# Service difficulty reports: N812FD, cancelled Feb 6, 2024 A list on [N812FD, cancelled Feb 6, 2024](https://openairdocs.org/deregistered/N812FD-2024-02-06.md). Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first. Page 1 of 2 · 85 reports - [SDR FDEA201403120491](https://openairdocs.org/sdr/FDEA201403120491.md): Check Valve · leaking · Mar 12, 2014 · N812FD · Airbus A310324 · Hydraulic System, Main > LOST GREEN HYD AIR AT FLT LEVEL 390 IAW QRH QTY WAS MONITORED AFTER 1 MIN GREEN HYD QTY FLUCTUATED & PEGGED AT MAX. IAW QRH GREEN HYD PUMPS 1 & 2 WERE SECURED, IAW QRH LANDED. REPLACED DEPRESSURIZATION RELEIF VALVE IAW AMM 29-11-27-04. ALSO REPLACED GREEN - [SDR FDEA201312102953](https://openairdocs.org/sdr/FDEA201312102953.md): Controller · failed · Dec 10, 2013 · N812FD · Airbus A310 · Cabin Pressure Controller > ON DESCENT TO KMDT RECEIVED CAD REG 2 FAULT, RESET NO HELP. ON LANDING, ACFT SHOWED 3300 CAB ALT, WENT TO MANUAL, TURNED OFF BLEEDS & PACKS. CABIN OUTFLOW VLVS FWD & AFT STAYED CLOSED. OVERBOARD VENT PARTIALLY OPENED, ACFT STILL PRESSURIZED. SAFETY VLV STA - [SDR FDEA201308021750](https://openairdocs.org/sdr/FDEA201308021750.md): Jackscrew · contaminated · Aug 2, 2013 · N812FD · Airbus A310324 · Leading Edge Slat Control System > NR 1 & 2 SLAT SYSTEMS FAULTED ON APPROACH. COMPLIED WITH PHASE 1, NO HELP. COMPLIED WITH ECAM AND QRH. ON CONFIGURING FOR LANDING IAW QRH SLAT EXTENDED NORMALLY. SFCC 1 & 2 FAULT INDICATES SLAT 01111 SLAT BINDING IAW TSM 27-80-02, FIG 101. FOUND LT L/E TO - [SDR FDEA201301170121](https://openairdocs.org/sdr/FDEA201301170121.md): Connector · failed · Jan 17, 2013 · N812FD · Airbus A310324 · Ground Proximity System > CAPTAIN'S RA DOES NOT PROPERLY AGREE WITH FO'S RA. DURING TROUBLESHOOTING NR 1 R/A WOULD FLUCTUATE BETWEEN 150FT AND 450FT, THEN GO ABOVE 2500FT. DISCONNECTED BOTH TRANSMIT AND RECEIVING ANTENNAS AND METERED BOTH COAX CABLES FROM NR 1 R/A RACK CONNECTOR (1 - [SDR FDEA201212244367](https://openairdocs.org/sdr/FDEA201212244367.md): Skin · delaminated · Dec 24, 2012 · N812FD · Airbus A310324 · Trailing Edge Flaps > RIGHT WING INBD LOWER FLAP T/E MID SECTION FOUND DELAMINATED. REMOVED DELAMINATED DOUBLER & DAMAGED HONEYCOMB CORE IAW SRM 57-52-12/201. MADE NEW SKIN DOUBLER IAW SRM 57-52-12/201. MADE HONEYCOMB CORE PLUG SRM 57-52-12/201. INSTALLED HONEYCOMB CORE PLUG AN - [SDR FDEA201212244368](https://openairdocs.org/sdr/FDEA201212244368.md): Skin · delaminated · Dec 24, 2012 · N812FD · Airbus A310324 · Trailing Edge Flaps > LEFT WING OTBD FLAP T/E LOWER SURFACE FOUND DELAMINATED, FROM INBD TO OTBD 2000 MM, DIM:16" X 7". REMOVED DELAMINATED LOWER SKIN IAW SRM 57-53-12/201. MADE NEW SKIN DOUBLER IAW SRM 57-53-12/201. FILLED THE HONEYCOMB CORE WITH COMPOUND IAW SRM 57-53-12/201. - [SDR FDEA201212154307](https://openairdocs.org/sdr/FDEA201212154307.md): Fitting · corroded · Dec 15, 2012 · N812FD · Airbus A310324 · Wing, Landing Gear Attach Fittings > LEFT WING-MLG FITTING-INSPECTION OF RIB 5 FORWARD LUG CORROSION EXCEED LIMITS. REMOVED CORROSION IAW REPAIR DWG R57249389, ISSUE B, STEP 1B. IAW EA6-5710-163164. PENETRANT INSPECT THE LUG BORE IAW NTM 51-90-00 TO CONFIRM ALL DAMAGED COMPLETELY REMOVED. IAW - [SDR FDEA201212144299](https://openairdocs.org/sdr/FDEA201212144299.md): Spar · cracked · Dec 14, 2012 · N812FD · Airbus A310324 · Wing Spar > CENTER WING RT REAR SPAR NR 61 HOLE FOUND CRACKED. REAMED HOLE AT 0.4MM THROUGH ALL LAYERS PER EA6-5710-163167. INSPECTED PER NTM51-10-01,NO CRACK FOUND. REAMED UP THE HOLE ON ALL LAYERS TO 15.836-15.875MM IN TRANSITION FIT PER EA6-5710-163167. WET INSTALL - [SDR FDEA201212144297](https://openairdocs.org/sdr/FDEA201212144297.md): Plate · cracked · Dec 14, 2012 · N812FD · Airbus A310324 · Wing Miscellaneous Structure > FOUND A CRACK ABOUT 5MM IN LENGTH, 1MM IN DEPTH INITIATED FROM THE NR 2 FASTENER HOLE OF THE RT WING UPPER CORNER ANGLE AT FR40. REAMED NR 2 HOLE AT 0.4MM THROUGH ALL LAYERS PER EA6-5710-163166. INSPECTED PER NTM51-10-01,NO CRACK FOUND. REAMED HOLE ON ALL L - [SDR FDEA201109294213](https://openairdocs.org/sdr/FDEA201109294213.md): Solenoid Valve · leaking · Sep 29, 2011 · N812FD · Airbus A310324 · Hydraulic Indicating System > GREEN HYD SYS LO RSVR INDICATION INFLIGHT FOLLOWED QRH, AFTER LANDING GREEN SYS REVR INDICATION RETURNED TO NORMAL. RESTORED FREE FALL EXTENSION SYSTEM TO NORMAL CONDITION AS PER AMM 32-33-00-2. PRESSURED GREEN HYD SYS AS PER AMM29-00-00-06, FOUND KRUEGER S - [SDR FDEA201011164400](https://openairdocs.org/sdr/FDEA201011164400.md): Skin · corroded · Nov 16, 2010 · N812FD · Airbus A310324 · Fuselage Main, Plate/Skin > FUSELAGE SKIN EXTERIOR SURFACE FOUND CORROSION UNDER BULK CARGO DOOR SCUFF PLATE (FWD LWR CORNER). REMOVE THE CORROSION IAW SRM 51-74-10. APPLY ALODINE IAW SRM 51-21-10. MEASURE REMAIN THICKNESS OF THE REWORKED AREA IAW NTM51-10-04 (REMAINING THICKNESS WA - [SDR FDEA201009263716](https://openairdocs.org/sdr/FDEA201009263716.md): Computer · malfunctioned · Sep 26, 2010 · N812FD · Airbus A310324 · Fuel Indicating System > ON TAKEOFF ROLL, MASTER WARNING REPETITIVE CHIME, AT APPROX 130 KTS RTO. ECAM SHOWED PITCH TRIM 2 YD 2 OFF. PITCH TRIM 2 YD 2 BOTH RESET OK. BRAKE 3 670 DEGREES. WHILE WAITING FOR HOT BRAKES TO COOL, FUEL WENT BELOW RQR FOR FOR TO. SO RETURN TO GATE, O - [SDR FDEA201003301032](https://openairdocs.org/sdr/FDEA201003301032.md): B-Nut · leaking · Mar 30, 2010 · N812FD · Airbus A310324 · Hydraulic System, Main > HYD GREEN SYS SERVICED WITHIN LIMITS, 10 MINUTES AFTER DEPARTURE, QTY IN AMBER BAN D. TURNED OFF NR 1 ENG HYD PUMP PRIOR TO TO RED DOT IN AMBER BAND AT FLT LEVEL 20. 15 MINUTES LATER RESERVOIR EMPTY. COMPLIED WITH QRH. SAFE LANDING. FOUND FLUID LEAKING O - [SDR FDEA201003070672](https://openairdocs.org/sdr/FDEA201003070672.md): Jackscrew · failed · Mar 7, 2010 · N812FD · Airbus A310324 · Leading Edge Slat Control System > RECEIVED SLAT SYS 1 AND SYS 2 FAULT. SLAT STUCK AT APPROX 2 DEG, LANDED SLATS 2 DEG AND FLAPS 40 DEG, REPEAT WRITE UP. CYCLED ON THE GROUND PRIOR TO DEPARTURE AND THEY WORKED OK. CYCLED AIRBORN AND THEY STUCK. APPEAR TO BE AIRLOAD RELATED, CYCLED AT 210 KT - [SDR FDEA200911204098](https://openairdocs.org/sdr/FDEA200911204098.md): Brake Sys · malfunctioned · Nov 20, 2009 · N812FD · Airbus A310324 · Landing Gear Brake System > DURING TRO WITH MAX BRAKES SELECTED, ONLY WHEEL BRAKES ON NR1,2,5,6 (LT SIDE) OPERATED NORMALLY. ACFT STARTED ABRUPT PULL TO LT DESELECTED AUTO BRAKES AND STOPPED USING MANUAL BRAKES. MEL 20NOV09 14:24 GRR RELEASED FOR SERVICE IAW MEL: 32-42-05 CATEGORY: - [SDR FDEA200911204097](https://openairdocs.org/sdr/FDEA200911204097.md): Anti-Ice System · faulted · Nov 20, 2009 · N812FD · Airbus A310324 · Engine Anti-Icing System > DURING T/O POWER APPLICATION, WHEN TOGA PWR WAS SELECTED THE GREEN A/THR LIGHT ILLUMINATED HOWEVER THE THROTTLES WOULD NOT MOVE. ACCOMPLISHED RTO AT 25 KTS. VERIFIED AT BLOCK IN NR1 ENGINE ANTI ICE WAS FAULTING IN ECAM. RELEASED FOR SERVICE IAW MEL: 22-30-01 - [SDR FDEA200911204095](https://openairdocs.org/sdr/FDEA200911204095.md): Anti-Ice Valve · faulted · Nov 20, 2009 · N812FD · Airbus A310324 · Air Intake Anti/De-Ice System > DURING TAKEOFF ROLL AT 85KTS ECAM WARNING "ENG NAC ANTI ICE VALVE". ACCOMPLISHED RTO (ENG NR1) ENG ANTI ICE WAS ON DURING TAKE OFF. VERIFIED AT BLOCK IN NR 1 ENG ANTI ICE WAS FAULTING IN ECAM. VERIFIED AT BLOCK IN NR 1 ENG ANTI ICE WAS FAULTING IN ECAM. "ME - [SDR FDEA200911204093](https://openairdocs.org/sdr/FDEA200911204093.md): Anti-Ice Valve · warning message · Nov 20, 2009 · N812FD · Airbus A310324 · Air Intake Anti/De-Ice System > DURING TAKEOFF ROLL WITH ANTI-ICE ON, RECEIVED ECAM MESSAGE "ENG NR1 ANTI-ICE NAC VALVE". ACCOMPLISHED RTO AT 70 KTS. (RTO 1 OF 2) SEE WRI 30-20/3659 FOR DEFERRAL OF NR1 ENG NAC A/I VALVE. FAULT CLEARED WHEN REDUCING POWER, NO FURTHER FAULTS. CREW TAXIED - [SDR FDEA200811184905](https://openairdocs.org/sdr/FDEA200811184905.md): Control Unit · binding · Nov 18, 2008 · N812FD · Airbus A310324 · Rudder Control System > SECOND REJECTED T/O DUE TO BLUE RUDDER SERVO CONTROL JAM, ECAM WARNING CAME ON AT 40-50 PERCENT N1. NO FAULT FOUND ON 1ST RTO. RAN ENGINE & CHECKED ALL FLT CONTROL OPERATIONS (WRI 27-20/2731). REPLACED JAMMING DETECTION CONTROL UNIT IAW AMM 27-14-17-4 PREC - [SDR 08FDEA04905](https://openairdocs.org/sdr/08FDEA04905.md): Control Unit · inoperative · Nov 18, 2008 · N812FD · Airbus A310324 · Rudder Control System > 2ND REJECTED TAKEOFF DUE TO BLUE RUDDER SERVO CTL JAM, ECAM WARNING CAME ON AT 40-50 PERCENT N1. NO FAULT FOUND ON 1ST RTO, RAN ENG AND CHECKED ALL FLT CONTROL OPERATION (WRI 27-20/2731). REPLACED JAMMING DETECTION CONTROL UNIT PER AMM 27-14-17-4 PRE CAUTION - [SDR 08FDEA03353](https://openairdocs.org/sdr/08FDEA03353.md): Skin · damaged · Aug 9, 2008 · N812FD · Airbus A310324 · Rudder, Plate/Skin > UPON INSPECTION OF RUDDER BY THERMOGRAPHY IAW EO 6-5530-7-5004 PT 2 PARA 8 STEP C AND D THE FOLLOWING DEFECTS WERE NOTED IN ADDITION TO ORIGINAL FINDINGS REF EA 6-5740-118399 THE UPPER RT PORTION OF THE RUDDER HAS 1 ADDITIONAL AREA OF MOISTURE MEASURING.960 W - [SDR 08FDEA03264](https://openairdocs.org/sdr/08FDEA03264.md): Skin · dented · Aug 5, 2008 · N812FD · Airbus A310324 · Fuselage Main, Plate/Skin > EXTERNAL LT FUSELAGE SKIN HAS 2 DENTS. NR 1 AT FRAME 60 BETWEEN STRINGER 43 AND 44L 4 INCHES ABOVE BOTTOM SKIN LAP MEASURES 6 INCHES LONG BY.800 INCHES WIDE BY.037 INCHES DEEP. NR 2 DENT AT FRAME 61 BETWEEN STRINGER 43 AND 44L 3 INCHES ABOVE SKIN LAP MEASU - [SDR 08FDEA03263](https://openairdocs.org/sdr/08FDEA03263.md): Skin · dented · Aug 5, 2008 · N812FD · Airbus A310324 · Wing, Plate/Skin > DENT IN RT NR 1 LEADING EDGE SLAT, DENT MEASURES 4 INCH LONG BETWEEN RIBS 7 AND 8, 35 INCHES FROM INBD EDGE, 5 1/2 INCHES BELOW PAINTED SURFACE, AND 5/32 INCH DEEP. REMOVED DAMAGE AND REPAIRED DENT ON RT NR 1 LEADING EDGE SLAT BETWEEN RIBS 7 AND 8, 35 INCH FR - [SDR 07FDEA03644](https://openairdocs.org/sdr/07FDEA03644.md): Angle · mismanufactured · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > LESS EDGE MARGIN (5-6 MM) AT ANGLES STRG 26 RT AT FRAME 69 AND STRG 26 LT FRAME 63 AND 65. IT'S IMPOSSIBLE TO INSTALL DAN5-6X OR DAN5-8 FASTENER DURING PTOF. REPAIR PERFORMED BY INSTALLING REPAIR ANGLES FABRICATED IN EFW-DRS (RE0074-201/RE0074-200) IAW SRM 5 - [SDR 07FDEA03642](https://openairdocs.org/sdr/07FDEA03642.md): Fitting · cracked · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CRACKED ATTACHMENT HOLES IN CORNER PROFILE AT FRAME 25A BETWEEN STRG. 28-34 RT. REPLACEMENT OF CORNER PROFILE IAW SRM 51-72-10 AND PTOF DRW, R255B0061. - [SDR 07FDEA03641](https://openairdocs.org/sdr/07FDEA03641.md): Fitting · cracked · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CRACKED ATTACHMENT HOLES IN CORNER PROFILE AT FRAME 25A BETWEEN STRG 28-34 RT. REPLACEMENT OF CORNER PROFILE IAW SRM 51-72-10 AND PTOF DRW, R255B0061. - [SDR 07FDEA03634](https://openairdocs.org/sdr/07FDEA03634.md): Bracket · cracked · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CRACKED BRACKET AT FRAME 19, STRG 50 LT. REPLACEMENT OF BRACKET IAW SRM 51-72-10. - [SDR 07FDEA03633](https://openairdocs.org/sdr/07FDEA03633.md): Bracket · cracked · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CRACKED BRACKET AT FRAME 19, STRG 49 LT. REPLACEMENT OF BRACKET IAW SRM 51-72-10. - [SDR 07FDEA03632](https://openairdocs.org/sdr/07FDEA03632.md): Bracket · cracked · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CRACKED BRACKET AT FRAME 19, STRG 46 LT. REPLACEMENT OF BRACKET IAW SRM 51-72-10. - [SDR 07FDEA03663](https://openairdocs.org/sdr/07FDEA03663.md): Fitting · damaged · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > FOUND MISDRILLED HOLE IN CORNER FITTING ADJACENT AND LESS MARGIN TO ROLLER TRACK HOLE, FRAME 60, CARGO FLOOR STRUCTURE, Y1460 LT. REPAIR PERFORMED BY CREATING AN OBLONG HOLE AND INSTALLING FASTENER WITH STRENGTHENING PLATE IAW 6-5317-95859 AND RAS/DAHAM/40202 - [SDR 07FDEA03662](https://openairdocs.org/sdr/07FDEA03662.md): Door Frame · damaged · Sep 13, 2007 · N812FD · Airbus A310324 · Passenger/Crew Doors > TOOLING IMPACTS FOUND ON DOOR FRAME 14 UNDER DOOR STOP 8 LH, PAX DOOR 1. REPAIR PERFORMED BY SMOOTH BLEND OUT, DVI INSPECTING OF FASTENER HOLES AND HFEC INSPECTION OF BLENDED AREAS FOR CRACK FREE CONDITION IAW EA 6-5312-95486 AND RAS 041687/013/2005 ISSUE A. - [SDR 07FDEA03659](https://openairdocs.org/sdr/07FDEA03659.md): Frame · dented · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Main, Frame > TOOL IMPACT CAUSES DENT IN FRAME 71, STRG 15 RHS. SPLICE REPAIR PERFORMED IAW SRM 53-10-13 / PG 210, 213 / FIG 203. - [SDR 07FDEA03658](https://openairdocs.org/sdr/07FDEA03658.md): Frame · dented · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Main, Frame > TOOL IMPACT CAUSES DENT IN FRAME 70, STRG 15 RHS. SPLICE REPAIR PERFORMED IAW SRM 53-10-13 / PG 210, 213/FIG 203. - [SDR 07FDEA03656](https://openairdocs.org/sdr/07FDEA03656.md): Frame · corroded · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Main, Frame > HEAVY CORROSION FOUND ON THE T-SECTION AT FRAME 92, BETWEEN STRG 19-23 LT (TAILCONE). REPAIR PERFORMED BY CUT OUT THE T-SECTION AND INSTALLING NEW PORTION AND REPAIR ANGLES IAW EA 6-5319-92229 AND RAS/DAHAM/4020157/2005 ISSUE B. - [SDR 07FDEA03653](https://openairdocs.org/sdr/07FDEA03653.md): Floor Support · corroded · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > HEAVY CORROSION ON FLOOR SUPPORT BETWEEN FRAME 14-17, STRINGER 26, Y-1959 RT. REPAIR PERFORMED BY REINFORCING WITH ANGLE IAW SRM 53-12-15/FIG 207. - [SDR 07FDEA03651](https://openairdocs.org/sdr/07FDEA03651.md): Fitting · damaged · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > MISDRILLED HOLE IN CORNER FITTING FRAME 54.1 RT DUE TO FAILED INSTALLED ROLLERTRACK ON CARGO FLOOR STRUCTURE. REPLACEMENT OF CORNERFITTING IAW SRM 51-72-10. - [SDR 07FDEA03650](https://openairdocs.org/sdr/07FDEA03650.md): Angle · failed · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > LESS MARGIN AT ONE HOLE AT FRAME 59, STRG 26 LT. NEW SUPPORT CAN'T BE INSTALLED BETWEEN FRAME 59 AND SEAT TRACK AS PER DRW, R539H0112. REPAIR PERFORMED BY INSTALLING REINFORCING PLATE WHICH IS FIXED WITH HI-LOK'S DAN5-5 IAW, SRM 51-72-10 AND EFW DD-0467024 - [SDR 07FDEA03648](https://openairdocs.org/sdr/07FDEA03648.md): Skin · corroded · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Main, Plate/Skin > HEAVY CORROSION UNDER ANTI-CHAFING PLATE ON SKIN PANEL BETWEEN FRAME 92-94, STRG 9-13 LT AND RT, OUT OF LIMIT. REPLACEMENT OF BOTH SKIN-PANELS (FABRICATED BY EFW-DRS) IAW SRM 51-72-10. - [SDR 07FDEA03647](https://openairdocs.org/sdr/07FDEA03647.md): Stringer · damaged · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Main, Longeron/Stringer > SEVERAL MISDRILLED HOLES ON STRINGER 33 RT BETWEEN FRAME 69-70. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201 / SEC "C-C". - [SDR 07FDEA03645](https://openairdocs.org/sdr/07FDEA03645.md): Skin · dented · Sep 13, 2007 · N812FD · Airbus A310324 · Elevator, Plate/Skin > DENT IN BOTTOM SKIN OF LT ELEVATOR TRAILING EDGE (30X30X1,5). REPAIR PERFORMED IAW SRM 55-21-11/CONFIG 1/PARA 5D/FIG 204. - [SDR 07FDEA03637](https://openairdocs.org/sdr/07FDEA03637.md): Plate · cracked · Sep 13, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CRACKED SHEAR PLATES BETWEEN FRAME 79-80/82, STRG 26 LT AND RT. REPLACEMENT OF BOTH SHEAR PLATES IAW SRM 51-72-10. - [SDR 07FDEA03631](https://openairdocs.org/sdr/07FDEA03631.md): Skin Panel · chafed · Sep 13, 2007 · N812FD · Airbus A310324 · Wing, Plate/Skin > CHAFING MARKS FOUND AROUND MANHOLE 9 APERTURE ON THE UPPER SURFACE OF THE BOTTOM WING SKIN PANEL NR 2 BETWEEN RIB 14-15, BOTH WINGS. REPAIR PERFORMED BY SMOOTH BLEND OUT, NDT INSPECTION FOR CRACK FREE AND FILLING BLEND LEVEL RESIN IAW EA 6-5720-92205 AND RAS/ - [SDR 07FDEA03616](https://openairdocs.org/sdr/07FDEA03616.md): Skin · corroded · Sep 12, 2007 · N812FD · Airbus A310324 · Wing, Plate/Skin > FOUND SKIN BULGE (CORROSION) ON LEADING EDGE OF RT WING INBOARD FLAP, NEAR TO TRACK 1. REPLACEMENT OF L/E SKIN AT FLAP IAW SRM 51-72-10. - [SDR 07FDEA03615](https://openairdocs.org/sdr/07FDEA03615.md): Tube · cracked · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > DAMAGED (CRACKED) TUBE ASSY BETWEEN FRAME 24-25, STRG 52 RT. REPLACEMENT OF TUBE ASSY IAW SRM 51-72-10. - [SDR 07FDEA03628](https://openairdocs.org/sdr/07FDEA03628.md): Stringer · corroded · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Main, Longeron/Stringer > CORROSION ON STRINGER 53, 54 AND 55 LHS BETWEEN FRAME 70-71. STRINGER SPLICE REPAIRS PERFORMED IAW SRM 53-10-14/FIG 201. - [SDR 07FDEA03627](https://openairdocs.org/sdr/07FDEA03627.md): Web · damaged · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > FOUND DAMAGED WEB PLATE BETWEEN FRAME 86-87, STRG 36 LT. REPLACEMENT OF WEB PLATE IAW SRM 51-72-10 AND SRM 53-19-18/PG 76/ ITEM 40. - [SDR 07FDEA03626](https://openairdocs.org/sdr/07FDEA03626.md): Web · damaged · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > FOUND DAMAGED WEB PLATE BETWEEN FRAME 86-87, STRG 39 RT. REPLACEMENT OF WEB PLATE IAW SRM 51-72-10 AND SRM 53-19-18 / PG 76 / ITEM 10. - [SDR 07FDEA03625](https://openairdocs.org/sdr/07FDEA03625.md): Web · damaged · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > FOUND DAMAGED WEB PLATES BETWEEN FRAME 86-87, STRG 33 LT AND RT. REPLACEMENT OF WEB PLATES IAW SRM 51-72-10 AND SRM 53-19-18/PG 53. - [SDR 07FDEA03624](https://openairdocs.org/sdr/07FDEA03624.md): Fitting · corroded · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Miscellaneous Structure > CORROSION ON FITTING AT FRAME 63, STR 41-45 LT, OUT OF LIMIT. REPLACEMENT OF FITTING IAW SRM 51-72-10. - [SDR 07FDEA03623](https://openairdocs.org/sdr/07FDEA03623.md): Longeron · misrepaired · Sep 12, 2007 · N812FD · Airbus A310324 · Fuselage Main, Longeron/Stringer > FOUND SPLICE REPAIR ON EXTRUSION BETWEEN FRAME 12A-14, Y-953 RT, MATERIAL NOT CONFORM TO SRM 53-12-15/FIG 207. SPLICE REPAIR ON EXTRUSION RENEWED IAW SRM 53-12-15/FIG 207. Next page: https://openairdocs.org/deregistered/N812FD-2024-02-06/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 n_number = 'N812FD' AND deregistration_id = 'N812FD-2024-02-06' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/deregistered/N812FD-2024-02-06/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.