AND THE WASHROOM FELT A LOW FREQ VIBRATION ON THE FLOOR. THE VIBRATION WAS NOTICEABLE TO THE FLIGHT ATTENDANT ALSO. THE INFORMATION WAS RELAYNov 30, 2001 · Dhav DHC7102 · Air Intake Anti/De-Ice SystemSDR CA011121012Panel · separated(CAN) ON DESCENT, A LOUD BANG WAS HEARD, FOLLOWED SHORTLY THEREAFTER BY ANOTHER SMALLER ONE. THE FLIGHT CARRIED ON TO A NORMAL APPROACH AND LANDING WITHOUT FURTHER INCIDENT. UPON INSPECTION AFTER LANDING, THE CAPTAIN NOTED THE ARMPIT PANEL WAS MISSING FROM UNNov 8, 2001 · Dhav DHC7102 · Wing, Plate/SkinSDR 2001F00200Line · crackedFLT 1253 - HAV - AFTER TAKEOFF, AT 4,800 FEET, NR 4 ENGINE EXPERIENCED A POWER LOSS. PERFORMED ENGINE FAILURE IN FLIGHT CHECK LIST. REMOVED AND REPLACED NR 4 ENGINE P3 LINE. RAN ENGINE. OPERATIONAL CHECK NORMAL. (M)Jul 7, 2001 · N706GA · Dhav DHC7102 · Fuel Controlling SystemSDR CA010713003Nut · sheared(CAN) DURING SCHEDULED MAINTENANCE, FOUND THAT THE NR 4 STARTER/GENERATOR COULD ROTATE 1/4 TURN ON IT'S MOUNT. THE SELF LOCKING NUT ON THE CLAMP HAD NO FRICTION AND BACKED OFF. THE CLAMP WAS LOOSE. THE STARTER HAD SHEARED THE ALIGNMENT PIN. WE REPLACED THE NUTJun 29, 2001 · Dhav DHC7102 · Engine StarterSDR CA010529015Plate · cracked(CAN) DURING LPI OF BARREL PLATE IT FOUND TO HAVE A CRACK THAT GOES ACROSS PACKING GROOVE FOR PACKING THAT SEALS BARREL PLATE TO BARREL. THIS PACKING SEALS BARREL LUBRICATING OIL INTO BARREL.THE BARREL PLATE IS ITEM #682.IPL FIGURE #1A, CMM 61-13-01,REVISION 1May 15, 2001 · Dhav DHC7102 · Propeller Hub SectionSDR CA010509003Spar Cap · chafed(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOLLOWING AIRCRAFT:(1) Apr 23, 2001 · Dhav DHC7102 · Wing SparSDR CA010509002Spar Cap · chafed(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THEE EARLIER MAINTENANCE PROJECTS, ON THE FOLLOWING AIRCRAFT: (1) Apr 23, 2001 · Dhav DHC7102 · Wing SparSDR 20010524SG008Engine · failedFLT 1253 - HAV-MIA - EN ROUTE FROM HAVANA TO MIAMI, NR 1 ENGINE FAILED IN FLIGHT. REMOVED AND REPLACED NR 1 ENGINE. (M)Apr 18, 2001 · N706GA · Dhav DHC7102 · Engine (Turbine/Turboprop)SDR CA001228029Filter · plugged(CAN) PENUMATIC DE-ICE SYSTEM FAILED IN FLIGHT. DE-ICE PRESSURE WAS DOWN TO 12-15 PSI INFLIGHT AND 8-10 PSI ON GROUND. MANUAL PRESSURE 1518 +/-1 PSI. MAINTENANCE FOUND THE SYSTEM FROZEN, AND ALL THE WATER SEPARATOR FILTERS PLUGGED WITH SOOT. THE FILTERS WERE ADec 1, 2000 · Dhav DHC7102 · Airfoil Anti/De-ice SystemSDR CA001109004Fitting · broken(CAN) DURING CLIMB NR 2 HYDRAULIC PUMP CAUTION LIGHT ILLUMINTED, SYSTEM PRESSURE AND QUANTITY DROPPED TO ZERO. NR 1 HYDRAULIC PUMP THEN FAILED SHORTLY AFTER. MAINTENANCE DISCOVERED AN ALUMINUM HYDRAULIC LINE BROKEN AT THE FLARED FITTING. THIS LINE IS LOCATED Oct 26, 2000 · Dhav DHC7102 · Hydraulic System, MainSDR CA001106011Fuel Control · failed(CAN) ON THURSDAY 19 OCT. 2000, 11.22 GMT THE AIRCRAFT AT LIFT OFF THE PILOT NOTICED ENGINE NR 1 TORQUE INDICATOR STARTED TO DELAY AND ENGINE AUTO FEATHERED. CORRECTIVE ACTION TAKEN 1) FULL POWER RUNS CARRIED OUT PROBLEM COULD NOT BE REPEATED ON GROUND. 2) FUEOct 19, 2000 · Dhav DHC7102 · Fuel Control/Turbine EnginesSDR 20001128AP002Connector · looseAT SCHEDULED SERVICE CHECK, DETERMINED EMERGENCY PATH LIGHTS AT SEAT 9F NOT ILLUMINATING. INSPECTED AND DETERMINDED CONNECTOR TO BE LOOSE. SECURED CONNECTOR. (M)Jul 24, 2000 · N706GA · Dhav DHC7102 · Emergency LightingSDR CA000713016Fuel Control · failed(CAN) FUEL CONTROL UNIT WAS REPLACED. ENGINE RUN CARRIED OUT, TEST OKAY.AIRCRAFT RELEASED TO SERVICE.Jun 24, 2000 · Dhav DHC7102 · Fuel Control/Turbine EnginesSDR CA000713010Skin · bulged(CAN) DURING ROUTINE INSPECTION THE AIRCRAFT SKIN WAS FOUND BULGING OUTWARDS & 3 RIVETS WERE PULLED THROUGH THE SKIN.Jun 14, 2000 · Dhav DHC7102 · Fuselage Main, KeelSDR 20001128AP003Hinge · wornDURING SCHEDULED MAINTENANCE, FOUND LEFT WING INNER TRAIL FLAP OUTBOARD HINGE ARM WORN. REPAIRED LEFT WING INNER FORE FLAP TO TRAIL FLAP OUTBOARD HINGE ARM IAW BOMBARDIER (DEHAV) RD7-57-030. (M)Jun 14, 2000 · N173RA · Dhav DHC7102 · Leading Edge DevicesSDR 20001219AP002Fitting · crackedAT SCHEDULED COMPLIANCE OF AD 2000-02-07, EDDY CURRENT INSPECTION REVEALED ONE CRACK ON THE BAGGAGE DOOR AFT UPPER RETENTION PIN FITTING. REMOVED AND REPLACED AFT UPPER RETENTION PIN FITTING IAW DEHAV MM. (M)Jun 8, 2000 · N173RA · Dhav DHC7102 · Cargo/Baggage DoorsSDR 20001128AP004Fitting · crackedAT SCHEDULED COMPLIANCE OF AD 2000-02-07, EDDY CURRENT INSPECTION REVEALED ONE CRACK ON THE BAGGAGE DOOR AFT UPPER RETENTION PIN FITTING. REMOVED AND REPLACED AFT UPPER RETENTION PIN FITTING IAW DEHAV MM. (M)Jun 8, 2000 · N173RA · Dhav DHC7102 · Cargo/Baggage DoorsSDR 20001017AP003Light · inoperativeFLT 9516 - FLL-NAS - EMERGENCY LIGHTS AT ROW 12 SEAT C INOPERATIVE. SECURED PLUG FOR EMERGENCY LIGHT AT ROW 12 SEAT C. OPERATIONAL CHECK NORMAL. (M)May 31, 2000 · N706GA · Dhav DHC7102 · Emergency LightingSDR 20000721AP002Connector · disconnectedFLT 9516 - FLL/NAS - EMERGENCY LIGHTS AT ROWS 12 SEAT C INOPERATIVE. SECURED PLUG FOR EMERGENCY LIGHT AT ROW 12 SEAT C. OPERATIONAL CHECK NORMAL. (M)May 31, 2000 · N706GA · Dhav DHC7102 · Emergency LightingSDR 20001017AP002Longeron · corrodedAT SCHEDULED COMPLIANCE OF AD 99-26-11, RIGHT NACELLE LEFT UPPER LONGERON EDDY CURRENT INSPECTION REVEALED EIGHT AREAS OF CORROSION OUT OF LIMITS. REMOVED AND REPLACED DAMAGED LONGERON IAW FAA APPROVED DATA CONTAINED IN BOMBARDIER SERVICE BULLETIN 7-54-19. (May 26, 2000 · N706GA · Dhav DHC7102 · Nacelle/Pylon, Longeron/StringerSDR 20001017AP001Longeron · corrodedAT SCHEDULED COMPLIANCE OF AD 99-26-11, LEFT NACELLE RIGHT UPPER LONGERON EDDY CURRENT INSPECTION REVEALED ONE CRACK AND TWO AREAS OF CORROSION OUT OF LIMITS. REMOVED AND REPLACED DAMAGED LONGERON IAW FAA APPROVED DATA CONTAINED IN BOMBARDIER SERVICE BULLETINMay 23, 2000 · N706GA · Dhav DHC7102 · Nacelle/Pylon, Longeron/StringerSDR CA000301037Fcu · leaking(CAN) FUEL LEAK WAS FOUND AT GROUND IDLE SPEED ADJUSTMENT SCREW. P&W REPORT TO FOLLOW.Feb 13, 2000 · Dhav DHC7102 · Fuel Control/Turbine EnginesSDR CA000209026Pitot Tube · blocked(CAN) DUE TO CLIMATIC CONDITIONS IN FRENCH GUIANA AT THIS TIME OF YEAR, IN EFFORT TO PROTECT THE STATIC SYSTEM FROM WATER CONTAMINATION, THE PORTS WERE COVERED WITH TAPE WHEN THE AIRCRAFT WAS PARKED. ONE PORT WAS BLOCKED WITH A SMALL PIECE OF TAPE AND THE OTHEFeb 1, 2000 · Dhav DHC7102 · Pitot/Static SystemSDR CA000120026Compressor · stalled(CAN) COMPRESSOR STALLS EXPERIENCED IN FLIGHT, ENG REMOVED, SUSPECTED COMPRESSOR FAULTY.TEARDOWN TO FOLLOW.Jan 7, 2000 · Dhav DHC7102 · Turbine Engine Compressor SectionSDR CA000110065Case · cracked(CAN) CRACK FOUND ALONG LT BLEED AIR DUCT ADAPTER BOTTOM WELD LINE WHICH CARRIED ON .5 INCHES INTO THE CASE. SURVEY MADE AND NO SIMILAR CRACKS WERE FOUND ON OTHER ENGINES IN OPERATION.Jan 5, 2000 · Dhav DHC7102 · Turbine SectionSDR CA991209060Valve · failed(CAN) WHILE TAXING FOR TAKE OFF NR1 HYD PUMP CAUTION LITE ILLUMINATED. THERE WAS NO LOSS OF FLUID SO A SHEARED PUMP WAS SUSPECTED.THE PUMP WAS EXAMINED AND FOUND SERVICEABLE.FURTHER INVESTIGATION REVEALED THE HYD SHUT-OFF VALVE IN THE CLOSED POSITION, OPPOSITOct 26, 1999 · Dhav DHC7102 · Hydraulic System, MainSDR CA991028036Actuator · jammed(CAN) CREW HAD A SPOILER JAM INDICATION ON THE GROUND. THE CREW CONFIRMED THAT BOTH LEFT ROLL SPOILERS WERE JAMMED UP. ACTUATOR REPLACED.Oct 14, 1999 · Dhav DHC7102 · Drag Control ActuatorSDR CA991007094Actuator · cracked(CAN) DURING PRE-FLIGHT, PILOTS NOTICED THAT ROLL SPOILERS WOULD NOT STOW WITH INBOARD, OUTBOARD FAILURE INDICATION AND NO HYDRAULIC FLUID IN NR 2 SYSTEM. INVESTIGATION REVEALED THE HOUSING FOR THE ROLL SPOILER ACTUATOR WAS CRACKED COMPLETELY AROUND ITS CIRCUSep 30, 1999 · Dhav DHC7102 · Drag Control Actuator
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