# Service difficulty reports: N460AW

A list on [N460AW](https://openairdocs.org/aircraft/N460AW.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 5 · 250 reports

- [SDR A6WA202408148791](https://openairdocs.org/sdr/A6WA202408148791.md): Bpsu · faulted · Aug 14, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control System
  > FLAP 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 2537
- [SDR A6WA202408118790](https://openairdocs.org/sdr/A6WA202408118790.md): Fcu · faulted · Aug 11, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control System
  > FLAP 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 TO
- [SDR A6WA202408098788](https://openairdocs.org/sdr/A6WA202408098788.md): Flap System · faulted · Aug 9, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control System
  > ON 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 REMOVE
- [SDR A6WA202408048787](https://openairdocs.org/sdr/A6WA202408048787.md): Sensor · faulted · Aug 4, 2024 · N460AW · Cndair CL6002B19 · Trailing Flap Position Indicating System
  > ON 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
- [SDR A6WA202407148777](https://openairdocs.org/sdr/A6WA202407148777.md): Control Unit · faulted · Jul 14, 2024 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control System
  > WHILE 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 CHE
- [SDR A6WA202407148776](https://openairdocs.org/sdr/A6WA202407148776.md): Thrust Reverser · malfunctioned · Jul 14, 2024 · N460AW · Cndair CL6002B19 · Engine Thrust Reverser
  > RECEIVED 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 S
- [SDR A6WA202308148646](https://openairdocs.org/sdr/A6WA202308148646.md): Control Unit · unknown · Aug 13, 2023 · N460AW · Cndair CL6002B19 · Trailing Edge Flap Control System
  > AMBER 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 IA
- [SDR A6WA202307018636](https://openairdocs.org/sdr/A6WA202307018636.md): Wheel · unknown · Jul 1, 2023 · N460AW · Cndair CL6002B19 · Wheel/Ski/Float
  > STANDING 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 THE
- [SDR A6WA202306128629](https://openairdocs.org/sdr/A6WA202306128629.md): Indicator · unknown · Jun 12, 2023 · N460AW · Cndair CL6002B19 · Navigation System
  > STANDBY ATTITUDE INDICATOR PERCUSSES IN PITCH AND BANK IN FLIGHT. AIRCRAFT REMOVED FROM SERVICE. R&R STANDBY ATTITUDE INDICATOR.
- [SDR A6WA202209088334](https://openairdocs.org/sdr/A6WA202209088334.md): Floor Support · damaged · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage, Door Hinge
  > FLOOR 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
- [SDR A6WA202209088335](https://openairdocs.org/sdr/A6WA202209088335.md): None · chafed · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Aileron Tabs
  > R/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. VERIF
- [SDR A6WA202209088336](https://openairdocs.org/sdr/A6WA202209088336.md): None · chafed · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Aileron Tabs
  > R/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. VERIFI
- [SDR A6WA202209088337](https://openairdocs.org/sdr/A6WA202209088337.md): None · none · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Accessory Compartment Doors
  > R/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 #AWA
- [SDR A6WA202209088324](https://openairdocs.org/sdr/A6WA202209088324.md): Hinge Fitting · gouged · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Elevator, Plate/Skin
  > R/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******
- [SDR A6WA202209088323](https://openairdocs.org/sdr/A6WA202209088323.md): Hinge Fitting · gouged · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Empennage Structure
  > L/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 BLE
- [SDR A6WA202209088327](https://openairdocs.org/sdr/A6WA202209088327.md): None · chafed · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Doors
  > PASSENGER 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),
- [SDR A6WA202209088333](https://openairdocs.org/sdr/A6WA202209088333.md): None · chafed · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Wing Structure
  > R/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 09/30/2022
- [SDR A6WA202209088325](https://openairdocs.org/sdr/A6WA202209088325.md): Hinge Fitting · gouged · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Horizontal Stabilizer, Plate/Skin
  > R/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. *********A
- [SDR A6WA202209088326](https://openairdocs.org/sdr/A6WA202209088326.md): Floor Panel · damaged · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)
  > MIS-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 P
- [SDR A6WA202209088332](https://openairdocs.org/sdr/A6WA202209088332.md): None · gouged · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)
  > AFT 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
- [SDR A6WA202209088316](https://openairdocs.org/sdr/A6WA202209088316.md): None · corroded · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)
  > R/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 RE
- [SDR A6WA202209088315](https://openairdocs.org/sdr/A6WA202209088315.md): Plate · corroded · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Fixed Partitions
  > CORROSION 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 I
- [SDR A6WA202209088317](https://openairdocs.org/sdr/A6WA202209088317.md): None · corroded · Sep 8, 2022 · N460AW · Cndair CL2151A10 · Fuselage Structure (General)
  > R/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 RE
- [SDR A6WA202110227927](https://openairdocs.org/sdr/A6WA202110227927.md): None · none · Oct 22, 2021 · N460AW · Cndair CL6002B19 · Landing Gear Retraction/Extension System
  > URING 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 FL
- [SDR A6WA202103037680](https://openairdocs.org/sdr/A6WA202103037680.md): Frame · punctured · Feb 22, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Frame
  > FRAME 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, PR
- [SDR A6WA202102287669](https://openairdocs.org/sdr/A6WA202102287669.md): Stringer · damaged · Feb 22, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Longeron/Stringer
  > TOOL 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, S25R
- [SDR A6WA202103027677](https://openairdocs.org/sdr/A6WA202103027677.md): Bulkhead Web · cracked · Feb 12, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Bulkhead
  > AFT 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 100.0
- [SDR A6WA202102237668](https://openairdocs.org/sdr/A6WA202102237668.md): Access Panel · damaged · Feb 12, 2021 · N460AW · Cndair CL6002B19 · Rudder, Plate/Skin
  > REPAIR 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 601R
- [SDR A6WA202103027676](https://openairdocs.org/sdr/A6WA202103027676.md): Skin · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Wing, Plate/Skin
  > R.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 THICKNES
- [SDR A6WA202103027678](https://openairdocs.org/sdr/A6WA202103027678.md): Skin · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Wing, Plate/Skin
  > L. 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 OF
- [SDR A6WA202102177650](https://openairdocs.org/sdr/A6WA202102177650.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage, Wing Attach Fittings
  > CORROSION 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 CHE
- [SDR A6WA202102177648](https://openairdocs.org/sdr/A6WA202102177648.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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,
- [SDR A6WA202102177649](https://openairdocs.org/sdr/A6WA202102177649.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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,
- [SDR A6WA202102177651](https://openairdocs.org/sdr/A6WA202102177651.md): Floor Panel · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Floor Panel
  > PRESSURE 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.
- [SDR A6WA202102177644](https://openairdocs.org/sdr/A6WA202102177644.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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
- [SDR A6WA202102177645](https://openairdocs.org/sdr/A6WA202102177645.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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
- [SDR A6WA202102177642](https://openairdocs.org/sdr/A6WA202102177642.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > LIGHT 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 CHEC
- [SDR A6WA202102177643](https://openairdocs.org/sdr/A6WA202102177643.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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,
- [SDR A6WA202102177638](https://openairdocs.org/sdr/A6WA202102177638.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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
- [SDR A6WA202102177639](https://openairdocs.org/sdr/A6WA202102177639.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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 499
- [SDR A6WA202102177646](https://openairdocs.org/sdr/A6WA202102177646.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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 CH
- [SDR A6WA202102177637](https://openairdocs.org/sdr/A6WA202102177637.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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 HFEC
- [SDR A6WA202102177640](https://openairdocs.org/sdr/A6WA202102177640.md): Floor Support · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous Structure
  > CORROSION 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. PERFORMED
- [SDR A6WA202102177641](https://openairdocs.org/sdr/A6WA202102177641.md): Floor Support · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous Structure
  > CORROSION 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 INCH
- [SDR A6WA202102177647](https://openairdocs.org/sdr/A6WA202102177647.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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 THICKNESS
- [SDR A6WA202102167636](https://openairdocs.org/sdr/A6WA202102167636.md): Strap · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous Structure
  > CORROSION 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.
- [SDR A6WA202102167653](https://openairdocs.org/sdr/A6WA202102167653.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous Structure
  > CORROSION 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 W
- [SDR A6WA202102167658](https://openairdocs.org/sdr/A6WA202102167658.md): Floor Support · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Miscellaneous Structure
  > CORROSION 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 INS
- [SDR A6WA202102167635](https://openairdocs.org/sdr/A6WA202102167635.md): Channel · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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.
- [SDR A6WA202102167652](https://openairdocs.org/sdr/A6WA202102167652.md): Floorbeam · corroded · Feb 10, 2021 · N460AW · Cndair CL6002B19 · Fuselage Main, Floor Beam
  > CORROSION 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 PERFOR

Next page: https://openairdocs.org/aircraft/N460AW/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 = 'N460AW' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N460AW/reports

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