# Service difficulty reports: Eci IO-360

A list on [Eci IO-360](https://openairdocs.org/engine/eci-io-360.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 2 · 86 reports

- [SDR 2023FA0000622](https://openairdocs.org/sdr/2023FA0000622.md): Cylinder · cracked · Oct 20, 2023 · N174GF · Cessna 172R · Reciprocating Engine Cylinder Section
  > PILOT REPORTED LOSS OF ENGINE POWER. BEGAN TO RUN ROUGH. MADE A PRECAUTIONARY NORMAL LANDING. MECHANIC REMOVED COWLING AND FOUND A CRACKED NR 4 CYLINDER. LB STATED NEW CYLINDERS WERE INSTALLED AT ENGINE OVERHAUL AT 1481.6 HOURS AGO. THE CYLINDER WAS REPLACED
- [SDR 2021FA0000407](https://openairdocs.org/sdr/2021FA0000407.md): None · loose · Dec 16, 2021 · N1420J · Gulstm 112A · Aileron Control System
  > DURING R/H AILERON BELLCRANK CABLES DISCONNECTION FOR CLEANING / INSPECTION / LUBE, FOUND BELLCRANK ASSY P/N 47350-2 CONSTITUTED OF PIVOT BALL BEARING HOUSING P/N MS20218-1 SECURED TO BELLCRANK PLATE P/N 47349-2 EXHIBITING ONE (1) EACH OUT OF THREE (3) EACH L
- [SDR 4RPA201307010001](https://openairdocs.org/sdr/4RPA201307010001.md): Pump · failed · Jun 28, 2013 · N9450C · Piper PA34200T · Engine Fuel Pump
  > LEFT ENGINE FUEL FLOW DROPPED FROM 25 GALLONS AN HOUR AT TOP OF CLIMB TO 7 GALLONS AN HOUR AT ALL POWER SETTINGS. ELECTRIC FUEL PUMP SWITCH ALSO FAILED. PILOT USED ENGINE PRIMER BUTTON TO KEEP ENGINE RUNNING. USE OF PRIMER BUTTON INCREASED FUEL FLOW TO 25 G
- [SDR 2012FA0000727](https://openairdocs.org/sdr/2012FA0000727.md): Power Supply · failed · Oct 25, 2012 · N2075T · Cirrus SR20 · Exterior Lighting
  > LEFT STROBE INOPERATIVE. TESTED FLASH TUBE WITH ANOTHER POWER SUPPLY - FUNCTION CHECK OK. PULLED THE POWER SUPPLY AND OPENED - EVIDENCE OF CAPACITOR EXPLOSION AND ELECTROLYTE SPILLAGE.
- [SDR 2012FA0000517](https://openairdocs.org/sdr/2012FA0000517.md): Cowl Door · departed · Jul 9, 2012 · N4428T · Piper PA28R200 · Engine Cowling System
  > DURING DESCENT THROUGH 7,000 FT, TOP COWL ASSEMBLY DEPARTED THE ACFT AND STRUCK THE LEFT WINDSCREEN CAUSING A LARGE HOLE. FURTHER INSPECTION REVEALED THAT THE RIGHT SIDE BOTTOM COWL PLATE ASSY WAS ELONGATED FROM WEAR WITH THE TOP COWL ENGAGEMENT PIN, AND THE
- [SDR 2012FA0000343](https://openairdocs.org/sdr/2012FA0000343.md): Case · cracked · May 29, 2012 · N579RC · Cirrus SR20 · Reciprocating Engine Power Section
  > DURRING PRE FLIGHT FOUND OIL ON COWLING. INVESTIGATION FOUND A CRACK IN THE RT FWD TOP OF THE ENGINE CASE.
- [SDR 2011FA0000544](https://openairdocs.org/sdr/2011FA0000544.md): Bolt · loose · Aug 22, 2011 · N1148J · Gulstm 112A · Horizontal Stabilizer, Attach Fittings
  > WHILE COMPLYING WITH AD 11-07-13 LT AND RT ELEVATOR SPAR, IT WAS NOTED THAT THE HORIZONTAL STAB WAS LOOSE AT BOTH THE FRONT AND REAR MOUNTING POINTS. MOVEMENT WAS MOST NOTED AT THE FWD PORTION OF THE STAB WITH A ROCKING MOVEMENT SIDE TO SIDE. UPON INVESTIGAT
- [SDR 2011FA0000373](https://openairdocs.org/sdr/2011FA0000373.md): Filter Element · split · Jun 9, 2011 · N41AT · Piper PA28R200 · Engine Air Intake System
  > DURING ROUTINE INSPECTION, AIR FILTER WAS FOUND SPLIT OPEN AT THE SEAM. IT IS A CYLINDRICAL SHAPE AND IT WRAPS AROUND A METAL SCREEN. THE SPLIT AREA COMPRISED SEVERAL SQ INCHES OF UNFILTERED AIRPATH.
- [SDR 2011FA0000334](https://openairdocs.org/sdr/2011FA0000334.md): Spar · corroded · May 18, 2011 · N41WA · Piper PA28R180 · Wing Spar
  > DURING REPAIR OF LT WING THE AFT SPAR ATTACH FITTING WAS REMOVED. SEVERE CORROSION WAS FOUND UNDER THE FITTING. PROBABLE CAUSE IS TRAPPED MOISTURE, LACK OF PREVENTATIVE TREATMENT AND LACK OF PROPER INSPECTION OF AREA.
- [SDR NX4R000013](https://openairdocs.org/sdr/NX4R000013.md): Mount · cracked · Apr 28, 2011 · N701ER · Piper PA28R201 · Engine Mount Section
  > DURING ROUNTINE MX, THE TECH WAS PERFORMING A PRELIMINARY/HIDDEN DAMAGE INSP OF THE AREA SURROUNDING THE AREA WHERE WORK WAS TO BE PERFORMED. NOTICED THE SMALL TUBE THAT IS WELDED TO THE LOWER ENGINE MOUNT TUBE THAT THE LOWER COWL IS MOUNTED TO, WAS MOVING SLI
- [SDR NX4R000011](https://openairdocs.org/sdr/NX4R000011.md): Attach Fitting · broken · Apr 20, 2011 · N716ER · Piper PA28R201 · Fuselage Main, Attach Fittings
  > DURING TAKEOFF, THE PILOT RETRACTED THE LANDING GEAR. THE GEAR "UNSAFE LIGHT" REMAINED ILLUMINATED. ALSO THE ATC TOWER CONTROLLER ADVISED THE CREW THAT THEIR NLG APPEARED TO REMAIN IN THE DOWN POSITION. AN UNEVENTFUL LANDING WAS MADE AND THE LANDING GEAR INS
- [SDR 2011FA0000054](https://openairdocs.org/sdr/2011FA0000054.md): Shaft · failed · Jan 28, 2011 · N705CM · Amtr RV7 · Magneto/Distributor
  > MAG SHAFT COMPLETELY SEPARATED FROM THE MAG AS THE SHAFT EXITED THE MAG. CAUSING INOPERATIVE SYS, LOSS OF 1/2 ENGINE IGNITION AND ASSOCIATED WARNING LIGHTS IN THE COCKPIT.
- [SDR 2010FA0001258](https://openairdocs.org/sdr/2010FA0001258.md): Distributor Blk · melted · Dec 20, 2010 · N710MD · Cirrus SR20 · Magneto/Distributor
  > DURING A 500 HOUR INSP, COMPLIANCE OF M/N 6314 MAGNETOS, LT MAGNETO SHOWED SIGNS OF EXTREAM HIGH HEAT INTERNALLY. SB SB3-08A ADDRESSES PROBLEM CAUSED BY "SOFT" CARBON BRUSHES PACKAGED FROM SEPT 1, 2004 THROUGH AUGUST 14, 2008. TT OF MAGNETO WAS DOCUMENTED AS
- [SDR 2010FA0001132](https://openairdocs.org/sdr/2010FA0001132.md): Spring · broken · Aug 21, 2010 · N123TA · Amtr DR107 · Nose/Tail Landing Gear
  > ON LANDING TAILSPRING BROKE. ACFT GROUND LOOPED CAUSING SUBSTANTIAL DAMAGE TO AIRCRAFT. INVESTIGATION OF BROKEN TAILSPRING REVEALED 2 EXISTING LOW CYCLE FATIGUE FRACTURES AND 1 OVERSTRESS POINT. MFG SUGGESTS REPLACING WITH A BOLT IN REDESIGNED UNIT.
- [SDR ZB0R20100002](https://openairdocs.org/sdr/ZB0R20100002.md): Master Switch · burned · May 31, 2010 · N963AC · Cessna 172S · DC Power Distribution System
  > ((ZB0R)) PILOT REPORTED BURNING SMELL AND FAILURE OF AVIONICS BUSS NR 2 ON RUN-UP. ACFT REPORTED TO MX. TROUBLESHOOTING REVEALED AVIONICS MASTER SWITCH RT SIDE (BUSS 2) ARCING INTERNALLY. REPLACED AVIONICS SWITCH AND OPS CK OK.
- [SDR 2010FA0000425](https://openairdocs.org/sdr/2010FA0000425.md): Guide · broken · Apr 19, 2010 · N55SV · Cessna 172S · Flight Compartment Equipment
  > (HE8S) PILOT`S SEAT HARNESS GUIDE BROKE AT SHOULDER HARNESS MOUNT TUBE. SUGGEST MAKING THIS PART WITH MORE DURABLE MATERIAL OR HAVING A REINFORCEMENT AT AREA OF BREAKAGE. THE BROKEN PART HAS A STRESS AREA WHERE IT WAS BROKEN DUE TO THE HOLE WHERE HEAD REST M
- [SDR 2010FA0000228](https://openairdocs.org/sdr/2010FA0000228.md): Mount · broken · Mar 12, 2010 · N35LA · Mooney M20F · DC Generator-Alternator
  > HAVE HAD MULTIPLE PROBLEMS WITH THE MOUNTING KIT FOR THE ALTERNATOR THROUGH STC SA334SW. A NEW ALTERNATOR WAS INSTALLED ON 9/8/2006. AFTER 64 FLIGHT HOURS, THE ALUMINUM MOUNTING BLOCK BROKE DURING FLIGHT ON 6/5/07, AND WAS REPLACED ON 6/13/07. AFTER 127 FLI
- [SDR 2010FA0000196](https://openairdocs.org/sdr/2010FA0000196.md): Solenoid · sticks · Mar 3, 2010 · N7884N · Cessna 172E · Engine Starter
  > BURNED ODOR OF ELECTRICAL COMPONENTS AFTER ENGINE START UP. SELECTED ACFT MASTER SWITCH OFF AND SHUTDOWN ENGINE. INSP REVEALED STARTER MOTOR HAD OVERHEATED. FURTHER EXAMINATION REVEALED STARTER SOLENOID HAD STUCK IN THE CLOSED POSITION DURING ENGINE START A
- [SDR 2010FA0000045](https://openairdocs.org/sdr/2010FA0000045.md): Track · broken · Jan 15, 2010 · N1871M · Cessna 337G · Landing Gear Retraction/Extension System
  > PN 1513055-1 CAM TRACK ASSY BROKE UPON GEAR RETRACTION. NOSE GEAR THEN WOULD NOT RETRACT PROPERLY OR EXTEND AND LOCK PROPERLY. PUMP MOTOR C/B CONTINUED TO TRIP DURING THE FLIGHT. ACFT WAS LANDED WITHOUT INCIDENT. IT WAS NOTICED THAT THE NOSE GEAR WAS COCKE
- [SDR 2009FA0000986](https://openairdocs.org/sdr/2009FA0000986.md): Shaft · fractured · Nov 20, 2009 · N96EV · Amtr RV6A · Magneto/Distributor
  > ROTOR SHAFT FRACTURED AT THE BOTTOM OF THE RUBBING BROOK SLOT. (K)
- [SDR 2009FA0000873](https://openairdocs.org/sdr/2009FA0000873.md): Nut · cracked · Oct 22, 2009 · N722PA · Diamon DA40 · Propeller System
  > WHEN REMOVING PROPELLER FOR RESEAL, FOUND 2 MOUNTING NUTS CRACKED. THE PROP HAS 93.5 HRS SINCE INSTALLATION. THE PROPELLER PREVIOUSLY HAD THE BLADES REPLACED DUE TO PROP STRIKE.
- [SDR 2009FA0000921](https://openairdocs.org/sdr/2009FA0000921.md): Screen · cracked · Aug 14, 2009 · N908DS · Diamon DA40 · Engine Air Intake System
  > REPAIR STATION IS HOLDER OF STC SA03674AT FOR THE INSTALATION OF R-134 COOLANT AIR CONDITIONER SYS IN THIS ACFT. IAW THIS STC INSTALLATION, A CONDENSER HOUSING IS MOUNTED ON THE BOTTOM OF THE ACFT FUSELAGE. IT HAS BEEN DISCOVERED THAT THE SCREEN WHICH COVERS
- [SDR 2009FA0000922](https://openairdocs.org/sdr/2009FA0000922.md): Screen · cracked · Aug 14, 2009 · N385DS · Diamon DA40 · Cabin Cooling System
  > REPAIR STATION IS HOLDER OF STC SA03674AT FOR THE INSTALATION OF R-134 COOLANT AIR CONDITIONER SYS IN THIS ACFT. IAW THIS STC INSTALLATION, A CONDENSER HOUSING IS MOUNTED ON THE BOTTOM OF THE ACFT FUSELAGE. IT HAS BEEN DISCOVERED THAT THE SCREEN WHICH COVERS
- [SDR 2009FA0000510](https://openairdocs.org/sdr/2009FA0000510.md): Air Filter · defective · Jun 9, 2009 · N1244S · Cessna 337H · Engine Fuel and Control
  > UPON RECEIVING INSP OF NEW MFG AIR FILTERS PN P107336 IT WAS FOUND THAT 3 OUT OF 4 NEW FILTERS HAD A DEFECTIVE SEALING SURFACE CAUSING THE SEALING/MATING SURFACE TO CRACK AND CRUMBLE. THIS DEFECTIVE SEALING SURFACE COULD POTENTIALY ENTER THE ENGINE INLET. THE
- [SDR 2009FA0000449](https://openairdocs.org/sdr/2009FA0000449.md): Control Cable · broken · May 12, 2009 · N62045 · Maule M5210C · Trailing Edge Flap Control System
  > AN INSP OF RT WING FLAP CABLE REVEALED BROKEN STRANDS WHERE THE CABLE THIMBLE AND SHACKLE TO THE FLAP BELLCRANK INSIDE THE WING. THERE IS INSUFFICIENT CLEARANCE BETWEEN THE CABLE AS IT WRAPS AROUND THE THIMBLE AND THE BELLCRANK AND IT WAS GETTING PINCHED WHEN
- [SDR 2009FA0000396](https://openairdocs.org/sdr/2009FA0000396.md): Plunger · damaged · May 11, 2009 · N286DS · Diamon DA40 · Propeller Governor
  > PLUNGER P/N 210332 INSPECTED IAW SB 33571C AND FAILED.
- [SDR 2008FA0000841](https://openairdocs.org/sdr/2008FA0000841.md): Latch · disengaged · Nov 24, 2008 · N661DS · Diamon DA40 · Passenger/Crew Doors
  > AT 10500 FT IN CRUISE FLIGHT, GOT AN AUDIBLE "DING" ON THE G1000 WARNING AND THEN A LIGHT SAYING THAT A DOOR WAS OPEN. BACK DOOR HAD COME OPEN IN FLIGHT. THE DOOR HAD BEEN SHUT AND THERE HAD BEEN NO WARNING DURING PRE-FLIGHT CHECK AND RUN-UP. WAS IN THE RT S
- [SDR 2008FA0000880](https://openairdocs.org/sdr/2008FA0000880.md): Sensor · defective · Nov 22, 2008 · N212LV · Cirrus SR20 · Engine Oil Pressure
  > SENSOR PRODUCED A FALSE HIGH OIL PRESSURE INDICATION DURING ACFT APPROACH TO AIRPORT. PROBABLE CAUSE WAS INTERNAL FAILURE, RECOMMENDATIONS TO PREVENT RECURRENCE ARE UNAVAILABLE, AS THE FREQUENCY OF THIS TYPE OF OCCURRENCE HAS BEEN VERY LOW.
- [SDR 2010FA0000758](https://openairdocs.org/sdr/2010FA0000758.md): Wire · chafed · Nov 7, 2008 · N893CD · Cirrus SR20 · Electrical Power System Wiring
  > (NU7R) PILOT REPORTED AVIONICS INTERMITTENT TO COME ON WITH AVIONICS SWITCH. MFG DWG PAGE 24-50-01, PAGE 1 SHOWS AVIONICS RELAY NR 1 WITH WIRE CSVA661-14 LEAVING THE RELAY GOING TO THE AVIONICS ESSENTIAL BUSS. THIS WIRE WAS CHAFING ON THE BOTTOM HINGE ATTACH
- [SDR CA081009009](https://openairdocs.org/sdr/CA081009009.md): Wire · broken · Sep 27, 2008 · Diamon DA40 · Electrical Power System Wiring
  > (CAN) A+ TERMINAL MELTED OFF ALTERNATOR AND LOOSE. PROBLEM CAUSED BY BROKEN TERMINAL ON A+ WIRE GOING TO ALTERNATOR. WIRE WAS ORIGINALLY VERY TIGHT CAUSING THE BREAKAGE, THEN IT ARCED CAUSING HEAT AND EVENTUAL FAILURE.
- [SDR 2008FA0000661](https://openairdocs.org/sdr/2008FA0000661.md): Casting · broken · Sep 17, 2008 · N273DS · Diamon DA40 · Engine Starter
  > CUSTOMER ATTEMPTED TO START ENGINE. WHILE CRANKING ENGINE, CUSTOMER REPORTED A LOUD "CLUNK" AND THE PROPELLER STOPPED ROTATING. INVESTIGATED PROBLEM AND FOUND THE STARTER DRIVE CASTING BROKE FROM STARTER MOTOR. THE CASTING INCLUDED A BEARING FOR THE STARTER DR
- [SDR 2008FA0000505](https://openairdocs.org/sdr/2008FA0000505.md): Connector · damaged · Jul 22, 2008 · N412PJ · Diamon DA40 · Propeller/Propulsor System Wiring
  > ON JUNE 28TH, 2008, DURING CLIMB OUT, PASSING THROUGH 4000 FEET THE ENGINE SUDDENLY WENT INTO AN OVER SPEED CONDITION OF OVER 3100 RPM. THE AIRCRAFT REMAINED UNDER CONTROL AND WAS LANDED SAFELY AT AIRPORT AFTER AN EMERGENCY WAS DECLARED. UPON DISASSEMBLY OF T
- [SDR 2008FA0000278](https://openairdocs.org/sdr/2008FA0000278.md): Valve · loose · Apr 15, 2008 · N105UV · Diamon DA40 · Air Conditioning System
  > THE ALTERNATE AIR VALVE IS VIBRATING AND CAUSING FRETTING BETWEEN THE INLET RING, PN D41-7166-20-31 AND FLANGE, PN D41-7166-20-33. THE "DUST" IS BEING INGESTED INTO THE FUEL CONTROL SERVO AND ENGINE. THERE NEEDS TO BE A TIGHTER FIT BETWEEN THESE PARTS.
- [SDR 2008FA0000234](https://openairdocs.org/sdr/2008FA0000234.md): Valve · broken · Mar 7, 2008 · N51430 · Maule M4210C · Engine Air Intake System
  > THE ENG AUTOMATIC ALTERNATE INDUCTION AIR VALVE THAT IS PARTIALLY LOCATED INSIDE THE CYLINDRICAL PAPER INDUCTION AIR FILTER CAME APART AND SOME OF ITS PART (2 INCH LONG,.2500 INCH DIAMETER BOLT. 2 INCH LONG SPIRAL SPRING WASHER, AND COTTER PIN) WERE INGESTED
- [SDR 2008FA0000254](https://openairdocs.org/sdr/2008FA0000254.md): Servo · damaged · Mar 5, 2008 · N103UV · Diamon DA40 · Engine Fuel Distribution
  > WHILE PERFORMING A 100 HR INSP, THE TECH DISCOVERED FINE METAL PARTICLES COVERING THE THROAT AND VALVE OF THE FUEL INJECTION SERVO (2576568-1, SN 70B10709). THE SERVO WAS SENT TO A REPAIR FACILITY TO DETERMINE WHETHER OR NOT ANY OF THE METAL PARTICLES ENTERED
- [SDR 2008FA0000238](https://openairdocs.org/sdr/2008FA0000238.md): Bushing · incorrect · Feb 27, 2008 · N362HE · Cirrus SR20 · Pitot/Static System
  > STATIC SYSTEM FAILED LEAK CHECK DURING 2 YEAR STATIC SYS IFR CERTIFICATION, LEAKS WERE CAUSED BY REDUCED BUSHING FAILING TO SEAL STATIC LINE SUMP. (ON BOTH SIDES, PILOT AND COPILOT). TO REPAIR THE LEAKAGE, PIPE THREAD TAPE (TEFLON TAPE) WAS USED ON THE REDUC
- [SDR 2007FA0000711](https://openairdocs.org/sdr/2007FA0000711.md): Resistor · damaged · Jul 10, 2007 · N187DS · Diamon DA40 · Electrical Power System Wiring
  > MFG FABRICATED AN IN-LINE RESISTOR FROM THE ALTERNATOR TO THE VOLTAGE REGULATOR. THE RESISTOR WAS LOCATED APPROXIMATELY 2 INCHES FROM AUX TERMINAL ON ALTERNATOR. IT WAS STRENGTHENED WITH MULTIPLE LAYERS OF HEAT-SHRINK AND TERMINAL WAS CRIMPED ON THE SOLID WI
- [SDR 2007FA0000554](https://openairdocs.org/sdr/2007FA0000554.md): Antenna · disconnected · Jun 28, 2007 · N5959A · Cirrus SR20 · Global Positioning System
  > WHILE IN CRUISE FLIGHT THE NR 1 GPS STOPPED RECEIVING A SIGNAL. AFTER LANDING, REMOVED THE MFD AND FOUND THE GLUE HOLDING THE VELCRO TO THE GPS ANTENNA HAD COME UNDONE. BOTH GPS ANTENNAS ARE HELD IN PLACE WITH VELCRO STRIPS AND IN THE HEAT OF SUMMER, THE GLUE
- [SDR 2007FA0000533](https://openairdocs.org/sdr/2007FA0000533.md): Strut · cracked · Jun 22, 2007 · N217JH · Cirrus SR20 · Nose/Tail Landing Gear Strut/Axle
  > NOSE LANDING GEAR STRUT HAS A CRACK AT THE TOP. THE STRUT COMES UP TO A Y FOR MOUNT. AT THE YOKE OF THE Y IS A WELDED REINFORCEMENT, AND THE CRACK IS AT THE TOP WHERE THIS REINFORCEMENT MEETS THE LEGS OF THE Y.
- [SDR AW42007F00000](https://openairdocs.org/sdr/AW42007F00000.md): Nut · loose · Jun 8, 2007 · N784WW · Cessna 172R · Horizontal Stabilizer Structure
  > DURING THE PERFORMANCE OF A 100 HOUR INSPECTION, SLIGHT MOVEMENT OF THE HORIZONTAL STABILIZER WAS NOTED RELATIVE TO THE RT SIDE OF THE FUSELAGE. INVESTIGATION FOUND THAT THE RT FWD ATTACH BOLT NUT APPEARED TO BE SLIGHTLY LOOSE OR UNDER-TORQUED. REMOVED ATTAC
- [SDR 2007FA0000571](https://openairdocs.org/sdr/2007FA0000571.md): Bracket · failed · May 31, 2007 · N56066 · Piper PA28R200 · Nose/Tail Landing Gear
  > THE PILOT STATED NOSE GEAR COLLAPSED ON LANDING. AFTER AIRCRAFT REMOVED FROM RUNWAY AND PUT ON JACKS. THE NOSE GEAR WOULD NOT EXTEND OR RETRACT. THE GEAR WAS EXTENDED BY EMERGENCY EXTENSION. THE NOSE GEAR ALIGNER BRACKET FELL OFF THE GEAR. AGAIN THE NOSE
- [SDR 2007FA0000577](https://openairdocs.org/sdr/2007FA0000577.md): Downlock · broken · May 12, 2007 · N5094S · Piper PA28R200 · Nose/Tail Landing Gear
  > THE LOWER LATCH HOOK WAS BROKEN OFF ALLOWING THE NOSE GEAR TO COLLAPSE. (K)
- [SDR 2007FA0000349](https://openairdocs.org/sdr/2007FA0000349.md): Spar · loose · Apr 1, 2007 · N9810M · Maule M4210C · Trailing Edge Flaps
  > DURING AN ANNUAL INSPECTION, THE RT FLAP IB HINGE/CONTROL BRACKET WAS FOUND TO BE LOOSE. FURTHER INSPECTION REVEALED THAT THE FLAP SPAR WAS CRACKED AT THE UPPER RIVET ATTACH POINTS. THE CRACK IS 3.5 INCH LONG AND EXTENDS PAST THE RIVET HOLES IN BOTH DIRECTIO
- [SDR 2007FA0000112](https://openairdocs.org/sdr/2007FA0000112.md): Air Filter · twisted · Jan 8, 2007 · N758EJ · Cessna R172K · Engine Air Intake System
  > DURING REMOVAL OF THE AIR FILTER THE CENTER WIRE MESH SCREEN WAS FOUND TWISTED AND BENT. SOME OF THE WELDS WERE BROKEN. SCREEN DEFORMATION CAN LEAD TO UNFILTERED AIR AND FOD ENTERING THE ENGINE. APPARENT CAUSE IS EITHER OVERTORQUEING WING NUT AND/OR INSUFFI
- [SDR 2006FA0001020](https://openairdocs.org/sdr/2006FA0001020.md): Line · chafed · Oct 18, 2006 · N777ND · Cirrus SR20 · Aircraft Fuel Distribution System
  > FUEL LINE CHAFED, LINE REPLACED.
- [SDR 2006FA0000561](https://openairdocs.org/sdr/2006FA0000561.md): Attach Bracket · cracked · May 31, 2006 · N6622E · Cessna 175 · Fuselage, Powerplant Attach Fittings
  > ENGINE MOUNT ATTACHMENT BRACKET WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION. CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER. NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED. POSSIBLE CAUSE AN960-616 WASHER TOO SMALL. LARGER AREA AND THICKER WASHER NEE
- [SDR 2006FA0000134](https://openairdocs.org/sdr/2006FA0000134.md): Attach Bracket · broken · Jan 31, 2006 · N6612E · Cessna 175 · Engine Mount Section
  > THE AC EXPERIENCED A HARD LANDING. DURING THE LANDING THE 2 TOP ENGINE MOUNT ATTACH BRACKETS FAILED BEHIND THE FIREWALL, ALLOWING THE TOP HALF OF THE FIREWALL TO FAIL, PULLING FORWARD AND DOWN ABOUT 18 INCHES. PN 051313211 ENGINE MOUNT ATTACH BRACKET FITS ON
- [SDR 10943282](https://openairdocs.org/sdr/10943282.md): Frame · cracked · Jan 20, 2006 · N314X · Maule M5210C · Fuselage Main, Structure
  > FOUND CRACK APPROXIMATELY.3750 INCH IN LENGTH ON RT FRAME 20 WING ATTACH POINT.
- [SDR 2005FA0001483](https://openairdocs.org/sdr/2005FA0001483.md): Hinge · failed · Oct 5, 2005 · N541DS · Diamon DA40 · Fuselage, Door Hinge
  > UPON INSTALLATION OF A NEW AFT CABIN DOOR SUPPORT STRUT, THE DOOR WAS CLOSED, AND THE AFT CABIN DOOR HINGE FAILED. UPON FURTHER INSPECTION, THE DOOR HINGE WAS FOUND TO HAVE BEEN DELAMINATED WHICH COULD NOT WITHSTAND THE PRESSURE OF THE NEW SUPPORT STUT. THE
- [SDR 2005FA0001311](https://openairdocs.org/sdr/2005FA0001311.md): Engine · stopped · Sep 9, 2005 · N37E · Cessna P337H · Engine (Reciprocating)
  > DURING CRUISE CLIMB, PILOT REPORTED BOTH ENGINES QUIT RUNNING AND DEVERTED. DURING DECENT ENGINES CAME BACK TO LIFE. SUMPED 1 PINT EACH FROM FRONT, BACK FUEL STRAINERS, LT AND RT WING DRAINS. FUEL APPEARED NORMAL COLOR BLUE AND NO CONTAMINATES FOUND. (K)

Next page: https://openairdocs.org/engine/eci-io-360/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 = 'IO360'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/engine/eci-io-360/reports

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