N418QX

Part: CONTROLLER — FAILED (ANTI ICE) · airframe 24,346 hrs · 26,020 cycles

LEVEL AT FL 250 "WSHLD CTRL" CAUTION ILLUMINATED. COMPLIED WITH EMERGENCY CHECKLIST.RETURNED TO FIELD. LANDING UNEVENTFUL. FOUND FAULTS R&L WSHLD CTRL FAIL IN CDS. CLEARED FAULTS AND PERFORMED OPS TEST OF THE WINDSHIELD AND PILOT SIDE WINDOW IAW AMM 30-41-00-710-801 AND 30-41-00-710-802 AND FOUND PILOT SIDE WINDOW NOT HEATING UP. R & R THE NR 2 ANTIC-ICE CONTROLLER IAW AMM 30-41-000-801/400-801. ALL TEST GOOD. NO CAUTION LIGHT AND FAULTS DID NOT RETURN. RETURNED TO SERVICE.

Part: TRANSDUCER — MALFUNCTIONED (BRAKE SYS) · airframe 24,296 hrs · 25,967 cycles

DURING LANDING ROLLOUT AND BRAKE APPLICATION LEFT BRAKE FELT UNRESPONSIVE AS MORE PRESSURE WAS APPLIED THE ANTI-SKID ENGAGED RELAXED BRAKE PRESSURE TO DISENGAGE ANTI-SKID AND MISSED NORMAL RUNWAY EXIT. FOUND #1 AND #2 WHEEL SPEED TRANSDUCERS WORN, REPLACED #1 AND #2 W.S.T. IAW 32-46-11-000-801 & 32-46-11-400-801 FUNCTIONAL TEST GOOD. RETURNED TO SERVICE.

Part: GENERATOR — MALFUNCTIONED (WHEEL SPEED) · airframe 24,293 hrs · 25,962 cycles

BRAKING ACTION IS POOR AFTER LANDING. INNER WHEEL ASSEMBLY ON BOTH SIDES ARE COLD, WHILE THE OUTER WHEELS ARE HOT. FOUND NO FAULT CODES IN CDS. FAOUND FAULT CODE RH INBD WST IN HISTORY. REPLACED THE RH INBOARD WHEEL SPEED GENERATOR IAW AMM 32-46-11-00-801 AND 400-801. TAXI CHECK OF AIRCRAFT OK, BRAKES FUNCTION NORMALLY. RETURNED TO SERVICE.

Part: ECU — MALFUNCTIONED (ZONE 100) · airframe 23,895 hrs · 25,551 cycles

ON DEPARTURE OUT OF SEA WE GOT A PITCH TRIM CAUTION LIGHT. 2X-INTERROGATED CDS FOUND FAULT CODES 6E,6D,EE,ED,E7,E3,67,74,75,76,77,78 AND 79. PER MOM REQUEST REPLACEMENT OF THE FCECU REQUIRED. R&R FCECU IAW AMM 27-00-01-000-802,400-802. OPS TEST REF TSK 27-00-01-710-802 AND 27-00-01-720-801. NO FAULTS NOTED IN CDS OPS TEST NORMAL. A/C OK FOR CONT SERVICE.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 24,018 hrs · 25,681 cycles

AFT LEFT EMERGENCY EGRESS LIGHT INOPERATIVE. REPLACED THE LAMPS IAW AMM 33-51-11-000-801 AND 33-51-11-400-801. CHECKED GOOD.

Part: SEAL — FAILED (NR 1 PROPELLER) · airframe 23,794 hrs · 25,441 cycles

NR 1 ENGINE TOOK 1.5 MINUTES TO COME OUT OF FEATHER AFTER ENGINE START. REPLACED THE NR 1 ENGINE PROPELLER DOME SEALS. RETURNED TO SERVICE.

Part: COUPLING — LOOSE (LT WING) · airframe 23,247 hrs · 24,857 cycles

AT CRUISE FLIGHT OF 23,000, THE NR 1 ENGINE FUEL PRESSURE CAUTION FLASHED ON AND OFF ABOUT 12 TIMES. DID NOT SELECT THE NR 1 AUXILIARY PUMP ON, DUE TO THE CAUTION FLASHING ON FOR LESS THAN 1-2 SECONDS EACH TIME. DIVERTED AND ACCOMPLISHED UNEVENTFUL LANDING. FOUND NR 1 ENGINE CHANNEL A AND CHANNEL B FAULT 911, LOW FUEL PRESSURE. REPLACED NR 1 ENGINE FUEL FEED LINE COUPLING. FOUND CLAMSHELL FELL OFF AND OTBD O-RING CUT 25 PERCENT. ACCELERATION CHECK IAW AMM 71-00-00-868-807. RETURNED TO SERVICE.

Part: BRAKE — OVERHEATED (MLG) · airframe 22,715 hrs · 24,298 cycles

AFTER LANDING DURING POST FLIGHT INSPECTION FOUND THE LT OTBD MAIN WHEEL SMOKING. EXCESSIVE BRAKING WAS NOT USED. PERFORMED INSPECTION AND FOUND SIGNS OF OVERHEATING ON THE BRAKE. REPLACED THE TIRE AND THE BRAKE AND PERFORMED EXCESSIVE BRAKING INSPECTION IAW AMM 05-50-56-210-801. RETURNED TO SERVICE.

Part: AUTOFEATHER SYS — MALFUNCTIONED (NR 1) · airframe 22,102 hrs · 23,623 cycles

NR 1 ENGINE FAILS DAILY AUTOFEATHER CHECK. CYCLED ACFT POWER OFF/ON. PERFORMED A/F TEST. NR 1, AND 2 A/F TEST SHOWED PASSED. NO FURTHER DEFECTS NOTED.

Part: BATTERY PACK — MALFUNCTIONED (EMERGENCY LIGHTS) · airframe 22,067 hrs · 23,604 cycles

EMERGENCY LIGHTS COME ON WHEN SWITCH IN ARM POSITION. REPLACED BATTERIES IN POSITIONS 1-4. RETURNED TO SERVICE.

Part: SEAT TRACK — CORRODED (BS 967-728) · airframe 21,398 hrs · 22,872 cycles

REPLACE SEAT TRACK FROM BS 697.6 - 728.102 AT Y-29.320. REMOVED SEAT TRACK, NR 4, PN:85337843-103, REF SRM 51-42-05 AND 51-42-45. INSTALLED NEW SEAT TRACK NR 4, PN:85337843-103, REF SRM 51-42-05 AND 51-42-45, PO:TX-3661. LOCATED, DRILLED AND COUNTERSUNK SEAT TRACK, NEW, NR 4, PN:85337843-103, REF SRM 51-40-07. RESTORED FINISH IAW DWG 85338806, SHT 1. APPLIED AV-DEC TO SEAT TRACK NR 4 INNER CLAW AREA IAW SRM 51-21-10, REPAIR -04, PG 6A THRU 6G.

Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 21,398 hrs · 22,872 cycles

SEAT TRACK NR 16 CORRODED. REMOVED SEAT TRACK NR 16 S/W 85338210-119 IAW SRM 51-40-07. RECEIVED NEW SEAT TRACK NR 16, PN:85328710-119, PO:T-21571 LOCATED AND DRILL HOLES COMMON TO VERTICAL WEB FROM FS X670.0 TO FS X728.102 IAW SRM 51-40-07, REPAIR 01 PARA 5B SECTION NR 6 FOR CONTINUED LOCATING AND DRILLING OF SEAT TRACK NR 16. REMOVED APU BONDING BRACKET IAW SRM 51-40-07, TERMINAL DOUBLE. INSTALLED APU BONDING BRACKET IAW SRM 51-42-05. REMOVED CENTER TRACK FOR ACCESS FS 697.6 TO 767.6 IAW SRM 51-40-07. INSTALLED CENTER SEAT TRACK IAW SRM 51-42-05. PERFORMED BONDING CHECK ON BRACKET TO SEAT TRACK REF AMM 51-80-00-760-830, STEPS 1-4 AND 4.1. BONDING CHECK GOOD. REMOVED SEAT TRACK FROM SUPPORT ON SEAT TRACK NR 15, FS: 783.102. INSTALLED SEAT TRACK SUPPORT AT FS 783.102 IAW SRM 51-42-05. LOCATED, DRILLED AND DEBURRED COMPLETE SEAT TRACK NR 16, NEW PN:85338210-119, REF SRM 51-40-07-02-01. INSTALLED SPLICE COMMON TO SEAT TRACK NR 15 AND SEAT TRACK NR 16 REF SRM 51-40-15-02-01, STEP 6H2 AND SRM 51-42-05-02-01, STEP 4.D, 3-10. INSTALLED BOLTS 6EA ON NEW SEAT TRACK NR 16 AT BS X683.150, X697.600 AND X714.602 REF SWG 85330201, REV C. SEAT TRACK NR 16, PN:85338210-119 INSTALLED REF DWG 85336201, REV E. REMOVED SEAT TRACK NR 16 GROUNDING CABLE FROM TERMINAL DOUBLER, REF AMM 24-31-51-000-801. INSTALLED 16 SEAT TRACK GROUND CABLE TO TERMINAL DOUBLER IAW AMM 24-31-51-400-801.

Part: CHANNEL — CORRODED (PAX DOOR) · airframe 21,398 hrs · 22,872 cycles

FORWARD PAX DOOR LWR CHANNEL ASSY HAS CORROSION. REMOVED CHANNEL ASSY PN 85329540-001, REF SRM 51-42-05-02-01. J. INSTALLED THRESHOLD CHANNEL ASSY, PN:85329540-001, REF SRM 51-42-05, NEW THRESHOLD CHANNEL. RECEIVED NEW FWD PAX DOOR LWR CHANNEL ASSY PN:85329540-001. REPLACEMENT OF FWD PAX DOOR THRESHOLD CHANNEL REQUIRED IF ANY EVIDENCE OF CORROSION IS FOUND, REF TASK CARD 6-53-1160-FWD PAX DR, WO:190607, ITEM 5. LOCATED AND DRILLED NEW THRESHOLD CHANNEL FOR FASTENER HOLES, REF SRM 51-40-07.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

REPLACE SEAT TRACK NR 14, PN: 85338210-113. REMOVED SPLICE COMMON TO SEAT TRACK, NR 13 & 14, PN 85338215-101 AND 85338216-101. INSTALLED SPLICE COMMON TO SEAT TRACK NR 13 AND NR 14, REF SRM 51-42-05, SRM 51-40-15, AND DWG NR 85338201, REV-C. REMOVED SPLICE COMMON TO SEAT TRACK NR 14 AND 15, PN 85338210-113 AND PN 85338210-115, REF SRM 51-40-15, SRM 51-41-00, SRM 51-42-05. INSTALLED SPLICE COMMON TO SEAT TRACK NR 14 AND 15, REF SRM 51-42-05, SRM 51-40-15 AND DWG NR 85338201, REV-C. REMOVED SEAT TRACK NR 14, PN 85338210-113, REF SRM 51-40-15, REPAIR-01, SRM 51-41-00, SRM 51-42-05, REPAIR-01. INSTALLED SEAT TRACK NR 14, PN 85338201-113, REF SRM 51-42-05, SRM 51-40-15, SRM 51-41-00 AND DWG, NR 85338201, REV-C. LOCATED AND DRILLED NEW SEAT TRACK, PN 85338210-113, REF DWG 85338201, REV-E.

Part: SPLICE — CORRODED (ZONE 100) · airframe 21,398 hrs · 22,872 cycles

SPLICE ANGLE CORRODED AT STA X102.5 BETWEEN SEAT TRACK NR 11, AND SEAT TRACK NR 12, PN 85338210-112 TO BE REPLACED WITH SPLICE ANGLE'S, PN 85338216-101 AND PN 85338215-101. LOCATED AND DRILLED SPLICES ANGLES, PN 85338216-101 AND 85338215-101 TO SEAT TRACK NR 11, REF Q400, DWG 85328201. LOCATED AND DRILLED SPLICE ON SEAT TRACK NR 12 REF SRM 51-40-07-02-01.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

SEAT TRACK NR 13 CORRODED. REMOVED SPLICE AND SEAT TRACK NR 13 AND INSTALLED NEW TRACK IAW SRM 51-40-00.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

NR 11 SEAT TRACK CORRODED. INSTALLED SEAT TRACK IAW SRM 51-42-05-02-01 AND SRM 51-40-15-02-01.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

REPLACE SEAT TRACK NR 15, PN: 85338210-115. REMOVED SPLICE COMMON TO SEAT TRACKS NR 14 AND 15 PN 85338210-113 AND PN 85338210-115, REF SRM 51-40-15, SRM 51-41-00, SRM 51-42-05. INSTALLED SPLICE COMMON TO SEAT TRACKS NR 14 AND NR 15, REF SRM 51-42-05, SRM 51-40-15 AND DWG NR 85338201, REV-C. REMOVED SPLICE COMMON TO SEAT TRACKS NR 15 AND NR 16 REF SRM 51-40-15, SRM 51-41-00, SRM 51-42-05. SPLICE COMMON TO SEAT TRACK NR 15 AND NR 16 INSTALLED ON JOB 5414331, OP 230. REMOVED SEAT TRACK NR 15, PN 85338210-115, REF SRM 51-40-15 REPAIR-01, SRM 51-41-00, SRM 51-42-05, REPAIR-01. INSTALLED SEAT TRACK NR 15, PN 85338210-115, REF SRM 51-40-15, SRM 51-41-00, ARM 51-42-05 AND DWG NR 85338201, REV-C. LOCATED AND DRILLED NEW SEAT TRACK, PN 85338210-115, REF DWG 85338201, REV-E.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

REPLACE SEAT TRACK NR 7, CORRODED. REMOVED DRIP TRAY FROM LT SIDE FROM FS X 71.00 TO FS X 388.000, REF SRM 51-41-00-00-01. INSTALLED DRIP TRAY FROM FS X 71.200 TP FS X 388.000 REF SRM 51-41-00-00-01. REMOVED 2 EA DRIP ANGLES FROM LT SIDE FROM FS X 116.000 TO FS X 301.000, REF SR, 51-42-05-02-01. INSTALLED 2 EA DRIP ANGLES FROM FS X 116.000 TP FS X 301.000 REF SRM 51-42-05-02-01. REMOVED 6EA FRAME DRIP TRAYS FROM FS 71.00, 116.000, 176.000234.475, 321.000. 361.000. REF SRM 51-41-00-00-01. INSTALLED 6EA FRAME DRIP TRAYS FROM FS 71.200, 116.00, 234.475, 321.000, 361.000, REF SRM 51-41-00-00-01. DISPLACED 5 EA WIRE BUNDLES AND 2 EA GROUND WIRES 2421-GS12 AND 2421-GS13. REINSTALLED 5EA WIRE BUNDLES WITH WIRE TIES AND INSTALLED 3EA GROUND WIRES 2421-GS12 AND 2421-GS13. REMOVED FWD SEAT TRACK SPLICE COMMON TO SEAT TRACK NR 6 AND NR 7 REF SR, 51-42-05-02-01 AND SR 1-40-15-02-01. INSTALLED SEAT TRACK SPLICE COMMON TO NR 6 AND NR 7 REF SRM 51-42-00-01 AND SRM 51-40-15-00-01. REMOVED SEAT TRACK NR 7, PN 85361510-103, REF SRM 51-42-05-02-01 AND SRM 51-41-00-00-01. BOLTS INSTALLED ON NEW SEAT TRACK INSTALLATION, PN 85361510-103, REF DWG 85361501, REV E. NEW SEAT TRACK NR 7, PN 85361510-103, LOCATED AND DRILLED REF SRM 51-40-07, DWG 85361501 REV E. HOLES DEBURRED AND HOLES COUNTERSINK COMMON TO SPLICE REF SRM 51-42-05 DWG 85361501, REV E. DRIP ANGLE LOCATED AND DRILLED REF SRM 51-40-07, DWG 85307401, REV C. HOLES COMMON TO DRIP ANGLE COUNTERSINK REF SRM 51-42-05, DWG 85307401, REV C. INSTALLED SEAT TRACK NR 7, PN 85361510-103, REF SRM 51-42-05-00-02 AND SRM 51-4100-01.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

SEAT TRACK NR 8 CORRODED. REMOVED FWD SEAT TRACK SPLICE COMMON TO SEAT TRACK NR 7 AND NR 8 REF SRM 51-42-05-02-01 AND SRM 51-40-15-02-01. SEAT TRACK SPLICE INSTALLED REF DWG 85307071, REV A 98/10/06 COMMON TO SEAT TRACK NR 7 & NR 8. REMOVED SEAT TRACK NR 8 IAW SRM 51-40-07. INSTALLED SEAT TRACK NR 8, REF SRM 51-41-05 AND 51-42-05. REMOVED SEAT TRACK SPLICE COMMON TO SEAT TRACK 8 AND 9, REF SRM 51-42-05. SEAT TRACK SPLICE COMMON AND SEAT TRACK NR 8 AND NR 9 REF DWG 85307071, REV 1, INSTALLED. LOCATED AND DRILLED SEAT TRACK NR 8 IAW SRM 51-40-07 AND DWG 85338201.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

SEAT TRACK NR 9 CORRODED. REMOVED SEAT TRACK NR 9, PN 85338210.000 IAW SRM 51-40-07. INSTALLED 25 PERCENT OF FASTENERS ON SEAT TRACK NR 9 REF DWG 85338201 REV-1E AND SRM 51-42-05-02-01, STEP 4D (3-10). LOCATED AND DRILLED SEAT TRACK NR 9, PN 85338210-111 IAW SRM 51-40-02 AND DWG 85338201 LOWER FLANGE. LOCATED AND DRILLED SEAT TRACK NR 9 TOP LANGE COMMON TO SHEAR WEB BETWEEN FS X 698.000 AND X 789.102 IAW SRM 51-40-07. LOCATED AND DRILLED SEAT TRACK SPLICE COMMON TO SEAT TRACK NR 8 AND NR 9 REF SRM 51-40-07-02-01. INSTALLED FASTNERS IN NR 9 SEAT TRACK FROM BS X 683.450 TO BS 776.102-01 SRM. INSTALLED 7 FASTENERS IN AFT FITTING A7 BS X 783-102 ON SEAT TRACK NR 9 REF 51-42-05.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

SEAT TRACK NR 12 CORRODED. DISPLACED ANVC ACCELERMETER AT BS X 223.00 REF AMM 23-35-01-000-801. INSTALLED ANVC ACCELERMETER AT BS X 223.0, REF AMM 23-35-01-400-801. DISPLACED 3EA WIRE BUNDLES BETWEEN BS X 94.8 TPSTAF X 116.0, 2EA BETWEEN BS X 136.0 TO X BS 156.0, 2EA BETWEEN BS X 156.0 TP, BS X 176.0. 7 EA WIRE BUNDLES REATTACHED, REF WM 20-12-10. REMOVED DRIP TRAY FROM BS X 49.5 TO BS X 301.0 REF SRM 51-41-00-01. DRIP TRAY INSTALLED REF DWG 82570100, REV "E". REMOVED DRIP ANGLE FROM BS X 176.0 TO BS X 281.0 REF SRM 51-42-05-00-01. COMPLETED INSTALLATION OF DRIP ANGLE, REF SRM 51-42-05, DWG 85307401, REV "C" COMMON TO NR 12 AND NR 13. REMOVED NR 12 SEAT TRACK, PN 85338210-112, REF SRM 51-41-00-00-01. LOCATED AND DRILLED NEW SEAT TRACK NR 12, P/N 85338210-112, REF SRM 51-40-07-02-01.

Part: SEAT TRACK — NOT REPORTED (NOT REPORTED) · airframe 21,398 hrs · 22,872 cycles

NR 10 SEAT TRACK. INSTALLED SEAT TRACK IAW SRM 51-42-05 AND SRM 51-40-15.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 21,398 hrs · 22,872 cycles

ANGLE AT FS X6.70, STR 25P REQUIRES REPLACEMENT DUE TO EXFOILIATION CORROSION ANGLE COMMON TO MACHINED INTERCOSTAL. RECEIVED NEW ANGLE, PN 85329576-103. REMOVED CORRODED ANGLE PN 85329576-103 FROM MACHINED INTERCOSTAL COMMON TO MACHINED WEB AT X6.70, STR 25P REF SRM 51-42-05. INSTALLED NEW ANGLE, PN 85329576-103 ON MACHINED INTERCOSTAL COMMON TO MACHINED WEB AT X6.70 STR 25P, REF SRM 51-42-05. LOCATED AND DRILLED NEW ANGLE, PN 85329576-103 FOR FASTENER HOLES REF SRM 51-40-07. COMPLIED WITH FORM M-184 CORROSION REPORT.

Part: ANGLE — CORRODED (ZONE 200) · airframe 21,398 hrs · 22,872 cycles

ANGLE AT FS X26.0, STR 25P CORRODED. ANGLE REMOVED AND REPLACED IAW SRM 51-40-07.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 21,398 hrs · 22,782 cycles

ANGLE, COMMON TO MACHINED WEB, RIB AT FS X 26.70 BETWEEN STR 25P AND LOWER PAX DOOR THRESHOLD HAS CORROSION AND REQUIRES REPLACEMENT IAW T/C 6-53-1160-FWD PAX DOOR. RECEIVED NEW ANGLE, PN 85329542-116. REMOVED CORRODED ANGLE FROM PARTIAL WEB AT X19.50 COMMON TO FUSELAGE SKIN UNDER MCD. REF SRM 51-42-05. INSTALLED NEW ANGLE, PN 85329542-116 ON MACHINED WEB AT X 26.70 , REF SRM 51-42-05, MOVED LOWER SURROUND. LOCATED AND DRILLED NEW ANGLE FOR FASTENER HOLES, REF SRM 51-40-07, ANGLE, PN 85329542. COMPLIED WITH FORM M-184, CORROSION REPORT.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 21,398 hrs · 22,872 cycles

ANGLE COMMON TO MACHINED WEB, RIB AT FS X6.70 BETWEEN STR 25P AND LWR PAX DOOR THRESHOLD HAS CORROSION AND REQUIRES REPLACMENT TC:6-53-1160-FWD PAX DOOR. RECEIVED NEW ANGLE, PN 85329542-115. REMOVED CORRODED ANGLE FROM MACHINED WEB AT X6.70 COMMON TO FUSELAGE SKIN UNDER MCD, REF SRM 51-42-05. INSTALLED NEW ANGLE PN 85329542-115 ON MACHINED WEB AT X6.70 , REF SRM 51-42-05, MVD LOWER SURROUND. LOCATED AND DRILLED NEW ANGLE, PN 85329542-115 FOR FASTENER HOLES, REF SRM 51-40-07. COMPLIED WITH FORM M-184 CORROSION REPORT.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 21,398 hrs · 22,872 cycles

ANGLE, COMMON TO PARTIAL WEB, RIB, AT FS X19.50 BETWEEN STR 25P AND LWR PAX DOOR THRESHOLD HAS CORROSION AND REQUIRES REPLACMENT TC:6-53-1160-FWD PAX DOOR. RECEIVED NEW ANGLE, PN 85329573-101. REMOVED CORRODED ANGLE FROM PARTIAL WEB AT X19.50 COMMON TO FUSELAGE SKIN UNDER MCD REF SRM 51-42-05. INSTALLED NEW ANGLE, PN 85329573-101 ON PARTIAL WEB AT X19.50, REF SRM 51-42-05, MOVED LOWER SURROUND. LOCATED AND DRILLED NEW ANGLE, PN 85329573-101 FOR FASTENER HOLES, REF SRM 51-40-07. COMPLIED WITH FORM M-184 CORROSION REPORT.

Part: STRINGER — CORRODED · airframe 21,398 hrs · 22,872 cycles

STRINGER 25P CORRODED, FWD PAX DOOR UNDERFLOOR. PERFORMED CUTOUT OF LOWER MAIN SILL, STR 25P FROM FS X1.00 TO FS X32.40, REF TC 6-53-1160-FWD PAX DR ITEM 17. C/W ET INSP ON STR 25P CUT LINES REF NDTM PT1 51-00-06. NO DEFECTS NOTED. FABRICATED NEW LOWER MAIN SILL SECTION, STR 25P FOR MCD LOWER SURROUND IAW SRM 53-20-17, REPAIR-2, FIG 201, SHEET 2 AND LOCATED AND DRILLED FASTENER HOLES IAW SRM 51-40-017. USED STR 85329349-101 PO 1788. FABRICATED 4-OFF EXTERNAL REPAIR DOUBLERS OUT OF 2024T-3 .063 PO T00020092 AND DRILLED FASTENER HOLES ON DOUBLERS AND SKIN REF SRM 53-20-17, REPAIR-02 PROCEDURE 7F AND G AND FIG 201, SHEET 3 AND 4. REPAIRED THE EXISTING FASTENER COUNTERSINKS REMAINING IN THE SKIN UNDERNEATH THE EXTERNAL REPAIR DOUBLERS, MCD LOWER SURROUND, REF SRM 51-18-00 STRUCTURE IDENT-08. INSTALLED 4-OFF EXTERNAL REPAIR DOUBLERS IAW SRM 53-20-17 REPAIR-02, FIG 201. INSTALLED NEW LOWER MAIN SILL SECTION STR 25P BETWEEN X1.00 AND X32.40 REF SRM 53-20-17, REPAIR-02, FIG 201 AND DWG 85329330 RELEASE P, REV-A.

Part: CIRCUIT BREAKER — TRIPPED · airframe 20,496 hrs · 21,854 cycles

WRB BAGGAGE CB POPPED, LESS K-2. DIVERTED AND ACCOMPLISHED A UNEVENTFUL LANDING. CHECKED FWD AND AFT CARGO LT OPS ALL CHECKS GOOD C/W CB RESET PROCEDURE IAW GPM REF 9.2.2.1 CB REMAINED CLOSED ALL LAMPS REMAINED ILLUMINATED. NO HISTORY RECORDED LAST 60 DAYS. OK FOR CONTINUED SERVICE.

Part: STRUT — FAILED (PAX DOOR) · airframe 19,919 hrs · 21,224 cycles

MAIN CABIN DOOR DIFFICULT TO OPEN AND CLOSE. REPLACED GAS SPRING STRUTS IAW AMM 52-11-16-400-802. CHECKS GOOD RETURNED TO SERVICE.

Part: SWITCH — MISSING (EMERGENCY LIGHTS) · airframe 19,494 hrs · 20,754 cycles

F/A EMERGENCY LIGHT SWITCH MISSING. REPLACED SWITCH. RETURNED TO SERVICE.

Part: DOOR — LACK OF LUBE (MAIN PAX) · airframe 19,225 hrs · 20,460 cycles

MAIN CABIN DOOR DIFFICULT FOR THE F/A TO OPEN. LUBED THE DOOR IAW AMM 52-11-00-640-801. OPS TESTS GOOD IAW AMM 52-11-00-710-801. RETURNED TO SERVICE.

Part: LIGHT — ODOR (CARGO BAY) · airframe 19,010 hrs · 20,229 cycles

GROUND CREW REPORTED STRONG SULPHUR ODOR IN AFT CARGO BAY. FOUND TO BE COMING FROM AFT CARGO LIGHT. R & R LIGHT IAW AMM TASK 33-31-01-000-801, & 33-31-01-400-801. OPS CHECKED GOOD.

Part: SWITCH — FAILED (EMERGENCY LIGHTS) · airframe 17,868 hrs · 18,966 cycles

EMERGENCY LIGHT SWITCH INOPERATIVE. REPLACED SWITCH IAW AMM 33-51-05-00-800/400-801, OPS CHECKED GOOD. RETURNED TO SERVICE.

Part: LATCH — BROKEN (ZONE 200) · airframe 17,555 hrs · 18,650 cycles

COMPARTMENT DOOR UNDER LT F/A JUMPSEAT DOES NOT SPRING CLOSED. R & R LT AFT FA'S JUMPSEAT COMPARTMENT DOOR HINGE SPRINGS AS REQUIRED, COMPARTMENT DOOR OP CK'S GOOD. RETURNED TO SERVICE.

Part: ANTENNA — MALFUNCTIONED (VOR) · airframe 17,242 hrs · 18,320 cycles

ERRATIC INDICATIONS ON BOTH PFDS DURING APPROACH. FLIGHT GUIDANCE INDICATED A RT TURN WHEN LOC NEEDLE WAS MOVING LT. LOC NEEDLE WAS SELDOM STEADY AND CONSTANTLY MIGRATING AROUND. HGS DISPLAY WAS VERY ERRATIC. 2 APPROACHES WERE CONDUCTED. GOOD IDENTS ON BOTH LOCS. NO PLDS IN OPERATION. R & R NR 1 AND NR 2 VOR/LOC ANTENNAS IAW MAINTENANCE 6345102. OPS CHECK GOOD. CW MAINTENCE 6343510, OPS CHECK GOOD. LLM RTS AND CAT 3 STATUS CONFIRMED IAW MAINENEANCE 6345102 AND 6343510. RETURNED TO SERVICE.

Part: LATCH — BROKEN (STOWAGE BOX) · airframe 17,230 hrs · 18,308 cycles

STORAGE COMPARTMENT UNDER FORWARD F/A SEAT DOES NOT LATCH FULLY. REPLACED LATCH. RETURNED TO SERVICE.

Part: LENS — BROKEN (EMERGENCY LIGHT) · airframe 16,519 hrs · 17,539 cycles

EMEMERGENCY LIGHT COVER BROKEN AT FWD RT EMERGENCY EXIT. REMOVED FWD EMERGENCY EXIT REF AMM TASK 52-22-00-000-801. R & R SIGN ASSY REINSTALLED FWD EMERGENCY EXIT REF AMM TASK 52-22-000-400-801 AND MCN 65257701. OPS CHECKED GOOD. NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: INSERT — FAILED (PAX DOOR HANDLE) · airframe 16,299 hrs · 17,307 cycles

UNABLE TO OPEN MAIN CABIN DOOR, WHEN THE DAMPER OPERATED THE DOOR FROM OUTSIDE, A SCREW AT THE DOOR HANDLE CAME OFF. REPLACED INSERT ON FWD MCD RAIL AT 'BREAK-OVER' POINT. NO FURTHER DEFECTS. DOOR OPERATES NORMALLY. RETURNED TO SERVICE.

Part: WARNING HORN — ACTIVATED · airframe 16,126 hrs · 17,124 cycles

ADVANCED POWER LEVER FOR TAKE OFF RECEIVED A WARNING HORN AND OBSERVED INBD AND OTBD SPOILERS DID NOT RETRACT. ABORTED TAKEOFF AND RETURNED TO GATE. INTERROGATED CDS, FOUND NO FAULT CODES. PERFORMED OPS TEST OF THE ROLL SPOILER SYS IAW AMM TASK 27-61-00-710-801. OPS CHECKED GOOD. ALSO PERFORMED OPS CHECK OF THE TAKEOFF WARNING SYS. IAW AMM TASK 31-41-00-710-802 OPS CHECKS GOOD, INBD & OTBD SPOILERS RETRACTED NORMAL, WITH NO TAKEOFF WARNING HORN. NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: GUARD — BROKEN (LIGHT SWITCH) · airframe 15,841 hrs · 16,800 cycles

SWITCH COVER ON F/A EMERGENCY LIGHT FELL OFF FOWARD F/A POSITION. REPLACED SWITCH COVER FOR FORWARD F/A EMERGENCY LIGHT SWITCH. OPS CHECK GOOD. RETURNED TO SERVICE.

Part: PANEL — CORRODED · airframe 15,652 hrs · 16,606 cycles

PANEL 144HZ HAS CORROSION AROUND SCREW HOLES. CHEMICALLY REMOVED PAINT FROM AFFECTED AREA IAW SRM 51-26-10-02-01. FOUND CORROSION TO BE OUT OF LIMITS. RECEIVED NEW PANEL 144HZ, STEPPED UP AND COUNTER SUNK SCREW HOLES IAW SRM 51-40-07-02-01. TREATED SCREW HOLES IAW SRM 51-25-16-390-801.

Part: PANEL — CORRODED · airframe 15,652 hrs · 16,606 cycles

PANEL 144JZ HAS MULTIPLE SPOTS OF CORROSION. REMOVED PAINT IAW SRM 51-26-10-02-01. FOUND CORROSION OUT OF LIMITS. STEPPED UP AND COUNTER SUNK SCREW HOLES IAW SRM 51-40-07-02-01. TREATED IAW AMM 51-25-16-390-801.

Part: ANGLE — CORRODED (BS 783) · airframe 15,652 hrs · 16,606 cycles

FOUND CORROSION IN AFT CARGO ON LT SIDE AT STA 783.102. REMOVED CORRODED ANGLE IAW SRM 51-42-05-02-01 AND 51-42-45-02-01. LOCATED AND DRILLED NEW ANGLE IAW SRM 51-40-07-02-01. COUNTERSUNK HOLES ON SHEAR WEB AS REQUIRED. INSTALLED SHEAR WEB ANGLE IAW RD 8/4-53-4027. ALL COUNTERSINKING DONE IAW SRM 51-42-05-02-01 AND SRM 51-42-45-02-01. INSTALLED ANGLE PN 85339286-115 IAW SRM 51-42-05-00-01 AND 51-42-05-02-01. ALL WORK DONE IAW TC RD 8/4-53-4027.

Part: HINGE — CHAFED (CARGO DOOR) · airframe 15,652 hrs · 16,606 cycles

CHAFING DAMAGE ON AFT CARGO DOOR FWD OF AFT HINGE. REMOVED HINGE FOM. BLENDED AREA TO CONTOUR USING SCOTCH BRITE PADS. BLENDED AREA MEASURES .17" L .06" W AND .008" D. SENT TO ENGINEERING. BLENDED AREA FOUND TO BE WITH IN ACCEPTABLE LIMITS IAW RD 8/4-52-940. PERFORMED NDT INSPECTION OF THE AFT CARGO DOOR IAW NDT MANUAL PT 1 51-00-06-910-801 AND PT 6 51-00-01-250-801 EDDY CURRENT METHOD, NO DEFECTS NOTED. TREATED, PRIMED AND REINSTALLED HARDWARE IAW TC RD 8/4-52-940. ALL WORK PERFORMED IAW TC RD 8/4-52-940.

Part: SWITCH — UNSECURE (EMERGENCY LIGHTS) · airframe 23,701 hrs · 24,184 cycles

EMERGENCY LIGHT SWITCH ON F/A FWD BULKHEAD IS PULLED OUT OF BULKHEAD. INSPECTED LIGHT SWITCH AND FOUND RTV SEALANT AT BASE TO BE MISSING. RE-APPLIED IAW AMM TASK 33-51-05-400-801 STEPS 1-3, 4A4-5. PERFORMED OPS CHECK ON EMERGENCY LIGHT SYS IAW TASK 33-51-00-710-801. OPS CHECK GOOD. NO OTHER DESCREPANCIES NOTED AT THIS TIME. RETURNED TO SERVICE.

Part: DOOR FRAME — CHAFED (SERVICE DOOR) · airframe 15,652 hrs · 16,606 cycles

CHAFE DAMAGE ON AFT SERVICE DOOR SURROUND STRUCTURE AT THE 12:00 POSITION. CHEMICALLY REMOVED PAINT FROM CHAFE AREA FOR FURTHER EVALUATION IAW SRM 51-26-10-02-01. BLENDED AREA TO CONTOUR USING SCOTCHBRITE PAD. FOUND CHAFE TO BE .40" L .30" W AND MAX DEPTH OF .003. BLEND FOUND TO BE ACCEPTABLE FOR CONTINUED SERVICE IAW RD 8/4-53-5349. PERFORMED NDT INSPECTION OF THE AFT SERVICE DOOR SURROUND STRUCTURE IAW NDT MANUAL, PT 1 51-00-06-910-801 AND PT 6 51-00-01-250-801 EDDY CURRENT METHOD. NO DEFECTS NOTED. LODINED, PRIMED AND PAINTED IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01. ALL WORK PERFORMED IAW TC RD 8/4-53-5349.

Part: SHEAR WEB — CORRODED (BS 747-763)

CORROSION IN AFT CARGO BETWEEN BS 747.602 AND 763.603. BLENDED CORROSION FROM AFT CARGO SHEAR WEB, PN 85339601 AT FS 783.102. BLEND MEASURES 4.0" L 1.6" W .003" D. ORIGINAL MATERIAL THICKNESS .050" REMAINING THICKNESS .047". AREA IS FOUND TO BE WITHIN LIMITS AND ALL WORK DONE IAW SRM 53-40-43-02-01. BLENDED CORROSION FROM AFT CARGO SHEAR WEB PN 85339601 AT FS 763.602. BLEND MEASURES 1.3" L 1.0" W .003" D. ORIGINAL MATERIAL THICKNESS .050" REMAINING THICKNESS .047". AREA FOUND TO BE WITHIN LIMITS AND ALL WORK DONE IAW SRM 53-40-43-02-01. PERFORMED ECI ON BLENDED AREAS. NO CRACKS FOUND AT THIS TIME IAW NDTM PT 6 51-00-01. TREATED IAW SRM 51-21-10-02-01, PRIMED IAW SRM 51-25-10-02-01. NO TOP COAT REQUIRED. ALL WORK DONE IAW SRM 53-40-43-02-01.

Part: STRUCTURE — GOUGED (CARGO DOOR) · airframe 15,652 hrs · 16,606 cycles

FORWARD BAGGAGE DOOR HAS A GOUGE AT THE TOP OF THE DOOR. CHEMICALLY REMOVED PAINT FROM GOUGED AREA FOR FURTHER EVALUATION IAW SRM 51-26-10-02-01. BLENDED AREA TO CONTOUR USING SCOTCH BRITE PAD. FOUND 2 GOUGES, MOST FWD GOUGE WAS .04" W .20" L AND .004" D. AFT GOUGE WAS .08" W .20" L AND .0045" D. SENT TO ENGINEERING. BLEND FOUND TO BE ACCEPTABLE FOR CONTINUED SERVICE IAW RD 8/4-53-5348. PERFORMED NDT INSPECTION OF THE FWD BAGGAGE DOOR UPPER CUT OUT AREA IAW NDT MANUAL PT 1 51-00-06-910-801 AND PT 6 51-00-01-250-801 EDDY CURRENT METHOD NO DEFECTS NOTED. TREATED IAW SRM 51-21-10-02-01, PRIMED IAW SRM 51-25-10-02-01 AND TOP COATED IAW SRM 51-25-15-02-01. ALL WORK PERFORMED IAW TC RD 8/4-53-5348.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 15,652 hrs · 16,606 cycles

CORROSION FOUND ON RT SIDE FLOOR SEAT TRACK, BETWEEN FS X 35.000 AND X38.000. CLEANED SUSPECTED AREA IAW SRM 51-26-00-02-01, BLENDED CORROSION IAW SRM 51-21-00-00-02. BLEND IS WITHIN LIMITS IAW SRM 53-20-49-02-03. PERFORMED NDT INSPECTION OF SEAT TRACK IAW NDT MANUAL PT 1 51-00-06-910-801 EDDY CURRENT METHOD. NO DEFECTS NOTED. APPLIED ALODINE IAW SRM 51-21-10-02-01. APPLIED FAST WELD IAW SRM 51-22-35-02-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 15,652 hrs · 16,606 cycles

CORROSION FOUND ON RT SIDE FLOOR SEAT TRACK, BETWEEN BS 1 AND 11. CLEANED SUSPECTED AREA IAW SRM 51-26-00-02-01. FOUND CORROSION AT 2 LOCATIONS ON FWD RT SIDE. CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-20-49-02-03. REMOVED SEAT TRACK IAW SRM 51-42-05-02-01 AND 51-40-15-02-01. LOCATED AND DRILLED HOLES ON SERVICEABLE SEAT TRACK AND INSTALLED NUT PLATES IAW SRM 51-40-07-02-01 AND 51-42-05-02-01. INSTALLED SEAT TRACK IAW SRM 51-42-05-02-01, 51-40-15-02-01 AND 51-41-00-00-01. APPLIED AVDEC GREEN IAW SRM 51-21-10-02-01. PRIMED AND TOP COATED IAW SRM 51-25-10-02-01 AND 51-25-15-02-01. ALL WORK DONE IN COMPLIANCE WITH SRM 51-42-05-02-01, 51-40-15-02-01, 51-41-00-00-01 AND TC RD 8/4-53-5354.

Part: CONTROL VALVE — LEAKING (PARKING BRAKE) · airframe 14,823 hrs · 15,769 cycles

DURING DESCENT, NR 2 HYD FLUID QUANTITY DECREASED RESULTING IN NR 2 ENG HYD PUMP CAUTION AND NR 2 ISO VALVE CAUTION. RAN THE NR 2 HYD FLUID QUANTITY LOW CHECKLIST. PUMP MAY HAVE RAN FOR 1-2 MINUTES WITH 0 QTY. ALSO CONDUCTED ALTERNATE LANDING GEAR EXTENSION CHECKLIST. LANDING UNEVENTFUL. FOUND LEAK AT PARKING BRAKE CONTROL VALVE. R & R PARKING BRAKE CONTROL VALVE IAW AMM 32-44-01-000/400-801. OPS TEST GOOD. LEAK TEST GOOD. REF WO 145098 FOR ALL WORK PERFORMED. NO OTHER DEFECTS NOTED AT THIS TIME.

Part: COVER — UNSECURE (EMERGENCY LIGHT) · airframe 14,667 hrs · 15,612 cycles

FWD F/A EMERGENCY LIGHT SWITCH COVER BROKEN. SECURED FWD EMERGENCY LIGHT SWITCH COVER. RETURNED TO SERVICE.

Part: WIRE — DAMAGED (CARGO LIGHT) · airframe 14,128 hrs · 15,058 cycles

ELECTRICAL ODOR IN AFT CARGO COMPARTMENT. INSPECTED AFT CARGO COMPARTMENT FOR ANY OBVIOUS DEFECTS, NONE NOTED. REMOVED BOTH LIGHT ASSY AND INSPECTED FOR SIGNS OF ARCING OR BURNING. FOUND LOOSE GROUND WIRE AND BAD SOCKET ON FWD LIGHT ASSY IN AFT CARGO COMPARTMENT. REPLACED BOTH LIGHT ASSY WITH NEW ONES, OPS CHECK GOOD.

Part: LIGHT — DAMAGED (ZONE 200) · airframe 13,881 hrs · 14,800 cycles

EMERGENCY FLOOR PATH LIGHTING STRIP DISCOLORED MORE THAN 50 PERCENT OF THE WIDTH . CLEAN SEGMENTS AS REQUIRED AND REPLACED AFFECTED SEGMENTS THAT WERE OUT OF LIMITS.

Part: GOVERNOR — MALFUNCTIONED (PROPELLER) · airframe 13,731 hrs · 14,656 cycles

NR 2 PROPELLER SLOW TO COME OUT OF FEATHER, TAKES APPROX 10 SECONDS LONGER THAN NR 1, OVERALL TIME UNKNOWN. PERFORMED TROUBLESHOOTING IAW FIM TASK NR 61-20-00-810-803, STEPS 1-5A (7). INTERROGATED CDS AND PEC FOR FAULT CODES. NO FAULT CODES PRESENT. R & R OSG IAW AMM TASK NR 61-20-26-000-801 AND 61-20-26-400-801. PERFORMED OPS TEST OF THE OSG IAW AMM TASK 61-20-00-710-803. OPS TEST GOOD. NO LEAKS NOTED. NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: SKIN — CHAFED (FUSLEAGE) · airframe 13,472 hrs · 14,394 cycles

PANEL 262HT HAS CHAFE DAMAGE. BLENDED CHAFE DAMAGE REF RD 8/4-53-521. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-06 AND 51-00-04-910-801 PT 1. MATERIAL LOSS FOUND WITHIN LIMITS IAW RD 8/4-53-521 AND RD 8/4-53-4528. ALODINED AND PRIMED IAW RD 8/4-53-521 AND RD 8/4-53-451.

Part: SEAL — DAMAGED (PAX DOOR) · airframe 11,273 hrs · 12,172 cycles

RAMP REPORTS THAT AFT PASSENGER DOOR IS HARD TO OPEN. REPLACED AFT PASSENGER DOOR SEAL IAW AMM TASK 52-12-21-000/400-802. CHECKS GOOD. RETURNED TO SERVICE.

Part: SEAL — PINCHED (PAX DOOR) · airframe 11,262 hrs · 12,158 cycles

REAR PASSENGER DOOR IS HARD TO OPEN. INSPECTED AFT PAX DOOR. FOUND DOOR SEAL PINCHING LOWER LT CORNER. ADJUSTED DOOR SEAL AS REQUIRED. OPS CHECKS GOOD. SEAL NO LONGER PINCHED. NO FURTHER DEFECTS NOTED. NO PARTS REPLACED. RETURNED TO SERVICE.

Part: STRUCTURE — CORRODED (SERVICE DOOR) · airframe 11,145 hrs · 12,065 cycles

CORROSION FOUND ON RT AFT SERVICE DOOR CLOSE OUT PLATE. BLENDED CORROSION IAW 51-21-00-00-02. REMOVED DAMAGED PART IAW SRM 51-42-90-02-01. FABRICATED NEW PART IAW TASK CARD 6-53-994. INSTALL NEW PART IAW SRM 51-42-90-02-01 AND 51-42-65-02-01. APPLIED CORROSION PREVENTATIVE COMPOUND IAW SRM TASK 51-42-05-02-01.

Part: SUPPORT — DAMAGED (FUSELAGE) · airframe 9,908 hrs · 10,790 cycles

RT DC CIRCUIT BREAKER PANEL SUPPORT HAS 4 ARCING SPOTS ALONG THE LT SIDE NEXT TO THE FASTENERS. PERFORMED A TEMP REPAIR FOR THE PANEL FRAME IAW RD 8/4-53-3490.

Part: CIRCUIT BREAKER — ARCED · airframe 9,908 hrs · 10,790 cycles

CIRCUIT BREAKERS A1 AND C1 ON RT CB PANEL SHOW EVIDENCE OF ARCING AT THE TERMINAL LUG. RE-TERMINATED NEW TERMINAL LUGS AND REPLACED BOTH OF THE CB'S IAW WM 20-25-00. OPS TEST GOOD.

Part: SKIN — CHAFED (LT WING TE FLAP) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT OTBD FLAP UPPER SKIN IS CHAFED BETWEEN WING STA Y209.00 AND Y281.00. BLENDED AREA IAW SRM 57-52-30-02-01. MIN THICKNESS REMAINING .029" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-01-250-801. FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-1466. FABRICATED SHIMS FOR FLAP SHROUD IAW SRM 57-50-40 STEP 7((A)1-3). TREATED AND PRIMED SHIMS IAW SRM 57-50-40 STEP 7((A)4). INSTALLED SHIMS REF SRM 57-50-40. INSTALLED POLYURETHANE/ACRYLIC TAPE AND COMPLETED REPAIR IAW TASK CARD RD 8/4-57-1466.

Part: FRAME — CORRODED (BS 281 S31-32L) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - INTERIOR FUSELAGE LOWER FLANGE AT STA X281.000 HAS LIGHT CORROSION BETWEEN STRINGERS 31P AND 32P. REMOVED CORROSION IAW RD 8/4-53-2344. MEASURED AFFECTED AREA MIN THICKNESS REMAINING .043" REF NTM 51-00-02-250-801. CONFIRMED CRACK FREE CONDITION OF AFFECTED AREA REF RD 8/4-53-2344. FRAME FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-2344SECT. 1 SHT 2 STEP 7. TREATED AND PAINTED REF SRM 51-25-05, 51-21-10 AND 51-20-00.

Part: FLAP TRACK — CHIPPED (RT WING TE FLAP) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT WING NR3 LOWER FLAP TRACK HAS AN AREA OF CHIPPED/MISSING TUNGSTEN COATING. REMOVED ALL LOOSE MATERIAL FROM MARKED LOCATION (ON TOP SURFACE, AFT END) AND POLISHED AREA TO REMOVE ALL SHARP EDGES IAW RD 8/4-57-1468. CONFIRMED CRACK FREE CONDITION OF AFFECTED AREA REF 8/4-57-1468. C/W IAW TASK CARD RD 8/4-57-1468.

Part: SKIN — NICKED (BS 179 S16R) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - EXTERNAL FUSELAGE AT STA X179.000 ABOVE STR 16R HAS NICK. BLENDED NICK IAW SRM 53-00-00-02-01. MEASURED AFFECTED AREA MIN THICKNESS REMAINING .054" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF. NTM 51-00-01-250-801. FOUND TO BE IN LIMITS IAW RD 8/4-53-3412. TREATED BARE METAL IAW SRM 51-21-10-02-01. RESTORED SURFACE PROTECTION IAW SRM 51-25-05-02-01.

Part: FLAP TRACK — CHIPPED (LT WING TE FLAP) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT WING NR3 LOWER FLAP TRACK HAS AREAS OF CHIPPED/MISSING TUNGSTEN CARBIDE COATING. REMOVED ALL LOOSE MATERIAL FROM MARKED LOCATIONS (ON TOP SURFACE, AFT END) AND POLISHED AREA TO REMOVE ALL SHARP EDGES IAW RD 8/4-57-1468. CONFIRMED AFFECTED AREA IS CRACK FREE AND COMPLETED REPAIR IAW TASK CARD RD 8/4-57-1468.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT WING FUEL PANEL AND CUTOUT 624FT HAS FRETTING AND ARCING. REMOVED CORROSION FROM FUEL PANEL MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .088" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION, LEAVING A REMAINING MATERIAL THICKNESS .117", WITHIN ALLOWABLE LIMITS IAW RD 8/4-57-442. CONFIRMED PANEL IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 624FT IAW RD 8/4-57-442. APPLIED SEALS TO PANEL AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — DAMAGED (LT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT WING FUEL PANEL AND CUTOUT 524FT HAS FRETTING AND ARCING. REMOVED DAMAGE FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .080" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED DAMAGE FROM PANEL 524FT IAW RD 8/4-57-442, MATERIAL LOSS FOUND TO BE WITHIN ALLOWABLE LIMITS, LOWEST MEASURED POINT WAS .116" WITHIN LIMITS IAW RD 8/4-57-442. CONFIRMED PANEL IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 524FT IAW RD 8/4-57-442. APPLIED SEALS TO PANEL AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — DAMAGED (LT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT WING FUEL PANEL AND CUTOUT 524AT HAVE MINOR FRETTING. REMOVED DAMAGE FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .078" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION FROM PANEL, LEAVING A REMAINING MATERIAL THICKNESS .118", WITHIN ALLOWABLE LIMITS IAW RD 8/4-57-442. CONFIRMED PANEL IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 524FT IAW RD 8/4-57-442. APPLIED SEALS TO PANEL AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 9,685 hrs · 10,452 cycles

C2 CHECK - RT FUEL PANEL AND CUTOUT 626AT HAS FRETTING AND ARCING. BLENDED PANEL 624AT IAW RD 8/4-57-442. REMOVED CORROSION FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .078" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS FOUND TO BE WITHIN LIMITS ON MATING SURFACE IAW RD 8/4-57-445. REMOVED CORROSION FROM PANEL, REMAINING MATERIAL THICKNESS .109" WITHIN LIMITS IAW RD 8/4-57-442. CONFIRMED PANEL AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 624AT IAW RD 8/4-57-442. INSTALLED SEALS AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT WING FUEL PANEL AND CUTOUT 624BT HAS FRETTING. REMOVED CORROSION FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .084" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION, LEAVING A REMAINING MATERIAL THICKNESS .114", WITHIN ALLOWABLE LIMITS RD 8/4-57-442. CONFIRMED PANEL AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 624BT IAW RD 8/4-57-442. INSTALLED SEALS AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: BEARING — CORRODED (CARGO DOOR) · airframe 9,685 hrs · 10,542 cycles

COE - C2 CHECK - FORWARD BAGGAGE DOOR, FWD LIFT AND LATCH SHAFT BEARING HAS CORROSION BLEEDING. REMOVED BEARING SUPPORT AND PRESSED OUT BEARING IAW SRM 51-40-15-02-01. INSTALLED BEARING AND BEARING SUPPORT IAW SRM 51-40-15.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT WING FUEL PANEL AND CUTOUT 624CT HAS MINOR FRETTING. REMOVED CORROSION FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .085" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION, LEAVING A REMAINING MATERIAL THICKNESS .115", WITHIN ALLOWABLE LIMITS RD 8/4-57-442. CONFIRMED PANEL AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 624CT IAW RD 8/4-57-442. INSTALLED SEALS AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT WING FUEL PANEL AND CUTOUT 624DT HAS MINOR FRETTING. REMOVED CORROSION FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .083" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION, LEAVING A REMAINING MATERIAL THICKNESS .119", WITHIN ALLOWABLE LIMITS RD 8/4-57-442. CONFIRMED PANEL AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 624DT IAW RD 8/4-57-442. INSTALLED SEALS AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT WING FUEL PANEL AND CUTOUT 624ET HAS MINOR FRETTING AND ARCING. REMOVED CORROSION FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .084" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION, LEAVING A REMAINING MATERIAL THICKNESS .119", WITHIN ALLOWABLE LIMITS IAW RD 8/4-57-442. CONFIRMED PANEL AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 624ET IAW RD 8/4-57-442. INSTALLED SEALS AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: SEAT TRACK — GOUGED (BS 415) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT INBD SEAT RAIL NR7 IS GOUGED AT STA X415.00. DAMAGE REMOVED, MATERIAL REMOVED 0.010". FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-884 ISSUE 3. AREA ALODINED IAW SRM 51-21-10-02-01.

Part: ACCESS PANEL — DAMAGED (LT WING) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT WING FUEL PANEL AND CUTOUT 524BT HAVE MINOR FRETTING AND ARCING. REMOVED DAMAGE FROM WING MATING SURFACE IAW RD 8/4-57-445. MINIMUM REMAINING THICKNESS .073" REF NTM 51-00-02-250-801. CONFIRMED AFFECTED AREA IS CRACK FREE REF NTM 51-00-01-250-801. MATERIAL LOSS ON MATING SURFACE FOUND TO BE WITHIN LIMITS IAW RD 8/4-57-445. REMOVED CORROSION FROM PANEL, LEAVING A REMAINING MATERIAL THICKNESS .109", WITHIN ALLOWABLE LIMITS IAW RD 8/4-57-442. CONFIRMED PANEL IS CRACK FREE REF NTM 51-00-01-250-801. APPLIED ALODINE AND PRIMER TO WING MATING SURFACE IAW RD 8/4-57-445. APPLIED ALODINE AND PRIMER TO PANEL 524BT IAW RD 8/4-57-442. APPLIED SEALS TO PANEL AND COMPLETED PANEL REPAIR REF RD 8/4-57-442.

Part: ACCESS PANEL — CORRODED (CARGO BAY) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - AFT BAGGAGE COMPARTMENT FLOOR ACCESS PANEL 144JZ HAS AREA OF CORROSION ON TOP AND BOTTOM SURFACES. CLEANED AND REMOVED LIGHT SURFACE CORROSION WITH MINIMUM MATERIAL LOSS. MATERIAL THINKNESS .070", AFTER CORROSION REMOVAL MATERIAL THICKNESS .067 IAW SRM 51-21-00 AND 51-14-00. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01.

Part: SEAT TRACK — CORRODED (BS 720-780) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT INBD SEAT RAIL NR9 HAS AREA OF CORROSION AT STA X720.00 TO X780.00. CORROSION REMOVED, MATERIAL REMOVED AT STA 720.00 = .027", MATERIAL REMOVED AT STA 780.00 = .0245". BOTH AREA FOUND TO BE WITHIN LIMITS DONE IAW RD 8/4-53-884. AREA ALODINED IAW SRM 51-21-10-02-01.

Part: FLOOR SUPPORT — CORRODED (BS 783) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - AFT CARGO FLOOR SUPPORT ANGLE AT STA 783.102 ABOVE STRINGER 28P HAS AN AREA OF CORROSION. REMOVED CORROSION IAW SRM 51-21-00-00-02, FOUND AREA TO BE OUT OF LIMITS IAW SRM 51-14-00-02-03. REMOVED FLOOR PANEL FOR ACCESS REF SRM 51-41-00-00-01. REMOVED AFT CARGO FLOOR SUPPORT ANGLE AT STA 783.102 IAW SRM 51-42-05. MATCH DRILLED SUPPORT ANGLE TO ACFT IAW SRM 51-40-07. ALODINED AND PRIMERED SUPPORT ANGLE IAW SRM 51-21-10-AND 51-25-10. INSTALLED NEW ANGLE IAW SRM 51-42-05. INSTALLED FLOOR PANEL 145DZ REF AMM 20-10-01-430-801.

Part: FLOOR SUPPORT — CORRODED · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - REMOVEABLE FLOORBOARD SUPPORT PLATE AT STA X 32.400 LT HAS AREAS OF CORROSION. REMOVED PLATE ASSY AND INSTALLED NEW IAW AMM 20--10-01-430-801.

Part: FLOOR SUPPORT — CORRODED (CABIN) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - FWD LT PAX ENTRY FLOORBOARD SUPPORT WEB AT STA X32.400 JUST AFT OF PAX DOOR AFT HINGE ARM HAS AREAS OF CORROSION. REMOVED STUB WALL, FLOORBOARD SUPPORT TO FOM IAW SRM 51-42-45. FABRICATED STUB WALL SUPPORT ANGLE IAW TASK CAR 6-53-955. INSTALLED FLOORBOARD SUPPORT IAW SRM 51-42-45.

Part: FLOOR SUPPORT — CORRODED (BS 698) · airframe 9,685 hrs · 10,452 cycles

C2 CHECK - AFT CARGO LT FLOOR SUPPORT WEB HAS AREA OF CORROSION AT STA X698.00 TOP SURFACE. REMOVED CORROSION. REMOVED MATERIAL FOUND AT .002". FOUND TO BE WITHIN LIMITS IAW SRM 51-14-00-02-03. ALODINED AREA IAW SRM 51-21-10-02-01. PRIMED AREA IAW SRM 51-25-10-02-01.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 21,061 hrs · 18,521 cycles

C4 CHECK - RT INBD SEAT RAIL NR10 HAS AREAS OF CORROSION AND 2 CORRODED DRILLED OFF FASTENERS BETWEEN STA X39.00 AND X10.50. REMOVED NR10 SEAT TRACK IAW SRM 51-41-05, 51-40-15 AND 51-42-05. TRACK REMOVED DUE TO BEING OUT OF LIMITS IAW RD 8/4-53-884. DRILLED NEW NR10 SEAT TRACK TO ACFT AND ALODINED AND PRIMED HOLES IAW SRM 51-40-07, 51-21-00 AND 51-25-10. INSTALLED SEAT TRACK IAW SRM 51-41-05, 51-42-05, 51-40-15-02-01 AND 51-42-05-02-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - RT INBD SEAT RAIL NR11 HAS SCRATCHES AND AREAS OF CORROSION FROM STA X95.00 TO STA X102.500. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW RD 8/4-53-884. REMOVED NR11 SEAT TRACK REF SRM 51-40-15, 51-42-05 AND 51-41-05. MATCH DRILLED NEW SEAT TRACK, INSTALLED NEW NR11 SEAT TRACK IAW SRM 51-41-05, 51-40-15 AND 51-42-05.

Part: FRAME — CORRODED (BS 281) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - INTERIOR FUSELAGE FRAME LOWER FLANGE AT STA X281.000 HAS CORROSION BETWEEN STR 31S AND 32S. REMOVED RIVETS COMMON TO EXTERNAL SKIN FOR ACCESS IAW SRM 51-42-05-02-01. REMOVED CORROSION IAW RD 8/4-53-2344. MEASURED AFFECTED AREA MIN THICKNESS REMAINING .046" REF NTM 51-00-02-250-801. CONFIRMED CRACK FREE CONDITION REF RD 8/4-53-2344. FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-2344. INSTALLED RIVETS REF SRM 51-42-05. TREATED AND PAINTED REF SRM 51-25-05, 51-21-10 AND 51-20-00.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - FWD LT FLOORBOARD SUPPORT STRAP JUST INBD OF FWD LT AIRSTAIR TOP STEP HAS AREA OF CORROSION BETWEEN STA X1.000 AND X32.400. REMOVED CORROSION FROM THRESHOLD MEMBER, FOUND TO BE OUT OF LIMITS IAW RD 8/4-53-1660. REMOVED THRESHOLD MEMBER FROM THRESHOLD CHANNEL IAW SRM 51-42-05 AND REMOVED CORROSION FROM THRESHOLD CHANNEL IAW RD 8/4-53-1660 FOUND CHANNEL CORROSION WITHIN LIMITS, MATERIAL LOSS IS .004 WITH MAX ALLOWED OF .010. CONFIRMED AFFECTED AREA CRACK FREE, REF RD 8/4-53-1660. INSTALLED NEW THRESHOLD MEMBER IAW SRM 51-42-05 AND 51-42-45.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - INTERNAL FUSELAGE CTR FLOORBOARD SUPPORT ANGLE AT STA X18.250 HAS CORROSION. REMOVED RIVETS TO REPLACE ANGLE AND INSTALLED NEW ANGLE IAW SRM 51-42-05-02-01. TREATED AND PRIMED AREA IAW SRM 51-21-10-02-01.

Part: SEAT TRACK — CORRODED (BS 720-780) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT INBD SEAT RAIL NR9 HAS AREAS OF CORROSION AT STA X720.00 TO X744.00 AND X780.00. CORROSION REMOVED. MATERIAL REMOVED AT STA 720.00 TO 744.00 = .027". MATERIAL REMOVED AT STA 780.00 = .0245". BOTH AREAS FOUND TO BE WITHIN LIMITS. DONE IAW RD 8/4-53-884. AREA ALODINED IAW SRM 51-21-10-02-01.

Part: SEAT TRACK — CORRODED (BS 635-654) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT INBD SEAT RAIL NR8 HAS AREAS OF CORROSION BETWEEN STA X635.00 AND X654.00. REMOVED CORROSION. MINIMUM THICKNESS FOUND .4462". FOUND TO BE WITHIN LIMITS. DONE IAW RD 8/4-53-884. ALODINE DONE IAW SRM 51-21-10-02-01.

Part: WEB — CORRODED (CABIN) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - FLOOR SUPPORT WEB JUST OTBD OF THE LT INBD SEAT RAIL NR5 HAS AREAS OF CORROSION BETWEEN STA X5.400 AND X17.850. REMOVED FLOOR SUPPORT WEB IAW SRM 51-42-05. INSTALLED NEW FLOOR SUPPORT WEB IAW SRM 51-42-05.

Part: FRAME — CORRODED (FUSELAGE) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - INTERNAL FUSELAGE FRAME AT STA X6.00 BETWEEN STR 24P AND 25P HAS CORROSION. CLEANED AND REMOVED SURFACE CORROSION IAW SRM 51-21-00. MEASURED AFFECTED AREA, MIN THICKNESS REMAINING .048" REF NTM 51-00-02-250-801. CONFIRMED CRACK FREE CONDITION OF AFFECTED AREA, REF RD 8/4-53-2344. FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-2344. TREATED, PRIMED AND PAINTED IAW SRM 51-21-10, 51-25-10 AND 51-25-15. APPLIED CORROSION INHIBITING COMPOUND IAW SRM 51-25-00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - INTERNAL FUSELAGE FRAME AT STA X28.00 BETWEEN STR 24P AND 25P HAS CORROSION. CLEANED AND REMOVED SURFACE CORROSION IAW SRM 51-21-00. MEASURED AFFECTED AREA MIN THICKNESS REMAINING .046" REF NTM 51-00-02-250-801. FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-2344. CONFIRMED CRACK FREE CONDITION OF AFFECTED AREA REF RD 8/4-53-2344. TREATED, PRIMED AND PAINTED IAW SRM 51-21-10, 51-25-10 AND 51-25-15. APPLIED CORROSION INHIBITING COMPOUND IAW SRM 51-25-00.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 9,685 hrs · 10,542 cycles

C2 CHECK - LT INBD SEAT RAIL NR5 HAS AREAS OF CORROSION BETWEEN STA X95.00 AND X102.500. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW RD 8/4-53-884. REMOVED NR5 SEAT TRACK IAW SRM 51-40-15, 51-42-05 AND 51-41-05. MATCH DRILLED NEW NR5 SEAT TRACK TO ACFT IAW SRM 51-40-07. ALODINED AND PRIMED NEW SEAT TRACK AS REQUIRED IAW SRM 51-21-10. INSTALLED NEW NR5 SEAT TRACK IAW SRM 51-40-15, 51-41-05 AND 51-42-05.

Part: CONNECTOR — DAMAGED (MLG CONTROL) · airframe 8,657 hrs · 9,430 cycles

FOLLOWING GEAR SELECTION TO UP, GEAR DID NOT RETRACT NORMALLY. ON INITIAL GEAR RETRATION THE GEAR GEAR HANDLE ILLUMINATED AND ALL 3 RED GEAR UNSAFE LIGHTS ILLUMINATED, FOLLOWING A DELAY OF APROX 5-10 SECS GEAR RETRATION CONTINUED NORMALLY TO COMPLETION. FOR GEAR EXTENSION THE ALT PROCEDURE WAS USED. LANDING UNEVENTFUL. CHECKED PSEU, FOUND NO FAULTS. CHECKED ALL POWER AND GROUND INPUTS TO PSEU, LANDING GEAR CONTROL PANEL. RE-SEATED PINS 8A AND 13D IN CONNECTOR 3261-P1A, REF WDM 32-61-02, CONFIG 02, SHEET 4. REPLACED LANDING GEAR CONTROL PANEL IAW 32-31-01-000-801/400-801. AS A PRECAUTIONARY MEASURE. PERFORMED OPS CK OF GEAR EXTENSION/RETRACTION SYS IAW 32-31-00-710-801. OPS CHECKS GOOD. RETURNED TO SERVICE.

Part: BUSHING — DAMAGED (MLG DOOR ARM) · airframe 7,483 hrs · 8,045 cycles

AFTER THE TAKEOFF, AFTER F/O FINISHED HIS AFTER TAKEOFF FLOW, WE HAD "L DOOR R AND R DOOR" YELLOW LIGHTS ON LANDING GEAR PANEL "ON", FOLLOWED BY "OFF" DURING CLIMB WITH SPEED OF 140-160 KTS THESE LIGHTS CYCLED ABOUT 5 OR 6 TIMES RAN CHECK LIST. INTO RNO PERFORMED ALTERNATE GEAR EXTENSION. LANDING NORMAL. FOUND LT MLG AFT DOORS PROX SENSOR OUT OF RIG, RIGGED PROX SENSOR. REPLACED LT MLG AFT DOORS MECHANISM ARM BUSHINGS DUE TO WEAR. ADJUSTED RT MLG AFT DOORS DUE TO SAGGING. SHIMMED RT AND L/H AFT GEAR DOORS LOCK LINKS AND PERFORMED OPS TEST OF LANDING GEAR EXTENSION AND RETRACTION SYS. ACFT RETURNED TO SERVICE.

Part: CONTROL PANEL — MALFUNCTIONED (MLG) · airframe 7,416 hrs · 7,962 cycles

AMBER L DOOR AND R DOOR LIGHTS CYCLED IN FLIGHT COREESPONDING RED LT AND RT GEAR UN SAFE LIGHTS FLICKERED AS WELL. REMOVED AND REPLACED LANDING GEAR CONTROL PANEL IAW AMM TASKS 32-31-01-000-801 AND 32-31-01-400-801. PERFORMED LANDING GEAR OPS CHECK IAW AMM TASK 32-31-00-710-801. NO DEFECTS NOTED. RETURNED TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (NR 2 AC GEN) · airframe 6,015 hrs · 6,298 cycles

GEG - NR 2 AC GEN CAUTION ILLUMINATED. GENERATOR CAUTION WENT OUT WHEN RESET PER CHECKLIST. NO ELECTRICAL SYSTEM CONFIGURATION CHANGES WHAT SO EVER PRECEDED THE EVENT. DIVERTED TO GEG. LANDING UNEVENTFUL. INSPECTED CONNECTOR 9811P722 WITH NO DEFECTS FOUND. PERFORMED OPERATIONAL TEST OF GENERATOR IAW 24-21-00-710-801. CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED.

Part: UNKNOWN — ODOR (CABIN) · airframe 5,815 hrs · 6,068 cycles

RNO - BURNT SMELL NOTICED BY FLIGHT ATTENDANT, RAMP AGENT IN FRONT OF CABIN. WHEN COCKPIT DOOR OPENED PILOT SMELLED THE ODOR ALSO. CHECKED FOR POPPED C/B'S, NONE NOTED. RAN UP BOTH ENGINES AND APU, OPERATED BOTH PACKS, OPERATED TEMP SWITCHES FOR ABOUT 5 MINUTES, UNABLE TO DUPLICATE SMELL. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: RUDDER PEDAL — STUCK · airframe 5,140 hrs · 5,279 cycles

STS - AT TOP OF DESCENT CREW ATTEMPTED TO APPLY A SLIGHT AMOUNT OF RUDDER PRESSURE TO THE RIGHT RUDDER PEDAL AND ENCOUNTERED WHAT FELT LIKE A JAMMED RUDDER. A/P WAS ON AND AIRSPEED WAS 275 KIAS. BOTH DIRECTIONS AND PILOTS SAME FEEL AND RESULT. AFTER PUSHING WITH GREAT FORCE, THE PEDALS "BROKE LOOSE" AND RUDDER WAS CONTROLLABLE. AS AIR SPEED REDUCED FOR LANDING JAM WAS LESS. UNEVENTFUL LANDING. PERFORMED GVI OF RUDDER CABLES FROM RUDDER PEDALS TO RUDDER PCV'S NO DEFECTS NOTED. INSPECTED FEEL/SUMMING UNIT, NO DEFECT NOTED. PERFORMED OPS TEST OF RUDDER SYSTEM IAW TASK NR 27-20-00-710-802, OPS GOOD. REMOVED FLOORBOARD AND ACCESS PANEL AS REQUIRED. PERFORMED GVI OF RUDDER CABLES FROM RUDDER PCV. NO DEFECTS NOTED. COMPLETED FREEDOM OF MOVEMENT CHECK, ENSURED FULL TRAVEL AND PROPER DIRECTION OF MOVEMENT. NO DEFECT NOTED. CHECK FLIGHT PERFORMED AND PASSED. ACFT STILL DOWN FOR REPAIRS.

Part: PROXIMITY SENSOR — DAMAGED (ZONE 700) · airframe 5,041 hrs · 5,170 cycles

PDX - RT MAIN GEAR AMBER GEAR DOOR LIGHT ON AFTER T/O. INSPECTED FOUND RT MLG DOOR CLOSED PROX SENSOR UNREASONABLE NEAR FAULT. FOUND EVIDENCE OF CONTACT WITH PROX SENSOR AND TARGET. REMOVED AND REPLACED RGDRCL PROX SENSOR WITH NEW IAW AMM TASKS 32-61-06-000-802 AND 32-61-06-400-802. INSPECTED RT SSV FILTERS NO CONTAMINATION FOUND. PERFORMED OPERATIONAL TEST OF LANDING GEAR IAW AMM TASK 32-31-00-710-801 TR 32-240. RETURNED TO SERVICE.

Part: SENSOR — OUT OF ADJUST (MLG DOOR) · airframe 5,032 hrs · 5,159 cycles

BOI - "R DOOR" GEAR INDICATOR LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. RETURNED TO THE FIELD AND ACCOMPLISHED A UNEVENTFUL LANDING. FERRY TO PDX FOR REPAIR. PSEU - RGDRCL UNREASONABLE FAR, FLT LEG 03. RGDRCL RIGGING NEAR GAP TOO LARGE. ADJUSTED SENSOR S-20 IAW AMM TASK 32-61-06-830-801. FOUND NR 2 MLG FWD DOOR (LEFT DOOR) HAD A GAP BETWEEN FWD END + NACELLE. ADJUSTED DOOR IAW TASK 32-12-11-830-801. PERFORMED OPS TEST OF LANDING GEAR PRIMARY EXTENSION AND RETRACTION IAW 32-31-00-710-801. TR 32-240. OPS TEST GOOD. GEAR LIGHTS INDICATE NORMALLY. RETURNED TO SERVICE. NO PARTS.

Part: GOVERNOR — FAILED (NR 2 PROPELLER) · airframe 4,976 hrs · 5,074 cycles

SEA - NR 2 PROP WOULD NOT COME OUT OF FEATHER. REMOVED OVERSPEED GOVERNOR IAW Q400 AMM TASK 61-20-26-000-801 AND INSTALLED A NEW FROM STOCK OSG IAW Q400 AMM TASK 61-20-26-400-801. OPS AND LEAK CHECK GOOD. RETURNED TO SERVICE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 4,826 hrs · 4,916 cycles

PDX C1- POSSIBLE LIGHTNING STRIKE DAMAGE ON UPPER FUSELAGE AT APPROX STA X34.5 4.5 INCH LEFT OF STRINGER 1. REMOVED LIGHTNING STRIKE DAMAGE BY BLENDING IAW RD 8/4-53-666 FOUND TO BE BEYOND LIMITS PER RD 8/4-53-666. MAPPED FOR ENGINEERING. HFEC IAW Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. REMOVED DAMAGE AND CUT INTO INTERNAL STRAP, FABRICATED PACKER AND DOUBLER, REPAIRED SKIN COUNTERSINKS ALODINED AND PRIMED PARTS AND BARE METAL IAW RD8/4-53-2517/3 GENERAL NOTES 3,4,6-10 AND 12. HFEC AREA IAW -8 Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. FINISHED REPAIR IAW RD 8/4-53-2517/3 STEP 13-16.

Part: DIAPHRAGM — CRACKED (LT NACELLE) · airframe 4,826 hrs · 4,916 cycles

PDX - C1 - LT NACELLE INTERCOSTAL DIAPHRAGM IS CRACKED. REMOVED DIAPHRAGM P/N 85414131 AND P/N 85414117. LOCATED AND DRILLED HOLES IN DIAPHRAGMS. INSTALLED DIAPHRAGMS REF Q400 SRM 51-40-15.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 4,826 hrs · 4,916 cycles

PDX - C1 - FWD FUSELAGE EXTERIOR ROOF SKIN HAS LIGHTNING STRIKE AT RIVET EDGE AND SKIN AT APPROX FS X38.000 AND STR LT 6. DRILLED OUT RIVET, ENLARGED COUNTERSINK TO REMOVE DAMAGE FROM SKIN REF RD 8/4-53-1039. HFEC AROUND FASTENER FOR CRACKS IAW Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. INSTALLED SOLID RIVET IAW SRM 51-42-05. PRIMED AND PAINTED REF Q400 SRM 51-25-05.

Part: SKIN — CRACKED (NR 1 NACELLE) · airframe 4,826 hrs · 4,916 cycles

PDX - C1 - UPPER OUTBOARD SKIN OF THE NR 1 NACELLE IS CRACKED. ROUTED OUT CRACK AND RESTORED FINISH REF RD 8/4-54-157.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 4,826 hrs · 4,916 cycles

PDX -C1-POSSIBLE LIGHTNING STRIKE DAMAGE ON UPPER FUSELAGE AT APPROX STA X13.0 LEFT OF STR 1 ON TOP OF DOUBLER. REMOVED RIVET BY DRILLING, ENLARGED HOLE AND COUNTERSINK TO REMOVE DAMAGE TO SKIN REF RD8/4-53-1039. HFEC AREA IAW Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. INSTALL SOLID RIVET IAW SRM 51-42-05. PRIMED AND PAINTED REF Q400 SRM 51-25-05.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 4,826 hrs · 4,916 cycles

PDX - C1 - FWD FUSELAGE EXTERIOR ROOF SKIN HAS LIGHTNING STRIKE AT RIVET EDGE AND SKIN AT APPROX FS X-31.000 AND STR LT 3. DRILLED OUT RIVET, NO DAMAGE TO SKIN FOUND. PERFORMED HFEC AROUND REMOVED RIVET FOR CRACKS IAW Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. INSTALLED SOLID RIVET IAW SRM 51-42-05. PRIMED AND PAINTED REF Q400 SRM 51-25-05.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 4,826 hrs · 4,916 cycles

PDX - C1 - FWD FUSELAGE EXTERIOR ROOF SKIN HAS A LIGHTNING STRIKE ON RIVET HEAD AT APPROX X-55.000 AND STR LT 5. DRILLED OUT RIVET, ENLARGED COUNTERSINK TO REMOVE DAMAGE FROM SKIN REF RD 8/4-53-1039. HFEC INSPECTED IAW Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. INSTALLED SOLID RIVET IAW SRM 51-42-05. PRIMED AND PAINTED REF Q400 SRM 51-25-05.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 4,826 hrs · 4,916 cycles

PDX - C1- POSSIBLE LIGHTNING STRIKE DAMAGE ON UPPER FUSELAGE AT APPROX STA 71.5, 5.5 INCHES LEFT OF STRINGER NR 1. DRILLED OUT RIVET THAT WAS DAMAGED AND COUNTERSUNK TO REMOVE DAMAGE IAW Q400 RD 8/4-53-1039. HFEC AREA IAW Q400 NDTM PART 6, 51-00-01, NO CRACKS NOTED. INSTALLED SOLID RIVET IAW SRM 51-42-05, PRIMED AND PAINTED REF SRM 51-25-05.

Part: STOP — LACK OF LUBE (PAX DOOR) · airframe 3,815 hrs · 3,843 cycles

LAX - FLIGHT 2442 - MAIN CABIN DOOR HARD TO OPEN AFTER LANDING. MAINTENANCE LUBRICATED THE DOOR STOPS. OPERATIONAL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED. (A)

Part: NOZZLE — FAILED (STARTER) · airframe 3,702 hrs · 3,723 cycles

YYJ - FLIGHT 2375 - APU STARTED BLOWING SMOKE DURING A START AND PERFORMED A AUTO SHUTDOWN, FOR ABOUT 5 MINUTES IT LEAKED FUEL. MAINTENANCE FOUND FUEL LEAK TO BE FROM COMBUSTION CAN DRAIN LINE AND PLACED ON MEL 49-00-1. MEL CLEARED 5/28 IN BOI BY REPLACING EXCITER BOX WITH NO HELP, THEN REPLACED RT START NOZZLE. OPERATIONAL CHECKS GOOD MEL CLEARED AND AIRCRAFT RETURNED TO SERVICE.

Part: PROXIMITY SENSOR — MALFUNCTIONED (PAX DOOR) · airframe 3,626 hrs · 3,636 cycles

IDA0 FLIGHT 2269 - AFT PASSENGER DOOR INDICATES NOT CLOSED ON THE MFD DOOR PAGE, EVEN THOUGH IT IS CONFIRMED TO BE CLOSED. MAINTENANCE REPLACED THE PROX SENSOR FOR THE DOOR. OPERATIONAL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: DOOR — DIRTY (SERVICE DOOR) · airframe 3,473 hrs · 3,461 cycles

SEA - REAR SERVICE DOOR HARD TO OPEN FROM THE OUTSIDE. MAINTENANCE CLEANED AND LUBED THE DOOR HANDLE. OPERATIONAL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED.

Part: HANDLE — OUT OF RIG (PAX DOOR) · airframe 2,991 hrs · 2,921 cycles

LAX - FLIGHT 2304 - DURING CLIMB RECEIVED A FUSELAGE DOOR WARNING. F/A CAN'T CONFIRM THAT THE RIGHT AFT SERVICE DOOR IS CLOSED. NO LOSS OF PRESSURIZATION. RETURNED TO THE FIELD AND ACCOMPLISHED A UNEVENTFUL LANDING. FERRIED AIRCRAFT TO PDX FOR REPAIRS. IN PDX FOUND HANDLE OUT OF RIG NOT ALLOWING A FLUSH FIT. RIGGED DOOR. OPERATIONAL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED.

Part: WARNING LIGHT — ILLUMINATED (GENERATOR) · airframe 2,870 hrs · 2,806 cycles

BOI- FLIGHT 2391 - ON TAKEOFF ROLL AT ABOUT 45 KNOTS, THE NR 1 DC GENERATOR CAUTION LIGHT ILLUMINATED. ABORTED TAKEOFF. LIGHT WENT OUT AS ENGINES MOVED BACK TO DISC. RETURNED TO THE GATE. MAINTENANCE PLACED THE SYSTEM ON MEL 24-30-6. AIRCRAFT RETURNED TO SERVICE.

Part: SMOKE DETECTOR — FALSE ACTIVATION (LAVATORY) · airframe 2,723 hrs · 2,660 cycles

BOI- FLIGHT 2403 - LAVATORY SMOKE DETECTOR WENT OFF AFTER TAKEOFF FOR 30 SECONDS. FLIGHT ATTENDANTS NOTED NO SMOKE OR FIRE. MAINTENANCE COMPLIED WITH OPERATIONAL TEST OF THE SMOKE DETECTOR IAW 26-12-11-710-801. NO DEFECTS NOTED. COULD NOT DUPLICATE PROBLEM. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 2,455 hrs · 2,389 cycles

GEG - FLIGHT 2371 - CLIMBING OUT OF 8000 FEET, PRESSURIZATION WAS RAPIDLY INCREASING, AND 12000 GOT A MASTER WARNING. AIRCRAFT WOULD NOT DEPRESSURIZE IN MANUAL MODE, DESCENDING OUT OF 10000 MANUAL MODE STARTED TO OPERATE. RETURNED TO THE FIELD AND ACCOMPLISHED A UNEVENTFUL LANDING. MAINTENANCE REPLACED THE AFT OUTFLOW VALVE. OPERATIONAL CHECKS GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: WARNING MESSAGE — FALSE ACTIVATION (STICK PUSHER) · airframe 2,344 hrs · 2,280 cycles

SEA - DURING LANDING ROLL OUT, RECEIVED A PUSHER SYSTEM FAIL MESSAGE. PER THE CHECKLIST PERFORMED A PUSHER TEST. LIGHT STAYS ON. MAINTENANCE PERFORMED A OPERATIONAL CHECK OF THE ELEVATOR PUSHER SYSTEM, CHECKS GOOD WITH NO DEFECTS. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED.

Part: WARNING LIGHT — FALSE ACTIVATION · airframe 2,318 hrs · 2,248 cycles

BOI FLIGHT NR 2399: CABIN DUCT HOT CAUTION. AIRCRAFT RETURNED TO BLOCK. MAINTENANCE C/W Q400 FIM TASK 21-60-00-810-804. NO CABIN DUCT HOT CAUTION MESSAGE NOTED. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: GENERATOR — MALFUNCTIONED (NR 1) · airframe 2,287 hrs · 2,219 cycles

SJC FLIGHT NR 2452: NR 1 DC GEN CAUTION LIGHT ILLUMINATED AFTER START. EXTERNAL POWER KICKED OFF DURING START. AIRCRAFT RETURNED TO BLOCK. MAINTENANCE POWERED A/C DOWN AND REPOWERED/RESTARTED GEN. ALL OPERATE NORMALLY AS PER MTX CONTROL. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: VALVE — MALFUNCTIONED (SPOILERS) · airframe 2,184 hrs · 2,114 cycles

GTF FLIGHT: DURING CLIMB-OUT FROM HLN, SPOILER OUTBOARD CAUTION LIGHT ILLUMINATED. RAN CHECKLIST, NO ADDITIONAL/ASSOCIATED LIGHTS. THIS CAUTION LIGHT CAME ON BETWEEN 185-185 KNOTS. MAINTENANCE REMOVED AND REPLACED NR 2 UNLOAD VALVE IAW Q400 AMM 27-61-26-000-801/400-801. OPS CHECK GOOD. NO LEAKS NOTED. THE VALVE WAS CHANGED FOR PRECAUTIONARY MEASURE. AIRCRAFT RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (HYD IND C/B) · airframe 1,355 hrs · 1,290 cycles

EUG - ON FLIGHT 2421, RETURNED TO GATE, STANDBY HYDRAULIC INOP. FOUND STANDBY HYDRAULIC PRESSURE INDICATOR 1 CIRCUIT BREAKER POPPED. MAINTENANCE RESET CIRCUIT BREAKER, PERFORMED OPERATIONAL TEST OF POWER UNIT. NO DEFECTS NOTED. AIRCRAFT RETURNED TO SERVICE. NO PARTS REPLACED.

Part: UNKNOWN — UNKNOWN (NR 2 BLEED CAUT) · airframe 1,322 hrs · 1,262 cycles

SEA FLIGHT NR 2361: NR 2 BLEED HOT CAUTION ILLUMINATED EN ROUTE. PERFORMED CHECKLIST. VERIFIED LIGHT WAS STILL ILLUMINATED UPON MTX ARRIVAL TO AIRCRAFT. MAINTENANCE FOUND RT BLEED OVERTEMP MESSAGE IN CDS. DURING TROUBLE SHOOTING, CAUTION AND FAULT MESSAGES EXTINGUISHED. GROUND RAN ENGINES FOR 15 MINUTES WITH BLEED ON MAX. NO FURTHER FAULTS NOTED. UNABLE TO INDUCE FAULTS. CHECKS GOOD. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: DOOR — UNKNOWN · airframe 1,108 hrs · 1,050 cycles

SEA FLIGHT NR 2318: FA UNABLE TO OPEN REAR PASSENGER DOOR. MAINTENANCE FOUND PREVIOUS OPENED AND OUT OF SEQUENCE. RESEQUENCED DOOR AND PERFORMED OPS CHECK. OPS CHECK IS GOOD IAW Q400 AMM TASK 52-12-00-710-801. OK FOR CONTINUED SERVICE. NO FURTHER DEFECTS NOTED. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN · airframe 987 hrs · 942 cycles

SEA FLIGHT NR 2274: NR 2 DC GEN CAUTION LIGHT ILLUMINATED AFTER TOUCHDOWN. THE CHECKLIST WAS ACCOMPLISHED AND THE CAUTION LIGHT EXTINGUISHED. MAINTENANCE C/W FIM TASK 24-30-00-810-813. INTERROGATED EPCU FOR RELATED FAULT CODES. NONE FOUND. PERFORMED OPS CHECK OF MAIN 28 V DC GENERATION SYSTEM IAW AMM 24-31-00-710-802. OPS CHECK NORMAL. ALSO PERFORMED VISUAL INSPECTION OF NR 2 DC GENERATOR INSTALLATION. NO FAULTS NOTE. NO PARTS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: GENERATOR — INOPERATIVE (NR 2 DC) · airframe 972 hrs · 926 cycles

RNO FLIGHT NR 2440: NR 2 DC GENERATOR WILL NOT COME ON LINE. AIRCRAFT RETURNED TO BLOCK. MAINTENANCE REMOVED AND REPLACED NR 2 DC GEN IAW MTC 6243101. OPS CHECK GOOD. NO DEFECTS OR LEAKS NOTED. AIRCRAFT RETURNED TO SERVICE.

Part: AUTOFEATHER SYS — MALFUNCTIONED · airframe 663 hrs · 594 cycles

LAX FLIGHT NR 2307: AUTO FEATHER WILL NOT SELECT. AIRCRAFT RETURNED TO GATE. MAINTENANCE INTERROGATED CDS AND FOUND NR 1 AND NR 2 PROPELLER FAULTS 64. C/W Q400 FIM TASK 61-20-02-810-804. CLEARED FAULTS. GROUND RAN ENGINES AT DISC, AUTO FEATHER SELECTED NORMALLY. NO DEFECTS NOTED. FAULTS DID NOT RETURN. AUTO FEATHER TEST PASSED. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: VALVE — MALFUNCTIONED (DEICE SYSTEM) · airframe 640 hrs · 574 cycles

SEA FLIGHT NR 2425: DEICE PRESSURE CAUTION LIGHT ON, DEC AND APP RAN CHECKLIST. CAUTION LIGHT WENT OUT AND CAME BACK ON. MAINTENANCE INTERROGATED CDS AND FOUND FAULT 'LOW PRESS 6A'. GVI OF DEICE BOOTS ON VERTICAL AND HORIZONTAL STAB SHOWED NO DEFECTS. PERFORMED FUNCTIONAL TEST OF THE AIRFRAME PNEUMATIC DEICING SYSTEM PER Q400 AMM TASK 31-11-00-720-801. THE LOWER VERTICAL STAB AND THE RIGHT OUTBOARD TAIL BOOT DID NOT INFLATE WITH DEICE PRESSURE CAUTION. REMOVED AND REPLACED NR 6 DDV IAW Q400 AMM TASK 30-11-16 PG 401-408. FUNCTIONAL TEST OF THE AIRFRAME DEICING SYSTEM GOOD PER Q400 AMM TASK 30-11-00-720-801. AIRCRAFT RETURNED TO SERVICE.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 593 hrs · 530 cycles

SEA FLIGHT NR 2316: ON CLIMB-OUT AT ABOUT 13,000, NOTICED TORQUE SPLIT. NR 1 TORQUE WAS STAYING 6 PERCENT LESS THAN NR 2. ALSO, NR 1 NL AND NH WERE LOWER THAN 32. RETURNING TO SEA IN DESCENT AT LOW POWER SETTINGS, TORQUE SPLIT WOULD SEEM TO BE LESS NOTICEABLE. AIRCRAFT RETURNED TO FIELD. MAINTENANCE INTERROGATED CDS AND NO FAULTS WERE FOUND. C/W POWER ASSURANCE RUNS IAW AMM 71-00-00-868-806. CHECKS GOOD. RAN BOTH ENGINES AT VARIOUS POWER SETTINGS WITH BLEEDS ON AND OFF WITH NO TORQUE SPLIT NOTED. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: SWITCH — MALFUNCTIONED (BLEED SYS) · airframe 470 hrs · 425 cycles

BOI FLIGHT NR 2320: NR 1 BLEED HOT CAUTION LIGHT ON AFTER START UP. TURNED OFF BLEED SWITCH PER CHECKLIST AND CAUTION LIGHT STAYED ON. MAINTENANCE REPLACED NR 1 PRECOOLER TEMP SWITCH IAW AMM TASK 36-11-11-000-801 AND 36-11-11-400-801 AND NR 1 BLEED OVER TEMP SWITCH IAW AMM TASK 36-11-16-000-801 AND 36-11-16-400-801. GROUND RAN AIRCRAFT AT VARIOUS POWER SETTINGS AND BLEED SETTINGS FOR 30 MINUTES. NO BLEED CAUTIONS. CHECKED CDS FOR ECS FAULTS. NO FAULTS NOTED. AIRCRAFT RETURNED TO SERVICE.

Part: PITOT SYSTEM — MALFUNCTIONED (NR 1 & 2) · airframe 228 hrs · 191 cycles

PDX FLIGHT NR 2362: PITOT NR 1 AND PITOT NR 2 CB OUT. AIRCRAFT RETURNED TO BLOCK. MAINTENANCE RESET PITOT 1 AND 2 CB IAW GMM 5-18-0. GROUND RAN NR 2 ENGINE. SELECTED PITOT HEAT ON WITH NO DEFECTS NOTED. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: DOOR — UNKNOWN (MAIN PAX) · airframe 225 hrs · 187 cycles

BOI FLIGHT NR 2320: UPON DESCENT, RECEIVED FUSELAGE DOOR WARNING ILLUMINATED. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE PERFORMED GVI OF AFT PAX DOOR HANDLE LOCKS AND DOOR CLOSE SWITCH WITH NO DEFECTS NOTED. INTEROGATED PSEU FOR DOOR LOCK AND HANDLE FAULTS. NO FAULTS WERE NOTED. OPEN AND CLOSED DOOR MULITIPLE TIMES AND COULD NOT DUPLICATE DOOR WARNING LIGHT. LUBED DOOR CLOSED SWITCH. CHECKS GOOD. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (ENGINE) · airframe 132 hrs · 108 cycles

PDX FLIGHT NR 2356: RECEIVED A POWER PLANT MESSAGE WHEN REDUCED NP. MAINTENANCE INTEROGATED CDS AND FOUND CODE 494. CLEARED FAULT IAW AMM 61-20-36-070-801. AFTER NO FAULTS WERE FOUND, C/W FIM TASK 61-20-10-810-826 AND PERFORMED AUTO FEATHER TEST. TESTED GOOD. NO PARTS REPLACED. AIRCRAFT WAS RETURNED TO SERVICE.