N460AW

Service difficulty reports · 250

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Query with SQL
duckdb -csv -c "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 = 'N460AW' AND registry_match = 'registration'
  ORDER BY difficulty_date DESC"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR A6WA202408148791Bpsu · faultedFLAP FAIL 6 DEGREES ***** AIRCRAFT REMOVED FROM SERVICE ***** REF WO #337811 WC #1 AND 2 FOR CORRECTIVE ACTION R&R OF RH BPSU. RII: YES, P/N 855D100-15, S/N OFF 1702A, S/N ON 2537Aug 14, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control SystemSDR A6WA202408118790Fcu · faultedFLAP FAIL AT ZERO DEGREES INFLIGHT AT CRUISE. ***** AIRCRAFT REMOVED FROM SERVICE ***** WIRING CHECKS PERFORMED FROM BPSU HARNESS TO BACK OF FECU RACK. WIRING CHECKS GOOD. CONFIRMED CORRECT RIGGING OF BPSU'S. REF WO 337810 WC #2 FOR WORK PERFORMED. GOOD TOAug 11, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control SystemSDR A6WA202408098788Flap System · faultedON APPROACH AND SELECTING FLAPS 45. RECV'D FLAPS FAIL AT FLAPS 37 DEGREES. C/W QRH. PERFORMED NORMAL LANDING. BRAKE TEMPS NORMAL. PERFORMED FLAP RESET PROCEDURE IAW AWAC SUPPLEMENT 98-18I BOX 12. FLAPS RESET. PLACARDED AND PLACED ON MEL. ****AIRCRAFT REMOVEAug 9, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control SystemSDR A6WA202408048787Sensor · faultedON CLIMB OUT FLIGHT LEVEL 200 FLAP FAIL MESSAGE CW QRH PROCEEDED TO ORD WITHOUT INCIDENT. PERFORMED FLAP RESET PROCEDURE IAW AWAC SUPP. 98-18I BOX 12. FLAPS RESET. PLACARDED AND PLACED ON MEL. AIRCRAFT REMOVED FROM SERVICE. R/R THE LH BRAKE POSITION SENSOR Aug 4, 2024 · N460AW · Cndair CL6002B19 · Trailing Flap Position Indicating SystemSDR A6WA202407148777Control Unit · faultedWHILE DESCENDING THROUGH APPROX 14,000FT, RECEIVED FLAPS FAIL CAUTION AT FLAPS 0. C/W QRH AND MADE NORMAL LANDING. NO LEVER MOVMENT. EMERGENCY DECLARED. AIRCRAFT REMOVED FROM SERVICE. REPLACED SECU PER AMM 27-51 UNDER DIRECTION OF FIM 27-50 FIG 108. OPS CHEJul 14, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control SystemSDR A6WA202407148776Thrust Reverser · malfunctionedRECEIVED R REV UNLK CAUTION MESSAGE WHILE CLIMBING. COMPLIED WITH IAC AND QRH, MESSAGE REMAINED. RETURNED TO DAY. NO DRAG OBSERVED ON RIGHT ENGINE. OCCURRED AT 16,000 FT. VERIFIED TRS SELECTED TO "OFF". SELECTED EMER STOW PER QRH/IAC. AIRCRAFT REMOVED FROM SJul 14, 2024 · N460AW · Cndair CL6002B19 · Engine Thrust ReverserSDR A6WA202308148646Control Unit · unknownAMBER FLAPS FAIL CAUTION MSG FLAPS FAILED AT 0. MSG APPEARED DURING CRUISE. PERFORMED FLAP RESET PROCEDURE. IAW AWA SUP 98-018I BOX 12. FLAPS RESET. PLACARDED AND PLACED ON MEL. AIRCRAFT REMOVED FROM SERVICE. T/S IAW FIM 27-51 SUP 98-018I RR FECU IAAug 13, 2023 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control SystemSDR A6WA202307018636Wheel · unknownSTANDING TAKEOFF WITH FLAPS 20 WHEN BRAKES RELEASED A/C PULLS IMEDIATLEY TO LEFT UNABLE TO REGAIN CENTERLINE WITH FULL RIGHT RUDDER. ABORTED TAKEOFF APPROX 20 KNOTS. AIRCRAFT REMOVED FROM SERVICE. R+R #1 NLG TIRE IAW AMM SUP 12-016I. C/W M061 INSTRUCTIONS THEJul 1, 2023 · N460AW · Cndair CL6002B19 · Wheel/Ski/FloatSDR A6WA202306128629Indicator · unknownSTANDBY ATTITUDE INDICATOR PERCUSSES IN PITCH AND BANK IN FLIGHT. AIRCRAFT REMOVED FROM SERVICE. R&R STANDBY ATTITUDE INDICATOR.Jun 12, 2023 · N460AW · Cndair CL6002B19 · Navigation SystemSDR A6WA202209088334Floor Support · damagedFLOOR SUPPORT STRUCTURE BETWEEN FS 409+128 - FS 424 & LBL 9 - RBL 27 HAVE ELONGATED HOLES. ***************REMOVED AIRCRAFT FROM SERVICE********************* OPENED DAMAGED HOLES TO MINIMUM DIAMETER COMPLETELY REMOVING DAMAGE WITHOUT EXCEEDING .350" IAW MHIRJ Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage, Door HingeSDR A6WA202209088335None · chafedR/H I/B FLAP VANE L/E HAS WEAR DAMAGE AT WS 50.498+6. ************AIRCRAFT REMOVED FROM SERVICE************************** BLENDED DAMAGE TO A SMOOTH CONTOUR WITH DIMENSIONS OF 1.2"L X .500"W X .025"D IAW ASAP EA #AWAC-CRJ257-01891 REV B DATED 10/08/2022. VERIFSep 8, 2022 · N460AW · Cndair CL2151A10 · Aileron TabsSDR A6WA202209088336None · chafedR/H I/B FLAP VANE L/E HAS WEAR DAMAGE AT WS 98.50+7. ************AIRCRAFT REMOVED FROM SERVICE************************** BLENDED DAMAGE TO A SMOOTH CONTOUR WITH DIMENSIONS OF 1.2"L X .500"W X .014"D IAW ASAP EA #AWAC-CRJ257-01890 REV B DATED 10/12/2022. VERIFISep 8, 2022 · N460AW · Cndair CL2151A10 · Aileron TabsSDR A6WA202209088337None · noneR/H TRU ACCESS DOOR ASSEMBLY AT FS 173 TO FS 193 HAS DAMAGE/DELAMINATION ON OUTER PLIES INTO THE HONEYCOMB MEASURING 1"L X 1"W X .063"D. *************AIRCRAFT REMOVED FROM SERVICE************************* REPAIRED DAMAGE ON R/H TRU ACCESS DOOR IAW ASAP EA #AWASep 8, 2022 · N460AW · Cndair CL2151A10 · Accessory Compartment DoorsSDR A6WA202209088324Hinge Fitting · gougedR/H ELEVATOR HINGE #2 I/B FITTING GOUGED .8"L X .159"W X .010"D & O/B FITTING GOUGED .8"L X .159"W X .010"D AT RBL 55.89. EVALUATED DAMAGED AREAS AND FOUND NOT WITHIN ALLOWABLE LIMITS IAW CRJ200 SRM 55-20-00 REV 39. *********AIRCRAFT REMOVED FROM SERVICE******Sep 8, 2022 · N460AW · Cndair CL2151A10 · Elevator, Plate/SkinSDR A6WA202209088323Hinge Fitting · gougedL/H ELEVATOR HINGE #2 FITTING GOUGED .550"L X .500"W X .010"D BETWEEN FS 59.02 AND FS 62.02. EVALUATED DAMAGE AND FOUND NOT WITHIN ALLOWABLE LIMITS IAW CRJ200 SRM 55-20-00 REV 39. *********AIRCRAFT REMOVED FROM SERVICE*************************** PERFORMED BLESep 8, 2022 · N460AW · Cndair CL2151A10 · Empennage StructureSDR A6WA202209088327None · chafedPASSENGER DOOR HINGE LUG #1, #7, AND #9 ON DOOR SIDE OF HINGE HAVE WEAR AREAS ON OUTSIDE OF LUG. *************REMOVED AIRCRAFT FROM SERVICE************************ BLENDED PASSENGER DOOR HINGE LUGS TO MINIMUM REMAINING WALL THICKNESS OF #1 (.084), #7 (.082), Sep 8, 2022 · N460AW · Cndair CL2151A10 · DoorsSDR A6WA202209088333None · chafedR/H AILERON LOWER SHROUD L/E HAS WEAR DAMAGE AT WS 360. **************REMOVED AIRCRAFT FROM SERVICE************************* BLENDED DAMAGE AREA TO A SMOOTH CONTOUR WITH DIMENSIONS OF 2.0"L X 1.0"W X .037"D IAW ASAP EA #AWAC-CRJ257-01895 REV A DATED 09/30/2022Sep 8, 2022 · N460AW · Cndair CL2151A10 · Wing StructureSDR A6WA202209088325Hinge Fitting · gougedR/H HSTAB HINGE #2 I/B FITTING GOUGED .7"L X .1"W X .020"D & O/B FITTING GOUGED .6"L X .1"W X .011"D AT RBL 55.89 AND I/B PLATE .6"L X .1"W X .010"D & O/B PLATE .6"L X .1"W X .017"D. DAMAGE NOT WITHIN ALLOWABLE LIMITS IAW CRJ200 SRM 55-20-00 REV 39. *********ASep 8, 2022 · N460AW · Cndair CL2151A10 · Horizontal Stabilizer, Plate/SkinSDR A6WA202209088326Floor Panel · damagedMIS-LOCATED HOLE ON FLOOR PANEL #231ALF FOR FORWARD GALLEY ATTACH THROUGH POINT. *****************AIRCRAFT REMOVED FROM SERVICE******************** REMOVED DAMAGED OUTER PLIES IN AREAS OF MIS-LOCATED HOLE. POTTED HOLE USING MAGNABOND 92-1 AND APPLIED REPAIR PSep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)SDR A6WA202209088332None · gougedAFT FACE OF AFT PRESSURE BULKHEAD "Z" STIFFENER AT FS 621 BL 0 AND WL 135.12 HAS A GOUGE .800"L X .500"W X .060"D. **************AIRCRAFT REMOVED FROM SERVICE*********************** BLENDED GOUGE ON "Z" STIFFENER TO A SMOOTH CONTOUR ENSURING REPORTED DEPTH OF Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)SDR A6WA202209088316None · corrodedR/H FLOOR SEAT TRACK FROM FS 394 TO FS 409+128 RBL 9 HAS SEVERAL AREAS OF SURFACE CORROSION. EVALUATED CORROSION ON R/H FLOOR SEAT TRACK AT FS 394 TO FS 409+128 AT RBL 9 AND FOUND NOT WITHIN ALLOWABLE LIMITS IAW CRJ200 SRM 53-21-49 REV 39. *********AIRCRAFT RESep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)SDR A6WA202209088315Plate · corrodedCORROSION ON FWD GALLEY SUPPORT PLATE AT FS 321 TO FS 327 AND RBL 4 TO RBL 8 AT WL 73.5. *******************AIRCRAFT REMOVED FROM SERVICE********************* UPON FURTHER INSPECTION OF SUPPORT PLATE FOUND INTERGRANULAR CORROSION NOT WITHIN ALLOWABLE LIMITS ISep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Fixed PartitionsSDR A6WA202209088317None · corrodedR/H FLOOR SEAT TRACK FROM FS 559 TO FS 559+112 RBL 9 HAS SEVERAL AREAS OF SURFACE CORROSION. EVALUATED CORROSION ON R/H FLOOR SEAT TRACK AT FS 559 TO FS 559+112 AT RBL 9 AND FOUND NOT WITHIN ALLOWABLE LIMITS IAW CRJ200 SRM 53-21-49 REV 39. *********AIRCRAFT RESep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)SDR A6WA202110227927None · noneURING GEAR RETRACTION RECEIVED GEAR DISAGREE AND NOSE DOOR CAUTION MSG'S WITH NOSE GEAR 3724-DURING GEAR RETRACTION RECEIVED GEAR DISAGREE AND NOSE DOOR CAUTION MSG'S WITH NOSE GEAR INDICATING DOWN. COMPLIED WITH QRH-NOSE GEAR REMAINED DOWN. DURING POST FLOct 22, 2021 · N460AW · Cndair CL6002B19 · Landing Gear Retraction/Extension SystemSDR A6WA202103037680Frame · puncturedFRAME AT FS654.50 BETWEEN STR 24R AND STR 25R PUNCTURED . AIRCRAFT REMOVED FROM SERVICE. PERFORMED CUT OUT ON FRAME AT FS 654.50 BETWEEN STR 24R AND STR 25R, PERFORMED HFEC WITH NO DEFECTS NOTED. FORMED ANGLE, LOCATED AND DRILLED REPAIR ANGLE. ALODINED, PRFeb 22, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, FrameSDR A6WA202102287669Stringer · damagedTOOL MARKS FOUND ON STR 25R BETWEEN FS625.30 AND FS640.00 ***AIRCRAFT REMOVED FROM SERVICE*** IS N460AW ASAP ENGINEERING EA# AWAC-CRJ253-01571 REV IR DATED 2/23/2021 REPAIR Ï¿½ STRINGER, FA625.00-FA640.00, S25RFeb 22, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Longeron/StringerSDR A6WA202103027677Bulkhead Web · crackedAFT PRESSURE BULKHEAD WEB HAS MULTIPLE CRACKS CRACK #1 FS 621.00 RBL 27.5 WL 90.20 TO 92.90 LENGTH 2.7" CRACK #2 FS 621.00 RBL 27.5 WL 100.25 TO 104.90 LENGTH 4.65" CRACK #3 FS 621.00 RBL 18.0 WL 107.25 TO 109.75 LENGTH 2.5" CRACK #4 FS 621.00 RBL 9.5 WL 100.0Feb 12, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, BulkheadSDR A6WA202102237668Access Panel · damagedREPAIR RUDDER PCU PANEL 325DR PER 601R-55-31-333. AIRCRAFT REMOVED FROM SERVICE. REMOVED PROTECTIVE FINISH, PERFORMED HFEC INSPECTION, NO DEFECTS NOTED. PERFORMED UT THICKNESS CHECK, MINIMUM REMAINING THICKNESS .081". FOUND TO BE WITHIN LIMITS REF REO 601RFeb 12, 2021 · N460AW · Cndair CL6002B19 · Rudder, Plate/SkinSDR A6WA202103027676Skin · corrodedR.HAND LOWER WING PLANK ACCESS PANEL 640BB HAS FRETTING CORROSION. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION AT LOWER WING PLANK ACCESS AT PANEL 640BB REF. CRJ200 SRM 51-21-06, REV.38. PERFORMED UT THICKESS MEASUREMENT, MINIMUM REMAINING THICKNESFeb 10, 2021 · N460AW · Cndair CL6002B19 · Wing, Plate/SkinSDR A6WA202103027678Skin · corrodedL. HAND LOWER WING PLANK ACCESS PANEL 540BB HAS FRETTING CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION AT LOWER WING PLANK ACCESS AT PANEL 540BB REF. CRJ200 SRM 51-21-06, REV.38. PERFORMED UT THICKESS MEASUREMENT, MINIMUM REMAINING THICKNESS OFFeb 10, 2021 · N460AW · Cndair CL6002B19 · Wing, Plate/SkinSDR A6WA202102177650Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 544.00 RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 544.00 RBL 40 TO RBL 42. .65 INCH WIDE X 2.0 INCH LONG PERFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESS CHEFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage, Wing Attach FittingsSDR A6WA202102177648Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 439.00 RBL 41 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 439 RBL 41 TO RBL 42. .5 INCH WIDE X 1.2 INCH LONG PERFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESS CHECK, Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177649Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 461.00 RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 461 RBL 40 TO RBL 42. .8 INCH WIDE X 2.2 INCH LONG PERFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESS CHECK, Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177651Floor Panel · corrodedPRESSURE FLOOR PANEL AT FS 544.00+4.5 AND RBL 42 HAS CORROSION AROUND NUT PLATE HOLE. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 544.00+4.5 RBL 42. 1.0 INCH WIDE X 2.0 INCH LONG. PREFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESS CHECK .Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Floor PanelSDR A6WA202102177644Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 513.00+5 RBL 36 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 513.00+5 RBL 36 TO RBL 42. SPOT P1, .5 INCH WIDE X 1.0 INCH LONG. P2, .8 WIDE X 1.6 INCH LONG. P3, 1.8 WIDE X Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177645Floorbeam · corrodedCORROSION COMMON TO PESSURE FLOOR ANGLE AT FUSELAGE STATION 499.00+4 RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 499.00+4 RBL 40 TO RBL 42. 1.0 INCH WIDE X 2.5 INCH LONG PERFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESS Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177642Floorbeam · corrodedLIGHT CORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 409.00 +128+3, RBL 43. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS409.00+128+3RBL 43. 0.3 INCH WIDE X 0.8 INCH LONG, PERFORMED HFEC NO DEFECTS NOTED. PERFORMED UT THICKNESS CHECFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177643Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 449.85+2 RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 449.85+2 RBL 40 TO RBL 42. P1, .5 INCH WIDE X 1.1 INCH LONG. P2, 1.0 INCH WIDE X 3.0 INCH LONG. PERFORMED HFEC, Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177638Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 559.00 LBL 40 . TO LBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION AT FS 559.00 LBL 40 TO LBL 42, 1.1 INCH WIDE X 1.2 INCH LONG PERFORMED HFEC NO DEFECTS NOTED, PERFORMED UT THICHNESS Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177639Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 499.00 + 7 TO FUSELAGE STATION 513.00 RBL 36 TO RBL43. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION AT FS 499 + 7 TO FS 513, RBL 36 TO RBL 43. SPOT P1, 1.0 INCH WIDE X 3.5 INCH LONG, FS 499Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177646Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 484.00 RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 484.00 RBL 40 TO RBL 42. 1.4 INCH WIDE X 1.4 INCH LONG PERFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESS CHFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177637Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FS 409.00 + 128 + 12 RBL 36 TO RBL 42 ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION AT FS409.00+128+12 RBL 36 TO RBL 42, SPOT P1 .7 INCH WIDE X .9 INCH LONG, P2 .6 INCH WIDE X 2.3 INCH LONG. PREFORMED HFECFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102177640Floor Support · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 529+9 TO FUSELAGE STATION 529+11, RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 529.00 + 9 TO FS 529.00 + 11 RBL 40 TO RBL 42. .7 INCH WIDE X 1.5 INCH LONG. PERFORMEDFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous StructureSDR A6WA202102177641Floor Support · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 513.00+10 TO FUSELAGE STATION 529 RBL 40 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 513.00+10 TO FS 529. RBL 40 TO RBL 42, SPOT P1, .3 INCH WIDE X .6 INCH LONG. P2, .4 INCHFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous StructureSDR A6WA202102177647Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 424.00+4 RBL 36 TO RBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FS 424.00+4 RBL 36 TO RBL 42. 1.0 INCH WIDE X 2.1 INCH LONG PERFORMED HFEC, NO DEFECTS NOTED. PERFORMED UT THICKNESSFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102167636Strap · corrodedCORROSION COMMON TO FLOOR SUPPORT AT FUSELAGE STATION 559.00 LBL 37 TO LBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED AND INSTALLED NEW FABRICATED FLOOR SUPPORT AT FUSELAGE STATION 559.00 LBL 37 TO LBL 42. REF CRJ200 SRM 53-41-43 REV 38.Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous StructureSDR A6WA202102167653Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 513.00 TO 513.00+5 LBL 36 TO LBL 42. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 513.00 TO FS 513.0+5 LBL 36 TO LBL 42. EVALUATED BLEND AREA FOUND TO BE WFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous StructureSDR A6WA202102167658Floor Support · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STA 461.00+12 LBL362 TO LBL42 ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS461+12 LBL 36 TO LBL 42. EVALUATED BLEND AREA FOUND TO BE WITHIN ALLOWABLE LIMITS.HFEC INSFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous StructureSDR A6WA202102167635Channel · corrodedCORROSION COMMON TO FLOOR STRUCTURE AT FUSELAGE STATION 559.00 RBL 38 TO RBL 41. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED AND INSTALLED NEW FABRICATED FLOOR STRUCTURE AT FUSELAGE STATION 559.00RBL 38 TO RBL 41 REF CRJ200 SRM 53-41-43 REV 38.Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor BeamSDR A6WA202102167652Floorbeam · corrodedCORROSION COMMON TO PRESSURE FLOOR ANGLE AT FUSELAGE STATION 513.00+11 LBL 40. ***AIRCRAFT REMOVED FROM SERVICE*** REMOVED CORROSION PRESSURE FLOOR ANGLE AT FS 513.00+11 LBL 40. EVALUATED BLEND AREA FOUND TO BE WITHIN ALLOWABLE LIMITS. HFEC INSPECTION PERFORFeb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
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