N437AW

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 41,570 hrs · 40,186 cycles

AFTER T/O OUT OF ORD, HEARD LOUD NOISE FROM NOSE OF AIRCRAFT. RH SIDE. ******AIRCRAFT REMOVED FROM SERVICE********* FOUND CREW O2 SERVICING DOOR OPEN ON ARRIVAL. VISUALLY INSPECTED DOOR AND LATCHES, NO DEFECTS AT THIS TIME. DOOR SECURES CLOSED.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 41,485 hrs · 40,080 cycles

ON CLIMBOUT, RECEIVED FUEL IMBALANCED CAUTION MSG WITH LH QTY EXCEEDING RH QTY BY 800+LBS AUTO CROSSFLOW WOULD NOT COMMENCE INITIALLY, BUT LATER WORKED NORMAL RETURNED AC TO A BALANCED CONDITION. SINGLE ENGINE TAXI PRIOR TO TAKEOFF ON RH ENGINE WITH LH BOOST PUMP OFF. L TANK 1200 R TANK 1210 AT GATE, FUEL BURN NORMAL AIRCRAFT REMOVED FROM SERVICE. INSPECTED AND FOUND RH FUEL BOOST PUMP CANISTER CHECK VALVE IMPROPERLY INSTALLED. REMOVED AND REINSTALLED RH FUEL BOOST PUMP CANISTER CHECK VALVE. OPS CHECK AND LEAK CHECK GOOD.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 41,367 hrs · 39,949 cycles

ON DEPARTURE UPON SELECTING GEAR UP RECIEVED NOSE DOOR OPEN AND GEAR DISAGREE WARNING MSGS C/W QRH EXTENDED GEAR GEAR MSGS WENT AWAY AIRCRAFT REMOVED FROM SERVICE. INSTALLED NOSE AND MAIN GEAR LOCK PINS PER AMM SUP. 11-054A FOR M ACTION OF MEL 32-30-01. SEE 358568/4 FOR MEL. REF MX WORK CARDS #2 AND 3 FOR REMOVED AND REPLACED OF S23 BRACKET AND NLG RIGHT HARNESS. OPS CHECK GOOD. REMOVED PLACARD AND FROM MEL

Part: BULKHEAD — NONE · airframe 39,784 hrs · 38,316 cycles

REAR PRESSURE BULKHEAD WEB REQUIRES MODIFICATION PER E17/003/453 ****AIRCRAFT REMOVED FROM SERVICE**** MODIFIED THE REAR PRESSURE BULKHEAD WEB FS 621.00 IAW GREO 601-53-61-1240 REV D

Part: BULKHEAD — GOUGED (FS 621.00) · airframe 39,784 hrs · 38,316 cycles

BULKHEAD Z-MEMBER AT FS 621.00, CENTER, SHOWS DEEP GAUGE LOCATED AT THE TOP END. ****AIRCRAFT REMOVED FROM SERVICE**** REPAIRED BULKHEAD AFT VERTICAL STIFFENER AT FS 621.00 IAW EA# AWAC-CRJ253-01806

Part: STIFFENER — CRACKED (FS 516.00) · airframe 39,784 hrs · 38,316 cycles

ANGLE STIFFENER AT FS 516, ON RH BL 45.00 IS CRACKED AS MARKED ****AIRCRAFT REMOVED FROM SERVICE**** REMOVED CRACKED ANGLE STIFFENER AND INSTALLED NEW ANGLE STIFFENER AT FS 516.00 ON RH BL 45.00 IAW ED# AWAC-CRJ 253-01816

Part: STIFFENER — CRACKED (FS 516.00) · airframe 39,784 hrs · 38,316 cycles

ANGLE STIFFENER AT FS 516, ON LH BL 45.00 IS CRACKED AS MARKED ****AIRCRAFT REMOVED FROM SERVICE**** REMOVED CRACKED ANGLE STIFFENER AND INSTALLED NEW ANGLE STIFFENER AT FS 516.00 ON LH BL 45.00 IAW ED# AWAC-CRJ253-01817

Part: BPSU — WARNING MESSAGE (TE FLAPS) · airframe 38,754 hrs · 37,240 cycles

FLAPS FAIL CAUTION ON TAKEOFF, PERFORMED FLAP RESET PROCEDURE IAW AWAC SUP 98-018I BOX 12 FLAP RESET. PLACARDED AND PLACED ON MEL. AIRCRAFT REMOVED FROM SERVICE. FOUND RT WING BRAKE AND POSITION SENSOR OUT OF RIG, AND RT WING POSITION 10 FLEX DRIVE WORN, RT BRAKE AND POSITION SENSOR R/R DUE TO WORN THREADS ON DRIVE. RT BRAKE R/R PER AMM 27-51-10-000-801, R/R DRIVE POSITION 10 RT WING 27-53-10-000-805, RERIGGED RT WING BRAKE (BPSU) PER AMM27-51-10-830-801, OPS TEST OF FLAPS PER AMM 27-54-00-710-801.REMOVED FROM MEL,REMOVED PLACARD AIRCRAFT OK FOR SERVICE

Part: CLAMP — LOOSE (BLEED DUCT) · airframe 38,483 hrs · 36,938 cycles

JUST AFTER VR RECEIVED WING OVERHEAT WARNING MESSAGE, FOLLOWED BY ANTI-ICE DUCT WARNING MESSAGE. CW QRH MESSAGES CLEARED. RETURNED TO MKE. 14TH STAGE SOVS AND WING AND COWL AI VALVES WERE ALL SELECED ON. THE 10TH STAGE SOVS WERE CLOSED AT THE TIME. QRH ACTION WAS TO TURN OFF BOTH 14TH STAGE SOVS AND ALL ANTI-ICE. MESSAGE CLEARED IN APPROXIMATELY 40 SECONDS. SYNOPTIC PAGE INDICATED LT WING RED.LANDING WEIGHT APPROXIMATELY 36K, MAX BTMS WAS 3. AIRCRAFT REMOVED FROM SERVICE. FOUND BLEED AIR LEAK AT CLAMP UNDER PANEL 520AT TORQUED CLAMP, NO LEAK NOTED. PERFORMED OPERATIONS TEST OF WING A-ICE SYSTEM, PER AMM 30-12- RAN LT ENGINE TO T/O AND CLIMB POWER DURING TESTING. CHECKS NORMAL.

Part: SKIN — CORRODED (TCAS ANTENNA) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

UPPER FUSELAGE TCAS ANTENNA MATING SURFACE FS 310, STGR 1R TO STGR 1L HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. BLENDED OUT DAMAGE ON TCAS ANTENNA MATING SURFACE FS 310, STGR 1R TO STGR 1L, P(1) 1.0L X 0.70W, P(2) 1.2L X 0.60W, P(3) 0.8L X 0.95W, P(4) 1.75L X 1.50W, P(5) 1.2L X 0.75W, REF AIRWIS SUPPLEMENT NR 16-122B DATED: 10-24-2017. PERFORMED HFEC INSPECTION ON TCAS ANTENNA MATING SURFACE FS 310, STGR 1R TO STGR 1L, REF AIRWIS SUPPLEMENT NR 16-122B DATED: 10-24-2017 AND CRJ200 PART (1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N:60007150515 CAL DUE: 10-09-2021. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA TCAS ANTENNA MATING SURFACE FS 310, STGR 1R TO STGR 1L, P(1) .0545, P(2) .0534, P(3) .0559, P(4) .0550, P(5) .0565, REF AIRWIS SUPPLEMENT NR 16-122B DATED: 10-24-2017 AND CRJ200 PART (4) NDTM 51-00-001, (REV 42). UT GAUGE S/N: DBP-CT-1033 CAL DUE:2-19-2021. EVALUATED BLENDS ON CHEM MILLED AREA OF BLENDED SKIN AND FOUND TO BE WITHIN LIMITS, REF AIRWIS SUPPLEMENT NR 16-122B DATED: 10-24-2017. APPLIED PROTECTIVE FINISH TO UPPER FUSELAGE TCAS ANTENNA MATING SURFACE FS 310, STGR 1R TO STGR 1L, REF AIRWIS SUPPLEMENT NR 16-122B DATED: 10-24-2017.

Part: SKIN — DENTED (FUSELAGE) · airframe 38,480 hrs · 39,936 cycles

UPPER SURFACE OF FUSELAGE HAS DENT AT FS 596.00, STGR 3R AND STGR 4R. AIRCRAFT REMOVED FROM SERVICE. EVALUATED DENT AT FS 596.00, STGR 3R AND STGR 4R, 1.7 L X 1.6 W X 0.057 D, FOUND TO BE OUT OF LIMITS FOR SHARP CREASES. IAW CRJ200 SRM 53-00-31, (REV 38). ALLOWABLE DAMAGE FIG 103 SHEET 4 DEPTH GAUGE S/N: 2151 CAL DUE: 10-21-2021. CUT OUT DAMAGED AREA 15.0 L X 4.2 W, REF CRJ200 DTM 53-00-31. PERFORMED HFEC INSPECTION ON CUT-OUT AREA ON UPPER FUSELAGE AT FS 596.00, STGR 1R TO STGR 2R, REF CRJ200 SRM 53-00-31 AND CRJ200 PART (1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N :60007150515 CAL DUE: 10-09-2021. FABRICATED, DRILLED, AND COUNTERSUNK REPAIR DOUBLER, 0.063 L X 9.500 W, REF CRJ200 SRM 53-00-31 FIG.201, REPAIR NR 1, (REV 38). APPLIED PROTECTIVE FINISH TO REPAIR DOUBLER AND REPAIR AREA, REF CRJ200 SRM 51-25-01, (REV 38). INSTALLED REPAIR DOUBLER AT FS 589.00 TO FS 596, STGR 3R TO STGR 4R, REF CRJ200 SRM 53-00-31 FIG.201, REPAIR NR 1, (REV 38). APPLIED PROTECTIVE FINISH ON REPAIR DOUBLER, REF CRJ200 SRM 53-00-31 FIG 201, REPAIR NR 1, (REV 38).

Part: FLANGE — GOUGED (FUEL PRESSURE BO) · airframe 38,480 hrs · 39,936 cycles

FUEL PRESSURE BOX AFT UPPER FLANGE, INBOARD AND OUTBOARD CORNERS GOUGED BLEND OUT DAMAGE ON FUEL PRESSURE BOX AFT UPPER RT FLANGE, 0.390 L X 0.120 W X 0.045 D, REF REO 601R-28-20-044, REV A DATE: 2021-01-21. BLENDED OUT DAMAGE ON FUEL PRESSURE BOX AFT UPPER LT FLANGE, P(1) 0.245 L X 0.120 W X 0.050 D, P(2) 0.155 L X 0.120 W X 0.015 D, P(3) 0.220 L X 0.120 W X 0.080 D, REF. REO 601R-28-20-044 , REV A DATE: 2021-01-21. PERFORMED HFEC INSPECTION ON FUEL PRESSURE BOX AFT UPPER FLANGE, INBOARD AND OUTBOARD CORNERS, REF REO 601R-28-20-044, REV A DATE: 2021-01-21 AND CRJ200 PART (1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N: 60007150515 CAL DUE: 10-09-2021. APPLIED SURFACE PROTECTION ON REWORKED AREAS, REF REO 601R-28-20-044, REV A DATE: 2021-01-21.

Part: ACCESS PANEL — CRACKED (VERTICAL STAB) · airframe 38,480 hrs · 39,936 cycles

VERTICAL STABILIZER PANEL 326AL AFT END BENT AND 1 EA DENT. AIRCRAFT REMOVED FROM SERVICE. EVALUATED AND MEASURED 1 (EA) DENT ON VERTICAL STABILIZER PANEL 326AL, 0.700 L X 0.500 W X 0.007 D, DENT FOUND TO BE WITHIN LIMITS, REF CRJ200 SRM 55-00-31 AND A.W. SUPPLEMENT NR 17-141 DATE OF ISSUE: 06-23-2017. GAUGE NR 643 CAL DUE: 10-21-2021, MICROMETER NO.242117 CAL DUE: 06-04-2021. HAND DRESSED TO RE-FORM VERTICAL STABILIZER PANEL 326AL TO ORIGINAL CONTOUR PER A.W. SUPPLEMENT NR 19-303A DATE OF ISSUE: 12-7-2018. PERFORMED HFEC ON VERTICAL STABILIZER PANEL 326AL AFT END, REF A.W. SUPPLEMENT NR 19-303A DATE OF ISSUE: 12-7-2018 AND CRJ200 PART (1) NDTM 51-20-06, REV (42). CRACK INDICATION NOTED, (0.250 L). ET TESTER S/N: 01124120 CAL DUE: 01-24-2021. PERFORMED LAYOUT ON REPAIR AREA OF VERTICAL STABILIZER PANEL 326AL, REF EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV. A. PERFORMED CUT-OUT OF VERTICAL STABILIZER PANEL 326AL, REF EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV A. PERFORMED HFEC ON VERTICAL STABILIZER PANEL 326AL AFT END CUT-OUT, REF EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV. A, AND CRJ200 PART (1) NDTM 51-20-06, REV (42). NO INDICATION NOTED. ET TESTER S/N: 01124120 CAL DUE: 01-24-2021. FABRICATED SKIN SECTION AND DOUBLER, REF EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV A. APPLIED SURFACE PROTECTION ON FABRICATED SKIN SECTION, AND DOUBLER REF EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV A. INSTALLED FABRICATED SKIN SECTION, AND DOUBLER ON VERTICAL STABILIZER PANEL 326AL AFT END EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV. A. PERFORMED HFEC ON VERTICAL STABILIZER PANEL 326AL REPAIR DOUBLER, REF EA AWAC CRJ255-01552 ISSUE DATE:1-19-2021, REV A. AND CRJ200 PART (1) NDTM 51-20-06, REV (42). NO INDICATION NOTED. ET TESTER S/N: 01124120 CAL DUE: 01-24-2021.

Part: CHANNEL — CORRODED (RT WING) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

RIGHT HAND WING AFT CHANNEL AT WS 48.30 HAS POSSIBLE CORROSION ON INBOARD SURFACE. AIRCRAFT REMOVED FROM SERVICE. REMOVED NUTPLATE AT WS 48.30, REF CRJ200 SRM 51-45-00, (REV 38). REMOVED CORROSION AT (2 EA) LOCATIONS ON CHANNEL AT WS 48.30, REF CRJ200 SRM 51-21-06, (REV 38). REWORKED AREA MEASURES P(1) 1.67L X 0.71W, P(2) 2.14L X1.61W, REF CRJ200 SRM 51-21-06, (REV 38). CALIPER S/N:61512501 CAL DUE:08-07-2021. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF RT WING AFT SPAR AT WS 48.30 P(1) 0.0494, (P)2 0.0474 REF EA: AWAC-CRJ253-01555 DATE OF ISSUE: 01-18-2021, (REV A) AND CRJ200 PART(1) NDTM 51-00-001, (REV 42). UT TESTER S/N: DBT-CT-1033 CAL DUE: 02-19-2021. PERFORMED HFEC ON BLENDED AREA OF RT WING AFT SPAR AT WS 48.30 P(1) AND P(2), REF EA: AWAC- CRJ253-01555 DATE OF ISSUE: 01-18-2021, (REV A) AND CRJ200 PART(1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N:200051301 CAL DUE: 01-24-2021. INSTALLED NUTPLATE AT WS 48.30, REF CRJ200 SRM 51-45-00, (REV 38). RESTORE SURFACE FINISH ON REWORKED AREA, REF EA: AWAC- CRJ253-01555 DATE OF ISSUE: 1-18-2021, (REV 38).

Part: CHANNEL — CORRODED (LT WING) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

LEFT HAND WING AFT CHANNEL AT WS 53.60 HAS POSSIBLE CORROSION AROUND UPPER LIGHTNING HOLE. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION AT LT WS.53.60, REF CRJ200 SRM 51-21-06, (REV 38). REWORKED AREA MEASURES 1.7L X 1.0W, REF CRJ200 SRM 51-21-06, (REV 38). CALIPER S/N:61512501 CAL DUE:08-07-2021. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF RT WING AFT SPAR AT WS 53.60 MINIMUM THICKNESS 0.047, REF EA: AWAC-CRJ253-01345 DATE OF ISSUE: 01-18-2021, (REV A) AND CRJ200 PART(1) NDTM 51-00-001, (REV 42). UT TESTER S/N: DBT-CT-1033 CAL DUE: 02-19-2021. PERFORMED HFEC ON BLENDED AREA OF RT WING AFT SPAR AT WS 53.60, REF EA: AWAC-CRJ253-01345 DATE OF ISSUE: 1-18-2021, (REV A) AND CRJ200 PART(1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N:200051301 CAL DUE: 01-24-2021. RESTORE SURFACE FINISH ON REWORKED AREA, REF EA: AWAC-CRJ253-01345 DATE OF ISSUE: 1-18-2021, (REV A).

Part: CHANNEL — CORRODED (RT WING) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

RIGHT HAND WING AFT CHANNEL AT WS 53.60 HAS POSSIBLE CORROSION ON INBOARD SURFACE. AIRCRAFT REMOVED FROM SERVICE. REMOVED ANGLE SUPPORT AND NUTPLATE AT RT WS 53.60, REF CRJ200 SRM 51-42-21 AND CRJ 200 SRM 51-45-00, (REV.38). REMOVED CORROSION AT (2 EA) LOCATIONS ON CHANNEL AT RT WS.53.60, REF CRJ200 SRM 51-21-06, (REV 38). REWORKED AREA MEASURES P(1) 1.47L X 0.63W, P(2) 1.73L X1.68W, REF CRJ200 SRM 51-21-06, (REV 38). CALIPER S/N:61512501 CAL DUE:08-07-2021. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF RT WING AFT SPAR AT WS 53.60 P(1) 0.0486, (P)2 0.0464, REF EA AWAC-CRJ257-01554 DATE OF ISSUE: 01-18-2021, (REV A) AND CRJ200 PART(1) NDTM 51-00-001, (REV 42). UT TESTER S/N: DBT-CT-1033 CAL DUE: 02-19-2021. PERFORMED HFEC ON BLENDED AREA OF RT WING AFT SPAR AT WS 53.60 P(1) AND P(2), REF EA: AWAC-CRJ257-01554 DATE OF ISSUE: 1-18-2021, (REV A) AND CRJ200 PART(1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N:200051301 CAL DUE: 01-24-2021. INSTALLED ANGLE SUPPORT AND NUTPLATE AT WS 53.60, REF CRJ200 SRM 51-45-00, (REV 38) AND CRJ200 SRM 51-42-21, (REV 38). RESTORE SURFACE FINISH ON REWORKED AREA, REF EA: AWAC-CRJ257-01554 DATE OF ISSUE: 1-18-2021, (REV A).

Part: BULKHEAD WEB — CRACKED (AFT) · airframe 38,480 hrs · 39,936 cycles

AFT PRESSURE BULKHEAD FWD SURFACE CRACKED AT FS 621.00 WL 131.98 TO WL 135.93 LENGTH 5.0'' RBL 18.0. AIRCRAFT REMOVED FROM SERVICE. CUT OUT DAMAGED AREA DIM L=4.9'' W=1.7''. CUT OUT ON STRAP FOR REPAIR DIM L=8.2'' W=2.5'', REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31. PERFORMED HFEC INSPECTION ON AFT PRESSURE BULKHEAD CUT OUTS AT FS 621.0 WL 131.98 TO WL 135.93, NO INDICATIONS NOTED, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31 AND CRJ-200 PART 1 51-20-06 REV 42. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. FORMED REPAIR PARTS FROM 2024-T3. DOUBLER 0.040, TRIPLER 0.063, FILLER 0.063, SPLICE 0.063, SHIM 0.040, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31. INSTALLED REPAIR PARTS AT FS 621.0 WL 131.98 TO WL 135.93 RBL 18.00 AFT PRESSURE BULKHEAD FWD FACE. REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31.

Part: BULKHEAD WEB — CRACKED (AFT) · airframe 38,480 hrs · 36,936 cycles

AFT PRESSURE BULKHEAD FWD SURFACE CRACKED AT FS 621.00 WL 126.88 TO WL 136.18 LENGTH 9.5'' BL 0.0. AIRCRAFT REMOVED FROM SERVICE. CUT OUT DAMAGED AREA DIM L=10.0'' W=1.85''. CUT OUT ON STRAP FOR REPAIR DIM L=7.0'' W=2.50'', REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31. PERFORMED HFEC INSPECTION ON AFT PRESSURE BULKHEAD CUT OUTS AT FS 621.0 WL 126.68 TO WL 136.18, NO INDICATIONS NOTED, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31 AND CRJ-200 PART 1 51-20-06 REV 42. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. FORMED REPAIR PARTS FROM 2024-T3. DOUBLER 0.040, TRIPLER 0.063, FILLER 0.063, SPLICE 0.063, SHIM 0.040, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31. INSTALLED REPAIR PARTS AT FS 621.0 WL 126.68 TO WL 136.18 BL 0.0 AFT PRESSURE BULKHEAD FWD FACE. REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31.

Part: BULKHEAD WEB — CRACKED (FS 621) · airframe 38,480 hrs · 39,936 cycles

AFT PRESSURE BULKHEAD FWD SURFACE CRACKED AT FS 621.00 WL 103.43 TO WL 114.93 LENGTH 11.5'' BL 0.0. AIRCRAFT REMOVED FROM SERVICE. CUT OUT DAMAGED AREA DIM. L=12.0'' W=1.8'', REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31. PERFORMED HFEC INSPECTION ON AFT PRESSURE BULKHEAD CUT OUTS AT FS 621.0 WL 103.43 TO WL 114.93, NO INDICATIONS NOTED, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31 AND CRJ-200 PART 1 51-20-06 REV 42. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. FORMED REPAIR PARTS FROM 2024-T3. DOUBLER 0.040, TRIPLER 0.063, FILLER 0.063,SPLICE 0.063, SHIM 0.040, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31. INSTALLED REPAIR PARTS AT FS 621.0 WL 103.43 TO WL 114.93 RBL 0.0 AFT PRESSURE BULKHEAD FWD FACE, REF BOMBARDIER REO 601R-53-61-1285 REV E DATED 2016-10-31.

Part: FLOORBEAM — CORRODED (FS. 599) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

FLOOR SUPPORT STRUCTURES AT FS 599, LBL 28 TO LBL 42, AND RBL 28 TO RBL 42 HAND AND RT HAND BLENDED OUT OF LIMITS. AIRCRAFT REMOVED FROM SERVICE. REMOVED RT HAND AND LT HAND FLOOR SUPPORT AT FS 599, LBL 28 TO LBL 42, AND RBL 28 TO RBL 42, IAW CRJ 200 SRM 51 42 06 REV (38). FABRICATED RT HAND AND LT HAND FLOOR SUPPORT STRUCTURE FROM P/N 0.005 7075-T6 UID 2678527, IAW CRJ 200 SRM 51 21 11 REV (38). APPLIED SURFACE PROTECTION ON FABRICATED RT HAND AND LT HAND FLOOR SUPPORT STRUCTURE, IAW CRJ 200 SRM 51 21 11, CRJ 200 SRM 51 25 06, AND CRJ 200 SRM 51 25 16, REV (38). INSTALLED FABRICATED RT HAND AND LT HAND FLOOR SUPPORT STRAP AT FS 599, LBL 28 TO LBL 42, AND RBL 28 TO RBL 42, REF CRJ 200 SRM 51 42 06, REV (38).

Part: ANGLE — CRACKED (FS 559) · airframe 38,480 hrs · 39,936 cycles

FLOOR CROSS MEMBER GAPPED DUE TO FASTENER SWOLLEN BETWEEN STRUCTURES AT FUSELAGE STATION 559.00, LBL 8. AIRCRAFT REMOVED FROM SERVICE. UPON EVALUATION OF DAMAGE OF CROSS MEMBER AT FUSELAGE STATION 559.00, LBL 8. DAMAGE FOUND TO MEASURE 1.78 L X 0.620 W X 0.085 D AND FOUND TO BE OUT OF LIMITS, REF CRJ200 SRM 53-00-00, FIG (101). DEPTH GAUGE S/N: 3581335 CAL DUE: 10-07-2021. REMOVED CROSS MEMBER FROM FS 559, BL 0.0 TO LBL 9.0, REF CRJ200 SRM 51-42-06, (REV.38). UPON FURTHER INSPECTION FOUND FLOOR SUPPORT CHANNEL UPPER FLANGE LOWER SIDE CRACKED 0.580 L, REF CRJ200 SRM 51-11-00. PERFORMED CUT OUT ON DAMAGE AREA, MEASUREMENTS OF CUTOUT 2.400 L X 1.0 W, REF REO 601R-53-41-2838, REV P1 DATE: 2021-01-08. PERFORMED HFEC INSPECTION ON CUT-OUT AREA OF FLOOR SUPPORT CHANNEL UPPER FLANGE FS 559.00, LBL 8, REF REO 601R-53-41-2838, REV P1 DATE: 2021-01-08 AND CRJ200 PART (1) NDTM 51-20-06, (REV.42). NO INDICATION NOTED. ET TESTER S/N: 200051301 CAL DUE: 01-24-2021. FABRICATED, LOCATED, DRILLED AND DE-BURRED: ANGLE, CROSS MEMBER, AND SHIMS REF REO 601R-53-41-2838, REV. P1 DATE: 2021-01-08. APPLIED SURFACE PROTECTION TO ANGLE, CROSS MEMBER, AND SHIMS REF. REO 601R-53-41-2838, REV. P1 DATE: 2021-01-08. INSTALLED ANGLE, CROSS MEMBER, AND SHIMS REF. REO 601R-53-41-2838, REV. P1 DATE: 2021-01-08.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS. 484.00, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 484.00, LBL 42. REWORKED DIMENSIONS P(1) 1.260 L X 0.640 W, P(2) 1.220 L X 0.710 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC PRESSURE FLOOR ANGLE AT FS 484.00, LBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA PRESSURE FLOOR ANGLE AT FS 484.00, LBL 42, REMAINING THICKNESS P(1) .0785 P(2) .0767. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 439.00, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE POSITIONS AT FS 439.00, LBL 42. REWORKED DIMENSIONS 2.2 L X 1.8 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION ON PRESSURE FLOOR ANGLE AT FS 439.00, LBL 42 REF. REO# 601R-53-41-666. REV (C) DATED 2012-11-06. AND CRJ 200 PART 1 REV.42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS.439.00, LBL 42. REMAINING THICKNESS .078. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 424.00+4, LBL 38 TO LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 424.00+4, LBL 38 TO LBL 42. REWORKED DIMENSIONS P (1) 0.4 L X 2.7 W, P(2) 0.76 L X 0.5, W P(3) 0.4 L X 0.3 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION ON PRESSURE FLOOR ANGLE AT FS 424.00+4, LBL 38 TO LBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 424.00+4, LBL 38 TO LBL 42. REMAINING THICKNESS .076. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 461.00 +9 RBL 36 TO RBL 38. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 461.00 + 9 RBL 36 TO RBL 38 BY BLENDING. BLENDED AREA MEASURED (P1) 1.20''L X 0.796''W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 461.00 + 9 RBL 36 TO RBL 38, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 461.00 +9 RBL 36 TO RBL 38. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0796'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 461.00 + 9 RBL 36 TO RBL 38. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 461.00 RBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 461.00 RBL 42.BY BLENDING. BLENDED AREA MEASURED (P1) 1.00''L X 1.700''W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 461.00 RBL 42, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 461.00 RBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0793'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 461.00 RBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513.00, RBL 36 TO RBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513.00, RBL 36 TO RBL 42. REWORKED DIMENSIONS P(1) 1.7 L X 1.0 W, P(2) 2.0 L X 0.6 W, P(3) 2.0 L X 0.7 W, P(4) 0.5 L X 0.7 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513.00, RBL 36 TO RBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513.00, RBL 36 TO RBL 42 REMAINING THICKNESS .071. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 513.00 TO FS 513.00 +5 AND LBL 36 TO LBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 513.00 TO FS 513.00 +5 AND LBL 36 TO LBL 42 BY BLENDING. BLENDED AREA MEASURED (P1) 1.180'' L X 0.590'' W (P2) 2.180'' L X 0.670'' W (P3) 1.820'' L X 1.230'' W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 513.00 TO FS 513.00 +5 AND LBL 36 TO LBL 42, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 513.00 TO FS 513.00 +5 AND LBL 36 TO LBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0791'' (P2) 0.0793'' (P3) 0.0771'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 513.00 TO FS 513.00 + 5 AND LBL 36 TO LBL 42. FOUND TO BE WITHIN LIMITS. REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 544 +11 TO FS 599, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 544 +11 TO FS 599, LBL 42. REWORKED DIMENSIONS 2.7 L X 1.5 W, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06. PERFORMED HFEC PRESSURE FLOOR ANGLE AT FS 544 +11 TO FS 599, LBL 42, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA PRESSURE FLOOR ANGLE AT FS 544 +11 TO FS 599, LBL 42. REMAINING THICKNESS .076. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06.

Part: PRESSURE DECK — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR PANEL AT NUT-PLATE FS 529.00 +10 AND LBL 43. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR PANEL AT NUT-PLATE FS 529.00 +10 AND LBL 43 BY BLENDING. BLENDED AREA MEASURED (P1) 1.530'' L X 0.630'' W (P2) 1.170''L X 0.470'' W (P3) 1.480'' L X 0.960'' W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE PANEL AT NUT-PLATE FS 529.00 +10 AND LBL 43, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR PANEL AT NUT-PLATE FS 529.00 +10 AND LBL 43. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.048'' (P2) 0.052'' (P3) 0.049'' REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR PANEL AT NUT-PLATE FS 529.00 +10 AND LBL 43. FOUND TO BE WITHIN LIMITS. REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06

Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 544.00 +11 TO FS 559 +2 AND LBL 41 TO LBL 43. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 544.00 +11 TO FS 559 + 2 AND LBL 41 TO LBL 43. BY BLENDING. BLENDED AREA MEASURED 2.480'' L X 0.800'' W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 544.00 +11 TO FS 559 +2 AND LBL 41 TO LBL 43, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 544.00 +11 TO FS 559 + 2 AND LBL 41 TO LBL 43. MINIMUM REMAINING THICKNESS MEASURES 0.0783'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE AT FS 544.00 +11 TO FS 559 +2 AND LBL 41 TO LBL 43 AND FOUND TO BE WITHIN LIMITS. REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 484.00 RBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 484.00 RBL 42 BY BLENDING. BLENDED AREA MEASURED (P1) 1.250'' L X 0.800'' W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 484.00 RBL 42. REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42, NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 484.00 RBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0784'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 484.00 RBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 439.00 RBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 439.00 RBL 42 BY BLENDING. BLENDED AREA MEASURED (P1) 1.00'' L X 0.720'' W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 439.00 RBL 42. REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 439.00 RBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0791'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 439.00 RBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS. 513.00 TO FS. 513.00 + 5, RBL 36 TO RBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 513.00 TO FS 513.00 +5, RBL 36 TO RBL 42. REWORKED DIMENSIONS P(1) 3.0 L X 1.0 W, P(2) 1.0 L X 2.0 W, P(3) 2.5 L X 0.5 W, P(4) 1.0 L X 5.5 W, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06. PERFORMED HFEC PRESSURE FLOOR ANGLE AT FS 513.00 TO FS 513.00 +5, RBL 36 TO RBL 42. REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA PRESSURE FLOOR ANGLE AT FS 513.00 TO FS 513.00 +5, RBL 36 TO RBL 42, REMAINING THICKNESS .077. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 449.85 AND LBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 449.85 AND LBL 42 BY BLENDING. BLENDED AREA MEASURED (P1) 2.780''L X 1.530''W (P2) 0.920''L X 0.340''W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 449.85 AND LBL 42, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42, NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 449.85 AND LBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.077'' (P2) 0.079'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 449.85 AND LBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOOR SUPPORT — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 499.00 TO FS 513 AND LBL 36 TO LBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 499.00 TO FS 513 AND LBL 36 TO LBL 42 BY BLENDING. BLENDED AREA MEASURED (P1) 2.64''L X 1.11''W (P2) 1.89''L X 0.94''W (P3) 1.86''L X 0.94''W (P4) 5.68''L X 0.81''W (P5) 3.80''L X 0.86''W. TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513.00 LBL 36 TO LBL 42, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42, NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513.00 AND LBL 36 TO LBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0771'' (P2) 0.0780'' (P3) 0.0785'' (P4) 0.0791'' (P5) 0.0791'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE AT FS 499.00 TO FS 513 AND LBL 36 TO LBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CAIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 461.00 + 9 AND LBL 36 TO LBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 461.00 + 9 AND LBL 36 TO LBL 42. BY BLENDING. BLENDED AREA MEASURED (P1) 2.330''L X 0.950''W (P2) 1.160''L X 0.420''W TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 461.00 + 9 AND LBL 36 TO LBL 42, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42 NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 461.00 + 9 AND LBL 36 TO LBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0784'' (P2) 0.0781'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 461.00 + 9 AND LBL 36 TO LBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

CORROSION ON PRESSURE FLOOR ANGLE FS 473.15 TO FS 473.15 +5 AND LBL 36 TO LBL 42. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE FS 473.15 TO FS 473.15 + 5 AND LBL 36 TO LBL 42 BY BLENDING. BLENDED AREA MEASURED (P1) 1.070'' L X 0.530'' W (P2) 3.260'' L X 0.920'' W (P3) 0.870'' L X 0.660'' W (P4) 0.650'' L X 0.380'' W. TOOL USED DIGITAL CALIPER S/N 0036003 CAL DUE 04/03/2021, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06. PERFORMED HFEC INSPECTION ON BLENDED AREA OF PRESSURE ANGLE FS 473.15 TO FS 473.15 + 5 AND LBL 36 TO LBL 42, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 1 51-20-06 REV 42, NO INDICATIONS NOTED. EDDY CURRENT TESTER S/N 60007150515 CAL DUE 10/09/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE FS 473.15 TO FS 473.15 +5 AND LBL 36 TO LBL 42. MINIMUM REMAINING THICKNESS MEASURES (P1) 0.0781'' (P2) 0.0783' (P3) 0.0787'' (P4)0.0779'', REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06 AND CRJ-200 NDTM PART 4 51-00-001 REV 42. UT THICKNESS GAUGE S/N DBT-CT-1033 CAL DUE 02/19/21. EVALUATED REWORK AREA OF PRESSURE FLOOR ANGLE FS 473.15 TO FS 473.15 + 5 AND LBL 36 TO LBL 42. FOUND TO BE WITHIN LIMITS, REF BOMBARDIER REO 601R-53-41-666 REV C DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 409.00 +128 +11, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 409.00 +128 +11, LBL 42. REWORKED DIMENSIONS 0.720 L X 0.420 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION PRESSURE FLOOR ANGLE AT FS 409.00 +128 +11, LBL 42 REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 409.00 +128 +11, LBL 42. REMAINING THICKNESS .069. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666. REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 461.00, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 461.00, LBL 42. REWORKED DIMENSIONS 0.6 L X 0.3 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION PRESSURE FLOOR ANGLE AT FS 461.00, LBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 461.00, LBL 42. REMAINING THICKNESS .077. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO# 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 439.00, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE POSITIONS AT FS 439.00, LBL 42. REWORKED DIMENSIONS 2.2 L X 1.8 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION ON PRESSURE FLOOR ANGLE AT FS 439.00, LBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 439.00, LBL 42. REMAINING THICKNESS .078. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: PRESSURE DECK — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR PANEL AT FS 484.00 +9, LBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR PANEL AT FS 484.00 +9, LBL 429, LBL 42. REWORKED DIMENSIONS P(1) 0.5 L X 0.34 W, P(2) 1.0 L X 1.0 W, P(3) 0.59 L X 0.45 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. DIGITAL CALIPER NR 0036003 CAL DUE: 04/03/2021. PERFORMED HFEC PRESSURE FLOOR PANEL AT FS 484.00 +9, LBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S\N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR PANEL AT FS 484.00 +9, LBL 42. REMAINING THICKNESS P(1) 0.049, P(2) 0.047, P(3) 0.050 REF CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF EA AWAC-CRJ253-01549. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 473.15 +5, RBL 36 TO RBL 38, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 473.15 +5, RBL 36 TO RBL 38. REWORKED DIMENSIONS 1.45 L X 0.55 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC INSPECTION PRESSURE FLOOR ANGLE AT FS 473.15 +5, RBL 36 TO RBL 38, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA OF PRESSURE FLOOR ANGLE AT FS 473.15 +5, RBL 36 TO RBL 38. REMAINING THICKNESS .0781. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: FLOORBEAM — CORRODED (CABIN) · corrosion level 2 · airframe 38,480 hrs · 39,936 cycles

PRESSURE FLOOR ANGLE AT FS 544.00, RBL 42, HAS CORROSION. AIRCRAFT REMOVED FROM SERVICE. REMOVED CORROSION FROM PRESSURE FLOOR ANGLE AT FS 544.00, RBL 42. REWORKED DIMENSIONS 1.1 L X 0.7 W, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06. PERFORMED HFEC PRESSURE FLOOR ANGLE AT FS 544.00, RBL 42, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 1 REV 42 NDTM 51-20-06, NO INDICATION NOTED. EDDY CURRENT TESTER S/N: 200051301 CAL DUE: 01/24/21. PERFORMED UT THICKNESS MEASUREMENT ON BLENDED AREA PRESSURE FLOOR ANGLE AT FS 544.00, RBL 42 REMAINING THICKNESS .0793. EVALUATED BLENDS FOUND TO BE WITHIN LIMITS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06 AND CRJ 200 PART 4 REV 42 NDTM 51-00-001. UT GAUGE S/N 151136107 CAL DUE: 09-16-21. APPLIED PROTECTIVE FINISH TO BLENDS, REF REO 601R-53-41-666 REV (C) DATED 2012-11-06.

Part: PRESSURE BLKHD — CRACKED (FS 621) · airframe 38,480 hrs · 39,936 cycles

AFT PRESSURE BULKHEAD FWD SURFACE FS 621.00, WL 130.93 TO WL 133.93 CRACKED. AIRCRAFT REMOVED FROM SERVICE. REMOVED SPRING BRACKET AND CARGO DOOR TRACK AT REPAIR AREA, REF CRJ200 SRM 51-40-11, (REV 38) AND BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV A). CUT-OUT DAMAGE AREA 5.0 L X 2.100 W, REF BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV A). PERFORMED HFEC INSPECTION ON CUT-OUT AREA OF AFT PRESSURE BULKHEAD FWD SURFACE FS 621.00, WL 130.93 TO WL 133.93, REF BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV A) AND CRJ200 PART (1) NDTM 51-20-06, (REV 42). NO INDICATION NOTED. ET TESTER S/N: 60007150515 CAL DUE: 10-09-2021. FABRICATED REPAIR PARTS ALUMINUM 2024-T3, SHIM = 4.830 L X 2.400 W X 0.063 D, DOUBLER = 13.880 L X 5.275 W X 0.040 D, AND TRIPLER = 11.870 L X 3.980 W X 0.063 D, REF BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV. A). APPLIED PROTECTIVE FINISH ON FABRICATED PARTS REF. CRJ200 SRM 51-25-01, (REV.38). INSTALLED FABRICATED PARTS AT AFT PRESSURE BULKHEAD FWD SURFACE FS 621.00, WL 130.93 TO WL 133.93, REF BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV A). FABRICATED SHIM FOR CARGO DOOR TRACK, 5.1 L X 7.500 W X 0.063 D, REF BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV A). APPLIED SURFACE PROTECTION ON CARGO DOOR TRACK SHIM, REF BOMBARDIER REO 601R-53-61-1541 DATED: 2020-12-06, (REV A). INSTALLED SPRING BRACKET AND CARGO DOOR TRACK ON AFT PRESSURE BULKHEAD, REF SRM 51-42-06, (REV 38).

Part: DISPLAY — FAILED (COCKPIT) · airframe 37,937 hrs · 36,434 cycles

BOTH MFD FAILED AT 1000 FT AGL AIRCRAFT REMOVED FROM SERVICE REPLACED L MFD IAW AMM 31-61-01. OPS CK GOOD

Part: WARNING MESSAGE — FALSE ACTIVATION (ANTI SKID SYS) · airframe 37,363 hrs · 35,890 cycles

THE CREW RECEIVED AN OUTBOARD ANTI SKID MESSAGE UPON LOWERING LANDING GEAR. THE CREW OPTED TO DIVERT TO MKE FOR A LONGER RUNWAY. FLIGHT LANDED NORMALLY, NO EMERGENCY DECLARED AND NO ADVERSE REACTION FROM PASSENGERS. SYSTEM WAS SUCCESSFULLY RESET ONCE THE AIRCRAFT WAS ON THE GROUND.

Part: WARNING MESSAGE — ILLUMINATED (ANTI ICE SYSTEM) · airframe 36,852 hrs · 35,427 cycles

INFLIGHT WITH WING ANTIICE ON IN NORMAL MODE, RECEIVED WING OVERHEAT WARNING. SUSPECT LEFT WING. C/W'D QRH & SELECTED WING ANTI-ICE OFF. MESSAGE CLEARED IMMEDIATELY. PER QRH, SELECTED WING ANTI-ICE TO STBY, THEN RECEIVED LEFT WING ANTI-ICE CAUTION & SYNOPTIC SHOWED LEFT WING AMBER. C/W'D QRH & SELECTED 14TH ISOL OPEN, LEFT WING ANTI-ICE CAUTION CLEARED & THEN REOCCURRED. CLEARED ICING CONDITIONS & SELECTED WING ANTIICE OFF. UPON RE-ENTERING ICING CONDITIONS, SELECTED ANTIICE ON IN STBY WITH 14TH ISOL VALVE OPEN , NO ANTIICE MESSAGES PRESENT. DIVERTED.

Part: BLEED AIR SYS — CLOSED (RIGHT) · airframe 36,695 hrs · 35,275 cycles

AT 25,000FT RECEIVED CABIN ALT CAUTION MSG WITH A RATE OF 800FT AND RISING STARTED EMER DESCENT RAN QRH. RT 10TH STAGE BLEED SHOWS CLOSED WITH SWITCH IN OPEN POSITION. RT PACK ZERO PSI.

Part: SKIN — DAMAGED (TE FLAP) · airframe 35,658 hrs · 34,274 cycles

RIGHT I/B FLAP LOWER SKIN AREAS OF DENTS AND PITS. REPLACED LOWER SKIN IAW SRM 51-25-16.

Part: LANDING — CRACKED (FUSELAGE) · airframe 35,658 hrs · 34,274 cycles

LT TRU DOOR AFT LATCH CUTOUT CRACKED AT LANDING. FWD LWR CORNER. REPLACED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,658 hrs · 34,274 cycles

FRAME 605 ON THE FWD SIDE ABOVE AND BELOW STRINGER 9L CRACKED. REPAIRED FRAME 605 IAW REO 601R-53-61-5214.

Part: FRAME — CRACKED (FUSELAGE) · airframe 35,658 hrs · 34,274 cycles

FRAME 605 ON THE FWD SIDE ABOVE AND BELOW STRINGER 9L CRACKED. REPAIRED FRAME 605 IAW REO 601R-53-61-5214.

Part: SKIN — CHAFED (TE FLAP) · airframe 35,658 hrs · 34,274 cycles

RT I/B FLAP VANE MID LEADING EDGE CHAFED. REPLACED FLAP VANE MID LEADING EDGE IAW SRM 51-42-13.

Part: RETAINER — CRACKED (PANEL) · airframe 35,658 hrs · 34,274 cycles

PANEL 422BT SEAL RETAINER CRACKED. REPLACED SEAL RETAINER IAW SRM 51-42-06, 51-40-11.

Part: STRIP — CRACKED (CARGO BAY) · airframe 35,658 hrs · 34,274 cycles

CARGO SIDE WALL MOUNT RAIL STRIP CRACKED FS FS559+96 TO 559+112 AT STR 16L. REPLACED CARGO SIDE WALL RAIL STRIP IAW SRM 51-42-06, 51-24-21, 51-40-11.

Part: SKIN — CHAFED (TE FLAP VANE) · airframe 35,658 hrs · 34,274 cycles

LT I/B FLAP VANE I/B LEADING EDGE CHAFED. REPLACED FLAP VANE I/B LE IAW SRM 51-42-13.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,658 hrs · 34,274 cycles

RIGHT SIDEWALL SEAT TRACK NR 7 CORRODED. REMOVED AND REPLACED RIGHT SIDEWALL SEAT TRACK NR 7 AFTER BLENDING IAW REO601R-53-00-055, AND AMM 53-01-11.

Part: SKIN — CHAFED (TE FLAP VANE) · airframe 35,658 hrs · 34,274 cycles

LEFT INBOARD FLAP VANE MID LEADING EDGE CHAFED. REPLACED FLAP VANE LEADING EDGE IAW SRM 51-42-13.

Part: SEAT TRACK — CHAFED (FUSELAGE) · airframe 35,658 hrs · 34,274 cycles

SEAT TRACK NR 9 RIGHT IS CHAFED FROM FS 559+80 TO 559+96, RBL9. REPLACED SEAT TRACK NR 9 IAW AMM 53-00-49, REO 601R-53-00-485 REV-D.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,658 hrs · 34,274 cycles

FS 349.00, LBL43 FLOOR SUPPORT CUTOUT CORRODED. REMOVED AND REPLACED FLOOR SUPPORT CUTOUT IAW SRM 51-21-06, 51-40-11, 51-42-06, 53-21-23.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,658 hrs · 34,274 cycles

SEAT TRACK CORRODED AT FS 559+80 TO 559+90, RBL27. REPLACED SEAT TRACK IAW SRM 53-00-49 AND REO601R-53-00-485 REV-D.

Part: BRACKET — CRACKED (LT MLG) · airframe 35,658 hrs · 34,274 cycles

LEFT MLG BRAKE FUSE BRACKET IS CRACKED. REPLACED BRACKET IAW SRM 51-42-*06, 51-41-02, 51-40-11.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 35,658 hrs · 34,274 cycles

ANGLE CLIP HAS A HOLE IN IT AT FS333.00, LBL9. REPLACED ANGLE CLIP IAW SRM 51-42-21, 51-42-06.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,658 hrs · 34,274 cycles

LEFT FLOOR SEAT TRACK NR 1 CORRODED. REPLACED SEAT TRACK NR 1 IAW SRM 53-01-11.

Part: SKIN — DAMAGED (TE FLAP) · airframe 35,658 hrs · 34,274 cycles

LEFT I/B FLAP LOWER SKIN HAS LARGE AREA OF DINGS AND PITS. REPLACED LEFT I/B FLAP I/B LOWER SKIN IAW SRM 51-25-16.

Part: BULKHEAD — CRACKED (BS 621) · airframe 34,960 hrs · 33,565 cycles

DURING EDDY CURRENT INSPECTION FOUND 11.5 INCH CRACK IN AFT PRESSURE BULKHEAD.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 34,571 hrs · 33,156 cycles

DURING FIRST FLIGHT, CREW REPORTED THAT THE EMERGENCY LIGHTS FROM ROW 8-12 WOULD NOT ILLUMINATE. INSPECTED AND FOUND BROKEN WIRES AT ROW 12. APPLIED ELECTRICAL TAPE TO BROKEN WIRES.

Part: BALLAST — BURNED (CABIN LIGHTS) · airframe 34,297 hrs · 32,898 cycles

ELECTRICAL SMOKE ODOR OVER ROWS 2, 3, AND 4. FOUND CEILING LIGHT BALLAST AT SEAT 4CA BURNED. REMOVED AND REPLACED CEILING BALLAST. OPS CHECKED GOOD IAW AMM 33-21-04.

Part: LIGHT — INOPERATIVE (ROW 8) · airframe 34,142 hrs · 32,754 cycles

FLOOR EMERGENCY LIGHTS AFT OF ROW 8 WILL NOT ILLUMINATE. R & R THE EMERGENCY LIGHT IAW AMM 16-371A. OPS CHECKED GOOD.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 33,777 hrs · 32,411 cycles

EMERGENCY FLOOR TRACK LIGHTNING DIM OUT OF ROW 9-12 AFTER SWITCH FLIPPED ON. R & R THE NR 4 EMERGENCY LIGHT BATTERY PACK IAW MM 33-51-04. OPS CHECKED GOOD.

Part: PACKING — LEAKING (APU FUEL LINE) · airframe 33,489 hrs · 32,123 cycles

FUEL ODOR IN REAR OF CABIN WITH APU RUNNING, AND BOTH PACKS ON AT GATE. REPLACED THE PACKING FOR THE LT ENGINE FUEL FEED LINE AND REPLACED AC PACK COALESCERS.

Part: LIGHT — MALFUNCTIONED (CABIN) · airframe 33,133 hrs · 31,792 cycles

EMERGENCY LIGHTS ON WITH SWITCH IN ARMED POSITION. REMOVED AND REPLACED AC SERVICE BUSS RELAY K5XD IAW AMM 24-51-27, REMOVED AND REPLACED AC ESS BUSS RELAY K1XD IAW AMM 24-51-27 OPS CHECKED GOOD. EMERGENCY LIGHTS OPS CHECKED GOOD.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

FRAME 409 IS CORRODED ON FWD FACE OF WEB BETWEEN STR 25L AND STR 25R.

Part: ANGLE — CRACKED (PAX DOOR) · airframe 31,835 hrs · 30,588 cycles

PASSENGER DOOR COVER PLATE FWD ATTACH POINT, AFT ANGLE IS CRACKED.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

FRAME FS 333 CORRODED BETWEEN STR 23R AND STR 22R.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

STRINGER 23R CORRODED AT FS 333.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 31,835 hrs · 30,588 cycles

PASSENGER CABIN STR 3L IS CRACKED AT FS 379.00. REPAIRED STR 3L AT FS 379.00 IAW SRM 53-00-03.

Part: BRACKET — CRACKED (RT WING) · airframe 31,835 hrs · 30,588 cycles

RT WING L/E REFUELING PORT BRACKET IS CRACKED AT OTBD LOWER RADIUS. REPLACED RT WING L/E REFUELING PORT BRACKET IAW SRM 51-42-06, 51-41-02.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 31,835 hrs · 30,588 cycles

FLIGHT DECK AFT FLOOR LANDING IS CRACKED ON THE FWD SIDE OF THE 280.00 BEAM AT LBL9 IN THE FWD ELECTRONIC EQUIPMENT BAY. REPLACED CRACKED FLIGHT DECK AFT FLOOR LANDING IAW SRM 51-42-06, 51-42-21.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

PASSENGER CABIN BEAM AT FS 513.00 HAS A SPOT OF CORROSION ON INBD FLANGE AT STR 5L. REPAIRED FS 513.00 FRAME IN PASSENGER CABIN ON INBD FLANGE AT STR 5L IAW EA AWAC-CRJ253-00401, REV-IR DATED 06/01/2016.

Part: BRACKET — CRACKED (LT WING) · airframe 31,835 hrs · 30,588 cycles

LEFT WING L/E ATTACH ANGLE BRACKET AT WA 149.58 CRACKED, REPLACED.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

SERVICE DOOR LOWER SILL ANGLE HAS CORROSION BETWEEN FS 319.7 AND FS 349.

Part: BRACKET — CRACKED (CARGO BAY) · airframe 31,835 hrs · 30,588 cycles

CARGO PIT DOOR CURTAIN BRACKET IS CRACKED AT FS 621.00 BULKHEAD. REPLACED BRACKET ON CARGO DOOR CURTAIN SUPPORT AT FS 621.00 IAW SRM 51-42-21.

Part: STRUCTURE — CRACKED (APU BAY) · airframe 31,835 hrs · 30,588 cycles

APU ENCLOSURE IS CRACKED ALONG AFT FLANGE AT STIFFENER LOCATIONS. 2 EA CRACKS PENETRATE AFT FLANGE AND 1EA CRACK IS BROKEN SPOT WELD.

Part: RIB — CORRODED (ACCESSORY DOOR) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

AFT ACCESSORY COMPARTMENT DOOR 2ND FROM RIB AFT, BENT AND CORRODED.

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

CARGO SEAT TRACK AT RBL9 AND LBL9 ARE CORRODED BETWEEN FS 559+109 AND FS 569.00. REPLACED CARGO SEAT TRACKS AT RBL9 AND LBL9, FS 559+109 TO FS569.00 IAW AMM 53-00-49-400-801.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 31,835 hrs · 30,588 cycles

PILOTS WINDSHIELD CENTER POST LOWER LT BRACKET AT BS 202.75 CRACKED.

Part: BRACKET — CRACKED (PAX DOOR) · airframe 31,835 hrs · 30,588 cycles

PAX DOOR CLOSE OUT PLATE AFT ATTACH POINT, AFT ANGLE IS CRACKED. REPLACED BRACKET IAW SRM 51-41-02.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

RIGHT FLOOR SILL HAS CORROSION JUST FOWARD OF THE SERVICE DOOR OPENING AT FS 319.70 IN CABIN.

Part: SUPPORT FITTING — GOUGED (FUSELAGE) · airframe 31,835 hrs · 30,588 cycles

RIGHT WINDSHIELD POST INBD SUPPORT FITTING IS GOUGED. REPLACED RT WINDSHIELD POST INBD SUPPORT FITTING IAW SRM 51-42-21.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 31,835 hrs · 30,588 cycles

LEFT WINDSHIELD POST OTBD SUPPORT FITTING CRACKED. REPLACED LT WINDSHIELD POST OTBD SUPPORT FITTING IAW SRM 51-42-21.

Part: SKIN — DENTED (TE FLAP) · airframe 31,835 hrs · 30,588 cycles

COMPLY WITH REPAIR TO LT INBD FLAP LOWER SKIN 601R-57-52-2118, 4DMI18552. REPAIRED LT INBD FLAP LOWER SKIN IAW REO 601R-57-52-2118.

Part: SPLICE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,835 hrs · 30,588 cycles

FRAME 319.70, OUTER T-SPLICE AT SERVICE DOOR OPENING IS CORRODED AT FLOOR LEVEL IN CABIN. REPLACED FRAME 319.70 OUTER T-SPLICE AT SERVICE DOOR OPENING AT FLOOR LEVEL IAW SRM 51-42-21.

Part: ATTACH ANGLE — CRACKED (SERVICE PANEL) · airframe 31,835 hrs · 30,588 cycles

EXTERNAL SERVICE PANEL LOWER ATTACH ANGLE IS CRACKED.

Part: FLAP — FAILED (WING) · airframe 31,591 hrs · 30,372 cycles

FLAPS FAILED AT ZERO ON SHORT FINAL.

Part: BRAKE — MALFUNCTIONED (MLG) · airframe 31,271 hrs · 30,088 cycles

ON BRAKE RELEASE ACFT PULLED LT. AFTER ABORT & 2ND BRAKE APPLICATION LT BRAKE RELEASED. BTMS 2, 2, 2, 3.

Part: UNKNOWN — NOT REPORTED (LANDING GEAR) · airframe 31,271 hrs · 30,088 cycles

AT BRAKE RELEASE ACFT PULLED LT, REACHED 47 KTS & ABORTED TAKEOFF.

Part: FLAP — MALFUNCTIONED (WING) · airframe 31,084 hrs · 29,914 cycles

WHILE IN FLIGHT, FLAPS FAILED AT 20 DEG WHEN SELECTING TO 30 DEG ON. APPROACH FAILURE AT APPROX 180 KNOTS. PERFORMED FLAP RESET PROCEDURE IAW SUP 98-18G BOX 12, FLAPS RESET.

Part: STATUS MESSAGE — ACTIVATED (COCKPIT) · airframe 30,295 hrs · 29,141 cycles

DURING CLIMB, WE EXPERIENCED A VERY SLIGHT YAW MOTION, A YAW YD1 INOPERATIVE STATUS MSG APPEARED SHORTLY THEREAFTER.

Part: WIRE — OUT OF POSITION (IDG) · airframe 27,304 hrs · 26,259 cycles

IDG WIRE TB208-1 ROUTED AGAINST THE PYLON SEPARATOR PN 601R37138-20 ON PANEL 422DB CAUSING AN EVENTUAL ARC & HOLE THROUGH THE SEPARATOR & DAMAGE TO THE WIRE. WIRE & SEPARATOR WERE REPLACED. THIS WAS DISCOVERED WHILE PERFORMING A ROUTINE RT ENG CHANGE.

Part: PANEL — DAMAGED (LT HORIZ STAB) · airframe 27,175 hrs · 26,142 cycles

COMPLIED WITH CARD 4DMI16980 REPAIR LT LWR H STAB PANEL 601R-55-11-467A. COMPLIED WITH PERMANENT REPAIR OF LT LWR H STAB AT PANEL 342 AB IAW REO 601R-55-11-488 & REPAIRED H STAB LT PCU ACCESS DOOR ATTACHMENT HOLES IAW REO 601R-55-11-491.

Part: COWLING — CRACKED (LT ENGINE) · airframe 27,175 hrs · 26,142 cycles

LT LOWER CORE COWL FWD BAYONET HOLE HAS CRACK. REPAIRED LT LOWER CORE COWL IAW EA 25-20144-177.

Part: RECEPTACLE — CRACKED (EXTERNAL POWER) · airframe 27,175 hrs · 26,142 cycles

RT LOWER NOSE COMPARTMENT GND POWER RECEPTACLE CRACKED. R & R GND POWER RECEPTACLE WITH NEW SERVICEABLE PART IAW SRM 51-40-11 & 51-42-21 REO 601R-53-009 REV A.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,175 hrs · 26,142 cycles

AFT FACE OF FRAME 349 HAS CORROSION FROM LOWER STRINGER 25L TO STRINGER 26R. REMOVED UNSERVICEABLE LOWER FRAME FS 349 & INSTALLED A SERVICEABLE LOWER FRAME IAW SRM 51-42-21, 51-40-11 & 51-21-11.

Part: AILERON — DAMAGED (RT WING) · airframe 27,175 hrs · 26,142 cycles

COMPLIED WITH CARD 4DMI16447 REPAIR RT AILERON OTBD TE 601R-57-61-438A. PERFORMED PERMANENT REPAIR ON RT AILERON IAW REO 601R-57-61-499 REV A.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

NLG CUT OUT AFT CORNERS LT & RT ARE CRACKED. REPAIRED AFT NLG CUT OUT LT & RT CORNERS IAW 601R-53-11-048 REV C.

Part: ANGLE — CRACKED (PAX DOOR) · airframe 27,175 hrs · 26,142 cycles

PAX DOOR POWER ASSIST MOTOR MOUNTING ANGLE CRACKED. R & R MOUNTING ANGLE PN 601R317745-7 IAW SRM 51-40-11 & 51-42-06.

Part: VANE — CHAFED (TE FLAP) · airframe 27,175 hrs · 26,142 cycles

54667-5000-0030 - RT INBD FLAP VANE CHAFED. REMOVED UNSERVICEABLE INBD FLAP VANE LE & INSTALLED NEW SERVICEABLE LE IAW SRM 51-42-13.

Part: BEAM — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

VERTICAL BEAM AT FS 409+128 & LBL 18 IS CRACKED LOWER AFT LEG. REPAIRED VERTICAL BEAM AT FS 409+128 LBL 18 IS CRACKED AT LOWER AFT LEG IAW REO 601R-53-41-056 REV F.

Part: HINGE — CRACKED (PAX DOOR) · airframe 27,175 hrs · 26,142 cycles

54667-8000-0019 - PAX DOOR TOP STEP 832 CT UPPER HINGE CRACKED. R & R HINGE PN 601R31980-41 IAW SRM 51-41-02.

Part: STATIC WICK — DAMAGED (RT WINGLET) · airframe 27,175 hrs · 26,142 cycles

54667-6000-0003 - COMPLIED WITH CARD REPAIR RT WINGLET UPPER STATIC WICK E07/009/423A. COMPLIED WITH EO E05 047 423F FOR REPAIR OF RT WINGLET UPPER STATIC WICK.

Part: DRAG ANGLE — CRACKED (PAX DOOR) · airframe 27,175 hrs · 26,142 cycles

PAX DOOR AFT DRAG ANGLE IS CRACKED AT DOOR ASSIST PULLEY BRACKET. REPAIRED PAX DOOR AFT DRAG ANGLE IAW REO 601R-52-11-513 REV A DATED 09 MAR 05.

Part: BEAM — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

VERTICAL BEAM AT FS 409+128 RBL 18 IS CRACKED LOWER AFT LEG NEAR FASTENER.

Part: MOUNT BRACKET — CRACKED (BRAKE TRANSDUCER) · airframe 27,175 hrs · 26,142 cycles

BRAKE TRANSDUCER MOUNT BRACKET CRACKED IN RT WW. R & R BRAKE TRANSDUCER BRACKET IAW 51-42-06.

Part: FAIRING — CRACKED (LT EXHAUST) · airframe 27,175 hrs · 26,142 cycles

LT TAIL PIPE FAIRING SECOND RING CRACKED ON INBD LOWER SIDE. REPAIRED LT TAIL PIPE FAIRING IAW CMM 78-11-00.

Part: DRAG ANGLE — CRACKED (RT MLG WW) · airframe 27,175 hrs · 26,142 cycles

RT MLG WW DRAG ANGLE CRACKED ON FWD END. REMOVED CRACKED ANGLE & INSTALLED NEW SERVICEABLE ANGLE IAW SRM 51-40-11, 51-42-21 & 51-25-16.

Part: FRAME — CHAFED (TE FLAP) · airframe 27,175 hrs · 26,142 cycles

RT INBD FLAP INBD LE FRAME CHAFED. R & R RT INBD LE FRAME IAW SRM 51-42-06.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

621 AFT FACE LT & RT OBLIQUE ANGLES ARE CRACKED. REMOVE CRACKED ANGLES & INSTALLED NEW SERVICEABLE OBLIQUE ANGLES ON RT & RT SIDE OF 621 AFT BULKHEAD IAW SRM 51-24-16, 51-21-16 & 51-40-11.

Part: FITTING — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

CLIPS AT FS 280 & STRINGER 3L ARE CRACKED. REMOVED INBD & OTBD CLIPS AT FS 280 & INSTALLED SERVICEABLE CLIPS IAW SRM 51-42-21, 51-42-21, 51-42-06 & 51-23-16.

Part: FITTING — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

LT FS 484 CLIPS CRACKED BL 27 & 36. R & R CRACKED 484 CLIPS WITH NEW SERVICEABLE CLIPS IAW SRM 51-21-16, 51-42-06 & 51-42-21.

Part: RING — CRACKED (RT EXHAUST) · airframe 27,175 hrs · 26,142 cycles

RT ENG EXHAUST FAIRING RIB RING CRACKED. REPAIRED RT ENG EXHAUST FAIRING FWD RIB RING IAW CMM 78-11-00.

Part: FITTING — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

280 RBL9 INBD & OTBD CLIPS CRACKED. R & R FS 280 RBL 9 INBD & OTBD CLIPS IAW SRM 53-21-43.REO 601R-53-11-171REV D.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,175 hrs · 26,142 cycles

LT SIDE SEAT TRACK FS 544 TO 574 HAS CORROSION. REMOVED CORRODED SEAT TRACK & REPLACED WITH SERVICEABLE TRACK IAW SRM 53-21-49 & AMM 53-01-11.

Part: RIB — CRACKED (RT WING) · airframe 27,175 hrs · 26,142 cycles

54667-7000-0008 - RT MLG WW BATTERY RIB CRACKED UPPER OTBD SIDE. REPAIRED RT MLG WW BATTERY RIB IAW REO 601R-57-51-046 REV B.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,175 hrs · 26,142 cycles

SEAT TRACK AT RBL 9+48 TO FS 559+80 HAS CORROSION. R & R SEAT TRACK AT RBL 9 AT FS 559+48 TO FS 559+80 IAW 53-01-05.

Part: BRACKET — CRACKED (COCKPIT) · airframe 27,175 hrs · 26,142 cycles

54667-1000-0057 - COPILOTS SIDE WINDOW POST LOWER BRACKET CRACKED. R & R WITH A NEW SERVICEABLE BRACKET IAW SRM 51-42-21 & 51-40-11.

Part: TIE DOWN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,175 hrs · 26,142 cycles

3 EA TIE DOWNS AT FS 559+96 TO 574.00 HAS CORROSION. R & R 3 EA TIE DOWNS AT FS 559.00 TO 574.00.

Part: TIE DOWN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 27,175 hrs · 26,142 cycles

54667-2000-0075 - 1 EA TIE DOWN ON LBL 9 AT FS 574 HAS CORROSION. R & R 1 EA TIE DOWN ON LBL 9 AT FS 574 IAW SRM 51 41- 02.

Part: FITTING — CRACKED (FUSELAGE) · airframe 27,175 hrs · 26,142 cycles

RT FS 484 CLIPS CRACKED AT BL 27 & 36. R & R CLIPS WITH SERVICEABLE CLIPS IAW REO 601R-53-41-059 REV B.

Part: AILERON — STIFF (WING) · airframe 26,971 hrs · 25,956 cycles

WITH AUTOPILOT OFF, AILERONS VERY STIFF TO MOVE IN BOTH DIRECTIONS. ON APPROACH FIRST OFFICER COULD ONLY ROLL AILERONS 1/2 TRAVEL TO THE RIGHT.

Part: UPLOCK — DAMAGED (RT MLG) · airframe 24,282 hrs · 23,375 cycles

GEAR DISAGREE MESSAGE POSTED UPON RETRACTION OF HANDLE NO NOSE DOOR WARNINGS RIGHT MAIN SHOWED UNSAFE PERFORMED MANUAL EXTENSION PER THE QRH NO TURBULANCE OR ABNORMAL FLIGHT CONTROL MOVEMENT NOTED. PINNED GEAR VERIFIED MANUAL EXTENSION HANDLE IN STOWED POSITION REF 242465/4 FOR MEL REF 242465/2 GEAR DISAGREE RIGHT MAIN SHOWED UNSAFE DURING RETRACTION INSTALLED PINS REMOVED STREAMERS AND PLACED IN SPARE BULB KIT. C/W M ACTION PLACARDED AND PLACED ON MEL. FOUND RIGHT UPLOCK TARGET PLETE LOOSE AND DAMAGED REMOVED AND REPLACED RIGHT MAIN GEAR UPLOCK REF AMM 32 32 05 AND AWAC SUP 08-068A & 08-069A OP AND LEAK CHECK GOOD. REMOVE PLACARD/MEL.

Part: WINDOW — BROKEN (COCKPIT) · airframe 23,820 hrs · 22,922 cycles

LEVEL AT 10,000FT CAPTAIN'S LEFT WINDOW SHATTERED (INSIDE PANE FAILED). DIVERTED TO ABE. NO PRESSURIZATION PROBLEMS ASSOCIATED WITH THE BREAKAGE. EMERGENCY DECLARED WITH ATC. DISPATCH, FA & PASSENGERS BRIEFED. UNEVENTFUL APPROACH AND LANDING CONDUCTED IN ABE. REMOVED AND REPLACED LEFT WINDOW IAW AMM 56-12-01. OPS CHECK/FUNCTIONAL CHECK GOOD.

Part: CONNECTOR — DIRTY (ANTI ICE SYSTEM) · airframe 22,302 hrs · 21,434 cycles

RT COWL ANTI-ICE CAUTION MESSAGE IN FLT WHEN SELECTED OFF. RAN NR 2 ENG WITH COWL SWITCH ON AND OFF. ALL CHECKED NORMAL. CLEANED CONNECTORS AT COWLS ANTI-ICE PRESSURE SWITCH, OK FOR SERVICE.

Part: HEAT SHIELD — DAMAGED (APU AFT EXHAUST) · airframe 22,249 hrs · 21,373 cycles

APU AFT EXHAUST HEAT SHIELD HAS 4 PULLED THROUGH FASTENERS, COMPLIED WITH REO 601R-49-81-051.

Part: CARGO TRACK — CORRODED (BS 521) · airframe 22,249 hrs · 21,373 cycles

CARGO TRACK AT LBL 9 & 521 CORRODED. REMOVED CORRODED CARGO TRACK AND REPLACED WITH NEW SERVICEABLE, IAW AMM 53-01-16.

Part: TRUNNION — DAMAGED (MLG) · airframe 22,249 hrs · 21,373 cycles

DURING COLD WORKING OF LT AND RT MLG TRUNNION LOWER FLANGE FOUND FIVE OVERSIZED HOLES. REPAIRED OVERSIZED HOLES ON LT AND RT MLG TRUNNION LOWER FLANGE. IAW REO 601R-57-21-1679, REV.

Part: SILL — CORRODED (PAX DOOR) · airframe 22,249 hrs · 21,373 cycles

PAX DOOR CUTOUT LOWER SILL IS CORRODED IN SEVERAL PLACES. REMOVED UNSERVICEABLE PAX DOOR SILL AND INSTALLED SERVICEABLE PAX DOOR SILL IAW SRM 51-42-06/51-42-21.

Part: SILL — CORRODED (FS 562-621) · airframe 22,249 hrs · 21,373 cycles

CARGO BAY DOOR SILL HAS SURFACE CORROSION AROUND NUTPLATES FS 574 - 621. SEVERAL NUTPLATES ARE RUSTY UNDERNEATH SILL. REMOVED UNSERVICEABLE CARGO BAY DOOR SILL. LOCATED, DRILLED, AND INSTALLED SERVICEABLE CARGO BAY DOOR SILL IAW SRM 51-40-11, 51-42-06, 51-42-27, REO 601R-53-61-690, REV DER.

Part: STOP FITTING — CRACKED (FS 589) · airframe 22,249 hrs · 21,373 cycles

FWD CARGO DOOR STOP HAS CRACKED ANGLE UNDER FLOOR SILL AT FS 589.0. REMOVED CRACKED ANGLE AND REPLACED WITH NEW FABRICATED ANGLE IAW SRM 51-42-21 AND 51-40-11.

Part: SKIN — DAMAGED (NACELLE) · airframe 22,249 hrs · 21,373 cycles

CORE COWL 435AB INNER SKIN DAMAGED IN 5 PLACES. REPLACED DAMAGE IAW REO 601R-71-12-4114 AND CMM 71-12-01.

Part: FLOOR SUPPORT — CORRODED (FS 589 TO 621) · airframe 22,249 hrs · 21,373 cycles

FLOOR SUPPORT LBL 27 AT FS 589 HAS CORROSION AROUND NUTPLATES. R & R LBL27 FROM FS 589 TO FS 610 AND BLEND 2 SPOT AT FS 615 AND INSTALLING 2 EA SHIMS AND DOUBLERS IAW REO 601R-53-61-4517.

Part: ATTACH FITTING — GOUGED (THRUST REVERSER) · airframe 22,249 hrs · 21,373 cycles

PANEL 444AB GOUGED ON INBD ATTACH FITTING. REPAIR GOUGE ON PANEL 444AB ATTACH FITTING IAW REO 601R-78-33-3992, REV NC.

Part: ATTACH FITTING — GOUGED · airframe 22,249 hrs · 21,373 cycles

PANEL 444AT GOUGED IN INBD SIDE ATTACH FITTING. REPAIR GOUGE ON INBD SIDE ATTACH FITTING IAW REO 601R-78-33-3992 REV, NC.

Part: SKIN — CORRODED (LT WING) · airframe 22,249 hrs · 21,373 cycles

LEFT WING LOWER FUEL TANK ACCESS PANEL CUTOUT HAS FRETTING CORROSION. BLENDED AREAS IAW REO 601R-57-21-030, REV H. MATERIAL LOSS AFTER BLEND .008. FOUND AREAS NOT TO EXCEED ALLOWED LIMITS IAW REO 601R-57-21-030, REV H.

Part: CARGO TRACK — CORRODED (FS 574) · corrosion level 2 · airframe 22,249 hrs · 21,373 cycles

CARGO TRACK ON LBL9 & FS 574 HAS CORROSION. INSTALLED SERVICEABLE CARGO TRACK ON LBL9 & FS 574 IAW SRM 51-41-04.

Part: VANE — CHAFED (LT WING TE FLAP) · airframe 22,249 hrs · 21,373 cycles

LEFT INBD FLAP VANE L/E CHAFED IN 3 PLACES. BLENDED AREAS ON LT INBD FLAP VANE L/E IAW REO 601R-57-52-004, REV C AND SRM 51-12-00. TREATED AREA SRM 51-21-11, 51-25-06, AND 51-25-26.

Part: RETAINER — CORRODED (AVIONIC DOOR) · corrosion level 2 · airframe 22,249 hrs · 21,373 cycles

AVIONICS DOOR SEAL RETAINER CORROSION. REMOVED UNSERVICEABLE 4 (EA) SEAL RETAINERS & 1 SEAL REPLACED W/4 (EA) SERVICEABLE SEAL RETAINERS AND 1 SERVICEABLE SEAL.

Part: DOOR — CHAFED (CLOSET) · airframe 22,249 hrs · 21,373 cycles

AFT GALLEY CLOSET DOOR CHAFED. REPAIRED IAW REO 601R-53-11-1727, REV E, DATE 01/14/2011.

Part: HINGE — CORRODED (LAVATORY DOOR) · airframe 22,249 hrs · 21,373 cycles

LAVATORY SERVICE DOOR LOWER HINGE AND HARDWARE CORRODED. REMOVED UNSERVICEABLE LAVATORY SERVICE DOOR LOWER HINGE AND HARDWARE AND REPLACED WITH SERVICEABLE HINGE IAW SRM 51-41-00.

Part: STRUCTURE — GOUGED (NACELLE) · airframe 22,249 hrs · 21,373 cycles

CORE COWL 435AB DAMAGE ON INNER CENTER STIFFENER. BLENDED GOUGE ON INNER CENTER HOT CHANNEL .050. REMOVED .008 REMAINING, .042 WITHIN LIMITS USING AMM 51-21-400 IAW CMM 71-12-01, SRM 51-21-11, 57-25-06, 51-25-26.

Part: STRUCTURE — DAMAGED (NACELLE) · airframe 22,249 hrs · 21,373 cycles

CORE COWLING 435AT INBD L/E CORNER DAMAGED CUTOUT DAMAGED AREA OF 435AT CORE COWLING INBD L/E CORNER IAW CMM 71-12-01. SRS18 SEE FORM 412 FOR INSTALL, FAB OF DOUBLER AND FILLER.

Part: STRUCTURE — DAMAGED (NACELLE) · airframe 22,249 hrs · 21,373 cycles

CORE COWLING 435AB INBD L/E CORNER DAMAGED. CUTOUT DAMAGED CORNER OF 435AB CORE COWL INBD L/E IAW CMM 71-12-01. SEE FORM 412 FOR FAB AND INSTALL OF FILLER AND DOUBLER.

Part: ANGLE — CRACKED (FS 621 TO 630) · airframe 22,249 hrs · 21,373 cycles

LEFT LOWER OBLIBUE ANGLE ON 621 BULKHEAD AFT SIDE CRACKED. REMOVED UNSERVICEABLE LT LOWER OBLIQUE ANGLE ON 621 BULKHEAD AFT SIDE. INSTALLED SERVICEABLE LT LOWER OBLIQUE ANGLE.

Part: WARNING MESSAGE — FALSE ACTIVATION (ANTI SKID SYS) · airframe 122,115 hrs · 21,252 cycles

RECEIVED CAUTION MESSAGE ON TAKE-OFF, ANTI-SKID OTBD MESSAGE DID NOT REAPPEAR WITH LANDING GEAR DOWN SELECTED DOWN. PERFORMED ASCU BITE TEST. OPS CHECKED GOOD IAW AMM 32-44-06.

Part: PCU — MALFUNCTIONED (SPOILERONS) · airframe 21,998 hrs · 21,151 cycles

AFTER TAKE OFF, RECEIVED WHITE SPOILERON FAULT "ON FLIGHT CONTROL, PAGE RT SPOILERON WAS WHITE" ON FINAL, RECEIVED RT SPOILERON CAUTION MESSAGE WITH WHITE T/B GROUND SPOILER FAULT AND OTBD SPOILERON FAULTS. REMOVED RT SPOILERON OTBD PCU IAW AMM 27-62-01. OPS CHECK GOOD.

Part: STEP — CRACKED (PAX DOOR) · airframe 17,504 hrs · 16,394 cycles

PAX DOOR HAS CRACK IN RADIUS OF 3RD STEP FROM TOP AFT REPAIRED TOP AFT RADIUS CRACK ON 3RD STEP IAW REO 601R-52-11-702 ZONE REPAIR 4,2, AND 3.

Part: ATTACH ANGLE — CRACKED (BS 280) · airframe 17,504 hrs · 16,394 cycles

FLOOR ATTACH ANGLE TO THE 280.0 BULKHEAD IS CRACKED JUST OTBD OF THE LBL 9. REPAIR FLOOR ATTACH ANGLE IAW REO 601R-53-11-136 REV A CUT OUT DAMAGE AND INSTALL SECTION OF FLOOR ANGLE.

Part: FAIRING — CHAFED (RT FUSELAGE) · airframe 17,504 hrs · 16,394 cycles

RT FUSELAGE HAS CHAFING DAMAGE AT AFT WING TO FUSELAGE POINT UNDER FLAP STUB FAIRING. BLENDED RT FUSELAGE AFT WING TO FUSELAGE DOES NOT EXCEED ALLOWABLE LIMITS IAW 601R-53-45-1215.

Part: LEVER — CHAFED (PAX DOOR) · airframe 17,504 hrs · 16,394 cycles

PAX DOOR FWD PULL IN LEVER CHAFED REPAIRED IAW REO 601R-52-11-524, REV A.

Part: HINGE — CHAFED (PAX DOOR) · airframe 17,504 hrs · 16,394 cycles

PAX DOOR HINGE (PIANO) HAS CHAFING DAMAGE ON LUG PAX DOOR HINGE. REPAIRED IAW REO 601R-52-11-1347.

Part: FAIRING — CHAFED (LT FUSELAGE) · airframe 17,504 hrs · 16,394 cycles

HAS CHAFING DAMAGE AT AFT WING TO FUSELAGE PART UNDER AND FWD OF FLAP STUB FAIRING BLENDED OUT DAMAGE AREA AS REQUIRED IAW REO 601R-53-41-1219 REV N/C DAMAGE DID NOT EXCEED EXISTING DEPTH.

Part: FITTING — CRACKED (BS 484) · airframe 17,504 hrs · 16,394 cycles

BATHTUB FITTING AT FS 484, RBL 9 CRACKED. FLAGGED R & R WITH SERVICEABLE BATHTUB FITTING PN 600-31068-19 AT FS 484, RBL9 ALL WORK DONE IAW SRM 51-42-06, 51-42-21, 51-21-11.

Part: BULKHEAD — CRACKED (BS 559) · airframe 17,504 hrs · 16,394 cycles

FS 559, WEB HAS INDICATED CRACK BETWEEN RBL9 AND RBL18. REPAIRED FS 559 CRACK BETWEEN RBL9 AND RBL18 BY INCORPORATION OR REO 601R-53-41-260, REV D AND 601R-53-41-609, REV B. DEVIATION E ON LT AND RT SIDES BETWEEN RBL 27 AND LBL 27.

Part: DRAG ANGLE — CRACKED (PAX DOOR) · airframe 17,504 hrs · 16,394 cycles

PAX DOOR FWD DRAG ANGLE CRACKED UNDER ASSIST CABLE PULLEY BRACKET SPLICED IN NEW DRAG ANGLE.

Part: ANGLE — CRACKED (RT PYLON) · airframe 17,504 hrs · 16,394 cycles

CRACK ON ANGLE ON PANEL 422AT, BLENDED OUT CRACK ON PANEL 422AT IAW SRM 51-12-00.

Part: ANGLE — CRACKED (BS 280) · airframe 17,504 hrs · 16,394 cycles

FLOOR ATTACH ANGLE ON THE 280.0 BULKHEAD IS CRACKED, 3RD RIVET OTBD OF RBL 9. REPAIRED FLOOR ATTACH ANGLE AT FS 280.0 BULKHEAD IAW REO 601R-53-11-136 REV A AND SRM 51-40-11, 51-24-36, 51-21-11, 51-25-06 AND 51-25-16, RBL 9.0.

Part: HINGE — CHAFED (PAX DOOR) · airframe 17,504 hrs · 16,394 cycles

PAX DOOR HINGE CHAFED.

Part: SILL — CORRODED (CARGO BAY) · airframe 17,504 hrs · 16,394 cycles

RT CARGO BAY FLOOR SILL CORRODED AROUND ANCHOR NUTS (NUT PLATES). CORROSION REMOVED IAW SRM 51-21-06.

Part: STIFFENER — CHAFED (BS 621) · airframe 17,504 hrs · 16,394 cycles

VERTICAL STIFFENER FOUND CHAFED AFT PRESSURE BULKHEAD BL 0. BLENDED CHAFED AREA IAW REO 601R-53-61-1523, REV: N/C AND 601R-53-61-3674, REV N/C FOUND WITHIN LIMITS FOR REO`S. APPLIED ALODINE, PRIMED, AND TOP COATED IAW SRM 51-21-11, 51-21-16, AND 51-25-06.

Part: BRACKET — CHAFED (RT WING)

CHAFING FOUND ON BRACKET PN 601R10371-2, RT WING ROOT. R & R BRACKET.

Part: STRIP — CHAFED (RT ENG NACELLE) · airframe 17,504 hrs · 16,394 cycles

RT ENGINE UPPER NOSE COWL AFT EDGE STRIP IS CHAFED, SHORTS IPS 71-14-01, FIG 1, ITEM 45. R & R WITH SERVICEABLE AFT EDGE STRIP PN 228-50080-108 AT RT ENGINE UPPER NOSE COWL ALL WORK DONE IAW CMM 71-14-01, SRM 51-21-11, 51-25-06, 51-25-16.

Part: STRIP — CHAFED (RT ENG NACELLE) · airframe 17,504 hrs · 16,394 cycles

RT ENGINE LOWER NOSE COWL AFT EDGE STRAP IS CHAFED, SHORTS IPC 71-14-01, FIG 2, ITEM 105. R & R WITH SERVICEABLE AFT EDGE STRIP PN 228-50081-108 AT RT ENGINE LOWER NOSE COWL WORN DOWN IAW SRM 51-21-11, 51-25-06, 57-25-18.

Part: SPLICE — CHAFED (LT ENG NACELLE) · airframe 17,505 hrs · 16,394 cycles

UPPER NOSE COWL AFT EDGE STRIP IS CHAFED, SHORTS IPC 71-14-01, FIG 1, ITEM 40. R & R WITH SERVICEABLE AFT EDGE STRIP PN 228-50080-107 ALL WORN DOWN IAW CMM 71-14-01 AND SRM 51-21-11, 51-25-06, 51-25-16.

Part: SEPARATOR — CHAFED (NACELLE) · airframe 17,504 hrs · 16,394 cycles

DIVIDER PLATES ARE KNIFE EDGED AND CHAFED, R & R DIVIDER PLATES PN 601R37138-27 AND 601R37138-25 IAW SRM 51-42-06, 51-42-13 AND 51-40-11.

Part: SEPARATOR — CHAFED (RT PYLON) · airframe 17,504 hrs · 16,394 cycles

DIVIDERS ON PANEL 422DB HAS CHAFING CONDITION. R & R 2 EA DIVIDER PANELS IAW SRM.

Part: SKIN — CHAFED (RT WING) · airframe 17,504 hrs · 16,394 cycles

LOWER L/E HAS EVIDENCE OF CHAFING REWORK CHAFING AREAS AS REQUIRE IAW REO 601R-57-60-020, REV N/C AND SRM 51-21-11, 51-25-06, 51-25-16.

Part: RIB — CRACKED (LT WING) · airframe 17,504 hrs · 16,394 cycles

BATT RIB CRACKED PN LT WW REPAIRED BATT RIB AT LT WW IAW REO 601R-57-51-046, REV B AND SRM 51-21-11, 51-25-06, 51-41-02 AND AMM 20-10-00.

Part: SKIN — DEBONDED (LT WING) · airframe 17,504 hrs · 16,394 cycles

LT WING OTBD L/E OTBD INNER SKIN DISBONDED AND 2 SHEARED RIVET. BONDED INNER SKIN ON LT WING OTBD L/E TO L/E SKIN AND REMOVED 2 SHEARED RIVETS, INSTALLED 2 NEW RIVETS PRIMED ALL AREAS INVOLVED IN WORK.

Part: UNKNOWN — VIBRATION (NLG WW) · airframe 16,607 hrs · 15,460 cycles

AFTER GEAR RETRACTION ON T/O, HEARD LOUD BANGING NOISE COMING FROM NOSE WHEEL AREA. SOUND LASTED 3 TO 5 MIN THEN EXTINGUISHED. DURING WHICH NOSE DOOR OPEN WARNING MSG WAS ON. INSP NOSE GEAR AREA, DOORS, NOSE GEAR, NO DAMAGE NOTED. INSP FUSELAGE, ENGS AND ENG INLETS, NO DAMAGE NOTED. TAXIED ACFT, NO MALFUNCTIONS NOTED. (K)

Part: CONTROLLER — MALFUNCTIONED (ANTI ICE SYSTEM) · airframe 16,600 hrs · 15,455 cycles

AFTER TAKEOFF RECEIVED RT STATIC HEAT, RT PITOT HEAT, RT AOA HEAT, TAT HEAT. C/W`D QRH MSG`S PERSIST. C/W`D OPS TEST OF AIR DATA HEAT CONTROLLERS IAW AMM 30-31-15-710-801, ALL PROBES HEAT & NO CAS MSG`S. (K)

Part: SENSOR — MALFUNCTIONED (BRAKE POSITION) · airframe 12,775 hrs · 11,828 cycles

FLAP FAIL MESSAGE WHEN FLAPS SET TO 8 DEGREES ON APPROACH TO LGA. DIVERTED TO PHL, ZERO FLAP LANDING. REMOVED AND REPLACED RT BPSU LAW AMM 27-51-10. OPS CHECK AND RIG CHECK OF BPSU AND FLAPS ARE GOOD AT THIS TIME. (A)

Part: FLAP — FAILED (WING) · airframe 12,632 hrs · 11,699 cycles

FLAPS FAILED AFTER TAKEOFF AT 12 DEGREES, PERFORMED QRH, RETURNED TO CMH. OPEN (A)

Part: FLAP — MALFUNCTIONED (WING) · airframe 12,625 hrs · 11,692 cycles

FLAP FAILURE AFTER TAKEOFF DURING RETRACTION FROM 20 DEGREES. FAILED AT 16 DEGREES. COMPLIED WITH RESET PROCEDURE IAW AWAC SUPPLEMENT 98-018B STEPS 1.3 AND 1.4, FLAP SYSTEM RESET OK. (S)

Part: RING — WORN (COWLING) · airframe 12,580 hrs · 11,644 cycles

CORE COWL 445 CLOSURE RING WORN BEYOND LIMITS. CORE COWL 445AB CLOSURE RING REPLACES IAW 71-12-01-300-820-A01 REPAIR. (A)

Part: STRIP — CHAFED (RT NACELLE) · airframe 12,580 hrs · 11,644 cycles

RT ENGINE NOSE ACCESS COWL (LOWER) TRAILING EDGE STRIP CHAFED BEYOND LIMIT. RT ENGINE NOSE ACCESS COWL (LOWER), NEW TRAILING EDGE STRIP INSTALLED IAW CMM 71-14-01-300-815-A01.

Part: STRIP — GOUGED (LT NACELLE) · airframe 12,580 hrs · 11,644 cycles

LT ENGINE UPPER NOSE ACCESS COWL AFT EDGE STRIP GOUGE. LT UPPER ENGINE COWL, AFT EDGE STRIP REPLACED IAW CMM 71-14-01-300-814-A01.

Part: PICCOLO TUBE — DENTED (RT WING) · airframe 12,580 hrs · 11,644 cycles

RT WING INTERNAL OUTBOARD LEADING EDGE AT W/S 252, PICCOLLO TUBE DENTED (.300 X .200 X .040 DEEP). PICCOLLO TUBE REPLACED IAW AMM TASK 30-11-41-400-801. (A)

Part: ANGLE — CRACKED (FUSELAGE) · airframe 12,580 hrs · 11,644 cycles

ANGLE CRACK ON ACCESS PANEL 422 BT. CRACKED ANGLE REPLACED ON ACCESS PANEL 422BT IAW SRM 51-42-06.

Part: SILL — CORRODED (BS 317-349) · corrosion level 2 · airframe 12,580 hrs · 11,644 cycles

SERVICE DOOR LOWER SILL PLATE CORRODED OVER LIMITS. SERVICE DOOR LOWER SILL PLATE REPLACED IAW SRM 51-41-02. (A)

Part: INTERCOSTAL — CRACKED (BS 621-625) · airframe 12,580 hrs · 11,644 cycles

CRACK EXISTS ON INTERCOSTAL FS 621 TO 625 STR R14. REPLACED IAW SRM 51-42-06. (A)

Part: INTERCOSTAL — CRACKED (BS 621-625) · airframe 12,580 hrs · 11,644 cycles

CRACK EXISTS ON INTERCOSTAL FS 621 TO 625 LT. REPLACED IAW SRM 51-42-06. (A)

Part: SEPARATOR — CRACKED (ACCESS PANEL) · airframe 12,580 hrs · 11,644 cycles

SEPARATOR CRACK ON ACCESS PANEL 422DB. NEW SEPARATOR INSTALL ON ACCESS PANEL 422DB IAW CRJ200 SRM 51-42-06. (A)

Part: DRAG ANGLE — CRACKED (PAX DOOR) · airframe 12,580 hrs · 11,644 cycles

PAX DOOR AFT DRAG ANGLE FOUND CRACKED. PAX DOOR DRAG ANGLE REPAIRED IAW REO 601R-52-11-513.

Part: STRUCTURE — CRACKED (PAX DOOR) · airframe 12,580 hrs · 11,644 cycles

REPAIR CRACK ON AFT OF PAX DOOR. REPAIR ON AFT SIDE OF PAX DOOR IAW REO 601R-52-11-279. (A)

Part: INTERCOSTAL — CRACKED (BS 484) · airframe 12,580 hrs · 11,644 cycles

INTERCOSTAL FS 484 CRACK AT RBL 29 AND RBL 36. INTERCOSTAL FS 484 AT RBL 27 AND RBL 36 ANGLE INSTALLED IAW REO 601R-53-41-059 REV A.

Part: INTERCOSTAL — CRACKED (BS 484) · airframe 12,580 hrs · 11,644 cycles

INTERCOSTAL FS 484 CRACK AT LBL 27 AND LBL 36. INTERCOSTAL FS 484 AT LBL 27 AND 36 ANGLE INSTALLED IAW REO 601R-53-41-059 REV A.

Part: HANDLE — CORRODED (ESCAPE HATCH) · airframe 12,579 hrs · 11,644 cycles

CREW ESCAPE HATCH OUTSIDE HANDLE IS SEIZED AND CORRODED. CREW ESCAPE HATCH HANDLE REPLACED IAW CRJ 200 AMM 52-22-03-400-801 AND HARTWELL CMM 52-22-03. (A)

Part: LONGERON — CORRODED (BS 319-345) · airframe 12,580 hrs · 11,644 cycles

CORROSION EXISTS ON LOWER SILL LONGERON OF PAX DOOR FS 319 TO 345. CORROSION REMOVED ON LOWER SILL LONGERON OF PAX DOOR FS 319 TO 345 IAW SRM 51-21-06.

Part: LENS — ERODED (LT WING) · airframe 12,580 hrs · 11,644 cycles

ERROSION OF THE LT WING TIP POSITION LIGHT LENS. REPLACED LT WINGTIP POSITION LIGHT LENS IAW AMM 57-30-39-400-801 SUPP NR 07-009.

Part: SILL — CORRODED (BS 574-621) · airframe 12,580 hrs · 11,644 cycles

CORROSION EXISTS ON LOWER SILL OF CARGO DOOR FS 574 TO FS 621 LBL 45. CORROSION REMOVED ON LOWER SILL OF CARGO DOOR FS 574 TO FS 621 LBL 45 IAW SRM 51-21-06.

Part: SILL — CORRODED (BS 315-343) · airframe 12,580 hrs · 11,644 cycles

LOWER SILL ON PAX DOOR FS 315 AND 343 LBL 40 IS CORRODED. CORROSION REMOVED ON LOWER SILL OF PAX DOOR FS 315 ANDF FS 343 LBL 40 IAW SRM 51-21-06.

Part: BULKHEAD — CRACKED (BS 202.75) · airframe 12,580 hrs · 11,644 cycles

CRACK EXISTS ON FS 202 AT LBL 23 PRESSURE BULKHEAD AROUND PARKING BRAKE CABLE. REPAIR PERFORMED ON FS 202.75 LBL 23.72 PRESSURE BULKHEAD AROUND PARKING BRAKE IAW REO 601R-53-11-563. (A)

Part: SUPPORT BRACKET — CRACKED (BS 529) · airframe 12,580 hrs · 11,644 cycles

HYD SUPPORT BRACKET CRACK IN RT MLG BAY AT FS 529 AND BTWN RBL 18 TO RBL 27. REPLACED HYD SUPPORT BRACKET IN RT MLG BAY AT FS 529 RBL 18 TO RBL 27 REPLACED IAW SRM 51-42-06 AND 51-23-00.

Part: SILL — CRACKED (BS 574) · airframe 12,580 hrs · 11,644 cycles

CRACK EXISTS ON LOWER SILL OF CARGO DOOR FS 574 LBL 45 UNDER BRACKET. REPAIRED IAW REO 601R-53-61-1741. (A)

Part: SUPPORT BRACKET — CRACKED (BS 523.60) · airframe 12,580 hrs · 11,644 cycles

HYD SUPPORT BRACKET CRACK IN RT MLG BAY AT FS 523 AND BTWN RBL 18 TO RBL 27. REPLACED IAW SRM 51-42-06. (A)

Part: FRAME — CRACKED (BS 280) · airframe 12,580 hrs · 11,644 cycles

CRACK EXISTS ON PILOT BULKHEAD FRAME FS 280 LBL 9. REPAIRED IAW REO 601R-53-11-171 REV D. (A)

Part: STIFFENER — CRACKED (PAX DOOR) · airframe 12,580 hrs · 11,644 cycles

STIFFENER CRACK INSIDE PAX DOOR ON FIXED STAIR AFT PANEL. STIFFENER INSIDE PAX DOOR ON FIXED STAIR AFT PANEL REPLACED IAW SRM 51-42-06. (A)

Part: SUPPORT BRACKET — CRACKED (BS 531.75) · airframe 12,580 hrs · 11,644 cycles

HYD SUPPORT BRACKET CRACK IN LT MLG BAY AT FS 531 AND BTWN LBL 18 - 27. REPLACED IAW SRM 51-42-06. (A)

Part: BULKHEAD — CRACKED (BS 621) · airframe 12,580 hrs · 11,644 cycles

REAR PRESSURE BULKHEAD CRACK AT LINTEL ATTACHMENT POINT. AFT PRESSURE BULKHEAD IN LINTEL FITTING AREA REPAIRED IAW REO 601R-53-61-1230 REV D. (A)

Part: DRAIN LINE — CHAFED (NR 2 HYD SYS) · airframe 11,384 hrs · 10,499 cycles

HYD 2 LOW PRESSURE CAUTION MESSAGE WITH ZERO QUANTITY AND ZERO PRESSURE. COMPLIED WITH QRH. DECLARED EMERGENCY, NORMAL LANDING. SHUT DOWN ENGINE NR 2 AFTER LANDING. TOTAL TIME AT ZERO QUANTITY 23 MINUTES. APU BAY LEAKING FLUID. FOUND NR 2 HYDRAULIC CASE DRAIN LINE P/N 601R75286-51 CHAFED. REMOVED AND REPLACED LINE IAW 29-10. OPS CHECK GOOD. (M)

Part: COALESCER BAG — DIRTY

MEDIUM TO STRONG ODOR OF FUEL NOTICED FLIGHT DECK AND FORWARD CABIN AREA. REMOVED AND REPLACED COALESCER BAGS IAW CRJ AMM 21-51-13, RAN PACKS USING BOTH APU AND ENGINE AIR. NO DEFECTS NOTED. VISUAL INSPECTION FOR LEAKS, NO LEAKS NOTED. (M)

Part: APU — FAILED (APU BAY)

APU FAULT MESSAGE AND FAINT ODOR OF SOMETHING BURNING AT GATE, APU EGT NOTED IN RED. APU WAS SUPPLYING BLEEDS AND ELECTRICS. REMOVED AND REPLACED APU ASSEMBLY. (M)

Part: BRAKE ASSY — BROKEN (MLG)

DURING NR 2 MAIN LANDING GEAR TIRE ASSEMBLY CHANGE, NR 2 BRAKE ASSEMBLY, OUTBOARD ROTOR ASSEMBLY WAS BROKEN IN HALF AT THE TRUNNION CONTACT AREA. BRAKE ASSEMBLY WAS REMOVED AND REPLACED IAW AMM.

Part: SKIN — DENTED (FUSELAGE)

1 DENT TO LEFT FUSELAGE 7.375 INCH AFT OF FS 755 JUST FORWARD OF MID SPAR DATUM VS 43.75. MAINTENANCE REPAIRED PER BOMBARDIER ENGINEERING ORDER 601R-53-9230B. COMPLIANCE WITH FAR 25.571, REQUIRED WITHIN 12 MONTHS. (M)

Part: DRAG ANGLE — CRACKED (PAX DOOR)

FOUND DOOR AFT DRAG ANGLE CRACKED APPROX 1.4 INCH LONG IN AREA OF PULLEY BRACKET. MAINTENANCE REPAIRED PAX DOOR AFT DRAG ANGLE IAW BOMBARDIER REO 601R-52-11-513 REV A. (M)

Part: FLOORBEAM — DAMAGED (BS 280)

INBOARD CLIP AT FS 280, RBL 9, FLOORBEAM IS CRACKED IN RADIUS APPROX .5 INCH. MAINTENANCE REMOVED AND REPLACED FS 280 RBL 9 INBOARD CLIP IAW CRJ 200 SRM 51-42-21, 51-42-13 AND BSC STANDARD REPAIR 601R-53-0057A. (M)

Part: FLOORBEAM — CRACKED (BS 280)

OUTBOARD CLIP AT FS 280, RBL 9, FLOORBEAM IS CRACKED IN RADIUS APPROX .5 INCHES. MAINTENANCE REMOVED & REPLACED FS 280 RBL 9 OUTBOARD CLIP IAW CRJ 20 SRM 51-42-21, 51-42-13, AND BSC STANDARD REPAIR 601R-53-0057A. (M)

Part: INTERCOSTAL — CRACKED (FS 621-625)

RIGHT SIDE FS 621 TO FS 625.3 INTERCOSTAL AT STRINGER 14R IS CRACKED NEAR RADIUS APPROX .8 INCH LONG. MAINTENANCE REMOVED AND REPLACED INTERCOSTAL IAW CRJ200 SRM 52-42-06. (M)

Part: FRAME — CRACKED (BS 640)

RIGHT SIDE FS 640 FRAME DOUBLER IS CRACKED IN RADIUS APPROX .8 INCHES LONG AT WL 119, STRINGER 10R. MAINTENANCE REMOVED CRACKED DOUBLER AREA WAS MODIFIED AND REPAIRED WHILE INCORPORATING SB 601R-53-059 REV F. (M)

Part: FRAME — CRACKED (BS 640)

LEFT SIDE FS 640 FRAME DOUBLER IS CRACKED IN RADIUS APPROX .6 INCH LONG AT WL 119, STRINGER 10L. MAINTENANCE REMOVED CRACKED DOUBLER AREA WAS MODIFIED AND REPAIRED WHILE INCORPORATING SB 601R-53-059 REV F.

Part: ODOR — DETECTED (CABIN)

AT THE GATE, APU FAULT MESSAGE APPEARED, APU AUTO SHUTDOWN OCCURRED. ALSO, BEFORE SHUTSDOWN OCCURRED, COULD DETECT ELECTRICAL BURNING ODOR THROUGHOUT CABIN WITH PACKS ON APU AIR. INSPECTED APU, NO NOTICEABLE BURNS NOTED. REMOVED AND REPLACED APU, S/N P-626, REMOVED OFF MEL. FINDINGS REVEALED THAT PRIMARY FAILURE WAS THE SEPARATION OF THE COMPRESSOR IMPELLER. STARTER CHARRED. (M)

Part: STRINGER — CRACKED (FUSELAGE)

STRINGER 17L IS CRACKED AND BENT JUST ABOVE THE GROUND AIR SUPPLY DOOR. MAINTENANCE REMOVED STRINGER 17L FROM FS 626 TO FS 660, FABRICATED STRINGER AND SPLICE FROM (PN 601R35004-51 AND INSTALLED REPAIR PARTS IAW SRM. (K)

Part: SKIN — DAMAGED (FUSELAGE)

FUSELAGE SKIN AROUND THE GROUND AIR SUPPLY CONNECTION DOOR IS DAMAGED. MAINTENANCE REMOVED DAMAGED SKIN SECTION, FABRICATED FILLERS FROM 2024-T3 .050 INCH, FABRICATED FILLER AND 2 EXTERNAL DOUBLERS FROM 2024-T3 .063 INCH, INSTALLED FILLERS AND NON-FLUSH EXTERNAL REPAIR DOUBLERS IAW BSC EO. (K)

Part: TIRE — DAMAGED (LT MLG)

REQUEST INSPECTION LT MLG TIRE FOR WEAR. AC PASSENGERS AND CARGO WERE UNLOADED, AIRCRAFT DEFUELED. AIRCRAFT WAS TOWED ONT RAMP AREA. WITHOUT INJURY OR DAMAGE TO AIRCRAFT, GEAR SWING AND MLG BAY ACCOMPLISHED AND REMOVAL/REPLACEMENT LT MLG TIRES AS A PRECAUTIONARY MEASURE. (K)

Part: COMPUTER — UNRELIABLE (AHRS) · airframe 3,833 hrs · 3,433 cycles

PITCH AND ROLL ANNUNCIATOR ILLUMINATED ON CAPTS EFIS IN FLIGHT. PITCH UNRELIABLE, MORE THAN 6 DEGREES THAN F/O EFIS ATTITUDE. PITCH ILLUMINATED ON GROUND DEPOWERED AND REPOWERED. TAXI TEST OK. PROBLEM REOCCURRED IN FLIGHT. REMOVED AND REPLACED NR 1 AHRS COMPUTER IAW 34-21-01, OPS CHECK GOOD.

Part: AHRS — INOPERATIVE (COCKPIT)

AFTER SWITCHING ATT/HDG FROM NORM TO (2) AT 31000, BOTH CAPT AND F/O AHRS WENT BLANK. A/P KICKED OFF AND YAW NR 2 DISENGAGED SWITCHED TO NORM AND CAPT AHRS CAME BACK. THEN 5 SECS LATER F/O AHRS CAME BACK. REENGAGED A/P AND YAW DAMP, TO FURTHER PROBLEM. REMOVED AND REPLACED AHRS NR2 COMPUTER IAW 34-21-01, OPS CHECK GOOD.

Part: BUSHING — MIGRATED (RT MLG TRUNNION)

RT MAIN LANDING GEAR AFT TRUNNION BUSHING IS MIGRATED .041. REMOVED ORIGINAL BUSHING IAW MM 20-26-00-910-802, REAMED WING TRUNNION IAW REO 601R-57-21-003B, INSTALLED NEW 1ST OVERSIZED BUSHING IAW REO 601R-57-21-003B AND REAMED INNER DIAMETER IAW DRG 601R85007.

Part: INTERCOSTAL — CRACKED (FUSELAGE)

FS 621-FS 625.3 INTERCOSTAL, RT SIDE STR 14R, IS CRACKED NEAR RADIUS APPROX 1.0 INCH LONG. REMOVED CRACKED INTERCOSTAL AND INSTALLED NEW INTERCOSTAL PN 601R35012-52, IAW SRM 51-42-06.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 3,804 hrs · 3,408 cycles

FS 621- FS 625-3 INTERCOSTAL, RT SIDE STR 14R, IS CRACKED NEAR RADIUS APPROX 1.0 INCH LONG. REMOVED CRACKED INTERCOSTAL AND INSTALLED NEW INTERCOSTAL (PN601R35012-52), IAW SRM 51-42-06.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 3,804 hrs · 3,408 cycles

FS 621-FS 625.3 INTERCOSTAL, LT SIDE, AT STR 14R IS CRACKED NEAR RADIUS, APPROX .75 INCH LONG. REMOVED CRACKED INTERCOSTAL AND INSTALLED NEW INTERCOSTAL, PN 601-35012-51, IAW SRM 51-42-06.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT)

ABORTED TAKEOFF DUE TO AILERON MISCONFIGURATION WARNING MESSAGE ABOVE 80 KNOTS. BTMS READINGS 03, 03, 04, 06 REPORTED WEIGHT 52,000 LBS. COMPLIED WITH SPECIAL INSPECTION PROCEDURE IAW 5-51-27, ABORTED TAKEOFF. REMOVED AND REPLACED NR 3 AND NR 4 MLG TIRES. OPS CHECKED ANTI-SKID, PROX SENSOR, FLT CONTROLS, BRAKES, TRIM SYSTEM. OPS CHECK GOOD. INTERROGATED MDC, NO FAULTS. AIRCRAFT RETURN TO SERVICE. (M)