# Service difficulty reports: Lycoming AEIO-540-D4A5 A list on [Lycoming AEIO-540-D4A5](https://openairdocs.org/engine/lycoming-aeio-540-d4a5.md). Newest first. General aviation reporting is voluntary. Page 1 of 2 · 61 reports - [SDR CA150504001](https://openairdocs.org/sdr/CA150504001.md): Control Tube · damaged · May 3, 2015 · Pitts S2B · Antenna/Radome Anti-Ice/De-Ice System > (CAN) COCKPIT CONTROL TUBE ASSEMBLY RUBBING ON INTERNAL VHF COMM ANTENNA DOUBLER: INVESTIGATION FOUND THAT DUE TO THE LIGHT GAUGE, 0.025", OF BOTTOM AFT PANEL AND UNDERSIZE OF THE VHF COMM ANTENNA DOUBLER, AIR LOAD CAUSES DOUBLER TO CONTACT THE COCKPIT CONTROL - [SDR CA120530005](https://openairdocs.org/sdr/CA120530005.md): Pitot Tube · contaminated · May 25, 2012 · Grob G120A · Pitot/Static System > (CAN) PITOT HEAT CAUTION LIGHT AFTER 20 MINS OF USE. DUE TO HEAVY RAINS, THE PITOT STATIC TUBE ASSY, SUPPORT ASSY, FILLED UP WITH WATER. THE WATER CAUSED A SHORT AT THE CONNECTOR INSIDE THE TUBE. WIRES REPAIRED AND PITOT STATIC TUBE REPLACED. SUGGEST A DRAI - [SDR CA111128005](https://openairdocs.org/sdr/CA111128005.md): Control Rod · gouged · Nov 28, 2011 · Grob G120A · Elevator Tab Control System > (CAN) ELEVATOR TRIM ROD, 120A-4441, HAS TWO SPOTS WHERE BOLTS FROM THE ELEVATOR CONTROL ROD, 120A-4441, WERE GOUGING INTO THE ROD WHEN THE SYS WAS BEING OPERATED. IN ORDER TO RECTIFY, THE BOLTS AT THE QUADRANT FOR THE ELEVATOR CONTROL ROD, 120A-4441, THE AILE - [SDR CA111021009](https://openairdocs.org/sdr/CA111021009.md): Fork · cracked · Oct 21, 2011 · Pitts S2B · Nose/Tail Landing Gear Strut/Axle > (CAN) ON LANDING, THE TAIL WHEEL FORK DEPARTED THE ACFT AS IT CRACKED THE CAST ALUMINUM FORK THAT THE TAIL WHEEL AXLE GOES THROUGH. THE ACFT LANDED WITH NO FURTHER DAMAGE BEYOND THE TAIL WHEEL ASSY. - [SDR CA110920010](https://openairdocs.org/sdr/CA110920010.md): Hose · worn · Sep 20, 2011 · Grob G120A · Air Distribution System > (CAN) DURING A LEAK TEST OF THE AIR CONDITIONING, IT WAS DISCOVERED THAT THE MAIN DELIVERY HOSE HAD A LEAK AND REQUIRED REPLACEMENT. THE AFFECTED HOSE IS LOCATED IN THE ENGINE COMPARTMENT AND IN CLOSE PROXIMITY TO THE EXHAUST MANIFOLD AND IS SUBJECT TO HIGH H - [SDR CA111019019](https://openairdocs.org/sdr/CA111019019.md): Pump · unsecure · Aug 6, 2011 · Engine Fuel Pump > (CAN) THE PILOT WAS PERFORMING AN AEROBATIC ROUTINE DURING AN AIRSHOW. WHILE PULLING THE POWER OFF TO PERFORM A TAIL SLIDE THE ENGINE QUIT. THE PILOT DECLARED A MAYDAY TO THE AIR BOSS AND MANAGED TO RESTART THE ENGINE. HE THEN CANCELLED THE REST OF HIS PERF - [SDR CA101021009](https://openairdocs.org/sdr/CA101021009.md): Washer · missing · Oct 20, 2010 · Grob G120A · Wing Miscellaneous Structure > DURING A 200 HR INSP ON 2 OTHER ACFT, MSB 1121-109/1 WAS BEING CARRIED OUT AS REQUIRED WHEN IT WAS NOTED THAT THE WASHERS WERE MISSING. THE MFG WAS CONTACTED AND DETERMINED THAT THIS WAS A NON CONFORMANCE TO THE TYPE CERTIFICATE. IT WAS DECIDED THAT THE REMA - [SDR CA090618012](https://openairdocs.org/sdr/CA090618012.md): Indicator · unserviceable · Jun 4, 2009 · Ayres S2C · Airspeed/Mach Indicator > (CAN) DURING PITOT/STATIC GROUND FUNCTION TEST, IT WAS NOTED THAT PILOTS (AFT) AIRSPEED INDICATOR WOULD ACCURATELY INDICATE AN INCREASE IN AIRSPEED BUT WOULD NOT SHOW A DECREASE ONCE PITOT PRESSURE IS RELIEVED AND BROUGHT BACK TO AMBIENT. THIS WOULD CAUSE THE - [SDR CA090515001](https://openairdocs.org/sdr/CA090515001.md): Tube · damaged · May 15, 2009 · Pitts S2B · Fuselage Miscellaneous Structure > (CAN) 4130 N FUSELAGE DIAGONAL TUBE PN 2-2100-241 FOUND DAMAGED BY IMPROPER CLEARANCE OF INSTALLED HARWARE OF THE FORWARD POSITION LT RUDDER PEDAL PIVOT BOLT AND SAFETY COTTER PIN. 74 PERCENT OF TUBE WALL MATERIAL GONE. RUDDER PEDAL FOUND TO BE "HOOKING AROUND - [SDR CA090515002](https://openairdocs.org/sdr/CA090515002.md): Aileron · obstructed · May 15, 2009 · Pitts S2B · Ailerons > (CAN) INSP OF THE CONTROL SURFACES FOUND THAT AILERONS DO NOT MAKE TRAVEL LIMITS AND PUSH RODS ARE HITTING FWD SPARS OF THE LWR WINGS. ELEVATOR TAB IS UNABLE TO MAKE LIMITS AS STATED. BOTH TRAVEL LIMITS AS STATED IN MM 70206-001 DATED 5-20-1998 PAGE 6 STATE TR - [SDR R019184](https://openairdocs.org/sdr/R019184.md): Bushing · loose · Mar 6, 2006 · Pitts S2B · Propeller Assembly > CUSTOMER REMOVED PROP DUE TO OIL LEAKING FROM BLADE. DISASSEMBLY OF THE PROPELLER REVEALED A LOOSE PITCH CHANGE ROD BORE BUSHING CAUSING THE OIL LEAK. THE PC ROD BUSHING WAS FOUND WEDGED BETWEEN THE FORK AND HUB. CENTRAL WEB AREA OF HUB WAS FULL OF OIL. TH - [SDR 2004FA0000229](https://openairdocs.org/sdr/2004FA0000229.md): Dope Film · delaminated · Feb 17, 2004 · N79D · Aviat PITTSS2B · Fuselage Main, Plate/Skin > ALL OF THE DOPE FILM DELAMINATED FROM THE CECONITE 102 FABRIC. AFTER SEVERAL PHONE CALLS, IT WAS DETERMINED THAT IMPROPER APPLICATION METHOD WAS USED. THE RANDOLPH DOPE PROCESS REQUIRES THE USE OF RANDO PROOF PRIMER FOR THE FIRST TWO COATS ON CECONITE FABRIC - [SDR 2003FA0001026](https://openairdocs.org/sdr/2003FA0001026.md): Cylinder · wrong part · Sep 30, 2003 · Cessna T182T · Reciprocating Engine Cylinder Section > DURING A ANNUAL INSPECTION, FOUND THE NR 1 CYLINDER TO BE INCORRECT FOR THIS INSTALLATION, INCORRECT CYLINDER INSTALLED MFG PRIOR TO INSTALLATION ON AIRCRAFT. CYLINDER WAS FOR SHORT REACH PLUGS, ENGINE USES LONG REACH. CYLINDER FOUND ON 2 ND ANNUAL INSPECTION - [SDR 2003FA0000731](https://openairdocs.org/sdr/2003FA0000731.md): Probe · failed · Jun 13, 2003 · N862AF · Grob G120A · Engine EGT/TIT Indicating System > ON GROUND RUN-UP EGT INDICATOR FLUCTUATED 25 DEGREES. ON FURTHER INVESTIGATION FOUND CARBON ON END OF PROBE. - [SDR 2003FA0000392](https://openairdocs.org/sdr/2003FA0000392.md): Bearing · failed · Apr 7, 2003 · N865AF · Grob G120A · Aileron Control System > DURING PROGRESSIVE INSPECTION OF THE AIRCRAFT THERE WAS A STRANGE SOUND FROM THE AILERON SYSTEM. FURTHER INVESTIGATION REVEALED THAT THE BEARING FROM THE LT AILERON ASSEMBLY WAS COMING APART. PROBABLE CAUSE IS DESIGN OF AILERON LEVER ASSEMBLY. THE ANGLE AND - [SDR 2003FA0000073](https://openairdocs.org/sdr/2003FA0000073.md): Distributor Blk · inoperative · Jan 16, 2003 · Magneto/Distributor > MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. DURING INSPECTION FOUND THAT THE CARBON BRUSH HAS EXCESSIVE WEAR. BECAUSE OF THIS EXCESSIVE WEAR IT IS CAUSING CARBON DUST WHICH IS SHORTING OUT MAGNETOS AND CAUSING THEM TO MELT DOWN. BECAUSE THE - [SDR VJ32003F00004](https://openairdocs.org/sdr/VJ32003F00004.md): Handle · shorted · Dec 9, 2002 · N865AF · Grob G120A · Landing Gear Selector > LANDING GEAR HANDLE COULD NOT BE SELECTED TO THE UP POSITION AFTER PROGRESSIVE INSPECTION WAS PERFORMED ON AIRCRAFT BY MAINTENANCE. BELIEVE THAT HANDLE HAS A SHORT INTERNALLY CAUSED BY THE SHORTING OUT THE HYDRAULIC CONTROL RELAY AND THE RELAY AND DIODES BOA - [SDR VJ32003F00007](https://openairdocs.org/sdr/VJ32003F00007.md): Motor · inoperative · Dec 9, 2002 · N865AF · Grob G120A · Hydraulic Pump (Electric/Engine), Main > DURING PROGRESSIVE INSPECTION AND CYCLING THE GEAR THE HYDRAULIC PUMP RCCB CIRCUIT BREAKER WOULD POP. THE HYDRAULIC MOTOR ON THE HYDRAULIC PUMP UNIT WAS PUTTING OUT OVER 75 AMPS. - [SDR VJ32003F00009](https://openairdocs.org/sdr/VJ32003F00009.md): Relay · shorted · Dec 9, 2002 · N864AF · Grob G120A · Hydraulic System, Main > DURING PROGRESSIVE INSPECTION AND CYCLE OF THE LANDING GEAR, WE HAD A FAILURE OCCUR. FOUND A BAD HYD. CONTROL RELAY THAT SHORTED. BECAUSE OF THAT SHORT, IT ALLOWED TOO MUCH CURRENT TO FLOW TO PC BOARD AND SHORT OUT BOARD BETWEEN RELAY K-13 PIN 13 AND 16 TO B - [SDR VJ32003F00003](https://openairdocs.org/sdr/VJ32003F00003.md): Shock Mount · damaged · Dec 4, 2002 · N862AF · Grob G120A · Engine Mount Section > DURING PROGRESSIVE INSPECTION OF ENGINE BAY, FOUND LOWER LEFT LORD MOUNT DAMAGED FROM HEAT OF EXHAUST SYSTEM. SUGGEST INSTALLING SOME TYPE OF HEAT SHIELDING OR CHANGING MOUNT TO A MORE HEAT RESISTANT STYLE. PART RETURNED FOR WARRANTY. - [SDR VJ32003F00005](https://openairdocs.org/sdr/VJ32003F00005.md): Shock Mount · damaged · Dec 4, 2002 · N861AF · Grob G120A · Engine Mount Section > DURING PROGRESSIVE INSPECTION OF ENGINE BAY FOUND LOWER LT MOUNT DAMAGED FROM HEAT OF EXHAUST SYSTEM. SUGGEST INSTALLING SOME TYPE OF HEAT SHIELDING OR CHANGING MOUNT TO A MORE HEAT RESISTANT STYLE. - [SDR VJ32002F00065](https://openairdocs.org/sdr/VJ32002F00065.md): Downlock Switch · failed · Sep 6, 2002 · N864AF · Grob G120A · Landing Gear Position and Warning > DOWN SWITCH FAILED CAUSING NO DOWN INDICATION OF NOSE GEAR IN THE DOWN POSITION. - [SDR VJ32002F00066](https://openairdocs.org/sdr/VJ32002F00066.md): Handle · failed · Sep 6, 2002 · N864AF · Grob G120A · Landing Gear Position and Warning > GEAR HANDLE EXPERIENCED INTERNAL FAILURE CAUSING MALFUNCTION OF THE HYDRAULIC GEAR PUMP. WHEN THE PUSH TO TEST BUTTON WAS PRESSED FOR THE ANNUNCIATOR PANEL, THE PUMP WOULD OPERATE. - [SDR VJ32002F00068](https://openairdocs.org/sdr/VJ32002F00068.md): Sensor · broken · Sep 6, 2002 · N864AF · Grob G120A · Magneto/Distributor > RPM INDICATION SENSOR RING FOUND BROKEN DURING ROUTINE INSPECTION. THIS SENSOR RING FITS UNDER THE VENT OF THE RIGHT MAGNETO AND PROVIDES ENGINE RPM INDICATIONS. APPEARS TO BE BROKEN DUE TO FLEXING/FATIGUE. PERHAPS A DIFFERENT SENSOR OR OTHER MORE SECURE MO - [SDR VJ32002F00044](https://openairdocs.org/sdr/VJ32002F00044.md): Baffle · cracked · May 21, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. - [SDR VJ32002F00045](https://openairdocs.org/sdr/VJ32002F00045.md): Pump · failed · May 21, 2002 · N864AF · Grob G120A · Pneumatic System > IN FLIGHT THE INSTRUMENT VACUUM SYSTEM FAIL. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR HAD FROZEN UP AND THE SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CHE - [SDR VJ32002F00039](https://openairdocs.org/sdr/VJ32002F00039.md): Rod · chafed · May 20, 2002 · N863AF · Grob G120A · Aileron Control System > AILERON ROD RUBBING AILERON BELL CRANK. REMOVED ROD AND INSTALLED NEW ROD. CONTROL ASSEMBLY WAS SHIMMED TO CORRECT THE PROBLEM. - [SDR VJ32002F00040](https://openairdocs.org/sdr/VJ32002F00040.md): Rod · chafed · May 20, 2002 · N863AF · Grob G120A · Elevator Control System > ELEVATOR CONTROL ROD RUBBING AILERON CROSS OVER TUBE. REMOVED TUBE AND INSTALLED NEW TUBE. NEW SHIM PLATES INSTALLED, TO CORRECT PROBLEM. - [SDR VJ32002F00041](https://openairdocs.org/sdr/VJ32002F00041.md): Clock · broken · May 20, 2002 · N863AF · Grob G120A · Independent Instruments > LEFT HAND STOP PIN BROKEN OFF. REMOVED AND REPLACED NEW CLOCK. - [SDR VJ32002F00038](https://openairdocs.org/sdr/VJ32002F00038.md): Pump · failed · May 16, 2002 · N865AF · Grob G120A · Pneumatic System > IN FLIGHT, THE INSTRUMENT VACUUM SYSTEM FAILED. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR HAD FROZEN UP AND THE SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM C - [SDR VJ32002F00043](https://openairdocs.org/sdr/VJ32002F00043.md): Baffle · cracked · May 16, 2002 · N865AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. - [SDR VJ32002F00042](https://openairdocs.org/sdr/VJ32002F00042.md): Pump · burned out · May 15, 2002 · N861AF · Grob G120A · Hydraulic Pump (Electric/Engine), Main > LANDING GEAR FAILED, WHEN THE GEAR WAS SELECTED TO THE UP POSITION AFTER TAKE OFF. THE GEAR WAS LOWER AND A SAFE LANDING WAS MADE. INSPECTION OF THE GEAR SYSTEM FOUND THAT THE MOTOR ON THE HYDRAULIC PUMP BURNED OUT. PUMP ASSEMBLY WAS REMOVED AND A NEW PUMP - [SDR VJ32002F00036](https://openairdocs.org/sdr/VJ32002F00036.md): Pump · failed · May 10, 2002 · N865AF · Grob G120A · Hydraulic Pump (Electric/Engine), Main > IN FLIGHT, THE LANDING GEAR HYDRAULIC PUMP CIRCUIT BREAKER POPPED WITH THE GEAR UP, THE GEAR WAS LOWERED AND A SAFE LANDING WAS MADE. AIRCRAFT WAS PLACED ON JACKS AND THE GEAR SYSTEM WAS OPERATIONAL CHECKED. WITH THE GEAR UP AND LOCKED THE HYDRAULIC PUMP WOU - [SDR VJ32002F00031](https://openairdocs.org/sdr/VJ32002F00031.md): Pump · inoperative · May 7, 2002 · N863AF · Grob G102ASTIR · Engine Fuel Pump > AT 800 RPM THE FUEL PRESSURE DROPS BELOW MINIMUM AND THE LOW PRESSURE LIGHT CAME ON AT IDLE. SYSTEM WAS CHECKED AND FOUND THAT THE PUMP OUT PUT WAS LOW. PUMP REMOVED AND A NEW PUMP INSTALLED. GROUND RUN AND FINAL ADJUSTMENTS TO THE PUMP WERE MADE. OPERATIO - [SDR VJ32002F00032](https://openairdocs.org/sdr/VJ32002F00032.md): Pump · sheared · May 7, 2002 · N862AF · Grob G120A · Pneumatic System > METAL SHAFT SHEARED IN PUMP. REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL. PUMP SENT IN FOR WARRANTY. - [SDR VJ32002F00033](https://openairdocs.org/sdr/VJ32002F00033.md): Baffle · cracked · May 6, 2002 · N862AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY. - [SDR VJ32002F00034](https://openairdocs.org/sdr/VJ32002F00034.md): Baffle · cracked · May 6, 2002 · N862AF · Grob G120A · Reciprocating Engine Cylinder Section > ENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY. - [SDR VJ32002F00029](https://openairdocs.org/sdr/VJ32002F00029.md): Bracket · cracked · Apr 26, 2002 · N863AF · Grob G102ASTIR · AC Generation System > ALTERNATOR SUPPORT BRACKET CRACKED. PART REMOVED AND A NEW SUPPORT BRACKET INSTALLED. PART SENT IN FOR WARRANTY. - [SDR 2002FA0000515](https://openairdocs.org/sdr/2002FA0000515.md): Pump · failed · Apr 15, 2002 · N865AF · Grob G102ASTIR · Hydraulic Pump (Electric/Engine), Main > THE LANDING GEAR WAS SWLECTED IN FLIGHT TO THE DOWN POSITION; THE RIGHT MAIN GEAR LIGHT FAILED TO COME ON IN THE DOWN AND LOCKED POSITION. THE AIRCRAFT WAS YAWED AND THE DOWN AND LOCK GEAR LIGHT CAME ON. A SAFE LANDING WAS MADE. AIRCRAFT WAS TAKEN TO MAINTE - [SDR 2002FA0000514](https://openairdocs.org/sdr/2002FA0000514.md): Handle · failed · Apr 12, 2002 · N862AF · Grob G102ASTIR · Landing Gear Selector > LANDING GEAR WAS CYCLED TO THE DOWN POSITION IN FLIGHT, BOTH MAIN GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS FAILED TO COME ON. THE SYSTEM WAS TESTED IAW FLIGHT MANUAL PROCEDURES AND THE LIGHTS FOR THE NOSE GE - [SDR 2002FA0000484](https://openairdocs.org/sdr/2002FA0000484.md): Audio Panel · failed · Apr 5, 2002 · N863AF · Grob G102ASTIR · Central Warning > AUDIO PANEL FAIL INTERNALLY GIVING AND UNSAFE GEAR INDICATION LIGHT, AND WHEN THE THROTTLE WAS PULLED TO IDLE, THE HYDRAULIC PUMP WOULD START TO RUN. REMOVED AND INSTALLED NEW AUDIO PANEL. THE LANDING GEAR OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRAN - [SDR 2002FA0000474](https://openairdocs.org/sdr/2002FA0000474.md): Switch · failed · Apr 2, 2002 · N865AF · Grob G102ASTIR · Magneto/Distributor > MAGNETO SWITCH FAILED TO START ENGINE, FOUND BAD SWITCH. NEW SWITCH INSTALLED, OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY. - [SDR 2002FA0000481](https://openairdocs.org/sdr/2002FA0000481.md): Actuator · failed · Apr 2, 2002 · N862AF · Grob G102ASTIR · Landing Gear Actuator > NOSE LANDING GEAR HYDRAULIC ACTUATOR BOTTOM SEAL AROUND SHAFT BLOW OUT AND LEAKING FLUID FROM CYLINDER. ACTUATOR REMOVED AND A NEW ACTUATOR INSTALLED. ACTUATOR SENT IN FOR WARRANTY. - [SDR 2002FA0000477](https://openairdocs.org/sdr/2002FA0000477.md): Pin · broken · Apr 1, 2002 · N861AF · Grob G102ASTIR · Independent Instruments > LEFT HAND STOP PIN BROKEN OFF, REMOVED AND INSTALLED NEW CLOCK. PART SENT IN FOR WARRANTY. - [SDR 2002FA0000478](https://openairdocs.org/sdr/2002FA0000478.md): Pump · damaged · Apr 1, 2002 · N861AF · Grob G102ASTIR · Pneumatic System > METAL SHAFT SHEARED IN PUMP. REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL. PUMP SENT IN FOR WARRANTY. - [SDR 2002FA0000480](https://openairdocs.org/sdr/2002FA0000480.md): Servo · sticking · Apr 1, 2002 · N862AF · Grob G102ASTIR · Aileron Tab Control System > TRIM SERVO STICKING IN OPERATION AND FAILS TO MOVE THE AILERON TRIM TAB. REMOVED AND INSTALLED NEW TRIM SERVO ASSEMBLY. PART SENT IN FOR WARRANTY. - [SDR 2002FA0000482](https://openairdocs.org/sdr/2002FA0000482.md): Pump · inoperative · Apr 1, 2002 · N863AF · Grob G102ASTIR · Hydraulic Pump (Electric/Engine), Main > ELECTRIC MOTOR SLOW IN FLIGHT, OVER 25 TO 30 SECONDS TO RETRACT AND EXTENT THE LANDING GEAR. NEW HYDRAULIC PUMP ASSEMBLY INSTALLED, CYCLED GEAR IAW MAINTENANCE MANUAL, LANDING GEAR OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY. - [SDR 2002FA0000483](https://openairdocs.org/sdr/2002FA0000483.md): Filter · inoperative · Apr 1, 2002 · N863AF · Grob G102ASTIR · Communications System > FEED BACK IN THE RADIOS, NEW FILTER INSTALLED, OPERATIONAL CHECK NORMAL. PART SENT IN FOR WARRANTY. - [SDR 2003FA0001092](https://openairdocs.org/sdr/2003FA0001092.md): Flange · cracked · Jul 1, 2001 · N260GR · Pitts S2B · Reciprocating Engine Power Section > FOUND CRACKED CRANKSHAFT FLANGE. INSTALLED 3 BLADE MT PROP TO DECREASE STRESS ON CRANKSHAFT.(K) - [SDR 2003FA0001091](https://openairdocs.org/sdr/2003FA0001091.md): Flange · cracked · Jun 1, 2001 · N260MM · Pitts S2B · Reciprocating Engine Power Section > FOUND CRACKED CRANKSHAFT FLANGE. INSTALLED 3 BLADE PROP TO DECREASE STRESS ON CRANKSHAFT. Next page: https://openairdocs.org/engine/lycoming-aeio-540-d4a5/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 = 'AEIO540D4A5' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/engine/lycoming-aeio-540-d4a5/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.