# Service difficulty reports: Continental IO-470 series

A list on [Continental IO-470 series](https://openairdocs.org/engine/continental-io-470-series.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 3 · 105 reports

- [SDR 2023FA0000199](https://openairdocs.org/sdr/2023FA0000199.md): Flow Divider · perforated · Apr 6, 2023 · N6922L · Cessna 310K · Engine Fuel and Control
  > THE FLOW DIVIDER ON TOP OF THE ENGINE AT THE SPINE HAS A SMALL COMPENSATION HOLE ABOVE THE DIAPHRAGM. IF THE DIAPHRAGM HAS A PERFORATION, RAW FUEL WILL RISE ABOVE THE DIAPHRAGM AND SPEW FROM THIS HOLE AND THUS CAUSE AND EXTREME FIRE HAZARD. I HAVE OBSERVED THI
- [SDR 2023FA0000180](https://openairdocs.org/sdr/2023FA0000180.md): Fairing · unknown · Mar 29, 2023 · N6922 · Cessna 310K · Standard Practices/Structures
  > SCREW TO HOLD FAIRING BETWEEN WING AND TIP TANK TOO LONG AND POSSIBLE PENETRATING / RUBBING ON FUEL TANK. THE INNER AERODYNAMIC FAIRING BETWEEN TIP TANK AND UPPER SURFACE OF WING HAS A TINNERMAN NUT PLATE TO CONNECT TO ANOTHER FAIRING. SCREWS IN THIS NUT PLATE
- [SDR 2022FA0000275](https://openairdocs.org/sdr/2022FA0000275.md): Vacuum Sys · failed · May 20, 2022 · N955RH · Beech 95B55 · Fuselage Structure (General)
  > TWO VACUUM PUMPS WERE INSTALLED AT ENGINE CHANGE THEY BOTH FAILED AT 25 HOURS PUMPS WERE PURCHASED FROM MCFARLAND AVIATION ON 2/8/22 MCFARLAND INVOICE 0453567-IN
- [SDR 2022FA0000276](https://openairdocs.org/sdr/2022FA0000276.md): Vacuum Sys · failed · May 20, 2022 · N955RH · Beech 95B55 · Fuselage Structure (General)
  > TWO VACUUM PUMPS WERE INSTALLED AT ENGINE CHANGE. THEY BOTH FAILED IN UNDER 25 HOURS. BOTH INTERNAL FAILURES. SHEARING THE DRIVE COUPLING. BOTH PURCHASED FROM MAFARLANE AVIATION ON 2/8/22. INVOICE 0453567IN.
- [SDR 2019FA0000089](https://openairdocs.org/sdr/2019FA0000089.md): Actuator Cable · unsecure · Mar 24, 2019 · N95BA · Beech 95B55 · Power Lever
  > DURING ANNUAL INSPECTION HEIM JOINT USED TO CONNECT THROTTLE CABLE TO THROTTLE BODY WAS FOUND TO BE PARTIALLY UNSCREWED FROM THROTTLE CABLE. THE WITNESS HOLE ALLOWED A WIRE TO PASS THROUGH, INDICATING INSUFFICIENT ATTACHMENT.
- [SDR 2016FA0000248](https://openairdocs.org/sdr/2016FA0000248.md): Rod · failed · May 17, 2016 · N555ZZ · Beech T34A · Landing Gear Retraction/Extension System
  > AFTER GEAR DROP, LT MAIN SHOWED DOWN, LOCKED, RT MAIN SHOWED UNSAFE AND NOSE WHEEL UNSAFE. ACFT LANDED AFTER TOWER REPORTED THE GEAR APPEARED DOWN. AT END OF ROLLOUT, ACFT STARTED A RT DRIFT AND A RT WING STARTED TO DROP. RIGHT GEAR FOLDED ONTO PARTIALLY
- [SDR 2015FA0000307](https://openairdocs.org/sdr/2015FA0000307.md): Tube · bent · Jun 16, 2015 · N2215F · Cessna 310L · Landing Gear Retraction/Extension System
  > LANDING GEAR WAS SELECTED DOWN AND EXTENDED AND THE PILOT FELT A STRANGE "CLUNK" UNDER HIS FEET. THE PILOT DID NOT GET A "GREEN" DOWN-AND-LOCKED INDICATION FOR THE NOSE GEAR. TOWER CONFIRMED NOSE GEAR WAS NOT DOWN. THE NOSE GEAR COLLAPSED UPON LANDING. SUB
- [SDR CA150616024](https://openairdocs.org/sdr/CA150616024.md): Support · damaged · Jun 16, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR CA150616026](https://openairdocs.org/sdr/CA150616026.md): Support · damaged · Jun 16, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR CA150616009](https://openairdocs.org/sdr/CA150616009.md): Support · damaged · Jun 15, 2015 · Cessna 182P · Elevator Miscellaneous Structure
  > (CAN) AT FULL UP ELEVATOR, WITH THE ELEVATOR RIGGED WITHIN LIMITS, THE ARM ASSEMBLY IS CONTACTING THE SUPPORT ASSEMBLY CAUSING DAMAGE TO THE SUPPORT ASSEMBLY.
- [SDR 2015FA0000090](https://openairdocs.org/sdr/2015FA0000090.md): Battery Box · mismanufactured · Mar 17, 2015 · N2071W · Beech C35BEECH · Battery Box Structure
  > THE FACTORY ACFT BATTERY BOX WAS REPLACED DUE TO ACID DAMAGE CAUSING LEAKS WITH A STAINLESS STEEL BATTERY BOX. IT WAS OBSERVED THAT THE STAINLESS BATTERY BOX WAS LEAKING ACID ON THE FIREWALL AND DAMAGED WIRE IN A WIRE BUNDLE RUNNING UNDER THE BATTERY BOX. TH
- [SDR 2015FA0000063](https://openairdocs.org/sdr/2015FA0000063.md): Bearing · failed · Feb 17, 2015 · N9404Q · Beech 95B55 · Landing Gear Door Retract Section
  > PILOT REPORTED THAT HE HAD GREEN GEAR DOWN AND LOCKED LIGHTS PRIOR TO LANDING AND WHEN THE NOSE TOUCHED DOWN IT FOLDED. FOUND THAT THE AFT RETRACT ROD,ROD-END AT THE EXTENSION IDLER FAILED CAUSING THE COLLAPSE. ONLY MINOR AIRFRAME DAMAGE TO THE NOSE AND NOSE
- [SDR 2014FA0000640](https://openairdocs.org/sdr/2014FA0000640.md): Clamp · failed · Oct 29, 2014 · N3333T · Cessna 310H · Main Landing Gear Attach Section
  > WHILE TAXIING ON THE RUNWAY, RIGHT MAIN GEAR COLLAPSED, RESULTED IN MINOR DAMAGE. INVESTIGATION REVEALED A BROKEN MOUNTING CLAMP FROM THE GEAR STRUT TO THE ROLL PIN. UNABLE TO DETERMINE CAUSE OF CLAMP FAILURE, CLAMP WAS FRACTURED AT THE LAST THREAD AND WAS MI
- [SDR 2014FA0000670](https://openairdocs.org/sdr/2014FA0000670.md): Throttle Cable · failed · Aug 27, 2014 · N101JB · Cessna 310K · Power Lever
  > LEFT THROTTLE CABLE SEPARATED FROM STATIONARY SWEDGE IN THE ENGINE COMPARTMENT REDUCING ENGINE POWER DURING ROTATION PHASE OF A TOUCH AND GO PROCEDURE. ACFT HAD DIFFICULITY MAINTAINING A POSITIVE RATE OF CLIMB DUE TO REDUCED ENGINE POWER AND A HIGH DENSITY AL
- [SDR 2013FA0000219](https://openairdocs.org/sdr/2013FA0000219.md): Line · leaking · Mar 21, 2013 · N5852X · Cessna 310F · Fuel Storage
  > PILOT REPORTED FUEL ODOR IN CABIN. DURING THE ANNUAL INSPECTION, HEAVY FUEL STAINING WAS NOTED IN THE SPAR BOX AND IT WAS DETERMINED THAT THE RIGID FUEL CROSS FEED LINES THAT RUN THROUGH THE FUSELAGE, INSIDE OF THE MAIN SPAR BOX, HAD CORRODED INTERNALLY RESUL
- [SDR 2013FA0000135](https://openairdocs.org/sdr/2013FA0000135.md): Bearing · failed · Feb 28, 2013 · N1565Z · Beech P35 · Landing Gear Retraction/Extension System
  > THE PILOT STATED THAT DURING GEAR RETRACTION AFTER TAKEOFF, HE HEARD A LOUD BANG IN FRONT GEAR AREA. GEAR INDICATOR SHOWED UP AND LOCKED, NO FAILURE INDICATIONS. PRIOR TO LANDING, LOWERED THE LANDING GEAR AND HAD NORMAL GEAR DOWN AND LOCKED INDICATIONS. UPO
- [SDR 2012FA0000658](https://openairdocs.org/sdr/2012FA0000658.md): Rod Bolt · damaged · Sep 27, 2012 · N7348R · Beech T42A · Reciprocating Engine Power Section
  > ENGINE FAILURE APPEARS TO HAVE BEEN CAUSED BY 1 ROD BOLT WITH INDICATIONS OF BEACH MARKS.
- [SDR 2012FA0000600](https://openairdocs.org/sdr/2012FA0000600.md): Gear · damaged · Aug 30, 2012 · N8956Z · Cessna 310G · Landing Gear Retraction/Extension System
  > WEAR IN THE LAST 13 TEETH OF THE HELICAL GEAR ON THE RETRACT END OF GEAR. THERE IS A.02 TO.035 STEP ON THE THRUST SIDE OF THE GEAR. THIS IS ENOUGH TO JAMB THE WORM DRIVE RENDERING GEAR INOPERATIVE TO NORMAL EXTENSION OR HAND CRANK. PROBLEM APPEARS TO BE AS
- [SDR 2012FA0000540](https://openairdocs.org/sdr/2012FA0000540.md): Motor · failed · Jun 30, 2012 · N308RB · Beech 95B55 · Landing Gear Retraction/Extension System
  > LANDING GEAR MOTOR WOULD TRIP CIRCUIT BREAKER DURING ALL ATTEMPTS AT LOWERING LANDING GEAR. EMERGENCY PROCEDURES FOR LANDING GEAR EXTENSION FAILURE AND MANUAL GEAR EXTENSION UNSUCCESSFUL RESULTING IN A GEAR-UP LANDING. ON INSPECTION OF LANDING GEAR COMPONENT
- [SDR 2011FA0000591](https://openairdocs.org/sdr/2011FA0000591.md): Cylinder Head · separated · Sep 14, 2011 · N9870E · Cessna 182R · Reciprocating Engine Cylinder Section
  > CYLINDER HEAD SEPARATION.
- [SDR 2011FA0000510](https://openairdocs.org/sdr/2011FA0000510.md): Hub · cracked · Aug 4, 2011 · N99EF · Cessna 414A · Propeller Hub Section
  > REAR HUB HALF CONTAINS 12 INCH LONG CRACK RESULTING IN SEPARATION OF ONE BLADE SOCKET.
- [SDR 2011FA0000116](https://openairdocs.org/sdr/2011FA0000116.md): Structure · cracked · Feb 18, 2011 · N9893R · Beech M35 · Leading Edge Devices
  > PERFORMED INSP IAW SAFETY COMUNIQUE NR 313. FOUND RT FLAP L/E CRACKED (ABOUT 1.5 INCH LONG) IN THE VICINITY OF THE "FLAP ACTUATOR BRACKET". FURTHER FOUND NOSE RIB CRACKED AS WELL. REMOVED FLAP FOR REPAIRS.
- [SDR 2010FA0001234](https://openairdocs.org/sdr/2010FA0001234.md): Line · corroded · Dec 7, 2010 · N464V · Beech 95B55 · Aircraft Fuel Distribution System
  > ACCESSED & CLOSELY INSPECTED RT FUEL FLOW/PRESSURE GAGE LINE WHERE IT CROSSED DEFROST DUCT BECAUSE IT LOOKED LIKE THEY MAY BE CONTACTING. FOUND EXTENSIVE CORROSION AT POINT OF CONTACT. AFTER LINE WAS REMOVED, SLIGHT BENDING PRESSURE CRACKED AREA WIDE OPEN AN
- [SDR 2010FA0000268](https://openairdocs.org/sdr/2010FA0000268.md): Downlock · lack of lube · Mar 24, 2010 · N5LH · Cessna 310Q · Landing Gear Retraction/Extension System
  > RT LANDING GEAR FAILED TO FULLY EXTEND AND LOCK. THE RT DOWNLOCK PN 5041018-1 SEIZED DUE TO LACK OF LUBRICATION. THE DOWN LOCK ROD END PN KWBS WAS ALSO SEIZED FOR THE SAME REASON. THE WEIGHT OF THE ACFT ON THE PARTIALLY EXTENDED GEAR PULLED THE BELLCRANK BRA
- [SDR 2010FA0000190](https://openairdocs.org/sdr/2010FA0000190.md): Strut · discharged · Feb 20, 2010 · N8073M · Cessna 310I · Nose/Tail Landing Gear Strut/Axle
  > DURING ROUTINE TAKEOFF AND AS LANDING GEAR RETRACTED A LOUD 'BANG' WAS HEARD. THE GEAR WAS THEN LOWERED AFTER LEVEL FLIGHT WAS ESTABLISHED; AFTER SEEING A 'GREEN' INDICATION THE AIRPLANE WAS LANDED WITHOUT INCIDENT. IT WAS DISCOVERED THAT THE NOSE STRUT HAD D
- [SDR 2010FA0000061](https://openairdocs.org/sdr/2010FA0000061.md): Blade · corroded · Jan 7, 2010 · Propeller Blade Section
  > PROPELLER RECENTLY OVERHAULED 10/29/2009 PROPELLER CAME IN FOR REPITCH WITH NO TIME ON SINCE OVERHAULED. 1 BLADE PAINT WAS REMOVED AND LOTS OF CORROSSION LEFT UNDER PAINT NOT REMOVED AS SHOULD BE WITH OVERHAUL. PROPELLER WILL HAVE TO BE REOVERHAULED TO DETERMI
- [SDR AG2R2010002](https://openairdocs.org/sdr/AG2R2010002.md): Cylinder Head · cracked · Oct 27, 2009 · Reciprocating Engine Cylinder Section
  > BOTTOM SPARK PLUG CRACK, EXHAUST SEAT CRACK, FUEL INJECTOR BOSS CRACK, AND INTAKE PORT CRACK. TOO SEVERE FOR REPAIR.
- [SDR 2009FA0000916](https://openairdocs.org/sdr/2009FA0000916.md): Linkage · bent · Oct 5, 2009 · N6879T · Cessna 310D · Nose/Tail Landing Gear
  > NOSE GEAR FAILED UPON RETRACT. EXACT CAUSE, UNKNOWN. FOUND LINKAGE FROM GEAR ACTUATOR BOX TO NOSE GEAR BENT. THE NOSE GEAR DOOR LINKAGE IS SUSPECT TO CAUSING THE INCIDENT, BUT CANNOT SAY WITH CERTAINTY.
- [SDR 2009FA0000330](https://openairdocs.org/sdr/2009FA0000330.md): Bulkhead · cracked · Apr 1, 2009 · N8453Z · Cessna 2105 · Fuselage Main, Bulkhead
  > INSP PURSUANT TO AD-72-07-09 REVEALED A CRACK IN THE UPPER LT FLANGE AREA OF THE BULKHEAD. BULKHEAD WAS REPLACED. (K)
- [SDR 2009FA0000320](https://openairdocs.org/sdr/2009FA0000320.md): Bellcrank · failed · Mar 26, 2009 · N7022L · Cessna 310K · Landing Gear Retraction/Extension System
  > IDLER BELLCRANK FAILED DURING RETRACTION CYCLE. THIS BELLCRANK IS CAST ALLOY. IN MY OPINION IT SHOULD BE A MACHINE PART. (K)
- [SDR 2007FA0000954](https://openairdocs.org/sdr/2007FA0000954.md): Battery · damaged · Oct 11, 2007 · N22GP · Cessna 210C · Emergency Locator Beacon
  > DURING ANNUAL INSPECTION FOUND DRIED ALKILINE BATTERY SUBSTANCE ON EXTERIOR OF CASE. OPEND CASE AND FOUND THAT THE BATTERIES, ALKALINE BATTERIES WERE COMING APART AT THE SEAMS AND LEAKING. CLEANED BATTERY COMPARTMENT AND INSTALLED FRESH SET OF BATTERIES. FU
- [SDR 2007FA0000908](https://openairdocs.org/sdr/2007FA0000908.md): Stop · broken · Sep 19, 2007 · N20SS · Cessna 310Q · Landing Gear Retraction/Extension System
  > PILOT HAD NO LT GEAR DOWN INDICATION. HE CYCLED GEAR WITH NO SUBSEQUENT GEAR DOWN INDICATION. HE ATTEMPTED MANUAL EXTENSION, CRANKED TO THE MECHANICAL STOP IN THE GEARBOX AND BROKE THE STOP. BELLCRANK CONTINUED PAST DOWN AND THEN WENT PARTIALLY (UP). GEAR
- [SDR 2007FA0000584](https://openairdocs.org/sdr/2007FA0000584.md): Rod End · failed · May 21, 2007 · N5918M · Cessna 310P · Landing Gear Door Retract Section
  > ROD END FAILED, ALLOWING NOSE GEAR DOOR TO PARTIALLY CLOSE IN FLIGHT. WHEN GEAR WAS RETRACTED, JAMMED NOSE GEAR ASSY ALONG WITH GEAR DOOR UP IN GEAR WELL. (K)
- [SDR 2007FA0000369](https://openairdocs.org/sdr/2007FA0000369.md): Landing Gear · malfunctioned · Apr 4, 2007 · N6981T · Cessna 310D · Main Landing Gear
  > THE PILOT NOTED THAT SOMETHING WAS HANGING DOWN UNDER THE AC IN CRUISE FLIGHT AND THAT THE AC WAS NOT GOING AS FAST AS IT NORMALLY DID. ANOTHER AC NOTED THAT THE GEAR WAS UP, BUT THAT THE LEFT IB GEAR DOOR WAS HANGING DOWN PART WAY. THE TOWER CONFIRMED THAT
- [SDR 2007FA0000332](https://openairdocs.org/sdr/2007FA0000332.md): Snap Ring · mismanufactured · Apr 1, 2007 · N4145 · Cessna 180A · Engine (Reciprocating)
  > SNAP RING USED TO RETAIN PLATE PN 643629 AND COUNTERWEIGHT PIN 643626-101 WAS BEING INSTALLED IN COUNTERWEIGHT. UPON INSTALLING, THE LAST SNAP RING, IT WAS NOTICED THAT THE SNAP RING DID NOT HAVE ANY RETAINING PROPERTIES. IT LACKED TEMPER TO SPRING BACK AND
- [SDR OMKR20071](https://openairdocs.org/sdr/OMKR20071.md): Drag Link · broken · Mar 31, 2007 · N4411 · Cessna 310C · Landing Gear Retraction/Extension System
  > UPON LANDING, THE NOSE LANDING GEAR DRAG LINK ASSEMBLY P/N 0842000-3 BROKE AT THE STRUT ATTACH POINT, ALLOWING THE NOSE GEAR TO COLLAPSE REARWARD, CAUSING THE AIRCRAFT TO SLIDE ON ITS NOSE UNTIL IT STOPPED. THE DRAG LINK ASSEMBLY APPEARS TO HAVE BROKEN THROUG
- [SDR 2007FA0000270](https://openairdocs.org/sdr/2007FA0000270.md): Control Cable · worn · Mar 26, 2007 · N1363Z · Beech N35 · Aileron Control System
  > (REF MODEL 35 SERIES IPC FIG. 27) LT AILERON CABLE FOUND RIDING ON PROP CONTROL CABLE SHEATH, ABOUT 2 INCHES AFT OF FIREWALL. AILERON CABLE WAS WORN ABOUT HALF THROUGH, AND THE PROP CABLE WAS WORN THROUGH THE SHEATH TO THE INNER STEEL CABLE. (VERY DIFFICULT
- [SDR ATL07LA057](https://openairdocs.org/sdr/ATL07LA057.md): Fuel Cell · leaking · Mar 19, 2007 · N500JP · Beech 95B55 · Fuel Storage
  > DURING START OF RT ENGINE, PILOT REPORTED HEARING A LOUD THUMP, NOTED FIRE COMING FROM THE BOTTOM OF THE RT COWLING. SHUTDOWN ENGINES, EVACUATED AIRCRAFT, AND NOTED APPARENT EXPLOSION HAD OCCURRED IN RT WING. VISUAL INSPECTION DID NOT REVEAL CAUSE OF EVENT
- [SDR 2007FA0000243](https://openairdocs.org/sdr/2007FA0000243.md): Antenna · misinstalled · Feb 26, 2007 · N1768G · Beech 35B33 · Fuselage Main, Structure
  > THE DOUBLER FOR THE VHF ANTENNA APPEARS TO HAVE BEEN TOO SMALL(SLIGHLY LARGER THAN THE BASE OF THE ANTENNA)AND WAS NOT RIVITED TO THE FUSELAGE,ALLOWING THE ANTENNA TO FLUTTER WHILE AIRBORNE.ON POST FLIGHT INSPECTION THE PILOT DISCOVERED TEARING ON THREE SIDES
- [SDR 2007FA0000195](https://openairdocs.org/sdr/2007FA0000195.md): Limit Switch · failed · Jan 29, 2007 · N3091L · Cessna 310J · Landing Gear Actuator
  > UP LIMIT SWITCH FAILED ON LANDING GEAR ACTUATOR, CAUSING OVER EXTENSION OF NOSE GEAR SYSTEM. THIS CAUSED THE INTERMEDIATE TORQUE TUBE TO BEND. (K)
- [SDR 2007FA0000030](https://openairdocs.org/sdr/2007FA0000030.md): Valve · failed · Dec 15, 2006 · N3845L · Beech 95B55 · Heating System
  > FOUND THERMOSTAT WORKING, BUT FUEL SOLENOID NOT STOPPING FUEL DELIVERY EVEN WITH POWER TO VALVE DISTUPTED. CABIN HEATER ONLY SHUTDOWN WHEN OVERHEAT SWITCH OPENED. VALVE INFO: MODEL NR 4400B.
- [SDR 2006FA0000925](https://openairdocs.org/sdr/2006FA0000925.md): Spar Cap · corroded · Sep 17, 2006 · N69704 · Cessna 310Q · Wing Spar
  > DURING THE ANNUAL INSPECTION, FOUND UPPER AND LOWER REAR SPAR DAMAGE ON THIS AIRCRAFT. THIS DAMAGE IS DUE TO CORROSION ON THE UPPER AND LOWER REAR SPAR CAPS. THE UPPER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CAP EXTENDING IB FROM
- [SDR 2006FA0000939](https://openairdocs.org/sdr/2006FA0000939.md): Hose · failed · Sep 13, 2006 · N98264 · Cessna 172P · Vacuum Distribution System
  > INVESTIGATION INTO FAILED ATTITUDE INDICATOR ON LISTED AIRCRAFT FOUND APPARENT CAUSE OF FAILURE TO BE FROM CONTAMINATION FROM DISINTEGRATING VACUUM HOSE. THE HOSES IN QUESTION ARE MARKED B906 AND B904 HOSE. TO PREVENT RECURRENCE, SB SEB96-10 SHOULD BE ACCOMP
- [SDR 2006FA0000907](https://openairdocs.org/sdr/2006FA0000907.md): Motor · failed · Aug 22, 2006 · N7940Q · Cessna 310Q · Landing Gear Retraction/Extension System
  > LANDING GEAR WOULD NOT EXTEND ELECTRICALLY ON APPROACH. OPERATIONS NORMAL WHEN LANDING GEAR EXTENDED WITH MANUAL EMERGENCY EXTENSION SYS. FOUND LANDING GEAR ACTUATOR MOTOR INOPERATIVE. WOULD MAKE NOISE BUT NOT ROTATE. REPLACED MOTOR WITH OVERHAULED REPLACEM
- [SDR 2006FA0000791](https://openairdocs.org/sdr/2006FA0000791.md): Hinge · cracked · Jul 8, 2006 · N9520Y · Beech P35 · Rudder Control System
  > FAIRLEADS IN RUDDERVATOR TRIM TAB CNTRL CABLE SYS ARE CRACKING UPON INSTALLATION, POSSIBLY DURING FLIGHT. BUTTON-HEAD RIVETS ARE INTERFERING WITH INSTALLATION, CAUSING CRACKS TO FORM IN (TANG) OF FAIRLEADS. CABLE TENSION USED IN RUDDERVATOR TRIM TAB CABLES I
- [SDR IGL032006007](https://openairdocs.org/sdr/IGL032006007.md): Strut · failed · Mar 29, 2006 · N7035L · Cessna 310K · Nose/Tail Landing Gear Strut/Axle
  > NOSE GEAR STRUT ASSEMBLY COLLAPSED DURING EITHER TAXI OR TAKEOFF. WHEN GEAR WAS RETRACTED THE NOSE FENDER CAUGHT ON THE GEAR DOOR BRACKETS. MOTOR CONTINUED UNTIL IDLER BELLCRANK BROKE. AIRCRAFT MADE AN EMERGENCY LANDING WITH THE NOSE GEAR COLLAPSED. PILOT
- [SDR 2006FA0000220](https://openairdocs.org/sdr/2006FA0000220.md): Encoder · out of adjust · Mar 1, 2006 · N1329Z · Beech 35A33 · ATC Transponder System
  > CHECKED ENCODER SYSTEM AND COULD NOT VERIFIED REPORT OF ATTITUDE ERROR. REPLACED TRANS CAL BLIND ENCODER AS PRECAUTIONARY MEASURE. RECERTIFY TRANSPONDER AND ENCODER IAW FAR. (K)
- [SDR 2006FA0000262](https://openairdocs.org/sdr/2006FA0000262.md): Fuel Cell · deteriorated · Mar 1, 2006 · N56JK · Beech 95B55 · Fuel Storage
  > FOUND FUEL SYTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE. AFTER HAVING THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN. AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGAIN AND THE SUBSTANC
- [SDR 2006FA0000265](https://openairdocs.org/sdr/2006FA0000265.md): Baffle · deteriorated · Mar 1, 2006 · N56JK · Beech 95B55 · Fuel Storage
  > FOUND FUEL SYSTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE. AFTER HAVE THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN. AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGAIN AND THE SUBSTANCE
- [SDR 2006FA0000097](https://openairdocs.org/sdr/2006FA0000097.md): Control Cable · broken · Dec 28, 2005 · N4110Q · Cessna 310N · Rudder Control System
  > THE LT RUDDER CABLE BROKE AT THE CLEVIS THAT ATTACHES IT TO THE RUDDER TORQUE TUBE ARM. UNDER NORMAL OPERATING CONDITIONS, DURING THE 37 YEARS AND HOURS THAT THE AIRCRAFT HAS BEEN IN SERVICE. THE RT RUDDER CABLE HAD ABOUT 25 PERCENT OF THE STRANDS BROKEN. T

Next page: https://openairdocs.org/engine/continental-io-470-series/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 engine_model_key = 'IO470'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/continental-io-470-series/reports

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