# Dehavilland DHC2 MK1 (L20A)

- Type: Aircraft model (FAA registry)
- Registry code: 2808008
- Manufacturer (registry): DEHAVILLAND
- Model: DHC2 MK1 (L20A)
- Aircraft type: Fixed wing single engine
- Category: Airplane
- Engines: 1 · Turbo-prop
- Seats: 8
- Weight class: Up to 12,499 lb
- Certification: Type certificated
- Registered aircraft: 0
- Page: https://openairdocs.org/model/dehavilland-dhc2-mk1-l20a

Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker.

## ADs that may apply (OpenAirDocs)

Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment.

None matched.

## Registered aircraft

None registered with this model now.

## NTSB investigations

None matched to aircraft with this model.

## FAA accident and incident reports

None matched to aircraft with this model.

## Service difficulty reports (244, newest 50)

As reported by operators and repair stations, by the model named in the report.

- [SDR 2023FA0000538](https://openairdocs.org/sdr/2023FA0000538), Sep 13, 2023: MAGNETO. NO INDICATION. PILOT TOOK OFF AND BELIEVED TO HAVE ENTERED A POWERFUL DOWN DRAFT, THE PLANE WAS NOT CLIMING AS IT SHOULD, HE APPLIED FULL POWER (VS TAKE OFF POWER). AFTER CLEA
- [SDR 2023F00243](https://openairdocs.org/sdr/2023F00243), Jul 11, 2023: BOLT. BROKEN. BRAKE CALIPER SEPARATION FROM TORQUE PLATE ON LANDING DUE TO UNEXPLAINED BREAKAGE OF ANCHOR BOLT (PN 069-01900).
- [SDR 2023F00013](https://openairdocs.org/sdr/2023F00013), Jan 3, 2023: OIL COOLER. MISMANUFACTURED. AFTER REPLACEMENT OF ENGINE OIL COOLER, OIL TEMPERATURE WOULD NOT RISE TO OPERATING TEMPERATURE. DISCOVERED REPLACEMENT COOLER WAS MANUFACTURED INCORRECTLY WITH
- [SDR 2021FA0000134](https://openairdocs.org/sdr/2021FA0000134), Apr 20, 2021: SPAR. DAMAGED. DURING THE ANNUAL INSPECTION A DISCREPANCY WAS MADE TO PULL OFF GROSS WEIGHT KIT RIGHT WING TO REMOVE WING STRAP OVER SPAR DUE TO A GAP AT ONE OF THE TAPPERED E
- [SDR 2021FA0000129](https://openairdocs.org/sdr/2021FA0000129), Apr 7, 2021: FLOORBOARD. DAMAGED. PILOT SIDE FRONT FLOOR BOARD BOWED/WARPED/SAGGED CAUSING POOR SEAT PIN LOCK PIN ENGAGEMENT.
- [SDR 2020F00364](https://openairdocs.org/sdr/2020F00364), Jul 19, 2019: TIE ROD. FAILED. FORWARD LT LOWER TIE-ROD (FLYING WIRE) WIRE-PULL ATTACHMENT FAILED. THE AFT RT UPPER TIE-ROD (FLYING WIRE) WIRE-PULL ATTACHMENT FAILED. THE AIRCRAFT'S RIGIDITY 
- [SDR ERHA2019F00038](https://openairdocs.org/sdr/ERHA2019F00038), Sep 1, 2018: CYLINDER HEAD. SEPARATED. THE CYLINDER HEAD SEPARATED FROM THE BARREL ON CYLINDER NR 9.
- [SDR ERHA2017053100002](https://openairdocs.org/sdr/ERHA2017053100002), May 7, 2017: G SWITCH. NO TEST. ELT G SWITCH FAIED DURING SCHEDULED MAINTENANCE.
- [SDR ERHA09022106](https://openairdocs.org/sdr/ERHA09022106), Aug 31, 2016: CYLINDER HEAD. SEPARATED. NR 1 CYLINDER HEAD SEPARATION, PRECAUTIONARY LANDING RESULTING IN NO OTHER DAMAGE.
- [SDR 2016FA0000353](https://openairdocs.org/sdr/2016FA0000353), Jul 30, 2016: NUT. DAMAGED. PILOT REPORTED A VIBRATION FROM THE ENGINE OR PROP. ON VISUAL INSPECTION, THE NR 3 PROPELLER BLADE SLIPPAGE INDICATION TAPE WAS FOUND TO BE BROKEN AND THE BLADE
- [SDR 2016F00151](https://openairdocs.org/sdr/2016F00151), Jul 20, 2016: PUSHROD. BROKEN. DURING CRUISE FLIGHT, ENGINE LOST PARTIAL POWER. PILOT TURNED AROUND TO RETURNED, COULD NOT MAINTAIN ALTITUDE, AND LANDED. DURING TAXIING THE ENGINE DIED. PILOT
- [SDR P9KA2016032301](https://openairdocs.org/sdr/P9KA2016032301), Mar 23, 2016: SHAFT. BROKEN. THE PILOT OF THE FLOAT-EQUIPPED ACFT DEPARTED ON A VFR CROSS COUNTRY FLIGHT. AS THE REAR TANK APPROACHED EMPTY, MOVED THE FUEL SELECTOR TO THE FRONT TANK POSITI
- [SDR P9KA2015103003](https://openairdocs.org/sdr/P9KA2015103003), Oct 28, 2015: ELT. INOPERATIVE. DURING A ROUTINE ELT INSPECTION IAW 14 CFR 91.207, THE G SWITCH WAS FOUND TO BE INOPERATIVE. THIS IS A RECURRING PROBLEM WITH THESE BEACONS.
- [SDR P9KA2015103002](https://openairdocs.org/sdr/P9KA2015103002), Oct 1, 2015: ELT. INOPERATIVE. DURING A ROUTINE ELT INSPECTION IAW 14 CFR 91.207, THE ELT G SWITCH WAS FOUND TO BE NON-FUNCTIONAL. THIS IS A RECURRING PROBLEM WITH THESE BEACONS.
- [SDR RI9A20150825002](https://openairdocs.org/sdr/RI9A20150825002), Aug 21, 2015: CYLINDER. FAILED. ROUGHNESS FELT DURING FLIGHT COMING FROM THE ENG. NR 2 CYLINDER FAILED.
- [SDR 2015FA0000383](https://openairdocs.org/sdr/2015FA0000383), Aug 18, 2015: FITTING. CORRODED. A FITTING IN THE LT FLOAT HYDRAULIC DISTRIBUTION BLOCK DEVELOPED A HOLE CAUSED BY CORROSION AND FAILED. THIS IN-TURN CAUSED THE HYDRAULIC FLUID TO ESCAPE AND UL
- [SDR P9KA20150113001](https://openairdocs.org/sdr/P9KA20150113001), Jan 13, 2015: O-RING. DAMAGED. AS THE AMPHIBIOUS FLOAT EQUIPPED ACFT CONDUCTED ITS LANDING APPROACH, THE PILOT ATTEMPTED TO EXTEND THE LG. BOTH MLG EXTENDED & BOTH NLG REMAINED RETRACTED. THE
- [SDR 2014F00137](https://openairdocs.org/sdr/2014F00137), Jul 21, 2014: STUD. FAILED. THREE MINUTES AFTER TAKEOFF, THE PILOT EXPERIENCED A LOSS OF POWER AND SLIGHT OIL ON THE WINDSHIELD IN HIS FLOAT EQUIPED ACFT. RETURNED TO THE WATER TAKEOFF ARE
- [SDR JKGC2013080701](https://openairdocs.org/sdr/JKGC2013080701), Aug 5, 2013: OIL SYSTEM. UNKNOWN. ENGINE OIL TEMPERATURE RISING AND ENGINE OIL PRESSURE DROPPING.
- [SDR J4HC2013F00112](https://openairdocs.org/sdr/J4HC2013F00112), Jun 27, 2013: EXHAUST STACK. BURNED. EXHAUST SEGMENTS BURNED THROUGH, CONTRIBUTING TO HIGHER THAN NORMAL INTAKE AIR TEMP RESULTING IN REDUCTION OF POWER DETECTED AT RUN UP.
- [SDR 2012F00149](https://openairdocs.org/sdr/2012F00149), Jul 22, 2012: ENGINE. SEIZED. DURING TAKEOFF ONCE THE AIRCRAFT REACHED 100 FT, THE ENGINE SEIZED. PILOT MADE AN EMERGENCY LANDING BACK AT AIRPORT. ENGINE WAS REMOVED AND ANOTHER INSTALLED. O
- [SDR ERHA20120619002](https://openairdocs.org/sdr/ERHA20120619002), Jun 14, 2012: CYLINDER HEAD. CRACKED. ENGINE CYLINDER HEAD IN THE NR 2 POSITION CRACKED, IN FLIGHT, CAUSING ENGINE ROUGHNESS AND PARTIAL POWER LOSS. PILOT MADE EMERGENCY LANDING OFF AIRPORT.
- [SDR ERHA20120619001](https://openairdocs.org/sdr/ERHA20120619001), Jun 14, 2012: CYLINDER HEAD. CRACKED. ENGINE CYLINDER HEAD IN THE NR 2 POSITION CRACKED, IN FLIGHT, CAUSING ENGINE ROUGHNESS AND PARTIAL POWER LOSS. PILOT MADE EMERGENCY LANDING OFF AIRPORT.
- [SDR P9KA2012F00065](https://openairdocs.org/sdr/P9KA2012F00065), Mar 14, 2012: CONTROL QUADRANT. CRACKED. EDO AMPHIBIOUS 4580 FLOATS, FOUND NOSE GEAR CONTROL QUADRANT, LOWER END WHERE THE CABLE ROUTS AROUND THE QUADRANT A CRACK THAT FORMED AT THE CABLE END AND RAN T
- [SDR TQ0A2012F00048](https://openairdocs.org/sdr/TQ0A2012F00048), Feb 2, 2012: PUSH-PULL ROD. CORRODED. PUSH/PULL TUBE WAS REMOVED FROM THE ACFT DURING AN ANNUAL INSPECTION AND WAS FOUND TO HAVE SEVERE PITTING AND HOLES THRU THE TUBE. FOUND THE ALUMINUM WAS SEVERL
- [SDR P9KA2011F00167](https://openairdocs.org/sdr/P9KA2011F00167), Jul 20, 2011: EXHAUST VALVE. CRACKED. ON ENGINE SHUTDOWN A SUCKING SOUND WAS HEARD AS ENGINE DIED. CYLINDER COMPRESSION CHECK WAS 0/80. AFTER STAKING THE VALVE THE COMPRESSION WAS STILL 0/80. AIR WA
- [SDR LAO2010F00000](https://openairdocs.org/sdr/LAO2010F00000), Mar 19, 2010: ROD. CORRODED. ELEVATOR CONTROL ROD ASSY WAS REMOVED FROM ACFT DURING AN ANNUAL INSPECTION. UPON INSPECTION A SMALL HOLE WAS FOUND AT THE AFT END OF THE ROD IN THE LOWER WALL 
- [SDR H0VC1](https://openairdocs.org/sdr/H0VC1), Feb 1, 2010: CYLINDER. BROKEN. NR 2 CYLINDER BROKE FREE FROM ENGINE CASE.
- [SDR CA071214003](https://openairdocs.org/sdr/CA071214003), Dec 14, 2007: CABLE. CORRODED. (CAN) FUEL SELECTOR CABLE VERY BADLY CORRODED, CABLE FAILED WHEN REMOVED. NO LOG BOOKS OR RECORDS AVAILABLE. (TC NR 20071214003)
- [SDR 2006FA0000122](https://openairdocs.org/sdr/2006FA0000122), Dec 15, 2005: TRANSCEIVER. MALFUNCTIONED. DURING POST INSTALLATION CHECKS, FOUND THE GDL90 UAT REPORTING CONTINUOUS EXTERNAL FAULT ERROR. NO EXTERNAL FAULTS FOUND. REPLACEMENT OF THE UNIT CORRECTED THE 
- [SDR 2005FA0001633](https://openairdocs.org/sdr/2005FA0001633), Nov 15, 2005: MOUNT. CRACKED. DURING THE REPLACEMENT OF THE AIR DATA COMPUTER. FOUND THE MOUNTING TRAY ASSY CRACKED COMPLETELY ACROSS ON THE OPPOSITE END OF THE THUMBSCREW. AIRCRAFT IS CONFI
- [SDR TQ0A20050001](https://openairdocs.org/sdr/TQ0A20050001), May 16, 2005: ENGINE. SEIZED. ENGINE SEIZURE DURING CLIMB-OUT. VISUAL INSPECTION OF ENGINE OIL SCREEN AND SUMPS REVEALED STEEL PARTICLES.
- [SDR 200501306](https://openairdocs.org/sdr/200501306), Jan 24, 2005: RACK. CRACKED. DURING THE REMOVAL OF THE AIR DATA COMPUTER FOUND TRAY CRACKED AT EACH CORNER OF THE THUMBSCREW CUTOUT AT THE BEND RADII.
- [SDR 200501305](https://openairdocs.org/sdr/200501305), Jan 24, 2005: TRANSMITTER. INOPERATIVE. FUEL FLOW TRANSDUCER HAS NO OUTPUT SIGNAL.
- [SDR 2004F00437](https://openairdocs.org/sdr/2004F00437), Dec 21, 2004: MOUNT. CRACKED. DURING A SCHEDULED INSPECTION, FOUND THE AIR DATA COMPUTER (ADC) BROKE LOOSE FROM ITS MOUNT. UPON FURTHER INVESTIGATION FOUND THE MOUNTING BRAKET FLANGE CRACKED
- [SDR 2004F00436](https://openairdocs.org/sdr/2004F00436), Dec 21, 2004: ADC. INACCURATE. AIR DATA COMPUTER (ADC) INSTALLED AS PART OF THE CHELTON FLIGHT SYSTEMS EFIS-SV SYSTEM UNDER STC SA02203AK REPORTING 500' ALTITUDE ERROR.
- [SDR 2005FA0000070](https://openairdocs.org/sdr/2005FA0000070), Sep 13, 2004: TRANSDUCER. MALFUNCTIONED. REMOVED FUEL FLOW TRANSDUCER (PN 660526AS) INSTALLED UNDER STC SA809GL. UNIT PROVIDING ERRONEOUS FULE FLOW READINGS AND CAUSING THE AIR DATA COMPUTER (ADC) ALSO
- [SDR 2004FA0000864](https://openairdocs.org/sdr/2004FA0000864), Sep 13, 2004: TRANSDUCER. MALFUNCTIONED. REMOVED FUEL FLOW TRANSDUCER, INSTALLED UNDER STC NR SA809GL. UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AND CAUSING THE AIR DATA COMPUTER (ADC) ALSO INSTALLED
- [SDR 2004FA0000863](https://openairdocs.org/sdr/2004FA0000863), Sep 13, 2004: TRANSDUCER. MALFUNCTIONED. REMOVED FUEL FLOW TRANSDUCER INSTALLED UNDER STC NR SA809GL. UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AND CAUSING THE AIR DATA COMPUTER (ADC) ALSO INSTALLED 
- [SDR 2004FA0000862](https://openairdocs.org/sdr/2004FA0000862), Sep 13, 2004: TRANSDUCER. MALFUNCTIONED. REMOVED FUEL FLOW TRANSDUCER PN 660526AS INSTALLED UNDER STC NR SA809GL. UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AND CAUSING THE AIR DATA COMPUTER (ADC) ALS
- [SDR HJB2004F00001](https://openairdocs.org/sdr/HJB2004F00001), Sep 13, 2004: TRANSDUCER. MALFUNCTIONED. REMOVED FUEL FLOW TRANSDUCER INSTALLED UNDER STC NR 809GL. UNIT PROVIDING ERRONEOUS FUEL FLOW READINGS AND CAUSING THE AIR DATA COMPUTER (ADC) ALSO INSTALLED IN
- [SDR GJR2004F00002](https://openairdocs.org/sdr/GJR2004F00002), Sep 1, 2004: PUMP. INOPERATIVE. LOSS OF FUEL PRESSURE.
- [SDR GJR2004F00001](https://openairdocs.org/sdr/GJR2004F00001), Sep 1, 2004: PUMP. INOPERATIVE. LOSS OF FUEL PRESSURE.
- [SDR GJR2004F00000](https://openairdocs.org/sdr/GJR2004F00000), Sep 1, 2004: PUMP. FAILED. LOSS OF FUEL PRESSURE.
- [SDR 2004FA0000943](https://openairdocs.org/sdr/2004FA0000943), Jul 29, 2004: TRANSDUCER. INOPERATIVE. FUEL FLOW TRANSDUCER INOPERATIVE-NOT PROVIDING SIGNAL TO IDU.
- [SDR CA040713004](https://openairdocs.org/sdr/CA040713004), Jun 30, 2004: BOLT. WORN. (CAN) DURING SCHEDULED INSPECTION RT ELEVATOR FOUND SLIGHTLY LOOSE AT TORQUE TUBE. NUT COULD NOT BE TIGHTENED DUE TO EXCESSIVELY WORN BOLT AW4-6. BOLT REPLACED 
- [SDR CA040622002](https://openairdocs.org/sdr/CA040622002), Jun 8, 2004: BRACKET. CRACKED. (CAN) LT FLOAT REAR DOCK FITTING SADDLE BRACKETS CRACKED AT BOLT HOLES.
- [SDR 2004FA0000832](https://openairdocs.org/sdr/2004FA0000832), Mar 24, 2004: DISPLAY. MALFUNCTIONED. FOLLOWING THE INSTALLATION OF THE EFIS-SV SYSTEM, THE SOFTWARE WAS LOADED ONTO A SMART MEDIA CARD AND THE SMART MEDIA CARD WAS INSERTED INTO THE INTEGRATED DISP
- [SDR CA040213011](https://openairdocs.org/sdr/CA040213011), Feb 10, 2004: ANTENNA. BROKEN. (CAN) ELT ANTENNA FOUND BROKEN AT THE BASE OF THE ANTENNA MOUNTING FLANGE (EXTERNAL).
- [SDR CA040213010](https://openairdocs.org/sdr/CA040213010), Feb 10, 2004: JACKSCREW. CORRODED. (CAN) MINOR CORROSION NOTED ON THE EXTERNAL SURFACE OF THE TRIM DRUM (CABLE GROOVES EXFOLIATING NEAR THE CABLE INDEX PIN) ON REMOVAL OF THE TRIM DRUM SCREW ASSE

All 244: https://openairdocs.org/model/dehavilland-dhc2-mk1-l20a/reports.md

## The same model under other registry codes

Amateur-built copies and renamed makers get their own codes.

- [Dehavilland DHC-2 MK 1](https://openairdocs.org/model/dehavilland-dhc-2-mk-1): 41 registered aircraft, registry code 2808006
- [Dehavilland DHC-2 MK 1](https://openairdocs.org/model/dehavilland-dhc-2-mk-1): 4 registered aircraft, registry code 2808011
- [Dehavilland Acft Of Canada DHC-2 MK 1](https://openairdocs.org/model/dehavilland-acft-of-canada-dhc-2-mk-1): 3 registered aircraft, registry code 2805075
- [Dehavilland/St Cloud Avn DHC-2 MK 1](https://openairdocs.org/model/dehavilland-st-cloud-avn-dhc-2-mk-1): 1 registered aircraft, registry code 2804003
- [Dehavilland/Lake Union Air DHC2 MK1](https://openairdocs.org/model/dehavilland-lake-union-air-dhc2-mk1): 1 registered aircraft, registry code 2805002
- [Dehavilland DHC-2 MK-1 (L-20)](https://openairdocs.org/model/dehavilland-dhc-2-mk-1-l-20): 1 registered aircraft, registry code 2808009

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