# Service difficulty reports: Boeing DHC 6

A list on [Boeing DHC 6](https://openairdocs.org/model/boeing-dhc-6.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 4 · 194 reports

- [SDR 2026FA0000824](https://openairdocs.org/sdr/2026FA0000824.md): Trim Tab · faulted · Oct 8, 2026 · N814SS · Dhav DHC6 · Flight Control System
  > AILERON TRIM INDICATION, AILERON TRIM TAB POSITION INDICATION. INTERMITTENT ERRATIC FLICKERING OF THE AILERON TRIM INDICATION. SYMPTOM APPEARS RANDOMLY, UNRELATED TO TRIM POSITION OR FLIGHT PHASE, AND HAS PERSISTED ACROSS MULTIPLE COMPONENT REPLACEMENTS. A
- [SDR 2024FA0000767](https://openairdocs.org/sdr/2024FA0000767.md): Propeller · fluctuates · Oct 10, 2024 · N70AR · Dhav DHC6 · Propeller System
  > LH PROP REVERSE RPM HIGH/AT MAX CAUSED PROP FLUCTUATIONS WHEN ENGAGED TO REVERS UPON LANDING AT KRVS. THIS CAUSED RUNWAY EXCURSION INTO GRASS. A&P ADJUSTED MAX REVERSE PROP RPM AND AIRCRAFT / PROP PERFORMED NORMAL.
- [SDR 3RAA201903288049](https://openairdocs.org/sdr/3RAA201903288049.md): Pushrod · abnormal · Mar 27, 2019 · N344CS · Dhav DHC6 · Power Lever
  > RIGHT ENGINE FCU PUSHROD (FCU CONTROL ROD) ADJUSTMENT TURNBUCKLE JAMNUTS LOOSENED AND THE TURNBUCKLE BACKED OUT LENGTHENING THE PUSHROD OVERALL LENGTH CAUSING LOW ENGINE POWER. BOTH JAMNUTS WERE FOUND SAFETIED ONLY TO THE TURNBUCKLE INSTEAD OF TO THE TURNBUCK
- [SDR 2018FA0000200](https://openairdocs.org/sdr/2018FA0000200.md): Transducer · failed · Jul 2, 2018 · N812SS · Dhav DHC6* · Engine BMEP/Torque Indicating
  > TORQUE PRESSURE TRANSDUCER FAILED
- [SDR 2018FA0000202](https://openairdocs.org/sdr/2018FA0000202.md): Fastener · loose · Jun 27, 2018 · N814SS · Dhav DHC6 · Elevator Structure
  > DURING INSPECTION, FOUND LOOSENING JO-BOLTS ATTACHING THE RT AND LT FLANGES OF THE CENTER ELEVATOR HINGE BRACKET WHERE THE BRACKET FLANGES ATTACH TO THE AFT HORIZONTAL STABILIZER SPAR AT THE TOP AND BOTTOM OF THE BRACKET. THERE ARE FOUR LOOSENING JO-BOLTS AT T
- [SDR FAA2018052500164](https://openairdocs.org/sdr/FAA2018052500164.md): Pressure Switch · intermittent · May 25, 2018 · N153QS · Dhav DHC6 · Propeller Controlling System
  > AFTER TAKE OFF, AT 300 FT, THE NR 2 PROPELLER AUTOFEATHERED, THE AUTOFEATHER WAS SELECTED OFF AND THE PROPELLER UNFEATHERED AND RETURNED TO NORMAL OPS. TORQUE WAS OBSERVED BY THE CREW DURING THE AUTOFEATHER AND THE THROTTLE WAS RETARDED TO PREVENT AN OVER TOR
- [SDR 2018FA0000040](https://openairdocs.org/sdr/2018FA0000040.md): Bellcrank · loose · Jan 16, 2018 · N153QS · Dhav DHC6* · Rudder Control System
  > RUDDER TORQUE TUBE, BELL CRANK ATTACHMENT RIVETS AND BELL CRANK SHOWING SIGNS OF BEING LOOSE. ATTACH RIVETS ARE SMOKING.
- [SDR S9BA201612040004](https://openairdocs.org/sdr/S9BA201612040004.md): Duct Clamp · cracked · Dec 2, 2016 · Dhav DHC6 · Pneumatic Distribution System
  > ON TAKEOFF, RIGHT T HANDLE FIRE WARNING.
- [SDR CA160125010](https://openairdocs.org/sdr/CA160125010.md): Door · mismanufactured · Jan 15, 2016 · Dhav DHC6* · Fixed Inner Doors
  > (CAN) DURING ROUTINE MAINTENCE, FOUND 2 PROBLEMS WITH THE ICA`S. ON AN EMMA, EQUALIZED MAINTENANCE MAXIMUM AVAILABILITY, INSPECTION CARD 15, SECTION 3B, THE FLIGHT COMPARTMENT DOORS ARE TO BE INSPECTED FOR HIRF BONDING WITH A SPECIFICATION OF 10 MILLIOHMS. T
- [SDR CA160111012](https://openairdocs.org/sdr/CA160111012.md): Seal · defective · Jan 11, 2016 · Dhav DHC6* · Aircraft Fuel Distribution System
  > (CAN) FUEL MOTIVE LINE STRAINER, CHECK VALVE FOUND TO HAVE A SWOLLEN RUBBER SEAL WHICH PREVENTED THE FLAPPER FROM SEALING. SPRING UNABLE TO RETURN VALVE TO CLOSED POSITION.
- [SDR CA151102015](https://openairdocs.org/sdr/CA151102015.md): Aileron · mismanufactured · Nov 2, 2015 · Dhav DHC6* · Aileron Control System
  > (CAN) PRODUCTION HAS REPORTED THAT THE HUB, FORK, AILERON OUTER WING, HAS BEEN MFG INCORRECTLY. IT HAS BEEN FOUND THAT HUBS WERE MISSING THE.03" X 45 CHAMFER AROUND THE.2495-.2505" DIAMETER HOLE. THE SHARP EDGE IS BROKEN, 0.005" TO 0.010", BUT THE CHAMFER
- [SDR CA151029025](https://openairdocs.org/sdr/CA151029025.md): Rod End · seized · Oct 14, 2015 · Dhav DHC6* · Fuel Control/Turbine Engines
  > (CAN) DURING GROUND RUN-UP FCU CONTROL ROD, PN C6CE1398-3 HAD STIFF/SEIZED END BEARINGS, PN DSC4-3A ON NR 2 ENGINE. FCU ROD AND END BEARINGS REPLACED.
- [SDR CA150721005](https://openairdocs.org/sdr/CA150721005.md): Door · open · Jul 10, 2015 · Dhav DHC6* · Passenger/Crew Doors
  > (CAN) AN AIR OPERATOR RECENTLY EXPERIENCED AN EVENT WHERE THE MAIN CABIN PASSENGER DOOR OPENED IN FLIGHT. THIS HAPPENED ON APPROACH IN TURBULENT WEATHER CONDITIONS. THE OPERATOR CONCLUDED THAT THERE WAS NO FAULT IN THE DOOR LOCKING MECHANISM BUT NOTED THAT THE
- [SDR 2015FA0000367](https://openairdocs.org/sdr/2015FA0000367.md): Structure · cracked · Jul 6, 2015 · N153QS · Dhav DHC6* · Nose/Tail Landing Gear
  > THE ACFT FITTED WITH AMPHIB FLOATS HAD A NOSE GEAR FAILURE PREVIOUSLY AT 344.5 HRS. INITIAL FINDINGS OF THE FAILURE WERE THOUGHT TO BE FROM INTERGRANULAR CORROSION. NEW PARTS WERE FITTED AT THAT TIME. AT AFTT 422.6, JULY 2, 2015 THE NOSE GEARS WERE REMOVED
- [SDR CA150622004](https://openairdocs.org/sdr/CA150622004.md): Wire · corroded · Jun 19, 2015 · Dhav DHC6* · Communications System Wiring
  > (CAN) HF ANTENNA WIRE FAILED DUE TO CORROSION, RESULTING FROM WATER INGRESS INTO THE FEED THROUGH IPC REFERENCE 23-10-00 FIG 1.
- [SDR CA141201002](https://openairdocs.org/sdr/CA141201002.md): Adapter · cracked · Nov 25, 2014 · Dhav DHC6* · Vertical Stabilizer
  > (CAN) WHILE COMPLETING SB 6/454, THE RT REAR STABILIZER ATTACHMENT ADAPTER FOUND CRACKED.(P/N C6FSM 1820-33). THE ATTACHMENT ADAPTOR WAS REPLACED WITH NO ADDITIONAL DEFECTS NOTED.
- [SDR CA141104011](https://openairdocs.org/sdr/CA141104011.md): Pressure Switch · failed · Nov 4, 2014 · Dhav DHC6* · Fuel Boost Pump
  > (CAN) FUEL BOOST PUMP LOW PRESSURE SWITCH FAILURE. MFG ENGINEERING CONTINUING TO INVESTIGATE.
- [SDR CA141031024](https://openairdocs.org/sdr/CA141031024.md): Rod End · seized · Oct 31, 2014 · Dhav DHC6* · Fuel Controlling System
  > (CAN) ROD END IS FOUND TO BE SEIZING. ROD FOUND TO HAVE STIFF ROD ENDS AS WELL. RODS REMOVED AND REPLACED. RODS ARE IN THE ENGINE FUEL CONTROL SYSTEM.
- [SDR CA141031023](https://openairdocs.org/sdr/CA141031023.md): Rod End · seized · Oct 31, 2014 · Dhav DHC6* · Fuel Controlling System
  > (CAN) ROD END WAS FOUND TO BE SEIZING. ROD FOUND TO HAVE STIFF ROD ENDS AS WELL. TWO RODS REMOVED AND REPLACED. RODS ARE IN THE ENGINE FUEL CONTROL SYSTEM.
- [SDR CA140912020](https://openairdocs.org/sdr/CA140912020.md): Cover · cracked · Sep 10, 2014 · Dhav DHC6* · Exterior Lighting
  > (CAN) PRODUCTION HAS REPORTED THAT THE LIGHT COVER ON THE WING TIP STROBE LIGHT, RED IS CRACKED AROUND THE SCREW ATTACHMENT HOLE.
- [SDR CA140912019](https://openairdocs.org/sdr/CA140912019.md): Cover · cracked · Sep 10, 2014 · Dhav DHC6* · Exterior Lighting
  > (CAN) THE LIGHT COVER ON THE WING TIP STROBE LIGHT, GREEN, IS CRACKED AROUND THE SCREW ATTACHMENT HOLE.
- [SDR CA140717016](https://openairdocs.org/sdr/CA140717016.md): Check Valve · missing · Jul 16, 2014 · Dhav DHC6* · Aircraft Fuel Distribution System
  > (CAN) DURING SCHEDULED MAINTENANCE INSPECTION THE INTERNAL FUEL SCREEN WAS FOUND TO BE MISSING FROM THE CHECK VALVE ASSEMBLY, INVESTIGATING.
- [SDR CA140717015](https://openairdocs.org/sdr/CA140717015.md): Bearing · damaged · Jun 17, 2014 · Dhav DHC6* · Rudder Structure
  > (CAN) BEARING IN THE LOWER RUDDER HINGE FITTING FOUND DAMAGED & NO SIGNS OF LUBRICATION. CONTINUING TO INVESTIGATE.
- [SDR CA140414010](https://openairdocs.org/sdr/CA140414010.md): Heat Exchanger · misrepaired · Apr 11, 2014 · Dhav DHC6* · Pneumatic Distribution System
  > (CAN) HEAT EXCHANGER ASSEMBLY, C6SF1515-3 HAS HAD ALL 48 PLUG WELDS GROUND FLUSH TO THE PARENT METAL AND POLISHED. GRINDING OF THE WELDS IS NOT ALLOWED IAW THE DWG REQUIREMENTS. HEAT EXCHANGER ASSEMBLIES INSTALLED ON THE FOLLOWING ACFT S/N`S ARE AFFECTED: 869
- [SDR 2014FA0000157](https://openairdocs.org/sdr/2014FA0000157.md): Bolt · loose · Mar 13, 2014 · Dhav DHC6 · Fuselage, Landing Gear Attach Fittings
  > DURING REMOVAL OF MLG ASSEMBLIES, SEVERAL MOUNTING BOLTS WERE FOUND LOOSE AND BACKED OFF, CAUSING DAMAGE TO ADJACENT STRUCTURE.
- [SDR CA140313015](https://openairdocs.org/sdr/CA140313015.md): Squib · misinstalled · Jan 14, 2014 · Dhav DHC6* · Fire Protection System Wiring
  > (CAN) DURING FIRST EMMA INSPECTIONS, RT FIRE EXTINGUISHER SQUIB FOUND WIRED BACKWARD. DURING TEST PRESSING THE FIRE BOTTLE BUTTON ONLY RESULTED IN A BREAKER POPPING.
- [SDR CA131209009](https://openairdocs.org/sdr/CA131209009.md): Bearing · failed · Dec 9, 2013 · Dhav DHC6 · Trailing Edge Flaps
  > (CAN) SRM FOR THE ACFT SPECIFICALLY STATES THAT STAKING BEARINGS IN HINGE ARMS IS NOT ALLOWED. IT HAS COME TO OUR ATTENTION THAT THIS SEEMS TO BE A SOMEWHAT STANDARD PRACTICE. IT`S UNKNOWN AT THIS TIME HOW MANY ACFT ARE AFFECTED.
- [SDR CA130923017](https://openairdocs.org/sdr/CA130923017.md): Pressure Switch · burned · Sep 20, 2013 · Dhav DHC6* · Hydraulic System, Main
  > (CAN) DURING CRUISE WHEN THE CREW SMELLED SMOKE. THERE WAS NO IMMEDIATE CAS MESSAGE THAT ANYTHING WAS WRONG BUT IT SOON DISPLAYED THAT THE HYDRAULIC PUMP AAT-600-029-100-1 WAS OVERHEATING. THE CREW PULLED THE APPROPRIATE C/B AND THE SMOKE ABATED. UPON LANDING
- [SDR CA130819019](https://openairdocs.org/sdr/CA130819019.md): Bulkhead · gouged · Aug 16, 2013 · Dhav DHC6* · Propeller Spinner Section
  > (CAN) RIGHT PROPELLER HAS LIGHT GOUGE MARKS ON THE PROPELLER SIDE OF THE PROPELLER SPINNER MOUNTING PLATE. ACFT MFG IS IN CONTACT WITH THE PROPELLER MANUFACTURE.
- [SDR CA130724010](https://openairdocs.org/sdr/CA130724010.md): Flapper Valve · obstructed · Jul 22, 2013 · Dhav DHC6* · Fuel Storage
  > (CAN) UPON INSPECTION OF THE FLAPPER VALVE IN CELL NR 5 A PORTION OF THE RETAINING CHAIN FOR FUEL CAP P/N 38040-1 WAS FOUND WEDGED IN THE FLAPPER KEEPING IT FROM SEALING AGAINST THE SUMP PLATE. VIKING IS INVESTIGATING.
- [SDR CA130717010](https://openairdocs.org/sdr/CA130717010.md): Valve · damaged · Jun 21, 2013 · Dhav DHC6* · Engine Oil Cooler
  > (CAN) VTS HAS REPORTED THAT FRETTING DAMAGE HAS BEEN FOUND ON THE VALVES INSTALLED IN THE OIL COOLER.
- [SDR CA130610015](https://openairdocs.org/sdr/CA130610015.md): Line · leaking · Jun 9, 2013 · Dhav DHC6* · Aircraft Fuel Distribution System
  > (CAN) THE PILOTS NOTICED A FUEL ODOR IN THE CABIN THAN NOTIFIED MAINTENANCE. THE CABIN ODOR WAS THE RESULT OF A LEAKING FUEL LINE LOCATED IN THE FUEL GALLEY AREA. THE PROBLEM WAS LOCATED IN FUEL BAY 5 FWD PUMP, WHICH WAS A RESULT FROM ARCING AT BOTH THE FUEL
- [SDR CA130613009](https://openairdocs.org/sdr/CA130613009.md): Rod · damaged · Jun 7, 2013 · Dhav DHC6* · Trailing Edge Flap Control System
  > (CAN) IT HAS BEEN FOUND THAT THE C6CW1083-1 FLAP ROD WAS FOUND SCUFFED AND FOULING ON ROOT RIB C6W1035-15/16. MFG IS CONTINUING TO INVESTIGATE.
- [SDR CA130611002](https://openairdocs.org/sdr/CA130611002.md): Piston · damaged · Jun 7, 2013 · Dhav DHC6 · Nose/Tail Landing Gear Strut/Axle
  > (CAN) DURING ROUTINE MAINTENANCE OF A NOSE GEAR PN 71-100-31, SN HS033 SUBASSEMBLY PN 71-300-29, IT WAS DISCOVERED THAT THE FLOATING PISTON ASSY PN 71-332-1 WAS MISSING PARTS OF THE GREEN COATING MATERIAL. SOME OF THE PIECES OF THE MATERIAL WERE LOCATED IN TH
- [SDR CA130510002](https://openairdocs.org/sdr/CA130510002.md): Filter · shorted · May 9, 2013 · Dhav DHC6* · Fuel System Wiring
  > (CAN) DURING A TRAINING FLIGHT, THE NR 1 FORWARD BOOST PUMP FAILED, AND THE PILOT NOTIFIED MAINTENANCE, ABOUT THIS FAULT. IT WAS FOUND THE NR 1 FWD BOOST PUMP NOISE FILTER PN A.3210 HAD SHORTED OUT AND NR 2 PUMP NOISE FILTER CONNECTION WAS ABOUT TO FAIL. TH
- [SDR CA130430020](https://openairdocs.org/sdr/CA130430020.md): Roller · worn · Apr 30, 2013 · Dhav DHC6 · Trailing Edge Flap Control System
  > (CAN) IT WAS DETERMINED THIS WEAR WAS THE RESULT OF THE FLAP ROLLERS P/N C6CWM1072-29, ALLOWING TOO MUCH FORE AND AFT MOVEMENT WHEN FLAPS WERE FULLY EXTENDED. NEW FLAP RODS P/N C6CW1083-1 INSTALLED AND ROLLERS ADJUSTED ACCORDINGLY. THERE WAS AN MRO FINDING RE
- [SDR CA130419008](https://openairdocs.org/sdr/CA130419008.md): Attach Fitting · corroded · Apr 19, 2013 · Dhav DHC6* · Fuselage Main, Attach Fittings
  > (CAN) RECEIVING INSPECTION DEPARTMENT HAS FOUND, SOME TRACE AMOUNTS OF SURFACE CORROSION, IN 1 BORE OF THE C6WM1741-27 PIN, WING TO FUSE ATTACHMENT. REAR SPAR. MFG IS CONTINUING TO INVESTIGATE.
- [SDR CA130422013](https://openairdocs.org/sdr/CA130422013.md): Shaft · failed · Apr 17, 2013 · Dhav DHC6* · Trailing Edge Flap Control System
  > (CAN) DURING THE CHECK FLIGHT TURNING FINALS FOR LANDING, SET 10 FLAPS THEN PILOT FLYING CALLED FOR 20 FLAPS. WHEN 20 WAS SELECTED AND RUNNING HEARD A BANG/SNAP SOUND FROM THE OVERHEAD CABIN ROOF. CONTINUED THE APPROACH AND LANDING WITHOUT FURTHER INCIDENT.
- [SDR CA130412017](https://openairdocs.org/sdr/CA130412017.md): Switch · failed · Apr 2, 2013 · Dhav DHC6* · Propeller Feathering/Reversing
  > (CAN) PILOT ENCOUNTERED LT AUTOFEATHER ACTIVATION WHEN REDUCING TO CLIMB POWER SETTING. PILOT RESUMED TO POWER LEVER SETTING AND PROP UNFEATHERED. PILOT SHUTOFF AUTOFEATHER SYS. UN COMMANDED AUTOFEATHER ACTIVATION WAS TROUBLESHOT TO UNSERVICEABLE LT AUTO-FE
- [SDR CA130410016](https://openairdocs.org/sdr/CA130410016.md): Valve Stem · gouged · Mar 27, 2013 · Dhav DHC6* · Wheel/Ski/Float
  > (CAN) MFG PRODUCTION HAS REPORTED THAT THE LT AND RT MAIN WHEEL ASSY OTBD WHEEL HALF, PN 040-21101 VALVE STEMS GOUGING DAMAGE. MFG IS CONTINUING TO INVESTIGATE. UPON INSPECTION OF NEW COMPONENTS IN INVENTORY THE VALVE STEM WAS FOUND DAMAGED AS DELIVERED BY TH
- [SDR CA130221012](https://openairdocs.org/sdr/CA130221012.md): Pulley · damaged · Feb 18, 2013 · Dhav DHC6* · Rudder Tab Control System
  > (CAN) VPS 20.03 REQUIRES THAT FPI BE PERFORMED BEFORE ANY SURFACE TREATMENT WHICH COULD RESULT IN OBSCURING OF CRACKS. VPS 20.03 DOES ALLOW FPI TO BE PERFORMED AFTER METAL SMEARING OPERATIONS PROVIDED THE PARTS ARE DEOXIDIZE ETCHED PRIOR TO FPI TO REMOVE A MI
- [SDR CA130215013](https://openairdocs.org/sdr/CA130215013.md): Rod · damaged · Feb 15, 2013 · Dhav DHC6* · Standard Practices/Structures
  > (CAN) VPS 20.03, REQUIRES THAT FPI BE PERFORMED BEFORE ANY SURFACE TREATMENT WHICH COULD RESULT IN OBSCURING OF CRACKS. VPS 20.03 DOES ALLOW FPI TO BE PERFORMED AFTER METAL SMEARING OPERATIONS PROVIDED THE PARTS ARE DEOXIDIZE ETCHED PRIOR TO FPI TO REMOVE A M
- [SDR CA130201008](https://openairdocs.org/sdr/CA130201008.md): Fairing · damaged · Jan 28, 2013 · Dhav DHC6* · Aerodynamic Fairings
  > (CAN) DAMAGE WAS CAUSED BY THE OIL TUBE BONDING LEAD ATTACHMENT BOLT WHICH WAS POSITIONED IN A MANNER THAT RESULTED IN CONTACT WITH THE FAIRING RESULTING IN A SMALL HOLE BEING CHAFED IN THE FAIRING. MFG ENGINEERING IS INVESTIGATING.
- [SDR CA130128027](https://openairdocs.org/sdr/CA130128027.md): Connector · unsecure · Jan 28, 2013 · Dhav DHC6* · Electrical Power System Wiring
  > (CAN) THERE ARE CONCERNS THAT AT BS 55, CONNECTOR P34 MAY NOT FULLY ENGAGE WITH THE MATING CONNECTOR J34 DUE TO POSSIBLE INTERFERENCE WITH THE FASTENER HEADS SECURING CONNECTOR J34. SYS WIRES ROUTED THROUGH P34 CONNECTOR CONSIST OF THE, PROPELLER OVERSPEED GO
- [SDR CA121221014](https://openairdocs.org/sdr/CA121221014.md): Latch · damaged · Dec 18, 2012 · Dhav DHC6* · Nacelle/Pylon, Main Frame
  > (CAN) MFG HAS FOUND, DURING PRODUCTION INSPECTIONS, THAT THERE EXISTS A POSSIBILITY THAT THE PIVOT PIN IN COWL LATCH, PN C6EC1002-95 CAN BECOME DISLODGED FROM THE LATCH HOUSING. MFG IS IN THE PROCESS OF NOTIFYING THE OPERATING FLEET OF THIS SITUATION.
- [SDR CA121217010](https://openairdocs.org/sdr/CA121217010.md): Connector · unknown · Dec 14, 2012 · Dhav DHC6* · Electrical Power System Wiring
  > (CAN) MFG ENGINEERING HAS DETERMINED THAT THERE ARE RELAYS DO NOT HAVE VOLTAGE SUPRESSION. AS A RESULT THERE EXISTS THE POTENTIAL FOR THE GIO CARD TO BE SUBJECTED TO VOLTAGE SPIKES THAT EXCEED THE 50VDC DESIGN LIMIT, THIS WILL RESULT IN THE FAILURE OF THE GIO
- [SDR CA121213010](https://openairdocs.org/sdr/CA121213010.md): Valve · misinstalled · Dec 12, 2012 · Dhav DHC6* · Pitot/Static System
  > (CAN) THERE IS A POSSIBILITY THAT THE STATIC SWITCH VALVE AND STATIC VALVE HANDLE HAVE BEEN INSTALLED INCORRECTLY ON SOME ACFT. IF INSTALLED INCORRECTLY, THE VALVE WOULD OPERATE AS FOLLOWS: THE VALVE HANDLE WOULD INDICATE NORMAL SOURCE WHEN THE VALVE IS IN THE
- [SDR CA121121007](https://openairdocs.org/sdr/CA121121007.md): Bushing · mismanufactured · Nov 19, 2012 · Dhav DHC6 · Main Landing Gear Attach Section
  > (CAN) THE VENDOR THAT SUPPLIES BUSHING, HAS NOTIFIED MFG THAT 2 BATCHES OF THE BUSHING WERE NOT HEAT TREATED TO THE FINAL HARDNESS SPECIFICATION AS REQUIRED IAW THE MFG DWG.
- [SDR CA121122009](https://openairdocs.org/sdr/CA121122009.md): Module · malfunctioned · Nov 16, 2012 · Dhav DHC6 · Weather Radar System
  > (CAN) WEATHER RADAR SYSTEM DISPLAYS: WX FAIL MESSAGE ON PILOTS PFD. REPLACED AGM MODULE NR 1 IN MODULAR AVIONICS UNIT.
- [SDR CA121114013](https://openairdocs.org/sdr/CA121114013.md): Power Lever · fouled · Nov 9, 2012 · Dhav DHC6 · Power Lever
  > (CAN) PRODUCTION NOTED THAT DURING RIGGING OF THE LT POWER LEVER THE STOP BOLT WAS CONTACTING THE ADJACENT STRUCTURE WHEN THE BOUNCE GAP OF 0.80, 0.120. REQUIRED BY DWG C6EC1007 WAS ACHIEVED. MFG ENGINEERING IS INVESTIGATING FURTHER.

Next page: https://openairdocs.org/model/boeing-dhc-6/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 = 'DHC6'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/boeing-dhc-6/reports

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