# Service difficulty reports: Boeing DHC-7-102 A list on [Boeing DHC-7-102](https://openairdocs.org/model/boeing-dhc-7-102.md). Newest first. General aviation reporting is voluntary. Page 1 of 5 · 246 reports - [SDR 2022FA0000365](https://openairdocs.org/sdr/2022FA0000365.md): Bracket · cracked · Dec 15, 2021 · N59AG · Dhav DHC7102 · Rudder Structure > AFTER INSPECTION PER VIKING SB V7-27-03 REV0 ISSUED 18 OCT 21. PILOTS RUDDER PEDAL ADJUSTMENT BRACKET WAS FOUND TO BE CRACKED. REPLACED BRACKET. AWAITING UPDATE TO 1-7-7E MM FOR NEW INSPECTION FREQUENCY. - [SDR 2022FA0000364](https://openairdocs.org/sdr/2022FA0000364.md): Bracket · cracked · Dec 15, 2021 · N158CL · Dhav DHC7102 · Rudder Structure > AFTER INSPECTION PER VIKING SB V7-27-03 REV0 ISSUED 18 OCT 21. PILOTS RUDDER PEDAL ADJUSTMENT BRACKET WAS FOUND TO BE CRACKED. REPLACED BRACKET. AWAITING UPDATE TO 1-7-7E MM FOR NEW INSPECTION FREQUENCY. - [SDR QM7R201906142503](https://openairdocs.org/sdr/QM7R201906142503.md): Bracket · cracked · Jun 14, 2019 · N158CL · Dhav DHC7102 · Rudder Structure > ONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS. - [SDR QM7R201906142502](https://openairdocs.org/sdr/QM7R201906142502.md): Bracket · cracked · Jun 14, 2019 · N89068 · Dhav DHC7102 · Rudder Structure > ONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS. - [SDR QM7R201906142501](https://openairdocs.org/sdr/QM7R201906142501.md): Bracket · cracked · Jun 14, 2019 · N59AG · Dhav DHC7102 · Rudder Structure > ONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS. - [SDR 2019FA0000111](https://openairdocs.org/sdr/2019FA0000111.md): Bracket · cracked · Apr 9, 2019 · N177RA · Dhav DHC7102 · Rudder Control System > PILOT'S RUDDER PEDAL CONTROL MECHANISM BRACKET ASSY CRACKED. IPC 27-20-00, FIG 10, ITEM 50, PN # 72710086-001. REPORTED A BRACKET HAD BROKEN ON THEIR AIRCRAFT AND RECOMMENDED "ONE TIME INSPECTION" FOR MAINTENANCE TO INSPECT THEIR ASSIGNED AIRCRAFT. INSPECTED A - [SDR 2019FA0000110](https://openairdocs.org/sdr/2019FA0000110.md): Bracket · cracked · Apr 9, 2019 · N705GG · Dhav DHC7102 · Rudder Control System > PILOT'S RUDDER PEDAL CONTROL MECHANISM BRACKET ASSY CRACKED. IPC 27-20-00, FIG 10, ITEM 50, PN 72710086-001. REPORTED A BRACKET HAD BROKEN ON THEIR AIRCRAFT AND RECOMMENDED "ONE TIME INSPECTION" FOR MAINTENANCE TO INSPECT THEIR ASSIGNED AIRCRAFT. INSPECTED ASS - [SDR 2019FA0000109](https://openairdocs.org/sdr/2019FA0000109.md): Bracket · cracked · Apr 9, 2019 · N765MG · Dhav DHC7102 · Rudder Control System > PILOT'S RUDDER PEDAL CONTROL MECHANISM BRACKET ASSY CRACKED. IPC 27-20-00, FIG 10, ITEM 50, PN 72710086-001. REPORTED A BRACKET HAD BROKEN ON THEIR AIRCRAFT AND RECOMMENDED "ONE TIME INSPECTION" FOR MAINTENANCE TO INSPECT THEIR ASSIGNED AIRCRAFT. INSPECTED ASS - [SDR QM7R201904020003](https://openairdocs.org/sdr/QM7R201904020003.md): Bracket · cracked · Apr 2, 2019 · N177RA · Dhav DHC7102 · Rudder Control System > ONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS. - [SDR QM7R201904020002](https://openairdocs.org/sdr/QM7R201904020002.md): Bracket · cracked · Apr 2, 2019 · N765MG · Dhav DHC7102 · Rudder Control System > ONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS. - [SDR QM7R201904020001](https://openairdocs.org/sdr/QM7R201904020001.md): Bracket · cracked · Apr 2, 2019 · N705G · Dhav DHC7102 · Rudder Control System > ONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS. - [SDR K6JY2019040800001](https://openairdocs.org/sdr/K6JY2019040800001.md): Bracket · cracked · Mar 25, 2019 · N158CL · Dhav DHC7102 · Rudder Control System > RUDDER CONTROL BRACKET ASSEMBLY P/N: 72710086-001 CRACKED AT PILOT'S RUDDER PEDAL'S ADJUSTMENT MECHANISM ASSEMBLY P/N 72710311-055. THE BRACKET APPEARS TO HAVE MATERIAL FATIGUE AT THE INBD ANGLE RUN-OUT OF THIS MACHINED PART. CRACK IS LOCATED IN THE RADII OF T - [SDR CA200102011](https://openairdocs.org/sdr/CA200102011.md): Pump · malfunctioned · May 12, 2017 · Dhav DHC7102 · Fuel Boost Pump > (CAN) THE TEST RESULTS FOR TWO FUEL PUMPS WERE CALLED INTO QUESTION DURING THE 2018 PVI. THE OUT OF TOLERANCE CONDITIONS WERE DOCUMENTED ON NON-CONFORMANCE REPORTS AND APPROVED INTERNALLY BY QA, ENGINEERING AND THE PRM IN MAY 2017. PUMP S/NS 8071 AND 8074 COUL - [SDR CA151229014](https://openairdocs.org/sdr/CA151229014.md): Tube · chafed · Dec 23, 2015 · Dhav DHC7102 · Aircraft Fuel Distribution System > (CAN) MAINTENANCE WAS TROUBLESHOOTING A REPORTED FUEL SEEP FROM THE FUEL SHROUD DRAIN FOLLOWING AIRCRAFT REFUELING. WELDED REFUEL/DEFUEL TUBE ASSEMBLY P/N 72810012-001 WAS FOUND WITH A PIN HOLE CAUSED BY CHAFING OF THE WELDED REFUEL/DEFUEL TUBE ASSEMBLY WITH - [SDR CA151009001](https://openairdocs.org/sdr/CA151009001.md): Indicator · malfunctioned · Oct 8, 2015 · Dhav DHC7102 · Engine Temperature Indicating System > (CAN) DURING CRUISE THE DECIMAL PART OF T5 GAUGE OF ENGINE 2 STOPPED GIVING INFORMATION. AFTER RECYCLING THE BREAKER THE CREW NOTICED THAT EVEN WITH BREAKER PULLED THE GAUGE WAS STILL POWERED. SHORTLY AFTER STARTING DESCENT, THE T5 GAUGE OF ENGINE 2 STOPPED G - [SDR CA150701009](https://openairdocs.org/sdr/CA150701009.md): Garlock Seal · damaged · Jun 4, 2015 · Dhav DHC7102 · Turbine Engine Oil System > (CAN) EN-ROUTE AT 15,000 FEET WHEN THE CREW RECEIVED A LOW OIL PRESS INDICATION FOR ONE OF THE LT ENGS. PT6A, & SHUT THE ENG DOWN AS A PRECAUTION. THE ACFT DIVERTED FOR A SAFE LANDING. IT WAS REPORTED THAT MX IDENTIFIED THE GARLOCK OIL SEAL ON THE HYD PUMP W - [SDR CA150515011](https://openairdocs.org/sdr/CA150515011.md): Pump · failed · May 13, 2015 · Dhav DHC7102 · Hydraulic Pump (Electric/Engine), Main > (CAN) THE AIRCRAFT WAS ON A CREW CHANGE FLIGHT FOR A CUSTOMER, UPON START UP FOR DEPARTURE, THE FLIGHT CREW SAW THE HYDRAULIC QUANTITY FALL TO 0. THEY DISEMBARKED THEIR PASSENGERS AND CALLED MAINTENANCE. MAINTENANCE ARRIVED AND FOUND THAT THE NR 3 PUMP, SN 16 - [SDR CA150113007](https://openairdocs.org/sdr/CA150113007.md): Fcu · faulted · Dec 4, 2014 · Dhav DHC7102 · Fuel Control/Turbine Engines > (CAN) WHEN THE CREW REDUCED ENGINE POWER FOR THE DESCENT, THE LT ENGINE REMAINED AT CRUISE POWER OF 3800 FT-LBS. THE CREW VERIFIED THE ENGINE WAS RESPONSIVE ABOVE 3800 FT-LBS BUT WOULD NOT REDUCE BELOW, THEN THE PILOT REQUESTED TO RETURN TO THE AIRPORT. WHEN - [SDR CA141209005](https://openairdocs.org/sdr/CA141209005.md): Fuel Control · failed · Dec 4, 2014 · Dhav DHC7102 · Fuel Control/Turbine Engines > (CAN) WHILE IN THE DESCENT, THE POWER LEVER WAS REDUCED AND THE NUMBER 1 ENGINE TORQUE REMAINED AT CRUISE POWER SETTING OF 3800 FT-LBS. THE CREW VERIFIED THAT THE ENGINE AND GAUGES WERE RESPONSIVE ABOVE 3800 FT-LBS TORQUE BUT WOULD NOT REDUCE. A DIVERSION WAS - [SDR CA141126003](https://openairdocs.org/sdr/CA141126003.md): Strap · corroded · Nov 25, 2014 · Dhav DHC7102 · Nacelle/Pylon, Main Frame > (CAN) FOLLOWING REMOVAL OF THE FOUR (4) ENGINE NACELLE INLET DEICE BOOTS, MISSING AND CORRODED RIVET HEADS WERE DISCOVERED ON THE FIBERGLASS INLET LIPS. FURTHER CORROSION WAS FOUND ON THE FOUR (4) ENGINE NACELLE STRAPS BENEATH THE FIBERGLASS INLET LIPS. MAI - [SDR CA131217009](https://openairdocs.org/sdr/CA131217009.md): Windscreen · arced · Dec 15, 2013 · Dhav DHC7102 · Flight Compartment Windows > (CAN) THE LT WINDSCREEN BEGAN ARCHING JUST AFTER TAKEOFF, THE WINDSHIELD HEAT WAS TURNED OFF AND THE ACFT RETURNED TO BASE, DURING THE RETURN TO DEPARTURE THE WINDSCREENS ICED UP REDUCING THE FLIGHT CREWS VISIBILITY. CADORS, 2013C5268 REFERENCES THIS INCIDENT - [SDR CA131218012](https://openairdocs.org/sdr/CA131218012.md): Gcu · failed · Nov 19, 2013 · Dhav DHC7102 · AC Generator-Alternator > (CAN) RETURNED DUE TO AN ELECTRICAL PROBLEM (RT DC BUSS FAULT). ENGINE 1 THRU 4 GROUND RUN. DC SYSTEM BROUGHT ONLINE. NR 4 DC GEN OPENS DC BUS TIE AND AFTER A SHORT DELAY THERE WAS A RIGHT DC BUS FAULT. REPLACED NR 4 DC GCU. SYSTEM FUNCTION CHECKED, NO FAU - [SDR CA130125004](https://openairdocs.org/sdr/CA130125004.md): Wire · damaged · Jan 14, 2013 · Dhav DHC7102 · Fire Protection System Wiring > (CAN) BOTH NR 4 ENGINE FIRE DETECTION ELEMENTS FOUND TO HAVE CHAFE DAMAGE FROM CONTACT WITH AIRFRAME STRUCTURE CAUSING ACTIVATION OF THE FIRE WARNING. BOTH DETECTION ELEMENTS REPLACED, CHECKED SERVICEABLE. - [SDR CA120605006](https://openairdocs.org/sdr/CA120605006.md): Turbine Blades · fractured · May 29, 2012 · Dhav DHC7102 · Turbine Section > (CAN) SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE FLIGHT RETURNED TO THE DEPARTURE POINT WHERE AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST FLIGHT INSPECTIO - [SDR CA120528009](https://openairdocs.org/sdr/CA120528009.md): Blade · separated · May 24, 2012 · Dhav DHC7102 · Turbine Engine Compressor Section > (CAN) APPROXIMATELY 40 NM NORTH OF AIRPORT, SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE NR 2 ENGINE WAS SHUTDOWN AND THE CREW RETURNED TO DEPARTURE. VISUAL INSPECTION OF THE 1ST STAGE - [SDR CA120327003](https://openairdocs.org/sdr/CA120327003.md): Angle · cracked · Mar 22, 2012 · Dhav DHC7102 · Nacelle/Pylon Miscellaneous Structure > (CAN) WHILE CONDUCTING A CORROSION INSPECTION, CRACKS WERE FOUND ON THE NR 1 NACELLE, OTBD LONGERON CHANNEL, PN 75410103-105, AND LONGERON ANGLE, PN 75410104-103, AND NR 4 NACELLE, INBD LONGERON CHANNEL, P/N 75410119-106, LONGERON ANGLE P/N 75410104-104, NR 4 - [SDR CA120216001](https://openairdocs.org/sdr/CA120216001.md): Wire · chafed · Feb 15, 2012 · Dhav DHC7102 · Electrical Power System Wiring > (CAN) WHILE CONDUCT EWIS TASK E-430 ON THE NR 3 NACELLE, NUMEROUS WIRES WERE FOUND TO HAVE BEEN CHAFED BY THE PHENOLIC BLOCK THAT SECURES THESE WIRES AS THEY PASS FROM THE RT MLG WHEEL WELL THROUGH THE FIRE WALL. THE WIRING AFFECTED IS AS FOLLOWS: 7160-30006D - [SDR CA120214006](https://openairdocs.org/sdr/CA120214006.md): Longeron · cracked · Feb 13, 2012 · Dhav DHC7102 · Nacelle/Pylon, Longeron/Stringer > (CAN) WHILE CONDUCTING A CORROSION INSPECTION, CRACKS WERE FOUND ON THE NR 1 NACELLE OTBD LONGERON CHANNEL, PN 75410103-105 AND LONGERON ANGLE, PN 75410104-103 AND NR 4 NACELLE INBD LONGERON CHANNEL, PN 75410119-106 AND LONGERON ANGLE, PN 75410120-104. THE C - [SDR CA120213003](https://openairdocs.org/sdr/CA120213003.md): Cable · broken · Feb 9, 2012 · Dhav DHC7102 · Aileron Control System > (CAN) DURING PRE-FLIGHT INSPECTION OF THE ACFT, AFTER PULLING THE AILERON DISCONNECT HANDLES, IT WAS NOTICED THAT THE AILERON CONTROL WAS NOT ROTATING FULLY TO THE LT. MAINTENANCE INSPECTED AND COULD NOT REPRODUCE THE EFFECT UNTIL AFTER THEY OPERATED THE AUTO- - [SDR CA111219010](https://openairdocs.org/sdr/CA111219010.md): Receiver · failed · Dec 15, 2011 · Dhav DHC7102 · Global Positioning System > (CAN) INBOUND FOR LANDING, THE NR 2 GPS SCREEN WAS SEEN TEMPORARILY GOING BLANK THAN COMING BACK ON. WITHIN A FEW SECONDS BOTH CREW MEMBERS NOTED AN ODD ODOR IN THE COCKPIT. THE NR 2 GPS WAS TURNED OFF AND THE CIRCUIT BREAKERS WERE PULLED. THE ODOR DISSIPATED - [SDR CA111110001](https://openairdocs.org/sdr/CA111110001.md): Tire · separated · Nov 7, 2011 · Dhav DHC7102 · Tire > (CAN) DURING A WALK AROUND A DEFECT WAS NOTICED ON THE INBD RT MAIN WHEEL TIRE. INVESTIGATION REVEALED THAT THE TIRE WAS SEPARATING/SPLITTING IN THE GAP BETWEEN THE TREAD, THIS WAS WELL INTO THE CORD. THE DEFECT WAS PRESENT 360 DEGREES AROUND THE TIRE IN VARY - [SDR CA110811005](https://openairdocs.org/sdr/CA110811005.md): Line · failed · Aug 1, 2011 · Dhav DHC7102 · Hydraulic System, Main > DURING CRUISE, ENROUTE, NR 1 HYD SYS FAILED. CREW COMPLETED THEIR CHECKLIST AND LANDED NORMALLY WITHOUT INCIDENT AT AN ALTERNATE DESTINATION. ON GROUND LOCATED LEAK IN NR 1 NACELLE AT THE HYD MANIFOLD SUPPLY LINE. THE TUBE IN QUESTION HAD FRACTURED FOR AP - [SDR CA110621009](https://openairdocs.org/sdr/CA110621009.md): Pump · leaking · Jun 16, 2011 · Dhav DHC7102 · Engine Fuel Pump > UPON STARTING THE NR 3 ENGINE, THE T5 WAS OBSERVED TO BE RISING WHILE THE NG WAS SLOW TO RISE. THE START WAS ABORTED WHEN THE T5 HIT 900 DEGREES. MX INVESTIGATED AND FOUND THAT THE FUEL PUMP WAS LEAKING AND THE FUEL WAS GOING THROUGH THE GARLOCK SEAL AND INT - [SDR CA100804014](https://openairdocs.org/sdr/CA100804014.md): Reservoir · leaking · Jul 19, 2010 · Dhav DHC7102 · Hydraulic Reservoir, Main > WHILE IN CRUISE FLIGHT, A ROUTINE CHECK OF THE ENGINES/SYS REVEALED THE NR 2 HYD FLUID QTY WAS INDICATING A SLIGHTLY LOWER LEVEL THAN EARLIER NOTED. AFTER A FEW MORE MINUTES OF MONITORING A SLIGHTLY FURTHER DROP WAS NOTED. THE DECISION WAS MADE TO RETURN TO B - [SDR K08R10FA0000470](https://openairdocs.org/sdr/K08R10FA0000470.md): Bearing Race · damaged · Mar 29, 2010 · N34HG · Dhav DHC7102 · Propeller Assembly > (K08R) UPON DISASSEMBLY OF THE PROPELLER ASSY, FOLLOWING REMOVAL FOR TIME CHANGE. THE NR 3 PROPELLER BLADE, PN PFA12D1-9, SN 862170, BEARING RACE WAS FOUND TO BE SIGNIFICANTLY DAMAGED WITH CONSIDERABLE SPALLING WITHIN THE RACE SURFACES WITH CRACKS AND THE END - [SDR 2010FA0000242](https://openairdocs.org/sdr/2010FA0000242.md): Lever · separated · Mar 2, 2010 · N34HG · Dhav DHC7102 · Main Landing Gear Attach Section > THE ACFT LANDED WITH AN UNSAFE NOSE GEAR INDICATION. THE SUBSEQUENT INVESTIGATION DETERMINED THAT THE NOSE GEAR LOCK PIN LEVER SEPARATED FROM THE ACFT SOMETIME DURING TRAINING FLIGHT. A MORE DETAILED INSP OF LANDING GEAR COMPONENTS REVEALED THAT THE LOCK LEV - [SDR CA091126002](https://openairdocs.org/sdr/CA091126002.md): Tube · misinstalled · Nov 18, 2009 · Dhav DHC7102 · Turbine Engine Oil System > (CAN) DURING FLIGHT, NR 4 ENGINE LOST OIL PSI INDICATION ALONG WITH MASTER CAUTION & OIL PSI LIGHT ILLUMINATED ON ANNUNCIATOR PANEL. ENGINE SHUTDOWN & ACFT LANDED WITHOUT FURTHER INCIDENT. ENGINE INSPECTED & FOUND TO HAVE NO OIL IN OIL TANK. AFTER SERVICING OI - [SDR HNAA2009081400254](https://openairdocs.org/sdr/HNAA2009081400254.md): Light · broken · Aug 12, 2009 · N814EX · Dhav DHC7102 · Emergency Lighting > DURING INSPECTION IN SBY, FOUND EMERGENCY LIGHT SUB-ASSEMBLY BROKEN ON SIDEWALL PANEL AT ROW 4 A & C. REMOVED AND REPLACED SUB-ASSEMBLY AND SPLICED IN WIRES. OPERATIONAL CHECK WAS GOOD. - [SDR CA081222004](https://openairdocs.org/sdr/CA081222004.md): Control Cable · corroded · Dec 6, 2008 · Dhav DHC7102 · Elevator Control System > (CAN) DURING A PREFLIGHT, THE LEFT ELEVATOR DID NOT MOVE WITH THE CONTROL COLUMN INPUT. MAINTENANCE INVESTIGATED AND FOUND ONE OF THE CABLES SNAPPED UNDER THE LAVATORY. SUSPECT THAT A PREVIOUSLY REPAIRED LEAK FROM THE LAVATORY HAD LEAKED ON THE CABLES, AND T - [SDR CA080124011](https://openairdocs.org/sdr/CA080124011.md): Skin Panel · corroded · Jan 24, 2008 · Dhav DHC7102 · Fuselage Main, Plate/Skin > (CAN) WHILE CONDUCTING A CORROSION INSP ON AC, VENEZUELAN REGISTRATION YV1000, IAW THE CUSTOMERS EQUALIZED MAINT PROGRAM. NUMEROUS AREAS OF CORROSION WERE DETECTED THROUGHOUT THE AC. A THRESHOLD AND REPETITIVE CORROSION INSP PROGRAM IS MANDATED BY ADCF-98-03 - [SDR CA080116017](https://openairdocs.org/sdr/CA080116017.md): Housing · cracked · Jan 15, 2008 · Dhav DHC7102 · Main Landing Gear Strut/Axle/Truck > (CAN) DURING A 6 YEAR CORROSION INSPECTION, A CRACK WAS FOUND ON THE LT MLG OUTER HOUSING. THE CRACK IS LOCATED ON THE FWD SIDE AT ABOUT THE ONE O’CLOCK POSITION JUST WERE THE HOUSING TAPERS DOWN. EDDY CURRENT WAS USED ON THE CRACK, IT WAS DEEPER THAN THE 0.04 - [SDR CA071217004](https://openairdocs.org/sdr/CA071217004.md): Control Cable · disconnected · Dec 12, 2007 · Dhav DHC7102 · Engine Controls > (CAN) AFTER FLIGHT, THE NR 2 CONDITION LEVER WOULD NOT MOVE TO FEATHER OR CUTOFF, THE ENGINE HAD TO BE SHUTDOWN USING THE T-HANDLE. FURTHER INVESTIGATION REVEALED THAT THE NR 2 TELEFLEX CABLE HAD BECOME UNSCREWED NEAR THE BEARING. WE WERE UNAWARE THAT THE CA - [SDR CA071115002](https://openairdocs.org/sdr/CA071115002.md): Bearing · failed · Oct 24, 2007 · Dhav DHC7102 · Wheel/Ski/Float > (CAN) AFTER LANDING THE LT OB MAIN WHEEL HUBCAP WAS DISCOVERED MISSING. FURTHER INVESTIGATION FOUND THE INNER BEARING WAS BLOWN APART, THE WHEEL AND BRAKE ASSY HAD EXTENSIVE DAMAGE FROM THE WHEEL RUBBING ON THE BRAKE ASSY. THE AXLE WAS INSPECTED, NO DAMAGE WAS - [SDR CA070829004](https://openairdocs.org/sdr/CA070829004.md): Intake Duct · corroded · Aug 27, 2007 · Dhav DHC7102 · Engine Air Intake System > (CAN) LEVEL 3 CORROSION WAS FOUND BETWEEN THE LOWER INTAKE FORWARD LIP AND THE NACELLE STRUCTURE. (TC NR 20070829004) - [SDR CA070830006](https://openairdocs.org/sdr/CA070830006.md): Rod · broken · Aug 23, 2007 · Dhav DHC7102 · Drag Control System > (CAN) DURING TROUBLESHOOTING, A PFCS INDICATOR PROBLEM, IT WAS NOTICED THAT THE ROD FOR THE RT IB ROLL SPOILER TRANSMITTER HAD SHEARED INSIDE OF THE ROD END AT THE SPOILER END. THERE WAS NO INDICATIONS OF THE ROD CONTACTING ANY OTHER SURFACE TO CAUSE IT TO BRE - [SDR HNAA0700136](https://openairdocs.org/sdr/HNAA0700136.md): Doubler · debonded · May 4, 2007 · N937HA · Dhav DHC7102 · Fuselage Miscellaneous Structure > DOUBLER UNDER STR 28 IS DISBONDED IN FRAME BAYS X424 TO X434. - [SDR CA070710004](https://openairdocs.org/sdr/CA070710004.md): Guide Vane · failed · Apr 26, 2007 · Dhav DHC7102 · Turbine Engine Compressor Section > (CAN) DURING FLIGHT, THE TURBINE TEMPERATURE ROSE SUDDENLY FROM 738 TO 785 DEGREES CELSIUS. A BORESCOPE INSPECTION REVEALED DAMAGE TO THE CT GUIDE VANE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE HOT SECTION WAS REMOVED FROM THE ENGINE A - [SDR CA070214005](https://openairdocs.org/sdr/CA070214005.md): Line · broken · Feb 12, 2007 · Dhav DHC7102 · Pneumatic Distribution System > (CAN) AFTER LANDING THE NR 1 PROP RPM WAS LOWER THAN NORMAL. MAINTENANCE FOUND THAT THE P3 LINE FROM THE P3 FILTER BOWL TO THE ENGINE WAS BROKEN PN 3035279. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070214005) - [SDR CA061106015](https://openairdocs.org/sdr/CA061106015.md): Diffuser · loose · Oct 22, 2006 · Dhav DHC7102 · Turbine Engine Compressor Section > (CAN) SHORTLY AFTER LEVELLING OFF AT 17000 FEET, THE NR 2 ENGINE BEGAN TO SURGE AFFECTING ALL ENGINE PARAMETERS. THE POWER WAS REDUCED TO ALLEVIATE THE RESULTING OVER TEMPERATURE CONDITION. AT POWER SETTING ABOVE 70% NG THE ITT WOULD FLUCTUATE WILDLY TO OVER - [SDR CA060821004](https://openairdocs.org/sdr/CA060821004.md): Fcu · failed · Aug 8, 2006 · Dhav DHC7102 · Fuel Control/Turbine Engines > (CAN) AFTER INSTALLING THE FRESHLY OVERHAULED ENGINE IN THE NR 1 POSITION, THE ENGINE WAS STARTED TO PERFORM THE BETA RIGGING; THE PROPELLER WAS UNFEATHERED, THE POWER LEVEL MOVED UP TO THE FWD BETA STOP TO RECORD NUMBERS, ALL THE PARAMETERS STABILIZED. THE N Next page: https://openairdocs.org/model/boeing-dhc-7-102/reports.md?page=2 ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql 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 ``` This list as a web page: https://openairdocs.org/model/boeing-dhc-7-102/reports --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.