N434MK

Part: MODULE — MALFUNCTIONED (TE FLAPS) · airframe 29,116 hrs · 31,499 cycles

FLAP POWER CATION ON APPROACH. WENT MISSED APPROACH AND DECLARED EMERGENCY. RAN THE CHECKLIST AND LANDED FLAP ZERO. REMOVED FROM SERVICE. INTERROGATED CDS FOUND FAULT ARMING SWITCH ON FLAP PAGE.C\W Q400 FIM 27-50-00-810-805 STEP (4)(A)(1).R+R THE FLAP CONTROL MODULE IAW Q400 AMM 27-51-06-000/400-801.PERFORMED OPS TEST OF WING FLAPS PER Q400 AMM 27-50-00710801.FLAP POWER CAUTION DID NOT COME BACK ON.ALL OPS TEST PASS.NO FURTHER DEFECTS NOTED.

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 28,682 hrs · 31,040 cycles

EMERGENCY LIGHT SWITCH NOT ILLUMINATED AT FWD F/A STATION. REMOVED FROM SERVICE. RE-LAMPED EMERGENCY LIGHT SWITCH AT FWD F/A STATION. LIGHT CHECKS GOOD. NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: SENSOR — MALFUNCTIONED (CABIN TEMP) · airframe 28,072 hrs · 30,416 cycles

TEMPERATURE GAUGE ON F/A CONTROL PANEL RED 44 DEG IN CRUISE FLIGHT WHEN ACTUAL TEMPERATURE IN CABIN WAS APPROX. 80 DEG F. DIVERTED. LANDING UNEVENTFUL. REMOVED FROM SERVICE. REPLACED CABIN TEMP SENSOR AND CORRECTED CABIN SENSOR EJECTOR ORIENTATION. OPS CHECK GOOD. F/A PANEL READS CORRECTLY AND AGREES WITH FLIGHT DECK GAUGE. RETURNED TO SERVICE.

Part: NONE — LOOSE (ZONE 200) · airframe 29,406 hrs · 31,811 cycles

PHOTO-LUMINESCENT STRIP IN FORWARD CABIN UNSECURED. REMOVED FROM SERVICE. RE-SECURED EMER. FLOOR PATH LIGHTING AT ROW BULKHEAD REF. Q400 AMM 33-51-16-400-801. AIRCRAFT RETURNED TO SERVICE.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 27,539 hrs · 29,896 cycles

SEAT RAIL 11 FROM FSX10.50-X102.50, Y9.250 IS CORRODED BEYOND LIMITS. REPLACED SEATRAIL 11 FROM FSX 10.50-X102.50 Y9.250 IAW SRM 51-42-05-02, 51-40-15-02, 51-41-05-00, 51-40-07-02.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 27,539 hrs · 29,896 cycles

SEAT RAIL 23 FROM FSX670-X698.00,Y0.00 IS CORRODED BEYOND LIMITS. REPLACED SEAT RAIL 23 FROM FSX-X698.00,Y0.00 IAW SRM 51-42-05-02-01 AND SRM 51-42-05-000-01 REV 21.

Part: LANDING GEAR — SLOW (NOSE) · airframe 27,221 hrs · 29,587 cycles

NOSE GEAR TOOK APPROXIMATELY 10 SECONDS LONGER TO RETRACT THAN MAIN GEAR. EXTENSION TIME WAS NORMAL. REMOVED FROM SERVICE. GVI OF NLG & BAY AREA FOR DEFECTS & OPERATIONAL CHECK OF RETRACT & EXTENSION, IAW Q400 AMM TASK 32-31-00-867-802. ALL INDICATIONS NORMAL. FERRIED FOR REPAIRS. REMAINS OUT OF SERVICE.

Part: SEQUENCE VALVE — INOPERATIVE (NLG) · airframe 27,218 hrs · 29,581 cycles

NOSE GEAR TOOK 35 SECONDS TO RETRACT, GEAR TRANSITION AND UNSAFE LIGHTS EXTINGUISHED AT ACCELERATION HEIGHT. GEAR LOWERED NORMALLY (LANDING GEAR RETRACTION SYSTEM). REMOVED FROM SERVICE. R & R NLG SSV. OPERATIONS CHECK GOOD CLEAR DEFECT 927751. PLACARDS REMOVED. AIRCRAFT RETURNED TO SERVICE.

Part: APU — MALFUNCTIONED · airframe 27,211 hrs · 29,573 cycles

APU FAIL DURING START AT GATE, GROUND CREW REPORTS 2' FLAME BRIEFLY (APU INOPERABLE). REMOVED FROM SERVICE. NO PRESENT FAULTS IN CDS. 12-2,133-2,102-3,110-0054-2 AND 053-2 UNDER HISTORICAL FAULTS. C/W VISUAL INSPECTION OF APU COMPARTMENT, REF Q400 HS NR 49-0008, NO DEFECTS NOTED. PERFORMED OPERATIONAL TEST OF APU, IAW Q400 AMM TASK 49-00-00-710-801. OPERATIONAL TEST GOOD, NO DEFECTS NOTED, THIS CLEARS MEL 49-00-1. DEFERRAL PLACARDS REMOVED. NO CDS FAULTS NOTED AFTER OPERATIONS TEST. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: LIGHT — DETACHED (CABIN FLOOR) · airframe 26,706 hrs · 29,042 cycles

FLOOR LIGHTING STRIP AT 2D IS COMING UP AND IS A TRIP HAZARD. REMOVED FROM SERVICE. REINSTALLED LIGHTING STRIP AT 2D. REF Q400 AMM TASK 33-51-16-400-801 FOR WORK PERFORMED. NO OTHER DEFECTS. NO TRIP HAZARDS PRESENT. RETURNED TO SERVICE.

Part: STOP FITTING — DAMAGED (PAX DOOR) · airframe 26,593 hrs · 28,920 cycles

MAIN CABIN DOOR RUBBER STOPPER DAMAGED. DOOR HANDLE DIFFICULT TO OPEN FROM OUTSIDE. REMOVED FROM SERVICE. REMOVED AND REPLACED MAIN CABIN DOOR STOPPER. REF Q400 AMM TASK 52-11-11-400-801 STEP4(E). NO FURTHER DEFECTS. AIRCRAFT RETURNED TO SERVICE.

Part: VALVE — INOPERATIVE (HYD SYSTEM) · airframe 26,497 hrs · 28,817 cycles

NR 1 HYDRAULIC ISOLATION VALVE WITH NR 1 INBD ROLL SPOILER, THEN NR 1 ENGINE HYDRAULIC PUMP AND NR 1 HYDRAULIC QTY DEPLETED. REMOVED FROM SERVICE. REMOVED AND REPLACED THE NR 1 HYD SYSTEM BALANCED RELIEF VALVE IAW AMM 29-11-51-000/400-801. OPS TESTED GOOD. NO LEAKS AND NO ASSOCIATED CAUTION LIGHTS. AIRCRAFT RETURNED TO SERVICE.

Part: NONSKID — PEELING (CABIN) · airframe 26,228 hrs · 28,488 cycles

GRIP TAPE AT REAR OF CENTER AISLE IS PEELING UP, CREATING A TRIPPING HAZARD. REMOVED FROM SERVICE. RE SECURED GRIP TAPE. NO FURTHER TRIPPING HAZARD NOTED. NO PARTS REPLACED. RETURNED TO SERVICE.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 26,224 hrs · 28,482 cycles

CABIN PRESS MASTER WARNING ON CLIMBOUT AT 13500'. UNABLE TO CONTROL PRESSURE IN AUTO & MANUAL. DIVERTED AND ACCOMPLISHED A UNEVENTFUL LANDING. REMOVED FROM SERVICE. REPLACED ECU IAW Q400 AMM TASKS 21-61-01-000-801/400-801 OPS CHECKS GOOD A/C PRESSURIZATION SYS OP CHECKS GOOD IAW Q400 AMM TASK 21-31-00-720-801. RETURNED TO SERVICE.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 26,156 hrs · 28,400 cycles

CABIN PRESS WARNING ILLUMINATED DURING CRUISE AT 12,000'. RAN CABIN PRESS WARNING CHECKLIST. RAN PRESSURIZATION FAIL CHECKLIST, COULD NOT CONTROL CABIN PRESSURE. RAN UNPRESSURIZED FLIGHT CHECKLIST WITH OPERATIONAL BLEEDS. FLIGHT ATTENDANT REPORTED AIR "GUSHING" INTO THE CABIN THROUGH THE TYPE II/III EMERGENCY EXIT. REMOVED FROM SERVICE. OPENED TYPE II/III DOOR AND FOUND EXCESS WATER CONTAINED IN BOTTOM SILL. REMOVED WATER AND REINSTALLED DOOR REF. MCN 652577-001 ISSUE 05. ATTEMPTED CABIN PRESSURIZATION, CABIN WOULD NOT PRESSURIZE. NO FUNCTION WAS NOTED AT THE CONTROL PANEL. REMOVED AND REPLACED CABIN PRESSURE CONTROLLER REF AMM TASKS 21-31-06-000-801 AND 21-31-06-400-801. OPS CHECK NORMAL. PRESSURIZED AND DE-PRESSURIZED AIRCRAFT REF AMM TASKS 21-00-00-863-801 AND 21-00-00-863-802. PRESSURIZATION NORMAL. NO ABNORMAL AIR NOISES NOTED. RETURNED TO SERVICE.

Part: GLOWSTRIP — LOOSE (CABIN) · airframe 26,141 hrs · 28,384 cycles

PHOTO LUMINESCENT STRIP ON FLOOR AT FORWARD GALLEY LOOSE. REMOVED FROM SERVICE. RE ATTACHED PHOTO LUMINESCENT STRIP AT FWD GALLEY. OK FOR SERVICE.

Part: GUARD — LOOSE (LIGHT SWITCH) · airframe 25,961 hrs · 28,188 cycles

FOWARD FA EMER LIGHT COVER ON PANEL BETWEEN JUMPSEAT AND MCD IS ABOUT TO FALL OFF. REMOVED FROM SERVICE. INSTALLED NEW GUARD ON FORWARD FA EMERGENCY LIGHT SWITCH. OPS CHECKS GOOD. A/C OK FOR CONTINUED SERVICE. AIRCRAFT RETURNED TO SERVICE.

Part: LIGHT — LOOSE (CABIN FLOOR) · airframe 25,870 hrs · 28,084 cycles

RUBBER STRIP PEELING UP NEXT TO INTERNAL BAG DOOR. REMOVED FROM SERVICE. SEALED ALONG EMERGENCY EXIT LIGHT STRIP NEXT TO INTERNAL BAG DOOR. NO OTHER DEFECTS. RETURNED TO SERVICE.

Part: WIRE HARNESS — DAMAGED (NLG) · airframe 25,288 hrs · 27,426 cycles

GEAR HANDLE LIGHT REMAINED ILLUMINATED AFTER RETACTING THE GEAR OUT OF EUG. LDG GEAR INOP CAUTION ILLUMINATED SHORTLY AFTER. WE COMPLETED THE ALTERNATE GEAR EXTENSION CHECKLIST AND LANDED NORMALLY. REMOVED FROM SERVICE. CHECKED PSEU AND FOUND PRESENT FAULT " NGLK2 FAULT PROX SENS OPEN ". SAME FAULT RECORDED NUMEROUS TIMES IN PSEU FAULT HISTORY. REPLACED NOSE LANDING GEAR ALTERNATE-LOCK ELECTRICAL HARNESS IAW MM 32-21-11-000-801 AND 32-21-11-400-801. LANDING GEAR PRIMARY EXTENSION AND RETRACTION SYSTEM OPERATIONAL TEST GOOD 5 TIMES IAW MM TASK 32-31-00-710-801 ALL INDICATIONS NORMAL DURING OPERATIONAL TESTS. RETURNED TO SERVICE.

Part: COVER — LOOSE (EMERGENCY LIGHT) · airframe 24,922 hrs · 26,966 cycles

ESCAPE PATH LIGHTING AT FWD R/H EMERGENCY EXIT IS LOOSE AND PLASTIC COVER IS COMING OFF. R/R EMERGENCY FLOOR PATH LIGHT ASSEMBLY AT FWD R/H EMERGENCY EXIT REF Q400 AMM TASKS 33-51-16-000-801 AND 33-51-16-400-801.

Part: LIGHT — LOOSE (CABIN) · airframe 24,306 hrs · 26,232 cycles

FLORESCENT FLOOR STRIP IN FRONT OF 1B LOOSE. REMOVED FROM SERVICE. RESECURED FLORESCENT FLOOR STRIP IN FRONT OF 1B AS REQUIRED. NO OTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: CONTROL UNIT — MALFUNCTIONED (ZONE 200) · airframe 24,045 hrs · 25,931 cycles

NR 2 ARCDU SHOWED FAILED IN THE "INT" PORTION OF THE ARCDU SCREEN - NR 2 ARCDU CORRECTED THE FAIL MESSAGE WHEN CAPTAIN CALLED FA ON NR 1 ARCDU. NOTE - NO CALLS TO THE FA'S WHERE OCCURRING WHEN NR 2 ARCDU FAILED. DIVERTED. LANDING UNEVENTFUL. REMOVED FROM SERVICE. REMOVED AND REPLACED THE RCAU. OP CHECKS GOOD. OK FOR SERVICE. AIRCRAFT RETURNED TO SERVICE.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 24,000 hrs · 25,877 cycles

EMERGENCY LIGHTS AT THE LEFT AND RIGHT FORWARD EXIT SIGNS ARE INOP DURING THE OPERATIONAL CHECK. REPLACED THE BATTERY SUPPLIES IAW AMM 33-51-00-820-801. CHECKS GOOD.

Part: PROPELLER — OUT OF BALANCE · airframe 23,175 hrs · 24,951 cycles

SUBSTANTIAL VIBRATION DURING CLIMB OUT. PROPS AT 900 RPM. AIRSPEED BETWEEN 190 - 250 KIAS, LEVELED OFF AT 17,000 FT. NR 2 PROP 850 RPM, AIRSPEED 250 KIAS, VIBRATIONS REMAINED. LANDING, FLAPS DID NOT SEEM TO ALLEVIATE THE VIBRATIONS. VIBRATION FELT AND SEEN IN CONTROL COLUMN AND FELT IN CABIN. RETURNED TO FIELD. LANDING UNEVENTFUL. REMOVED FROM SERVICE. PERFORMED INITIAL EVALUATION OF THE NR 1 & 2 PROPS IPS. FOUND BOTH PROPS OUT OF LIMITS. NR 1 PROP WAS AT .209 & NR 2 PROP WAS AT 0.157. COMPLETED PROP BALANCING AND 6 BLADES RETORQUE. C/W AMM 05-50-12-200-801 BOTH PROPS BALANCED, IAW MTC 6611001 AND NR 1 ENG HTCS SERVICED IAW AMM 71-22-00-600-801. NO PARTS REPLACED. AIRCRAFT RETURNED TO SERVICE.

Part: GENERATOR — MALFUNCTIONED (NR 2) · airframe 23,104 hrs · 24,861 cycles

NR 2 AC GENERATOR CAUTION ILLUMINATED ON TAKEOFF ROLL. ATTEMPTED THE RESET PROCEDURE IAW CHECKLIST AND RESET FAILED. REMOVED FROM SERVICE. INTERROGATED EPCU AND FOUND CODE 28. REMOVED AND REPLACED THE NR 2 AC GCU FOR TROUBLESHOOTING IAW AMM 24-21-06-000-801, AND 24-21-06-400-801. DID NOT FIX PROBLEM. REMOVED AND REPLACED THE NR 2 AC GENERATOR IAW TC 6242101. OPS AND LEAK CHECKED GOOD. NO DEFECTS NOTED. RETURNED TO SERVICE.

Part: LIGHT — INOPERATIVE (SWITCH) · airframe 22,983 hrs · 24,714 cycles

FA EMERGENCY LIGHTING BUTTON INOP. NOT INDICATING GREEN/NORMAL. REMOVED FROM SERVICE. RELAMPED FA EMERGENCY SWITCH LIGHT AS REQUIRED. LAMP TEST GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 22,382 hrs · 24,047 cycles

LEVELING OFF AT FL240, NOTICIED A LOUD HISSING FROM FWD PRESSURE BULKHEAD. DIFFERENTAL GAUGE SHOWED MAX PRESSURE AND PRESSURE CONTROL SHOWED A FAULT. STARTED IMMEDIATE DESCENT AND GAUGES DESCENDED NORMALLY. FAULT LIGHT EXTINGUISHED PASSING THROUGH FL 190. PRESSURIZATION WAS NORMAL BETWEEN 12000 AND 14000 FEET. REMAINDER OF DESCENT, APPROACH AND LANDING WAS NORMAL. OUT OF SERVICE. NTERROGATED CDS. FOUND FAULT CODES FOR THE AFT OUTFLOW VALVE FAIL. COC/OF CALCE DATA FAIL. COMPLIED WITH FIM 21-30-00-810-803, STEP 4A. REMOVED AND REPLACED THE AFT OUTFLOW VALVE IAW 21-31-16-000-801, AND 21-31-16-400-801. ERASED THE DATA FROM CDS. PERFORMED A FUNCTIONAL TEST OF THE PRESSURIZATION CONTROL. FUNCTIONAL TESTED GOOD. FAULTS DID NOT COME BACK. PRESSURIZED AIRCRAFT TO 5.5 PSI IAW AMM 21-00-00-863-801, USING APU. PRESSURIZATION WAS GOOD. HISSING NOISE ISOLATED TO FUSELAGE DRAIN VALVE. R & R THE FUSELAGE DRAIN VALVE IAW AMM 53-00-06-000/400-801. PERFORMED A PRESSURIZATION OPS CHECK IAW AMM 21-00-00-863-801. HISSING NOISE DID NOT RETURN.

Part: CONTROLLER — MALFUNCTIONED (CABIN PRESSURE) · airframe 22,338 hrs · 24,007 cycles

AT 1200 MSL, NOTED THAT THE AIRPLANE HAD ALREADY DEPRESSURIZED WITH PROPER FIELD ELEVATION SET. REMOVED FROM SERVICE. COMPLIED WITH FIM 21-30-00-810-804, PARA 1 - 3 A(2), TESTED IAW TASK 21-31-00-720-801. TEST FAILED, WOULD NOT PRESSURIZE IN AUTO. NO FAULTS REPORTED BY PILOT, NO FAULTS FOUND IN CDS, COMPLIED WITH FIM 21-30-00-810-814, FUNCTIONAL TEST OF PRESSURIZATION CONTROL OPERATES AS DESCRIBED IAW AMM 21-30-00-720-801. IN AUTO AND MANUAL. CABIN PRESSURE CONTROLLER REPLACED AS A PRECAUTION. AIRCRAFT RETURNED TO SERVICE.

Part: BEARING — FAILED (ROLLER GUIDE) · airframe 22,100 hrs · 23,735 cycles

FA REPORTED THE AFT PAX DOOR WAS HARD TO OPEN AND CLOSE. REMOVED FROM SERVICE. FOUND FWD LOWER DOOR GUIDE ROLLER SEIZED. REMOVED AND REPLACED THE GUIDE ROLLER BEARING. . OPS TESTED IAW AMM 52-12-00-710-802. TESTED GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: ACTUATOR — OUT OF RIG (LT MLG) · airframe 21,990 hrs · 23,604 cycles

AFTER SELECTING LANDING GEAR UP, THE LEFT MAIN GEAR WAS SLOW TO RETRACT. APPROXIMATELY 10 SECONDS AFTER NOSE GEAR AND RIGHT MAIN GEAR INDICATED UP. REMOVED FROM SERVICE. PERFORMED GVI OF THE LT MLG IAW AMM 32-11-00-210-801. NO DEFECTS FOUND. RIGGED THE LEFT MLG RETRACTION ACTUATOR. PERFORMED AN OPS TEST EXTENSION & RETRACTION IAW AMM 32-31-00-710-801. MLG EXTENDS AND RETRACTS NORMALLY. AIRCRAFT RETURNED TO SERVICE.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,860 hrs · 23,469 cycles

SEAT RAIL 5, FS -39.00 TO X 102.5 LBL 9.25, CORRODED. REPLACED IAW SRM 51-40-15 AND 51-42-05.

Part: SEAT TRACK — CORRODED (BS 102-228) · airframe 21,860 hrs · 23,469 cycles

HORIZON SEAT RAIL #6, FSX 102.5 X 228.5, LBL 9.25, CORRODED. HORIZON SEAT RAIL #6 FSX 102.5 TO X 228.5 LBL 9.25 REPLACED IAW SRM 51-40-15 AND 51-42-05.

Part: SEAT TRACK — CORRODED (BS 102-229) · airframe 21,860 hrs · 23,469 cycles

HORIZON SEAT RAIL #18, FSX 102.5 TO X 229.5, RBL 40.95, CORRODED. CORRODED SEAT RAIL #18, FS X102.5 TO X229.5 RBL 40.95 REMOVED AND REPLACED IAW SRM 51-42-05 AND 51-40-15.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,860 hrs · 23,469 cycles

SEAT RAIL 1, FS 32.4 TO X 229.5, LBL 40.95, CORRODED. REMOVED AND REPLACED IAW SRM 51-42-05 AND 51-40-15.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,860 hrs · 23,469 cycles

SEAT RAIL 16, FS 670.0 TO FS 782.0, RBL 9.25, CORRODED. REMOVED AND REPLACED SEAT RAIL 16, FS 670.0 TO FS 782.0 RBL 9.25 IAW SRM 51-42-05, 51-40-15, 51-41-05, 51-40-07.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,860 hrs · 23,469 cycles

SEAT RAIL NR 2, FS 229.5 TO X 571.5, LBL 40.95, CORRODED. CORRODED SEAT RAIL NR 2, FS 229.5 TO X571.5 LBL 40.95 REMOVED AND REPLACED IAW SRM 51-42-05, 51-40-15, 51-42-15 AND 51-41-15.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,860 hrs · 23,469 cycles

SEAT RAIL 7, FS 228.5 TO X 570.0, LBL 9.25, CORRODED. REPLACED IAW SRM 51-40-15 AND 15-42-05.

Part: SEAT TRACK — CORRODED (BS 668-782) · airframe 21,860 hrs · 23,469 cycles

HORIZON SEAT RAIL #9 FSX 668.0 TO FSX 782.0 Y LBL 9.25, CORRODED. REMOVED AND REPLACED SEAT RAIL #9 FSX668.0 TO FSX782.0 Y LBL 9.25 IAW SRM 51-42-05, 51-40-15, 51-41-05, 51-40-07.

Part: SEAT TRACK — CORRODED (BS 229-571) · airframe 21,860 hrs · 23,469 cycles

HORIZON SEAT RAIL #19, FSX 229.5 TO X 571.5, RBL 40.95, CORRODED. CORRODED SEAT RAIL #19, FSX 229.5 TO X571.5 RBL 40.95 REMOVED AND REPLACED IAW SRM 51-42-05, 51-40-15, 51-42-15 AND 51-41-15.

Part: SEAT TRACK — CORRODED (BS 570-670) · airframe 21,860 hrs · 23,469 cycles

HORIZON SEAT RAIL #8, FSX 570.00 TO X 670.00, LBL 9.25, CORRODED. REPLACED HORIZON SEAT RAIL #8, FSX 570.00 TO X670.00 LBL 9.25 IAW SRM 51-42-05, 51-40-15 & 51-41-05.

Part: SEAT TRACK — CORRODED (BS 571-670) · airframe 21,860 hrs · 23,469 cycles

SEAT TRACK 20, BS 571.5 TO 670, RBL 40.95 CORRODED. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-42-05, AND 51-41-15.

Part: SEAT TRACK — CORRODED (BS 571-668) · airframe 21,860 hrs · 23,469 cycles

SEAT TRACK 3, BS 571.5 TO 668, LBL 40.95, CORRODED. THE SEAT WAS REMOVED AND REPLACED IAW SRM 51-42-05 AND 51-41-15.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 21,860 hrs · 23,469 cycles

SEAT RAIL 15, FS 612.0 TO X 670.0, RBL 9.25, CORRODED. CORRODED SEAT RAIL 15, FS 612.0 TO X670.0 RBL 9.25. REMOVED AND REPLACED IAW SRM 51-42-05 AND 51-40-15.

Part: SEAT TRACK — CORRODED (BS 10-39) · airframe 21,860 hrs · 23,469 cycles

SEAT TRACK NR 10, BS 39 TO 10.5, RBL 9.25, CORRODED. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-40-05, 51-40-07, 51-40-15, 51-41-05, AND 51-42-05.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 21,860 hrs · 23,469 cycles

SEAT TRACK 11 CORRODED. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-40-05, 51-40-07, 51-40-15, 51-41-05, AND 51-42-05.

Part: LAMP — INOPERATIVE (LIGHT SWITCH) · airframe 21,207 hrs · 22,788 cycles

NORMAL EMERGENCY LIGHT SWITCH BACK LIGHT IS INOPERATIVE. THE LIGHT SWITCH BACK LIGHT LAMP WAS REMOVED AND REPLACED.

Part: BRAKE SYS — CONTAMINATED (MLG) · airframe 21,104 hrs · 22,678 cycles

EXCESSIVE BRAKE APPLICATION REQUIRED TO OBTAIN MODERATE BRAKING. STOPPING CAPABILITY FELT DIMINISHED. BLEED ALL FOUR MLG BRAKE ASSEMBLIES IAW AMM 32-42-00-870-80. TAXI OPS CHECK OF THE BRAKES APPEARED TO BE NORMAL AT THIS TIME. BLEED BOTH NR 1 & 2 HYD SYSTEMS IAW AMM TASK 29-10-00-870-801/870-802. LEFT OTBD BRAKE APPEARED TO HAVE A SMALL AMOUNT OF AIR IN THE ASSY. RETURNED TO SERVICE.

Part: BLEED VALVE — MALFUNCTIONED (NR 1 ENGINE) · airframe 20,467 hrs · 22,047 cycles

THE NR 1 ENGINE FADEC CAUTION MESSAGE, ALONG WITH ASSOCIATED POWERPLANT MESSAGES. DIVERTED AND ACCOMPLISHED UNEVENTFUL LANDING. INTERROGATED CDS FOUND FAULT CODE 912 ON THE NR 1 ENGINE . REMOVED AND REPLACED NR 1 P2.2 BLEED OFF VALVE IAW MCN 67375-01 ISSUE NR 2, AND AMM TASK 75-31-11-000-801 AND 75-31-11-400-801. THE FAULT CLEARED IN CDS , GROUND RAN THE NR 1 ENGINE, THE FADEC CAUTION, AND FAULT CODE 912 CLEARED. RETURNED TO SERVICE.

Part: WARNING LIGHT — MALFUNCTIONED (NLG) · airframe 20,204 hrs · 21,780 cycles

ON DEPARTURE, RT DOOR LIGHT ON GEAR PANEL REMAINED ILLUMINATED. NLG DOOR AND GREEN GEAR LIGHTS DID EXTINGUISH. LOWERED GEAR VIA ALTERNATE GEAR EXTENSION CHECKLIST. LANDING UNEVENTFUL. INTERROGATED PSEU, CHECKED FAULT HISTORY & FOUND RGDRCL UNREASONABLE FAR. GROUND RAN ENGINES. MLG DOORS OPENS AND CLOSES NORMALLY. CHECKED THE RIGGING OF THE RGDRCL & RGUPLK IAW AMM TASK 32-61-06-830-801. VERIFIED THAT IT WAS WITHIN LIMITS. OPERATIONAL CHECK FLIGHT GOOD. RETURNED TO SERVICE.

Part: HINGE — BROKEN (PANEL) · airframe 20,160 hrs · 21,738 cycles

EMERGENCY JUMP SEAT PANEL UNDER FWD F/A JUMPSEAT NOT RETRACTING. REPLACED SPRING FOR PANEL UNDER EMERGENCY JUMP SEAT. PANEL UNDER FA JUMPSEAT (EMERGENCY PANEL) RETRACTS FINE. RETURNED TO SERVICE.

Part: PROBE — MALFUNCTIONED (PROP DEICE) · airframe 19,667 hrs · 21,223 cycles

PROP DEICE ADVISORY LIGHTS DO NOT CYCLE. DIVERTED AND ACCOMPLISHED UNEVENTFUL LANDING. FOUND NO CDS FAULTS ON ICE AND RAIN PG. TMCU 1 & 2 SHOWED AIRINC RECEIVE BUSS 2/1 FAULTS. R & R STATIC TEMP PROBE IAW AMM TASKS 34-11-11-000-801 & 400-801. PROBE OPS CHECKED GOOD IAW AMM TASK 34-11-710-801. COMPLIED WITH FUNCTIONAL TEST OF PROP DE-ICING SYSTEM IAW AMM TASK 30-61-00-720-801. OP CHECKED GOOD. ALL TMCU FAULTS CLEARED. RETURNED TO SERVICE.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 19,343 hrs · 20,869 cycles

DURING CLIMB, PASSING 11,000 FT, HEARD AN AUDIBLE POPPING SOUND AND FELT A PRESSURE CHANGE, OBSERVED THE CABIN RATE OF CLIMB MAXED, CABIN ALT CLIMBING AND DIFF PRESS DECREASING. DESCENDED BACK DOWN TO 10,000 FEET AND COMPLETED THE LOSS OF CABIN PRESSURIZATION CHECKLIST. PRESSURIZATION OPERATION RETURNED TO NORMAL OPERATION. FOUND CDS FAULTS, CP CONTROLLER FAIL AND CPC/OF VALVE DATA FAIL. REPLACED CPC IAW AMM 21-31-06-000-801, 21-31-06-400-801 WITH ENGINES. PRESSURIZED AIRCRAFT IAW AMM 21-00-00-863-801 WITH ENGINES. PRESSURIZED GOOD. DEPRESSURIZED IAW AMM 21-00-00-863-802. PER MTX CONTROL, REMOVED AND REPLACED AFT OUTFLOW VALVE IAW AMM 21-31-10-000-801, 21-31-10-400-801. FUNCTIONAL CHECK GOOD AND PRESSURIZATION GOOD. PER MAINTENANCE CONTROL PERFORMED LEAK DOWN CHECK OF RESERVOIR. LEAK DOWN FAILED. FOUND SMALL CUT ON BOTTOM OF AFT CARGO DOOR SEAL. REPLACED SEAL. RETURNED TO SERVICE.

Part: BLOWOUT PANEL — LOOSE (CARGO BAY) · airframe 19,292 hrs · 20,831 cycles

DURING APPROACH AT 4,000 FEET, THERE WAS A NOISE, THEN THE RATE OF DESCENT WENT DOWN BY 3000 FEET FOR ABOUT 3 SECONDS, THEN BACK TO NORMAL. FOUND CARGO PIT BLOW OUT PANEL LOOSE. TOO LOOSE TO RESECURE, SO REPLACED PANEL IAW AMM 25-52-01-00-802/400-802. OPS CHECKED GOOD. RETURNED TO SERVICE.

Part: TIRE — FAILED (MLG) · airframe 18,860 hrs · 20,369 cycles

RT MAIN LANDING GEAR NR 3 TIRE TREAD CAME OFF DURING TAKE-OFF ROLL. FLIGHT CONTINUED. REPLACED 3 MLG TIRE AND WHEEL ASSY. REPLACED NR 4 MLG TIRE & WHEEL ASSY. COMPLIED WITH CHAPTER 5 INSP. AFTER A TIRE FAILURE.

Part: WARNING LIGHT — ILLUMINATED (NR 2 BLEED) · airframe 18,836 hrs · 20,336 cycles

NR 2 BLEED HOT CAUTION ILLUMINATED IN FLT. RETURNED TO FIELD. LANDING UNEVENTFUL. AFTER LANDING ACCOMPLISHED FSM BLEED HOT CAUTION RESET PROCEDURE. BLEED HOT CAUTION DID NOT ILLUMINATE.

Part: TRANSCEIVER — FAILED (WX RADAR) · airframe 18,689 hrs · 20,191 cycles

WEATHER RADAR FAILED ENROUTE. DIVERTED AND ACCOMPLISHED A UNEVENTFUL LANDING. REMOVED & REPLACED WEATHER RADAR TRANSCEIVER IAW AMM 34-41-01-000 & 400-801, OPS CHECKED GOOD.

Part: IGNITER — FAULTED (APU) · airframe 18,323 hrs · 19,802 cycles

PU FAIL ON LIGHT UP. ALSO NOTICED FUEL SPILLED ONTO RAMP AFTER LIGHT UP FAIL. RAMPERS NOTICED FUEL MISTING AND FUEL ODOR ON RAMP. CHECKED CDS FOR FAULT CODES, FOUND FAULT 55-2 IGNITER PLUG B OPEN. C/W FIM TASK 49-40-00-810-803 FOR FAULT ISOLATION. R & R BOTH IGNITOR PLUGS REF AMM TASK 49-40-04-000-801/400-801. SERVICED APU WITH OIL, OPS CHECK GOOD. MEL CLEARED.

Part: TRANSDUCER — MALFUNCTIONED (BRAKES) · airframe 18,174 hrs · 19,644 cycles

BRAKING ACTION FOR ACFT, MARGINAL AT HIGH SPEEDS. BRAKES MUSHY AT ALL SPEEDS INCLUDING TAXI SPEEDS. R & R NR 4 MLG WHEEL SPEED TRANSDUCER IAW AMM TASK 32-46-11-000/400-801. ALL TEST GOOD BRAKES NO LONGER MUSHY NO FURTHER DEFECTS, RETURN TO SERVICE.

Part: BRAKE SYS — MALFUNCTIONED (MLG) · airframe 17,492 hrs · 18,868 cycles

MAIN BRAKES ARE NOT RESPONSIVE, WITH OR WITHOUT THE ANTI-SKID BEING ON. PERFORMED VISUAL INSPECTION OF BRAKES AND BRAKE LINES, CONNECTIONS FOR LEAKS WITH NO LEAKS NOTED. C/W BLEED THE BRAKES WITH MAIN BRAKE SYS, REF Q400 AMM TASK 32-42-00-870-801. TAXIED ACFT, FOUND BRAKES TO OPERATE NORMAL, WITH NO DEFECTS NOTED. RETURNED TO SERVICE.

Part: COVER — DETACHED (EMERGENCY LIGHT) · airframe 16,792 hrs · 18,122 cycles

EMERGENCY EXIT SIGN ON THE FORWARD EMERGENCY EXIT DOOR IS VERY LOOSE. COVER FELL OFF. SECURED COVER. NO OTHER DEFECTS NOTED. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 16,080 hrs · 17,370 cycles

REMOVE SEAT TRACK NR 10 AND REPLACED PN 85328210-121. DUE TO CORROSION BEYOND LIMITS. DISCONNECTED MAIN ENGINES GROUND CABLE FROM SEAT TRACK NR 10 TO FOM REF SRM 51-41-00-00-01 AT BS X-39. GROUND CABLE RECONNECTED REF SRM 51-41-00. BONDING CHECK PERFORMED READINGS GOOD 2.87MO, REF AMM 51-80-00-760-801, TABLE 8. DISPLACED WIRE BUNDLE FROM SEAT TRACK NR 10 AT BS X-24 TO X38 TO FOM 7 EA IAW WM 20-12-10. PLACED WIRE BUNDLE ON SEAT TRACK NR 10 BS X-24 TO X38 7 EA REF WM 20-12-10, STEP 4. REMOVED KICK PLATE, PN 85311097-105 FROM N434MK, BS X-39 TO FOM REF SRM 51-42-45-02, 6H91-2. KICKPLATE INSTALLED REF SRM 51-42-45. REMOVED SEAT TRACK 10, PN 85328210-121 FROM N434MK AT BS X-39 & Y9.250, REF SRM 51-40-15-02-0

Part: PLATE — CORRODED (ZONE 100) · airframe 16,080 hrs · 17,370 cycles

UPPER TCAS ANTENNA MOUNTING PLATE HAS EVIDENCE OF CORROSION, UPPER FUSELAGE. REMOVED 7 EA INSULATION BLANKETS UNDER UPPER TCAS ANTENNA TO FOM REF AMM 25-80-01-000-801. INSTALLED 7 EA INSULATION BLANKETS UNDER UPPER TCAS ANTENNA REF AMM 25-80-01-400-801. DISPLACED 1 EA WIRE BUNDLE BY REMOVING BOLT AND SPACER AND CLAMPS 4 EA TO FOM REF SRM 51-41-00 STRUCT IDENT -01. INSTALLED 1 EA BOLT AND SPACER TO SECURE 4 EA CLAMPS TO SECURE 1 EA WIRE BUNDLE REF SRM 51-41-00, PG 1, STEP 3. DRILLED OUT 95 PERCENT OF RIVETS OF UPPER TCAS ANTENNA MOUNTING PLATE REF SRM 51-42-05, REPAIR 01, P.205, STEP 4E. COMPLETED REMOVAL OF UPPER TCAS ANTENNA MOUNTING PLATE REF SRM 51-42-05-02-01, 4E, 1-8. INSTALLED, NEW, UPPER TCAS ANTENNA MOUNTING PLATE IAW SRM 51-42-05, PN 85307805-051. FORM M-184 COMPLIED WITH. REMOVED UPPER TCAS ANTENNA DOUBLER IAW SRM 51-42-05. REPAIR-01, PG 205, STEP 4 E. INSTALLED UPPER TCAS ANTENNA DOUBLER IAW SRM 51-42-05, PN 85307889-101. LOCATED AND DRILLED UPPER TCAS ANTENNA DOUBLER REF SRM 51-40-07, REPAIR-01, PN QX85307889-101. LOCATED AND DRILLED UPPER TCAS ANTENNA MOUNTING PLATE REF SRM 51-40-07, REPAIR-01, PN 85307805-051, PO TX-3262. CONTINUED TO COUNTERSINK UPPER TCAS MOUNTING PLATE IAW SRM 51-40-07, ALL HOLES COMPLIED WITH.

Part: SKIN — DAMAGED (BS 156) · airframe 16,080 hrs · 17,370 cycles

DENT WITH GOUGE-JUST AFT OF FS, FS 156.000, BETWEEN STR 23P- STR 24P. REMOVED PAINT FROM DENT WITH GOUGE BETWEEN STR 23P AND 24P JUST AT OF FX 156.0 IAW SRM 53-00-00. REPAIR 02, PARA 7A, DENT ASPECT RATIO MEASURMENT IS .350/.017=20.5 PERCENT WHICH IS GREATER THAN 20, MEASURMENT TAKEN USING DEPTH GAUGE, TUC:5728, DUE 5/16. DENT WITHIN ALLOWABLE LIMITS IAW SRM 53-00-00-02-02. RECEIVED ENGINEERING REF FT05-15-17745525, STATING ACCOMPLISH REPAIR IAW SRM 53-00-00-02-08, DATED. DRILLED A HOLE AND REAMED TO 0.128/0.133 DIAMETER TO REMOVE THE DAMAGE IAW SRM 53-10-31, REPAIR -02, STEPS 5.C, TABLE 1. C/W ET INSP ON REWORKED AREA REF NDTM PT.1 51-00-06. NO DEFECTS NOTED. WET INSTALLED RIVET IAW SRM 53-10-31, REPAIR 02, STEP 5C, TABLE 1 AND SRM 51-42-05, STEP 4D. RESTORED FINISH IAW SRM 51-21-10, REPAIR-01 AND SRM 51-25-15, REPAIR-01. APPLIED YELLOW DOT TO DENT AREA IAW GPM 10.11.3. ENTERED DMI 689381. PERFORMED REPAIR FOR GOUGE IN DENTED AREA, REF SRM 53-00-00-02-08.

Part: PLATE — CORRODED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

KICKPLATE, HAS AN INNER GRANULAR CORROSION. DRILLED, COUNTERSUNK HOLES AND LOCATED THE KICK PLATE, IAW SRM 51-40-07. DRILLED, COUNTERSUNK AND INSTALLED A NUTPLATE ON THE PLATE IAW SRM 51-42-05-02-01 4D(3-11). KICK PLATE INSTALLED IAW SRM 51-42-45, COMPLIED WITH M-184.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

SEAT TRACK NR 14, CORRODED OUT OF LIMITS. REMOVED AND REPLACED THE SEAT TRACK IAW SRM 51-40-15, STEP 6M, SRM 51-42-05, STEP 4 E, SRM 51-41-00, AND DWG 85338201, REV D.

Part: DOUBLER — CORRODED (SERVICE PORT) · airframe 16,080 hrs · 17,370 cycles

LAVATORY SERVICE PORT EXTERNAL DOUBLER IS CORRODED. REMOVED INTERNAL DOUBLER BS 1.0 TO BS -18.2 STRINGERS 25 - 27R IAW SRM 51-42-05. DOUBLER INSTALLED, IAW SRM 51-42-05, DWG 85327507 REV B.

Part: SEAT TRACK — NOT REPORTED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

SEAT TRACK, NR 8, REQUIRES REPLACEMENT. REMOVED THE SEAT TRACK IAW SRM 51-40-15-02-01, STEP 6M. INSTALLED A NEW SEAT TRACK IAW SRM 51-42-05, STEP 4D, & SRM 51-40-15, REPAIR-01 AND SRM 51-41-00.

Part: SEAT TRACK — NOT REPORTED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

SEAT TRACK NR 15, PN 85338210-115, REQUIRES REPLACEMENT. NOTE: DUE TO CORROSION OUT OF LIMITS. REMOVED SEAT TRACK, PN:85338210-113 REF SRM 51-40-15, STEP 6M, SRM 51-42-05, STEP 4.E. INSTALLED SEAT TRACK, PN:85338210-115, REF SRM 51-41-00, SRM 51-42-05, SRM 51-40-15 AN DWG 85338201, REV D. LOCATED AND DRILLED NEW SEAT TRACK, PN:85338210-113, REF SRM 51-40-07.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

SEAT TRACK NR 13 CORRODED BEYOND LIMITS; LOCATED AND DRILLED SEAT TRACK NR 13 IAW SRM 51-40-07. INSTALLED SEAT TRACK, IAW SRM 51-41-00, SRM 51-42-05, STEP 4D, 2-10, SRM 51-40-15, STEP 6H AND 6J, DWG 85361501, REV E.

Part: SEAT TRACK — NOT REPORTED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

REMOVE SEAT TRACK NR 11 AND REPLACE PN 85328210-115. REMOVED SPLICE PLATES RT AT BS 100, COMMON TO SEAT TRACK 11 AND 12 FOR FOM REMOVAL OF SEAT TRACK 11 IAW SRM 51-42-05. INSTALLED SEAT TRACK SPLICE COMMON TO SEAT TRACK 11 & 12 IAW SRM 51-40-15, 51-40-05, DWG 85328201, REV E, 10/19/13. REMOVED 14 EA RIVETS FROM WEB TO SEAT TRACK NR 11 AT BS 19 TO 31 RT IAW SRM 51-42-05. 14 EA RIVETS INSTALLED TO WEB ON SEAT TRACK NR 11 AT BS 19-31 RT REF SRM 51-42-05, DWG: 85328201, REV E, DATED 2013/01/19. REMOVED 10 EA BOLTS IN SEAT TRACK NR 11 SUPPORT STRAPS AT RT BS 10-100 IAW SRM 51-41-00-00-01. INSTALLED 10 EA BOLTS IN SEAT TRACK NR 11 SUPPORT STRAPS AT RT BS 10-100 IAW SRM 51-41-00-00-01. REMOVED SPLICE PLATES AT RT BS 10.0 COMMON TO SEAT TRACK 10 AND 11 IAW SRM 51-42-05 AND 51-40-15. INSTALLED SPICE PLATES AT RT BS 10.0 COMMON TO SEAT TRACK 10 AND 11 IAW SRM 51-42-05 AND 51-40-15. REMOVED NR 11 SEAT TRACK, RT BS 10-100 IAW SRM 51-42-05 AND 51-41-00-00-01 AND 51-40-15. LOCATED NEW NR 11 SEAT TRACK AND DRILL IAW DWG: 85328201, SEAT TRACK, PN:85328210-115. CONTINUED AND DRILLED AND LOCATED NR 11 SEAT TRACK IAW SRM 51-40-07.

Part: SEAT TRACK — NOT REPORTED (NOT REPORTED) · airframe 16,080 hrs · 17,370 cycles

SEAT TRACK NR 12, PN 85328210-112, REQUIRES REPLACEMENT. REMOVED DRIP ANGLE, PN 85307401-16 FROM SEAT TRACK NR 12 TO FOM REF SRM 51-42-05 & SRM 51-40-15. INSTALLED DRIP ANGLE, PN 85307401-16 ON SEAT TRACK NR 12, REF SRM 51-42-05-02. DISPLACED WIRE BUNDLES AT 9 LOCATIONS FROM SEAT TRACK NR 12 TO FOM REF WM 20-12-10. INSTALLED WIRE BUNDLES, 9 ON SEAT TRACK NR 12 IAW WIRING MANUAL 20-12-10, STEP 5. DISCONNECTED A GROUND WIRE SWITCH FROM SEAT TRACK NR 12 AT BS 176 TO 290 TO FOM REF SRM 51-41-00. INSTALLED GROUND WIRE SWITCH ON SEAT TRACK NR 12 AMM 23-35-51-400-001, FIG 402. REMOVED SEAT TRACK NR 12, PN 85338210-112 FROM N434MK AT BS X102.5 TO X229.5, REF SRM 51-40-15, SRM 51-42-05 AND SRM 51-41-00. INSTALLED SEAT TRACK NR 12 IAW SRM 51-40-15, 51-40-00, DWG 85328201, REV E 2013-01-19. LOCATED AND DRILLED NEW SEAT TRACK NR 12, PN 85328210-112, REF DWG 85328201, REV E 01/19/2013. LOCATED AND DRILLED DRIP ANGLE COMMON TO SEAT TRACK NR 11 AND SEAT TRACK NR 12, REF SRM 51-40-07, REPAIR-01. RESTORED FINISH TO DRIP TRAY ANGLE RIVETS REF SRM SEC 51-25-10.

Part: SEAT TRACK — CORRODED · airframe 15,994 hrs · 17,286 cycles

CORROSION FOUND IN VARIOUS LOCATIONS ON SEAT TRACK, NR 3 PN:85338261-101. BLENDED DAMAGE AREAS ON SEAT TRACK NR 3. ORIGINAL THICKNESS ON UPPER CLAW IS .420, REMOVED .006 MAX ALLOWED IS .015 REMAINING THICKNESS IS .414 ORIGINAL THICKNESS OF INNER CLAW PORTION 15 .160 REMOVED, .006 MAX ALLOWED IS .035 REMAINING THICKNESS IS .154 FOUND TO BE WITHIN LIMITS, REF SRM 53-20-49, REPAIR OZ, PG 205, FIG 201, SHEET 3. C/W ET INSP ON REWORKED AREAS REF NDTM PT1 51-00-06. NO DEFECTS NOTED. APPLIED ALODINE TO BARE METAL ON SEAT TRACK NR 3 REF SRM 51-21-10-02-01. COMPLIED WITH FORM M-184.

Part: SEAT TRACK — CORRODED · airframe 15,994 hrs · 17,286 cycles

CORROSION FOUND IN VARIOUS LOCATIONS ON SEAT TRACK NR 1 PN:85328261-107. BLENDED DAMAGED AREAS OF SEAT TRACK NR 1. ORIGINAL THICKNESS OF UPPER CLAW IS 0.420. REMOVED 0.010 MATERIAL MAX REMOVAL ALLOWED 0.015. MATERIAL REMAINING IS 0.410 ORIGINAL THICKNESS ON INNER CLAW PORTION IS 0.160. REMOVED 0.027 MAX REMOVAL ALLOWED IS 0.035. REMAINING THICKNESS IS 0.133 FOUND TO BE WITHIN LIMITS REF SRM 53-20-49, REPAIR-02, PG 205, FIG 201, SHEET 3. C/W ET INSP ON REWORKED AREAS REF NDTM PT1 51-00-06. NO DEFECTS NOTED. APPLIED ALODINE TO BARE METAL ON SEAT TRACK NR 1, REF SRM 51-21-10-02-01. COMPLIED WITH FORM M-184.

Part: SEAT TRACK — CORRODED · airframe 15,994 hrs · 17,286 cycles

CORROSION FOUND ON VARIOUS AREAS OF SEAT TRACK NR 18. REMOVED CORROSION ON VARIOUS AREAS OF SEAT TRACK NR 18, PN 85328261-105, REF SRM 53-20-49, REPAIR-02. RT SIDE OTBD SEAT TRACK. MAXIMUM MATERIAL ALLOWABLE TO REMOVE IS .015" ON TOP CLAW AND .035" ON INSIDE OF CLAW PORTION OF OTBD SEAT RAIL IAW SRM 53-20-49, REPAIR-02. REMOVED .003" MATERIAL ON TOP CLAW AND .006" ON INSIDE CLAW AT LOWEST POINT OF BLEND. SEAT TRACK NR 18 WITHIN LIMITS. VERIFIED WITH TOOL. FORM M-184 CORROSION REPORT. ET INSP ON REWORKED AREAS REF NDTM PT.1 51-00-06. NO DEFECTS NOTED. APPLIED ALODINE TO BARE METAL ON SEAT TRACK NR 18 REF SRM 51-21-10-02-01.

Part: SEAT TRACK — CORRODED · airframe 15,994 hrs · 17,286 cycles

CORROSION FOUND IN VARIOUS LOCATIONS ON SEAT TRACK NR 2, PN: 85361561-103. BLENDED DAMAGE AREAS ON SEAT TRACK NR 2. ORIGINAL THICKNESS ON UPPER CLAW IS 0.420. REMOVED 0.011, OF MATERIAL MAX ALLOWED IS .015. REMAINING MATERIAL IS .409. ORG THK ON INNER PORTION IS .160. REMOVED .025. MAX ALLOWED IS .035. REMAINING MATERIAL IS .135 FOUND TO BE WITHIN LIMITS REF SRM 53-20-49, REPAIR-02, PG 205, FIG 201, SHEET 3. C/W ET INSP ON REWORKED AREAS REF NDTM PT1 51-00-06. NO DEFECTS NOTED. APPLIED ALODINE TO BARE METAL ON SEAT TRACK NR 2 REF SRM 51-21-10-02-01. COMPLIED WITH FORM M-184.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 15,994 hrs · 17,286 cycles

CORROSION FOUND IN VARIOUS LOCATION ON SEAT TRACK NR 5 . SEAT TRACK NR 6 FOUND TO BE WITHIN TOLERANCE OF SRM 53-20-49, FIG 201, SHEET 2, MAX DEPTH .005", UPPER CLAW AREA, DEEPEST DEPTH ON LOWER CLAW AREA .025". CHECKED WITH TUC DEPTH GAUGE NR 4745, DUE 2/28/16. C/W ET INSP ON REWORKED AREAS REF NDTM PT.1 51-00-06. NO DEFECTS NOTED, NDT REPORT. CLARIFICATION STATEMENT FOR ITEM NR 1: SEAT TRACK CORROSION BLENDED, REF SRM 53-20-49. C/W HORIZON FORM M-184. RESTORED FINISH TO BARE METAL ON SEAT TRACK NR 5 REF SRM 51-21-10-02-01.

Part: SEAT TRACK — CORRODED (NOT REPORTED) · airframe 15,994 hrs · 17,286 cycles

CORROSION FOUND IN VARIOUS LOCATIONS OF SEAT TRACK NR 6, PN:85328210-111. SEAT TRACK NR 5 FOUND TO BE WITHIN TOLERANCE OF SRM 53-20-49, UPPER CLAW AREA. FIG 201, SHEET 2. MAX DEPTH 0.005", DEEPEST DEPTH ON LOWER CLAW AREA .025. CHECK WITH TUC DEPTH GAUGE NR 4745. C/W ET INSP ON REWORKED AREAS REF NDTM PT 1, 51-00-06. NO DEFECTS NOTED. NDT REPORT. CLARIFICATION STATEMENT FOR ITEM NR 1: SEAT TRACK CORROSION BLENDED, REF SRM 53-20-49. C/W HORIZON FORM M-184. RESTORED FINSH TO BARE METAL ON SEAT TRACK NR 6 REF SRM 51-21-10-02-01.

Part: RELIEF VALVE — FAILED (HYD SYSTEM) · airframe 15,633 hrs · 16,902 cycles

NR 1 HYD PUMP CAUTION LIGHT ILLUMINATED. RAN THE CHECKLIST, ELEVATOR CAUTION ILLUMINATED AFTER PUSHING THE NR 3 HYD ISOLATION VALVE IAW THE CHECKLIST FOR THE NR 1 HYD PUMP CAUTION. PERFORMED VISUAL INSPECTION, FOUND THE NR 1 ENGINE NACELLE DRY AND FLUID ALONG BELLY FROM WING SECTION AFT. INSPECTED AND FOUND 1 HYD SYS BALANCED RELIEF VALVE REPLACED BALANCED RELIEF VALVE IAW 29-11-51-000-801/400-801. NO LEAKS NOTED. COMPLIED WITH T/C CSL84-29-071. REPLACED NR 1 EDP, NO LEAKS NOTED. OPS CHECKS GOOD. COMPLIED WITH MCN NR 5114929232/1. COMPLIED WITH GVI OF SPU, NO LEAKS OR DEFECTS NOTED. COMPLIED WITH TASK 05-54-00-280-801, PAR 1 THROUGH 5A3 AND 6AB. NO FURTHER DEFECTS OR LEAKS NOTED. RETURNED TO SERVICE.

Part: LIGHT — UNSECURE (CABIN) · airframe 15,582 hrs · 16,849 cycles

EMERGENCY LIGHT STRIP IN FWD GALLEY IN UNATTACHED. RESECURED FLOOR PATH STRIP. RETURNED TO SERVICE.

Part: CHANNEL — CORRODED (THRESHOLD) · airframe 14,580 hrs · 15,794 cycles

FWD PAX DOOR THRESHOLD CHANNEL ASSY CORRODED. REMOVED CHANNEL IAW SRM 51-42-05, REPAIR-01 PARA 4; E STEPS(1-8). INSTALLED NEW CHANNEL IAW SRM 51-42-05.

Part: ATTACH FITTING — CORRODED (DOOR SILL) · airframe 14,580 hrs · 15,794 cycles

FWD PAX DOOR LOWER SILL FS 19.5 CLEAT IS CORRRODED. REMOVED CLEAT IAW SRM 51-40-15 AND INSTALLED A NEW CLEAT IAW SRM 51-42-05 AND SRM 51-40-15.

Part: ANGLE — CORRODED (PAX DOOR) · airframe 14,580 hrs · 15,794 cycles

FWD PAX DOOR ANGLE CORRODED AT FS X5 AND FS X27. LOCATED AND DRILLED NEW ANGLE IAW SRM 51-40-07.

Part: INTERCOSTAL — CORRODED (PAX DOORWAY) · airframe 14,580 hrs · 15,794 cycles

FWD PAX DOOR HAS AN INTERCOSTAL CORRODED AT STRINGER 25P. LOCATED FIT AND DRILLED NEW INTERCOSTAL IAW SRM 51-40-07. INSTALLED NEW INTERCOSTAL IAW SRM 51-42-05-02-01, SRM 51-40-15-02-01, AND SRM 51-41-05.

Part: EXTINGUISHER — LOW PRESSURE (CARGO BAY) · airframe 14,040 hrs · 15,223 cycles

CHECK FIRE DETECTOR WARNING LIGHT ILLUMINATED RT AFT BAGGAGE BOTTLE LOW. REPLACED AFT HIGH-RATE FIRE BOTTLE IAW AMM TASKS 26-22-02-000-801 & 26-22-02-400-801. OPS CHECKED GOOD. RETURNED TO SERVICE.

Part: DUCT — LOOSE (CABIN PRESSURE) · airframe 14,031 hrs · 15,218 cycles

ACFT WOULD NOT PRESSURIZE ON TAKEOFF. RETURNED TO FIELD. LANDING UNEVENTFUL. FOUND CLAMP CONNECTING COMPRESSOR OUTLET DUCT AND COMPRESSOR OUTLET CROSSOVER DUCT FROM THE LT AIR CONDITIONING PACK CAME LOOSE AND LEAKING AIR. R & R LT COMPRESSOR OUTLET DUCT AND COMPRESSOR OUTLET CROSSOVER DUCT, REF AMM 21-51-21-000-801/400-801. PRESSURIZED THE ACFT IAW 21-00-00-863-801. PRESSURIZATION CHECK GOOD. ACM AIRFLOW CHECKS GOOD. NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: LAMP — INOPERATIVE (LIGHT SWITCH) · airframe 13,696 hrs · 14,865 cycles

FWD F/A EMERGENCY LIGHT IS OUT. REPLACED THE LAMP IN UPPER GREEN PORTION OF SWITCH, EMERGENCY LIGHTS, OPS CHECKED GOOD. RETURNED TO SERVICE.

Part: BRAKE SYS — MALFUNCTIONED (MLG) · airframe 13,599 hrs · 14,765 cycles

BRAKES ARE VERY SOFT, FULL APPLICATION REQUIRED TO SLOWLY DECELERATE ACFT. INTERROGATED CDS, NO FAULTS FOUND FOR THE ANIT-SKID SYS. PERFORMED A GVI OF ALL 4 MAIN BRAKES, NO DEFECTS NOTED. BLED THE BRAKES IAW AMM TASK 32-42-00-870-801. TAXIIED THE ACFT, MADE NUMEROUS STOPS USING VARIOUS BRAKING APPLICATIONS. NO DEFECTS NOTED. OPS CHECK FLIGHT DETERMINED TO BE NOT REQUIRED. PERFORMED HIGH SPEED TAXI WITH CREW, GREATER THAN 60 KTS, ACFT BRAKES NORMALLY, NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE.

Part: SOCKET — LOOSE (MLG IDICATOR) · airframe 13,194 hrs · 14,307 cycles

NORMAL APPROACH AND LANDING, THREE GREEN GEAR DOWN AND LOCKED INDICATION. DURING FINAL, RT MAIN GEAR INDICATION WENT DARK, NO GREEN, MISSED NORMAL APPROACH. LAMP TESTED TO CHECK BULB, BULB FLICKERS GREEN TO DARK, PUSH ON LIGHT FIXTURE BULB STAYS STEADY GREEN. RETURN FOR NORMAL LANDING WITH THREE GREEN INDICATIONS ON HANDLE PANEL AS WELL AS FLOOR PANEL. NO ALTERNATE EXTENSION. LANDING UNEVENTFUL. REPLACED LANDING GEAR CONTROL PANEL IAW AMM TASKS 32-31-01-000-801 AND 32-31-01-400-801. OPS CHECKED GOOD. RETURNED TO SERVICE.

Part: SEAL — MISSING (DITCHING DAM) · airframe 13,117 hrs · 14,226 cycles

PART OF THE DITCHING DAM RUBBER SEAL MISSING ON MAIN CABIN DOOR. R & R FWD MCD AIRSTAIR DITCHING DAM IAW AMM TASKS 25-62-01-000-801 AND 25-62-01-400-801. APPLIED MISSING PLACARDS ON TOP EDGE OF NEW DITCHING DAM. RETURNED TO SERVICE.

Part: PROPELLER — MALFUNCTIONED (LEFT) · airframe 12,778 hrs · 13,879 cycles

ON FINAL APPROACH AT 125 KTS IAS, LT PROPELLER RPM DECREASED FROM 1020 RPM TO 980 RPM. INTERROGATED CDS. NO FAULTS FOUND. COMPLIED WITH ENGINE TREND DOWNLOAD MAINTENANCE 6773101. VERIFIED MEASURED BETA CALIBRATION MEASURMENT TO BE WITHIN LIMITS. REMOVED AND REINSTALLED BETA TUBE IAW MAINTENANCE 6610001 AND 6610002. ALL OPS TESTS GOOD. NO LEAKS NOTED. NO PROP RPM FLUCTUATIONS NOTED DURING RUNS. RETURNED TO SERVICE.

Part: STOP — DAMAGED (PAX DOOR) · airframe 11,577 hrs · 12,606 cycles

F/A REPORTS MAIN CABIN DOOR DIFFICULT TO OPEN. R & R THE UPPER AFT STOP. RIG CHECKED REF 52-11-00-820-801, STEP 4 A. (10) (D). COMPLYED WITH OPS TEST IAW 52-11-00-710-802 CHECKS NORMAL. RETURNED TO SERVICE.

Part: BULKHEAD — LOOSE (CABIN) · airframe 11,552 hrs · 12,578 cycles

F/A REPORTS BULKHEAD PANEL TO RT OF MCD IS LOOSE. SECURED LEFT FWD BULKHEAD BY CLOSING LATCH'S. NO OTHER DEFECT NOTED. RETURNED TO SERVICE.

Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 11,106 hrs · 12,142 cycles

MAIN CABIN DOOR DIFFICULT TO CLOSE SCREW ON RT RAIL HITTING SIDEWALL. FOUND FWD BULKHEAD ON RT SIDE OF MAIN CABIN DOOR LOOSE AND INTERFERING WITH DOOR CLOSING. SECURED BULKHEAD. NO DEFECTS NOTED. MAIN CABIN DOOR OPEN AND CLOSED AS REQUIRED. RETURNED TO SERVICE.

Part: SHAFT — CORRODED (PAX DOOR) · airframe 10,385 hrs · 11,359 cycles

FWD PAX DOOR SHAFT ASSY BETWEEN LOWER NEWELS CORRODED. R & R WITH NEW FWD PAX DOOR SHAFT ASSY BETWEEN LOWER NEWELLS IAW AMM’S 52-11-21-000-801 STEP 4A (1 THROUGH 4) AND 52-11-21-400-801 STEP 4H (1 THROUGH 4) REV 40. ACCOMPLISHED STEPS 4H(7 AND 8) OF AMM TASK 52-11-21-400-801 REV 40.

Part: STOP FITTING — DAMAGED (PAX DOOR) · airframe 10,385 hrs · 11,359 cycles

PAX DOOR SURROUND STOP FITTING WORN AND CORRODED. SMOOTHED DAMAGE IAW SRM 51-14-00-02-04, REV 12. CONFIRMED AFFECTED AREAS OF FITTINGS CRACK FREE REF NTM 51-00-06-910-801, PT1, REV 7. FOUND TO BE IN LIMITS, IAW RD8/4-53-5225 ISS NR 1.

Part: ATTACH FITTING — CORRODED (PAX DOOR) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON LOWER FWD PAX DOOR SHELL ATTACH FITTING. REMOVED LOWER FWD PAX DOOR SHELL ATTACH FITTING IAW AMM 52-11-06-000-801, STEPS 1-3 (4B7) REV 40. PAINTED SERVICABLE PART FITTING IAW AMM 51-25-31-370-801. INSTALLED LOWER FWD PAX DOOR SHELL ATTACH FITTING IAW AMM 52-11-06-400-801 STEPS 1-3, 4 (A4-5) AND 5(C) REV 40.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 262FT IS CHAFED ON MATING SURFACE. REMOVED FASTENERS AS REQUIRED IAW SRM 51-44-30-02-01, REV 12. REMOVED DAMAGE IAW SRM 51-14-00-02-03, REV 12. MECHANICALLY MEASURED MIN REMAINING THICKNESS IS 0.098" IN LIMITS IAW SRM 53-75-06-02-01, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT 1 REV 7. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01 REV 12. INSTALLED FASTENERS IAW SRM 51-44-30-02-01, REV 12. VERIFIED SATISFACTORY GRIP LENGTH IAW SRM 53-75-06-02-01, REV 12.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 262AT IS CHAFED ON MATING SURFACE. REMOVED DAMAGE IAW SRM 51-14-00-02-03, REV 12. CONFIRMED AFFECTED AREA CRACK FREE NTM 51-00-06-910-801 PT REV 7. DAMAGE IS IN LIMITS IAW SRM 53-75-06-02-01, REV 12.

Part: SKIN — CHAFED (RT WING TE FLAP) · airframe 10,385 hrs · 11,359 cycles

RT WING OTBD FLAP UPPER SURFACE IS CHAFED. SANDED AFFECTED AREA IAW AMM 51-25-31-370-801, REV 40. SMOOTHED OUT DAMAGE IAW SRM 57-23-30-02-02, REV 12. FOUND TO BE OUT OF LIMITS. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6 TASK 51-00-01-250-801, REV 8. PERFORMED BOND TEST OF AFFECTED AREA NO DEFECT NOTED REF NTM 51-00-04-910-801 T1 REV 8. BLENDS ARE FOUND TO BE WITHIN LIMITS IAW RD8/4-57-2054 ISSUE 1. FABRICATED SHIMS IAW RD8/4-57-2054 ISSUE 1, INSTALLED SHIMS IAW SRM 57-50-40-02-03, REV 12.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 262HT IS CHAFED ON MATING SURFACE. REMOVED FASTENERS AS REQUIRED IAW SRM 51-44-30-02-01, REV 12. REMOVED DAMAGE IAW SRM 51-14-00-02-03, REV 12. MECHANICALLY MEASURED, MIN REMAINING THICKNESS IS 0.088" IN LIMITS IAW SRM 53-75-06-02-01. CONFRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT 1, REV 7. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. INSTALLED FASTENERS SRM 51-44-30-02-01, REV 12. VERIFIED SATISFACTORY GRIP LENGTH IAW SRM 53-75-06-02-01, REV 12.

Part: SPAR — DAMAGED (CENTER WING) · airframe 10,385 hrs · 11,359 cycles

CENTER WING REAR SPAR UPPER CAM LOCK RECEPTACLE FLANGE BETWEEN LT WING STA YW45 AND RT WING STA YW45 IS CHAFED. SMOOTHED CHAFE DAMAGE IAW SRM 57-10-05-02-01 R.12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801 PT1 & 51-00-06-910-801 PT1 REV 7. FOUND CAM-LOC RECEPTACLE FLANGE TO BE OUT OF LIMITS IAW SRM 57-10-05-02-01, REV 12. FILLED BLENDED AREAS FLUSH WITH EC2216 B/A IAW RD 8/4-57-2052 ISS NR 1.

Part: FAIRING — CRACKED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

RT UNDERWING FAIRING IS CRACKED AT FUSELAGE STA X428.500. REMOVED WING TO FUSELAGE FAIRING PANEL 262JT TO FOM IAW REV 40 20-50-53-000-802. REMOVED CRACKED UNDERWING FAIRING STRUCTURE IAW SRM REV 12 51-42-05-02-01. REMOVED 2(EA) FAIRING SUPPORT ANGLES TO FOM IAW SRM REV 12 51-42-05-02-01. REMOVED 2(EA) STIFFENERS TO FOM IAW SRM REV 12 51-42-05-02-01. PRIOR TO REMOVAL; SHELF FOUND TO BE OUT OF LIMITS IAW SRM REV 12 51-10-00-00-01, STEP 2(3)(A) NO LIMITS IN SRM. MATCH DRILLED NEW PART TO AC IAW SRM REV 12 51-42-05-02-01, ALODINED AND PRIMED IAW 51-21-10-02-01, AND 51-25-10-02-01. INSTALLED NEW SHELF ASSY IAW SRM 51-42-05-02-01, REV 12. OK TO INSTALL SEAL. INSTALLED 2 EA FAIRING SUPPORT ANGLES AND 2 EA STIFFENERS AT RT UNDERWING FAIRING STRUCTURE AT STA X428.5 IAW SRM 51-42-05-02-01, REV 12. NOTE: SEE NRI 200055 WO 122225 FOR FAB OF "SHELF ASSY" PT 85357184-004. COMPLIED WITH TASK CARD: DLA-2081-CCO-NO-29. INSTALLED SEAL AT RT UNDERWING FAIRING AT STA 428.5 IAW SRM 51-42-45-02-01, REV 12.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FLOORBEAM 19.4 HAS CORROSION AT ACFT CENTER LINE. REMOVED FWD AND AFT SPLICE TO FOM REMOVED CORROSION IAW SRM 51-42-05-02-01 AND 51-21-00-00-02, REV 12. VERIFIED CRACK FREE IAW NTM 51-00-06-910-801, PART 1, REV 8. MINIMUM REMAINING THICKNESS ON PORT SIDE BEAM IS 0.038" AND 0.040" ON STARBOARD SIDE OF BEAM. UT ACCOMPLISHED IAW NTM5 1-00-04-910-801 PART 1 REV 8. FLOORBEAM IS FOUND TO BE WITHIN LIMITS IAW RD8/4-53-5234 ISS 1. APPLIED ALODINE, PRIMER, TOPCOAT AND CPC IAW RD8/4-53-5234, ISSUE 1. COMPLIED WITH HRZ TC RD8/4-53-5234 DATED 2/27/13.

Part: SEAT TRACK — DAMAGED (NR 8) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 8 HAS AREAS OF GOUGES AND CORROSION. REMOVED GOUGES AND CORROSION IAW SRM 51-21-00-00-02, REV 12. FOUND OUT OF LIMITS IAW SRM 53-20-49-02-02, REV 12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801 PT 1, REV 8.

Part: PLATE — CORRODED (THRESHOLD) · airframe 10,385 hrs · 11,359 cycles

FORWARD AIRSTAIR THRESHOLD PLATE HAS CORROSION. REMOVED THRESHOLD PLATE IAW SRM 51-42-05-02-01, REV 12, THRESHOLD PLATE FOUND TO BE OUT OF LIMITS IAW SRM 53-20-23-02-01, REV 12. INSTALLED NEW THRESHOLD IAW SRM REV 12 51-23-00-00-01, 51-42-05-02-01, 51-42-45-02-01 AND 51-25-15-02-01.

Part: SEAT TRACK — DAMAGED (NR 15) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 15 HAS AREAS OF GOUGES AND CORROSION. REMOVED GOUGES AND CORROSION IAW SRM 53-20-49-02-02, REV 12. OUT OF LIMITS IAW SRM 53-20-49-02-02, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 8.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 341, STR 31 & 30 HAVE CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1 REV 8. FOUND WITHIN LIMITS SRM 53-00-00-02-09.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER 25P IS CORROSDED AT FR 19.4. REMOVED CORROSION IAW SRM 51-21-00-000-02, REV12. VERIFIED BLENDS ARE CRACK FREE IAW NTM 51-00-06-910-801 PART1 REV 8. CORROSION DAMAGE ON STRINGER FOUND TO BE OUT OF LIMITS IAW SRM REV 12 53-20-17-00-01.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

EXTERIOR SKIN , BELOW CARGO DOOR AND IN CARGO DOOR FRAME CUTOUT, MANY SMALL NICKS AND AREAS OF MISSING ORGANIC COATING. ACCOMPLISHED BLEND OUT IAW SRM 53-42-52-02-01, REV 12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801, PT 1, REV 8 AND NTM 8.2.1.1 REV 14. BLEND IS OUT OF LIMITS IAW SRM 53-40-52-02-01, REV 12.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FOUND CORROSION ON SKIN UNDER SKIN ATTACH ANGLES AT STA 6.7 AND 26.7 JUST OTBD OF STR 25P. BLENDED CORROSION IAW SRM REV 12 51-21-00-00-02. VERIFIED AFFECTED AREAS TO BE CRACK FREE, REF NDTM PART6, TASK 51-00-01-250-801, REV 8. WITHIN LIMITS IAW R/D 8/4-53-5229 ISSUE 1.

Part: THRESHOLD — CORRODED (CARGO DOORWAY) · airframe 10,385 hrs · 11,359 cycles

FORWARD BAG DOOR THRESHOLD PLATE HAS CORROSION. REMOVED FWD AND AFT DOOR SURROUND, THRESHOLD SILL PLATE AND ANGLE COVER PLATE FROM FWD BAG DOOR THRESHOLD IAW SRM REV 12 51-41-00-00-01. REMOVED FWD AND AFT CORNER FITTINGS, KICK PLATES, AND THRESHOLD GUSSETS, REMOVED THRESHOLD EDGE CHANNEL AND THRESHOLD PLATE IAW SRM REV 12 51-40-15-02-01, 51-45-02-01, 51-42-05-02-01, 51-41-00-00-01, 51-42-15-02-01. MATCH DRILLED NEW EDGE CHANNEL IAW SRM 51-40-07-02-01. OK TO TREAT & PRIME. APPLIED ALADINE AND PRIMER TO EDGE CHANNEL IAW SRM 51-21-10-02-01, 51-25-10-02-01. REMOVED FLOOR SUPPORT & CHANNEL AT STA 1 TO STA 70 AT STRINGER 245 TO FOM IAW SRM 51-42-05-02-01, REV 12. PRIOR TO REMOVAL OF BAG DOOR (FWD) THRESHOLD PLATE THE THRESHOLD PLATE AND EDGE CHANNEL (PN 85329603-103 AND 85329604-001) WERE FOUND TO BE CORRODED OUT OF LIMITS IAW SRM 53-20-25-00-01. MATCH DRILLED NEW THRESHOLD PLATE IAW SRM 51-40-07-02-01, REV 12. INSTALLED EDGE CHANNEL IAW SRM 51-42-05-02-01, REV 12. INSTALLED EDGE CHANNEL AND THRESHOLD PLATE, CORNNER FITTINGS AND KICK PLATES IAW SRM 51-42-05-02-01, 51-42-45-02-01 AND SRM 51-41-05-00-01 REV 12. INSTALLED FLOOR SUPPORT Z-CHANNEL IAW SRM 51-42-05-02-01 REV 12. APPLIED ALODINE, PRIMER, AND TOPCOAT IAW SRM 51-21-10-02-01, 51-25-10-02-01, 51-25-15-02-01 REV.12. PREVIOUS TO SURFACE PROTCTION, INSTALLED THRESHOLD GUSSETS FOR SRM 51-42-05-02-01, 51-40-15-02-01, AND 51-42-15-00-01, REV 12.

Part: FLOOR SUPPORT — CORRODED (AFT CARGO BAY) · airframe 10,386 hrs · 11,359 cycles

AFT CARGO BAY LOWER FLOOR SUPPORT ANGLE AT STA 783 HAS SPOTS OF CORROSION. REMOVED CORRSION FROM AFT CARGO BAY FLOOR SUPPORT ANGLE AT STA 783 IAW SRM 51-21-00-00-02, REV 12. MIN THICKNESS NOTED .054", CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801 PT 1 & 51-00-06-910-801 PT 1 REV 8. ANGLE FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-5243 ISSUE DATED 26FE2013, AND RD 8/4-53-5244, ISSUE 1 DATED 25FEB2013. APPPLIED SURFACE PROTECTION IAW BOMBARDIER RD 8/4-53-52-43 ISSUE 1 DATED 26FEB2013, AND RD 8/4-53-5244, ISSUE 1 DATED 25FEB2013. NOTE, AV-DEC TAPE WILL BE APPLIED AT TIME OF FLOORBOARD INSTALLATION ON HORIZON PANEL BOOK W/O 144032, COMPLIED WITH T/C RD NR 814-53-5243 W/O NR 144032, AND T/C RD 8/4-53-5244, W/O144032.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

AFT CARGO BAY FLOOR SUPPORT WEB HAS AREAS OF CORROSION. REMOVED CORROSION IAW SRM 53-40-43-02-01, STEPS (7A) 1 & 2 REV 12. REMOVED (3) EA NUTPLATE SUPPORT RINGS & (2) EA NUTPLATES IAW SRM 51-40-07-02-01, REV 12 . REMOVED ALL CORROSION FROM AFT BAG PIT FLOOR SUPPORT WEB THAT WAS MARKED IAW SRM 51-21-00-00-02, REV 12 MIN. THICKNESS NOTED .040", CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801 PT1 & 51-00-06-910-801 PT1 REV 7. FLOOR SUPPORT WEB FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-5244, ISSUE 1 DATED 25FEB2013, AND RD 8/4-52-5245, ISSUE 1 DATED 24FEB2013. APPLIED ALODINE, PRIMER, AND ALUMINIZED IAW RD 8/4-53-5244, ISSUE 1 DATED 25FEB2013, AND RD 8/4-53-5245 ISSUE 1 DATED 24FEB2013. REPLACED ALL NUTPLATES AND REINSTALLED SUPPORT RINGS IAW SRM 51-42-05-02-01 REV 12, APPLIED AV-8 IAW RD 8/4-53-5244, ISSUE 1, DATED 25FEB2013, AND RD 8/4-53-5245, ISSUE 1 DATED 24FEB2013. AVPEC TAPE WILL BE APPLIED ON PANEL BOOK W/O 144032, COMPLIED WITH HORIZON T/C RD 8/4-53-5245, W/O 144032.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 10,385 hrs · 11,359 cycles

AFT CARGO BAY FLOOR SUPPORT WEB OTBD STRAP HAS AREAS OF CORROSION. REMOVED CORROSION FROM AFT BAG PIT FLOOR SUPPORT STRAP IAW SRM 51-21-00-00-02, REV 12 MIN. THICKNESS NOTED .070", CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801 PT1 & 51-00-06-910-801, PT 1, REV 7. STRAP FOUND TO BE WITHIN LIMITS IAW RD 8/4-53-5244, ISSUE 1 DATED 25FEB2013. APPLIED, ALODINE, PRIMER, AND ALUMINIZED IAW RD 8/4-53-5244 ISSUE 1 DATED 25FEB2013. APPLIED AV-8 IAW RD 8/4-53-5244 ISSUE 1, DATED 25 FEB 2013. COMPLIED WITH HRZ TC RD8/4-53-5244 DATED 2/27/13.

Part: FRAME — CORRODED (FUELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME 32.4, RT STANCHION HAS CORROSION ON FORWARD SIDE. REMOVED CROSS BRACE FROM FRAME 19.4-32.4 IAW SRM REV 12 51-41-05-00-01. REMOVED STANCHION IAW SM 51-42-05-02-01. BACK DRILLED NEW STANCHION IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL STANTION MINUS MISDRILLED HOLE IN FRAME. INSTALLED STANTION MINUS MISDRILLED HOLD AD INSTALLED BOTTOM AND TOP CLEAT ALSO IAW SRM 51-42-05-02-01, REV 12. MISDRILLED HOLE FASTENER INSTALLED AS PART OF NR 2 W/O 122229. REINSTALLED CROSS BRACE TO FRAME IAW SRM 61-41-05-00-01, REV 12. APPLIED ALODINE, PRIMER, TOP COAT AND CPC IAW SRM 51-21-10-02-01, 51-25-10-02-01, 51-25-15-02-01 REV 12 AND AMM 51-25-01-390-801 REV 40. NOTE: BOTTOM & TOP CLEAT WERE REMOVED AS PART OF THE STANTON REMOVAL.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 10 HAS CORROSION. REMOVED CORROSION ON SEAT TRACK NR 10 IAW SRM 51-21-00-00-01, REV 12. SEAT TRACK FOUND TO BE OUT OF LIMITS IAW SRM 53-20-49-02-02, REV 12. REMOVED KICK PLATE TO FACILITATE OTHER MX IAW SRM 51-42-45-02-01, REV 12. REMOVED SEAT TRACK AND SPLICE NR 10 IAW SRM 51-40-15-02-01 AND 51-42-05-02-01, REV 12. DISCONNECTED AC GROUND WIRE TO FOM IAW SRM 51-41-00-00-01, REV 12. MATCH DRILLED NEW SPLICE BETWEEN SEAT TRACK 10 AND 11 IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL SPLICE BETWEEN 10 AND 11. MATCH DRILLED REMAINDER OF SEAT TRACK 10 IAW SRM 51-40-07-02-01, REV 12 AND SRM 51-40-15-02-01, REV1 2. OK TO INSTALL SEAT TRACK INTO ACFT. INSTALLED ENW SEAT TRACK IAW SRM 51-42-05-02-01 AND 51-41-05-00-01 AND 51-40-15-02-01, REV 12. INSTALLED AC GROUND WIRE IAW AMM 20-10-01-430-801, REV 40. PERFORMED BONDING CHECK REF SRM 51-80-00-02-01, REV 12, DOME SEALED IAW SRM 51-80-00-02-01, REV 12. INSTALLED KICK PLATE IAW SRM 51-42-45-02-01, REV 12.

Part: THRESHOLD — CORRODED (EMERGENCY EXIT) · airframe 10,385 hrs · 11,359 cycles

RT EMERGENCY EXIT THRESHOLD PLATE AND GUSSETS CORRODED. REMOVED THRESHOLD DOOR STOP FITTING AND THRESHOLD COVER PLATE IAW SRM 51-41-00-00-01. FOUND THRESHOLD OUT OF LIMITS IAW SRM 53-20-21-00-01. REMOVED THRESHOLD BEAM IAW SRM 51-42-05-02-01, SRM 51-42-45-02-01. MATCH DRILLED NEW THRESHOLD BEAM IAW SRM 51-40-07-02-01. MATCH DRILLED NEW THRESHOLD GUSSETS IAW SRM 51-40-07-02-01. INSTALLED NEW GUSSETS IAW SRM 51-42-45-02-01 & 51-42-05-02-01. INSTALLED THRESHOLD COVERPLATE IAW SRM 51-41-05-00-01.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER 25P HAS CORROSION BETWEEN FR216-236. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. VERIFIED AFFECTED AREA CRACK FREE, REF NDTM PART 6, TASK 51-00-01-250-801, REV 8. MINIMUM THICKNESS REMAINING NOTED, .036", REF NDTM PART 1, TASK 51-00-04-910-801, REV 8. BLENDS ARE WITHIN LIMITS IAW RD 8/4-55-5237, ISSUE 1. APPLIED ALODINE, PRIMER, AND TOPCOAT IAW RD 8/4-53-5237, ISSUE 1. APPLIED CPC IAW RD 8/4-53-5237, ISSUE 1. COMPLIED WITH TC RD 8/4-53-5237, WP 144032.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

SKIN SPLICE STRAP AT FR 236 HAS CORROSION FROM STR 32-29P. REMOVED RIVETS IAW SRM 51-42-05 02-01, REV 12. REMOVED CORROSION IAW SRM 51-21-00 00-02, REV 12. REMOVED MORE RIVETS AND REMAINING CORROSION IAW SRM REV 12 51-42-05-02-01, 51-21-00-00-02. VERIFIED AFFECTED AREAS TO BE CRACK FREE. REF NDTM PT.6, TASK 51-00-01-250-801, REV.8 MIN THICKNESS NOTED, .048". REF NDTM PART 1, TASK 51-00-04-910-801, REV.8. ALODINED AND PRIMED IAW SRM 51-21-10-02-01, 51-25-10-02-01, REV 12. INSTALLED RIVETS SRM 51-42-05-02-01, REV 12. APPLIED TOPCOAT SRM 51-25-15-02-01, REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40. BLENDS FOUND TO BE INLIMITS IAW 04" RD 8/4-53-52 42 185 1. COMPLIED WITH TC RD-8/4-53-5242 WO 144032.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 11 HAS AREAS OF CORROSION. BLENDED SEVERAL AREAS OF CORROSION MECHANICALLY MEASURED CLAWS AND FOUND SEAT TRACK 11 TO BE OUT OF LIMITS IAW SRM 53-20-49-02-02, REV 12. REMOVED SEAT TRACK NR 11 IAW SRM 51-41-00-00-01, 51-40-15-02-01 AND 51-42-05-02-01 REV 12. DISPLACED DRAIN CURTAIN FROM FR 49.5 TO FR 116 TO F.O.M. IAW SRM 51-42-05-02-01, REV 12. DISPLACED DRIP TRAY FROM FR 49.5 TO FR 388 TO F.O.M. IAW SRM 51-41-00-00-01, REV 12. MATCH DRILLED SEAT TRACK 11 IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL SEAT TRACK. INSTALLED SEAT TRACK IAW SRM 51-42-09-02-01, REV 12, SRM 51-40-15-02-01 REV 12, AND AMM 20-10-01-430-801, REV 40. REINSTALLED DRAIN CURTAIN IAW SRM 51-42-05-02-01, REV 12. REINSTALLED DISPLACED DRIP TRAY IAW SRM REV 12 51-41-05-00-01.

Part: FASTENER — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

GROUND WIRE CLIP ATTACHED TO STR 31S AFT OF FR 71.2 HAS CORROSION. AFTER CLEANING IAW SRM REV 12 51-26-00-02-01, CORROSION NOTED ON FASTENERS ONLY. REPLACED FASTENERS IAW SRM REV 12 51-42-05-02-01, 51-21-10-02-01, 51-25-10-02-01, AND 51-25-15-02-01.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 136 STR 33-32S HAS CORROSION. REMOVED RIVETS AS NEEDED AND BLENDED CORROSION IAW SRM REV 12 53-00-00-02-09. MIN THICKNESS NOTED .046", CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1, REV 8. APPLIED ALODINE AND PRIMER TO FRAME FLANGE IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. PRIOR TO ALODINE AND PRIME APPLICATION, FRAME FLANGE WAS FOUND TO BE WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12. NOMINAL THICKNESS .040". INSTALLED RIVETS IAW SRM 53-00-00-02-09. APPLIED TOP COAT AND CPC IAW SRM 53-00-00-02-09.

Part: STRINGER — CORRODED (24 RIGHT) · airframe 10,385 hrs · 11,359 cycles

STRINGER 24S HAS CORROSION AFT OF FR 216. REMOVED CORROSION IAW SRM 51-21-00-00-02 REV 12. REMOVED STRINGER SEGMENT IAW RD 8/4-53-4619, ISSUE 3. COMFIRMED STRINGER CUT LINE CRACK FREE REF NTM 51-00-06-910-801, PT1, REV8. FABRICATED STRINGER SECTION. INSTALLED STRINGER SECTION, REPAIR, SPLICE, PACKER AND AFT SPLICE IAW RD 8/4-53-4619 ISSUE 3, STEPS 11-14.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 258.5 STR 32-30S HAVE CORROSION. REMOVED FASTENERS AT FRAME X258.5 FROM STRINGER 30S-32S IAW SRM REV 12 51-42-05-02-01. REMOVED CORROSION FROM X258.5 FRAME FLANGES AT STRINGER 30S-32S IAW SRM REV 12 53-00-00-02-09. MIN THICKNESS NOTED .028", CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1, REV 8. FLANGE BETWEEN STR 31-30S MEASURED .042 WITHIN LIMITS IAW SRM 53-00-00-02-09 REV 12. FLANGE BETWEEN 32-31S OUT OF LIMITS IAW SRM 53-00-00-02-09, REV 12. OK TO TREAT PRIME AND INSTALL RIVETS BETWEEN 31S-30S AND DO FLANGE REPAIR IAW 53-00-00-02-18 32S-31S. ALODINED AND PRIMED IAW SRM 53-00-00-02-09, REV 12. REMOVED 32-31S FLANGE IAW SRM 53-00-00-02-18. CONFIRMED FLANGE CUTOUT CRACK FREE REF NDTM 51-00-06-910-801 PT 6, REV 7. FABRICATED ANGLE FOR LOOSE ANGLE REPAIR WITH 2024-T3 .050 PO 90512F IAW SRM 53-00-00-02-18 REV 12. LOCATED, DRILLED, ALODINED AND PRIMED IAW SRM 53-00-00-02-18, REV 12. OK TO INSTALL REPAIR ANGLE. INSTALLED REPAIR ANGLE IAW SRM REV 12 53-00-00-02-18. INSTALLED REMAINING FASTENERS IN WORKED FRAME FLANGES FROM STR 32-30S IAW SRM 51-42-05-02-01, REV 12. APPLIED PRIMER AND PAINT TO INTERIOR IAW SRM 51-25-10-02-01 AND 51-25-15-02-01, REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40. ALODINED PRIMED AND PAINTED EXTERIOR IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01, REV 12.

Part: STRINGER SPLICE — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER SPLICE FOR 31S BETWEEN FR 94.8-116 HAS CORROSION. NO DAMAGE ALLOWED, FOUND TO BE OUT OF LIMITS IAW SRM 53-20-03-00-01, REV 12. REMOVED STRINGER SPLICE IAW SRM 51-42-05-02-01, SRM 51-40-15-02-01, REV 12. LOCATED AND DRILLED NEW STRINGER SPLICE IAW SRM 51-40-07-02-01, REV 12. ALODINED AND PRIMERED BARE METAL AREAS IAW SRM 51-21-10-02-01, REV 12 AND SRM 51-25-10-02-01, REV 12. OK TO INSTALL SPLICE. INSTALLED SPLICE IAW SRM 51-42-05-02-01 REV 12 AND SRM 51-40-15-02-01, REV 12. ALODINED PRIMED AND APPLIED TOPCOAT IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01 REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40.

Part: STANCHION — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME 49.5 STANCHION HAS CORROSION. REMOVED STANCHION IAW SRM 51-42-05-02-01 AND 51-41-05-00-01, REV 12. REMOVED CROSS BRACES FROM FRAME 32-71 IAW SRM 51-41-05-00-01, REV 12. REMOVED STANCHION CORRODED BEYOND LIMITS IAW SRM REV 12 53-20-43-00-01. MATCH DRILLED STANCHION IAW SRM REV 12 51-40-07-02-01. INSTALLED STANCHION IAW SRM REV 12 51-42-05-02-01, 51-25-10-02-01 AND 51-25-15-02-01. REINSTALLED CROSS BRACES FROM FLANGES 32-71 IAW SRM REV 12 51-41-05-00-01.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 5 HAS AREAS OF CORROSION. REMOVED CORROSION FROM NR 5 SEAT TRACK IAW SRM 51-21-00-00-02, REV 12. CONTINUED REMOVING CORROSION FROM SEAT TRACK NR 5 IAW SRM REV 12 53-20-49-02-02. MECHANICALLY MEASURED SEAT TRACK NR 5 DEEPEST AREA FOUND 0.068". SEAT TRACK FOUND TO BE OUT OF LIMITS IAW SRM REV 12, 53-20-49-02-02. REMAINING THICKNESS FOUND TO BE 0.026" IAW SRM REV 12 53-20-49-02-02. REMOVED DIP TRAY FOR FOM IAW SRM 51-41-00-00-01, REV 12. REMOVED SEAT TRACK NR 5 IAW SRM 51-41-00-00-01 & 51-42-05-02-01 & 51-40-15-02-01, REV 12. MATCH DRILLED SEAT TRACK IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL SEAT TRACK NR 5. INSTALLED SEAT TRACK NR 5 IAW SRM 51-42-05-02-01, 51-40-15-02-01 AND 51-41-05-00-01 REV 12. WM 20-12-10-201, REV 1. PERFORMED GROUNDING OF METALLIC COMPONENTS, CHECK SATISFACTORY AT THIS TIME (.2 M OHMS). APPLIED TOPCOAT SURFACE PROTECTION TO RIVETS IAW SRM 51-25-15-02-01, REV 12. INSTALLED DRIP TRAY SRM 51-41-00-00-01, REV 12.

Part: STRINGER SPLICE — CORRODED (BS 116) · airframe 10,385 hrs · 11,359 cycles

STRINGER SPLICE AT FR 116 S24S HAS CORROSION. REMOVED STRINGER SPLICE IAW SRM REV 12 51-42-05-02-01. INSTALLED REPLACEMENT STRINGER SPLICE IAW SRM (R12) 51-42-05-02-01 & 51-40-15-02-01.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 258.5 STR 33-30P HAVE CORROSION. REMOVED FASTENERS AT FRAME 258.5 FROM STRINGER 30P-33 IAW SRM REV 12 51-42-05-02-01. REMOVED CORROSION FROM SKIN FLANGES AT FRAME 258.5 FROM STRINGER 30P-33 IAW SRM REV 12 53-00-00-02-09. MIN THICKNESS NOTED .035", CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1 REV 8. FLANGE BETWEEN 31-32P MEASURED .036, 32P-33 MEASURED .046, FLANGES 33-31P WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12, FLANGE 31-30P OUT OF LIMITS IAW SRM 53-00-00-02-09 REV 12. OK TO TREAT, PRIME AND INSTALL RIVETS 31P-33 AND DO FLANGE REPAIR IAW SRM 53-00-00-02-18 31P-30P. ALODINED AND PRIMED IAW SRM 53-00-00-02-09, REV 12. REMOVED 31-30P FLANGE IAW SRM 53-00-00-02-18, REV 12. CONFIRMED FLANGE CUTOUT CRACK FREE REF NDTM 51-00-06-910-801 PART 6, REV 7. FABRICATED ANGLE FOR LOOSE ANGLE REPAIR WITH 2024-T3 .050 PO 9051F IAW SRM 53-00-00-02-18, REV 12. LOCATED DRILLED ALODINED AND PRIMED ANGLE IAW SRM 53-00-00-02-18 REV 12. OK TO INSTALL REPAIR ANGLE. INSTALLED REPAIR ANGLE IAW SRM REV 12 53-00-00-02-18. INSTALLED REMAINING FASTENERS IN WORKED FRAME FLANGES FROM STR 30P-33 IAW SRM 51-42-05-02-01, REV 12. PRIMED AND PAINTED INTERIOR IAW SRM 51-25-10-02-01 AND 51-25-15-02-01, REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40. ALODINED PRIMED AND PAINTED EXTERIOR IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01, REV 12.

Part: STRINGER SPLICE — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER TIE AND SPLICE FOR STR 25S AT FR 236 HAS CORROSION. REMOVED CORRODED STRINGER TIE AND SPLICE FOR STRINGER 25S AT FRAME STANTION 236 IAW SRM 51-42-05-02-01, REV 12, NO REPAIRS ALLOWED TO STR TIE IAW SRM 53-30-15-00-01, REV 12 OR SPLICE IAW SRM 53-30-03-00-01, REV 12. LOCATED AND DRILLED NEW STRINGER SPLICE AND STRINGER TIE IAW SRM 51-40-07-02-01, REV 12. ALODINED AND PRIMERED BARE METAL AREAS IAW SRM 51-21-10-02-01, REV 12 AND SRM 51-25-10-02-01, REV 12. OK TO INSTALL PARTS. INSTALLED STRINGER SPLICE AND STRINGER TIE IAW SRM 51-42-05-02-01. APPLIED ALODINE PRIMER AND TOPCOAT IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01 REV1 2. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40.

Part: SKIN — DAMAGED (BS 955-970) · airframe 10,385 hrs · 11,359 cycles

DAMAGE SKIN BETWEEN BS 955 AND 970 AND ABOVE Z170 AFT TAIL. CLEANED DAMAGED AREA IAW SRM REV 12 51-26-10-02-01. FOUND TO BE OUT OF LIMITS IAW SRM REV 12 53-50-31-02-02, STEP 2B(4). CUTOUT DAMAGE IAW RD8/4-55-847, ISSUE 1. INSPECTED CUTOUT USING FLUORESCENT PENETRANT REF GPM 8.1.0, REV 14 AND FOUND TO BE CRACK FREE. FABRICATED REPAIR DOUBLER IAW RD8/4-55-847, ISSUE 1. INSTALLED REPAIR DOUBLER IAW RD8/4-55-847 ISSUE 1 STEPS 1-8.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 116 STR 33-29S HAVE CORROSION. REMOVED 22 RIVETS AND CORROSION FROM FRAME 116 FLANGES STR 33-29S IAW SRM REV 12 53-00-00-02-09. MIN THICKNESS NOTED .026", CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801, PT 1 REV 8. FLANGES 33-32S MEASURED .045, 31-30S MEASURED .043, 30-29S MEASURED .046 WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12, FLANGE 32-31S MEASURED .026 OUT OF LIMITS IAW SRM 53-00-00-02-09 REV 12. OK TO TREAT PRIME AND INSTALL RIVETS BETWEEN STGRS 33-32S AND 31S-29S AND TO DO FLANGE REPAIR IAW 53-00-00-02-18, 32S-31S. REMOVED DAMAGED FLANGE IAW SRM 53-00-00-02-18, REV 12, STEP 7B(3)-(4), FABRICATED REPAIR FLANGE USING 2024T3 .050" PO90512F IAW SRM 53-00-00-02-18, REV 12 STEPS 8A(1)-(9). VERIFIED TRIM FRAME EDGE CRACK FREE IAW NTM 51-00-06-910-801 PART 1 REV 8. OK TO INSTALL REPAIR ANGLE. INSTALLED REPAIR ANGLE AND RIVETS IN FRAME FLANGES FROM BS116 STR 33 TO 29S IAW SRM 51-42-05-02-01, REV 12 AND SRM 53-00-00-02-18, REV 12. PRIOR TO INSTALLAITON OF REPAIR ANGLE AND REMOVED RIVETS, APPLIED ALODINE AND PRIMER TO ALL REQUIRED AREAS IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. APPLIED TOP COAT TO INTERIOR AND EXTERIOR IAW SRM 51-25-15-02-01 REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40.

Part: GUSSET — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME 71.2, GUSSET AT STR 24S HAS CORROSION. REMOVED CORRODED GUSSET SRM 51-40-07-02-01, REV 12. INSTALLED NEW GUSSET IAW SRM 51-42-05-02-01, 51-40-15-02-01 AND 51-42-15-02-01 REV 12.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FORWARD DRAFT BULKHEAD LOWER MOUNTING PLATE AT FR 32.4 HAS CORROSION. REMOVED MOUNTING PLATE IAW SRM REV 12 51-42-05-02-01 AND 51-42-45-02-01. CORROSION DAMAGE FOUND TO BE OUT OF LIMITS IAW SRM REV 12 51-21-00-00-02. RECEIVED NEW PN 8Z4844-103 AND MATCH DRILLED TO ACFT IAW SRM REV 12 51-40-07-02-01. INSTALLED NEW MOUNTING PLATE IAW SRM 51-42-45-02-01, REV 12.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

TORQUE TUBE AND AFT BRACE ANGLES HAVE CORROSION AT FR 6.7 AND 26.7. REMOVED CORRODED ANGLES IAW SRM REV 12 51-42-05-02-01. CORROSION DAMAGE FOUND TO BE OUT OF LIMITS IAW SRM REV 12 53-20-23-00-01. RECEIVED NEW ANGLES, MATCH DRILLED, ALODINED, PRIMED AND PAINTED IAW SRM REV 12 51-40-07-02-01, 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01. OK TO INSTALL FWD AND AFT BRACE ANGLES. INSTALLED NWE ANGLES IAW SRM REV 12 51-42-05-02-01, 51-23-00-00-01.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FOUND CORROSION ON WEB TO INTERCOSTAL ATTACH ANGLES AT STA 6.7 ABD 26.7. CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-20-23-00-01, REV 12. INSTALLED NEW ATTACH ANGLES SRM 51-42-05-02-01 REV 12, 51-40-15-02-01 AND 51-23-00-00-01.

Part: SKIN — DENTED (RT WING) · airframe 10,385 hrs · 11,359 cycles

RT WING HAS A DENT ON UNDERSIDE JUST INBD OF NR 5 FLAP TRACK. DENT MEASURED 1.5" X 1.3" X .020" DEEP. DAMAGE IS OUT OF LIMITS IAW SRM 57-20-30-01-01, REV 12. CONFIRMED WING SKIN CRACK FREE IN AFFECTED AREA REF NTM 51-00-01-250-801, PT 6, REV 7. CUT AWAY DAMAGED SKIN IAW RD8/4-57-2043, ISSUE 1. PERFORMED FPI OF WING SKIN CUTOUT AND CONFIRMED IT TO BE CRACK FREE IAW HRZ NDTM R/4 8.2.0 AND RD8/4-57-2043, ISSUE 1. FABRICATED, LOCATED AND DRILLED REPAIR DOUBLER IAW RD8/4-57-2043, ISSUE 1. INSTALLED REPAIR DOUBLER IAW RD8/4-57-2043, ISSUE 1.

Part: SEAT TRACK — DAMAGED (NR 7) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 7 HAS AREAS OF GOUGES INSIDE THE CLAW. REMOVED CORROSION IAW SRM 53-20-49-02-02, REV 12. FOUND TO BE IN LIMITS REF SRM 53-20-49-02-02, REV 12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 8.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FOUND CORROSION ON VERTICAL LEG OF STRINGER 31S AFT OF X156. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. CONFIRMED AREA CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 8.

Part: SEAT TRACK — DAMAGED (NR 14) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 14 HAS AREAS OF GOUGES INSIDE CLAW. REMOVED GOUGES IAW SRM 53-20-49-02-02, REV 12. FOUND TO BE WITHIN LIMITS IAW SRM 53-20-49-02-02, REV 12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 8.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 1.0 STR 32-29P HAVE CORROSION. REMOVED RIVETS TO FOM REMOVED CORROSION IAW SRM 51-42-05-02-01 AND 51-21-00-00-02, REV 12 MIN THICKNESS NTOED .046, CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1 REV 8. BLENDS WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12. PRIMED IAW SRM 51-25-10-02-01, REV 12. NOTE: PREVIOUS TO PRIME, ALODINED IAW SRM 51-21-10-02-01, REV 12. INSTALLED RIVETS IAW SRM 51-42-05-02-01, REV 12. APPLIED PRIMER TO RIVET TAILS APPLIED TOPCOAT AND CPC IAW SRM 51-25-10-02-01, 51-25-15-02-01 REV 12 AND AMM 51-25-01-390-801, REV 40. APPLIED EXT PRIMER AND TOPCOAT IAW SRM 51-25-15-02-01 AND 51-25-45-02-01, REV 12. APPLIED CPC TO WORKED AREAS IAW AMM 51-25-01-390-801, REV 40.

Part: SEAT TRACK — GOUGED (NR 6) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 6 HAS AREAS OF GOUGES INSIDE CLAW. REMOVED DAMAGE FROM SEAT TRACK NR 6 IAW SRM 53-20-49-02-02, REV 12. FOUND TO BE IN LIMITS IAW SRM 53-20-49-02-02 REV1 2. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 8.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES, ST FR 236, STR 33-30P HAVE CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. CONFIRMED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1 REV 8. FOUND IN LIMITS SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 1.0 STR 32-29S HAVE CORROSION. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. CONFIRMED CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1 REV 8. FOUND WITHIN LIMITS IAW SRM 53-00-00-02-09 REV 12.

Part: SEAT TRACK — GOUGED (NR 12) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 12 HAS AREAS OF GOUGES INSIDE THE CLAW. BLENDED GOUGES ON SEAT TRACK NR 12 IAW SRM REV 12 53-20-49-02-02. FOUND TO BE WITHIN LIMITS IAW SRM REV 12 53-20-49-02-02. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 8.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 116 STR 32-30P HAS CORROSION. REMOVED CORROSION IAW SRM REV 12 53-00-00-02-09. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1, REV 8. WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: WEB — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

WEB AT FLOORBEAM 1.0 AND SEAT TRACK NR 5 HAS CORROSION. REMOVED WEB IAW SRM REV 12 51-42-05-02-01. INSTALLED NEW WEB IAW SRM 51-42-05-02-01, REV 12.

Part: INTERCOSTAL — CRACKED (LT NACELLE) · airframe 10,385 hrs · 11,359 cycles

WHILE WORKING LT NACELLE MOD TC 6-54-441/LT FOUND INTERCOSTAL, CRACKED AT XN197.81. REMOVED INTERCOSTAL IAW SRM 51-42-05-02-01, 51-40-15-02-01, REV 12. MATCH DRILLED NEW INTERCOSTAL IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL NEW INTERCOSTAL. INSTALLED INTERCOSTAL IAW SRM 51-42-05-02-01, 51-40-15-02-01 REV 12. PRIMED AND PAINTED RIVET HEADS IAW SRM 51-25-45-02-01 AND 51-25-15-02-01, REV 12.

Part: PLATE — CORRODED (PAX DOOR) · airframe 10,385 hrs · 11,359 cycles

FORWARD PAX DOOR FORWARD GOOSE NECK BACKING PLATE IS CORRODED. R & R, PAINTED TO MATCH IAW REF AMM 52-11-23-000-801, REV 40, STEP F6 AND Q400, AMM 52-11-23-400-801, REV 40 STEP 4A (15-17+21).

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 32.4, STR 32-29P HAVE CORROSION. BLENDED CORROSION IAW SRM REV 12 53-00-00-02-09. CONFIRED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT1 & 51-00-06-910-801 PT1, REV 8. FOUND WITHIN LIMITS SRM 53-00-00-02-09, REV 12. REMOVED FLANGE BETWEEN STRINGER 31-32P IAW SRM 53-00-00-02-18. FABRICATED NEW FLANGE IAW SRM 53-00-00-02-18, REV 12. CONFIRMED WEB CUT LINE CRACK FREE REF NTM 51-00-06-910-801, PT1, REV 8. ALODINED AND PRIMED NEW FLANGE AND FRAME CUT SECTION IAW SRM 51-21-10-02-01, REV 12, AND SRM 51-25-10-02-01, REV 12. INSTALLED FLANGE REPAIR IAW SRM 53-00-00-02-18, REV 12.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

SKIN STRAP AT 31P HAS CORROSION FROM FR196 - 236. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. VERIFIED BLENDS ARE CRACK FREE IAW NTM 51-00-06-910-801, PART 1, REV 8. FOUND TO BE IN LIMITS IAW RD8/4-53-5238 ISS NR 1.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 9 HAS AREAS OF CORROSION. REMOVED CORROSION, MECHANICALLY MEASURED MINIMUM REMAINING FLANGE THICKNESS TO BE .056", MINIMUM ALLOWABLE THICKNESS IS .060", FOUND TO BE OUT OF LIMITS IAW SRM 53-20-49-02-02, FIG 2. PARTIALLY REMOVED SEAT TRACK IAW SRM 51-42-05-02-01, REV 12. REMOVED SEAT TRACK IAW SRM 51-42-05-02-01, REV 12. MATCH DRILLED REPLACEMENT NR 9 SEAT TRACK IAW SRM REV 12 51-40-07-02-01. OK TO INSTALL REPLACEMENT NR 9 SEAT TRACK. INSTALLED FASTENERS IN NR 9 SEAT TRACK FROM X 654.5 TO X683.45 IAW SRM REV 12 51-42-05-02-01, 51-40-15-02-01 AND 51-41-05-00-01. INSTALLED RIVETS ON SEAT TRACK NR 9 TO VERTICAL WEB FROM FRAME 714 TO FRAME 801 IAW SRM 51-42-05-02-01, REV 12. INSTALLED REMAINING RIVETS IAW SRM 51-42-05-02-01, REV 12. INSTALLED HI LITES IAW SRM 51-40-15-02-01, REV 12. COMPLETED INSTALLATION OF SEAT TRACK 9 IAW SRM 51-42-05-02-01, 51-40-15-02-01 AND 51-41-05-02-01, REV 12. PERFORMED BONDING CHECK OF METALLIC COMPONENTS IAW SRM 51-80-00-02-01 REV 12. BONDING CHECK SATISFACTORY AT THIS TIME (1.5M). APPLIED PRIMER AND TOPCOAT TO RIVETS, FASTENERS AND TRACK NR 9 IAW SRM 51-25-10-02 AND SRM 51-25-05-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 489.5 STR 32-31S HAS CORROSION. BLENDED CORROSION IAW SRM 53-00-00-02-09, REV 12. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT1 & 51-00-06-910-801 PT 1 REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 49.5 STR 32-28S HAS CORROSION. BLENDED CORROSION ON FRAME FLANGE IAW SRM REV 12 51-21-00-00-02. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 & 51-00-06-910-801 PT 1, REV 8. FLANGES IN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — DENTED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME 32.4, STANCHION AT STR 31P HAS A DENT. REMOVED BOLTS FROM CROSS BRACE TO FOM IAW SRM REV 12 51-41-00-00-01. REMOVED STANCHION FROM FRAME 32.4 AT STR 31P IAW SRM REV 12 51-42-05-02-01. STANTION FOUND TO BE OUT OF LIMITS IAW SRM 53-20-43-00-01, REV 12 MATCH DRILLED NEW STANTION IAW SRM 51-42-05-02-01, REV 12. REINSTALLED STANTION AND BOLTS FROM CROSS BRACE IAW SRM 51-42-05-02-01 & SRM 51-41-05-00-01, REV 12. APPLIED TOP COAT + CPC IAW SRM 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 509 STR 32-31P HAS CORROSION. BLENDED CORROSION IAW SRM 53-00-00-02-09, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 & 51-00-06-910-801, PT 1 REV 8. FOUND WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 136 STR 32-30S HAS CORROSION. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. CONFIRMED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1 REV 8. FOUND IN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: STRAP — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

SKIN STRAP AT 31P BETWEEN FR 301-321 HAS AREAS OF CORROSION. BLENDED CORROSION IAW SRM REV 12 51-21-00-00-02. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6 TASK 51-00-01-250-801, REV 8. BLEND FOUND TO BE IN LIMITS IAW RD8/4-53-5238 ISS 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 71.2 STR 32-29P HAVE CORROSION. REMOVED RIVETS FOR ACCESS IAW SRM 51-42-05-02-01, REV 12. BLENDED CORROSION IAW SRM 53-00-00-02-09, REV 12. CLEANED BETWEEN STR 30-29P ON FRAME FLANGE 71.2, NO CORROSION NOTED IAW SRM REV 12 51-26-00-02-01. MIN THICKNESS NOTED .044", CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 PT1 + 51-00-06-910-801 PT 1 REV 8. BLENDS FOUND TO BE WITHIN LIMITS IAW SRM 51-42-05-02-01, REV 12. PRIOR TO INSTALLING RIVETS APPLIED ALODINE AND PRIMER IAW SRM 53-00-00-02-09, REV 12. APPLIED CPC IAW SRM 53-00-00-02-09, REV 12. PRIOR TO APPLYING CPC TOPCOAT APPLIED IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 19.4 STR 31-29S HAVE CORROSION. REMOVED RIVETS TO FOM, REMOVED CORROSION IAW SRM 51-42-05-02-01 & 51-21-00-00-02 REV 12. NO CORROSION NOTED BETWEEN 31S-32S. MIN THICKNESS NOTED .036", CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 PT 1 & 51-00-06-910-801 PT 1, REV 8. NOMINAL THICKNESS .040, FLANGES IN LIMITS IAW SRM 53-00-00-02-09 TR ALODINED, PRIMED, AND REINSTALLED RIVETS IAW SRM 51-42-05-02-01, REV 12, SRM 51-21-10-02-01 REV 12, AND SRM 51-25-10-02-01, REV 12. PRIMED RIVET TAILS, APPLIED TOP COAT AND CPC IAW SRM 51-25-10-02-01, 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40. APPLIED EXT PRIMER AND TOP COAT IAW SRM 51-25-45-02-01 AND 51-25-15-02-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 301 STR 32-30S HAVE CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 & 51-00-06-910-801, PT 1, REV 8. FOUND WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

SKIN STRAP HAS CORROSION AT 31P BETWEEN FR 71.2 - 94.8. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. VERIFIED BLENDS ARE CRACK FREE IAW NTM 51-00-06-910-801, PART 1, REV 8. MINIMUM REMAINING MATERIAL MEASURED 0.048" IAW NTM 51-00-04-910-801, REV 8, PART 1. BLENDS FOUND TO BE IN LIMITS IAW RD8/4-53-5238 ISS NR 1. ALODINED, PRIMED, PAINTED IAW RD8/4-53-5238 NR 1. APPLIED CPC IAW RD8/4-53-5238 NR 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 281 STR 32-30P HAVE CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09 REV 12. CONFIRMED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801, PT 1, REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-30-14-00-01, 53-00-00-02-09 REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 49.5 STR 32-31P HAS POSSIBLE CORROSION. REMOVED 1EA RIVET FROM 49.5 FRAME BETWEEN STR 32P-31P IAW SRM REV 12 51-42-05-02-01. BLENDED CORROSION ON FRAME 49.5 FLANGE BETWEEN 32P-31P STR IAW SRM REV 12 51-21-00-00-02 MIN THICKNESS NOTED .049", CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT1 & 51-00-06-910-801 PT 1, REV 8. NOMINAL THICKNESS .050, FLANGES IN LIMITS IAW SRM 53-00-00-02-09, REV 12. ALODINED, PRIMED & REINSTALLED RIVETS IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-42-05-02-01, REV 12. PRIMED RIVET TAILS, APPLIED TOP COAT AND CPC IAW IAW SRM 51-25-10-02-01, 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40. APPLIED EXT PRIMER AND PAINT IAW SRM 51-25-45-02-01 AND 51-25-15-02-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 604.5 STR 32-31P HAS CORROSION. REMOVED CORROSION IAW SRM (R12) 53-00-00-02-09. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-045-910-801 PT 1 & 51-00-06-910-801, PT 1, REV 8. FOUND WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 281 STR 32-30S HAVE CORROSION. REMOVED OF CORROSION IAW SRM 53-00-00-02-09, REV 12. CONFIRMED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 & 51-00-06-910-801 PT 1 REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-30-15-00-01, 53-00-00-02-09 REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 604.5 STR 32-31S HAS CORROSION. REMOVED CORROSION IAW SRM (R12) 53-00-00-02-09. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 & 51-00-00-910-801 PT 1, REV 8. FOUND WITHIN LIMITS IAW SRM 53-00-00-02-09, R12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 301 STR 32-30P HAVE CORROSION. REMOVED CORROSION AND FOUND WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1, REV 8.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER 32P AT -18.25 HAS CORROSION. NO CORROSION NOTED ON STRINGER LIMITED TO Z JOINT ONLY. REMOVED Z JOINT TO REPLACE FOUND TO BE OUT OF LIMITS IAW SRM 53-10-33-00-01 & SRM 51-42-05-02-01, REV 12. MATCH DRILLED NEW Z JOINT IAW SRM 51-40-07-02-01, REV 12 & APPLIED TOPCOAT IAW SRM 51-25-15-02-01, REV 12. OK TO INSTALL NEW Z JOINT. INSTALLED Z JOINT IAW Q400 SRM 51-23-00-00-01 + 51-42-05-02-01 REV 12. PRIMED RIVET TAILS, APPLIED TOP COAT AND CPC IAW SRM 51-25-10-02-01, 51-25-15-02-01 AND AMM 51-25-01-390-801 REV 40. APPLIED EXT PRIMER AND TOPCOAT IAW SRM 51-25-45-02-01 AND 51-25-15-02-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES, FR 176 STR 32-30S HAVE CORROSION. REMOVED CORROSION, VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6 TASK 51-00-01-250-801 REV 8 MINIMUM THICKNESS REMAINING NOTED .044" REF NDTM PART 1 TASK 51-00-04-910-801 REV 8. NOMINAL THICKNESS .040" REF DWG 85328142, FOUND TO BE WITHIN LIMITS IAW SRM 53-20-15-00-01, REV 12.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FLOORBEAM 19.4 FLOORBOARD MOUNT T-FITTING HAS CORROSION. REMOVED FLOORBOARD MOUNT-T-FITTING TO REPLACE IAW SRM 51-42-05-02-01, REV 12. FLOORBOARD SUPPORT FITTING FOUND TO BE OUT OF LIMITS IAW SRM 53-20-43-00-01, REV 12. MATCH DRILLED NEW T-FITTING IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL T FITTING. INSTALLED T FITTING IAW SRM 51-42-05-02-01 REV 12. APPLIED TOPCOAT AND CPC IAW SRM 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 644.5 STR 32-31P HAS CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09 REV 12. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1 REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-40-15-00-01 AND 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE FR 136 STR 32-29P HAS CORROSION. FOUND CORROSION TO BE LIMITED TO FASTENERS AT FRM 136 STR 32P-31P, AND STR 30P-29P, REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. CONFIRMED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1, REV 8. FOUND TO BE IN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 71.2 STR 33-28S HAVE CORROSION. REMOVED RIVETS FOR ACCESS FROM FR 71.2 STR 33-28S IAW SRM REV 12 51-42-05-02-01. BLENDED CORROSION IAW SRM REV 12 53-00-00-02-09. CLEANED BETWEEN STR 30-29S ON FRAME 71.2 IAW SRM REV 12 51-26-00-02-01, NO CORROSION NOTED. MIN THICKNESS NOTED .037", CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 PT1 + 51-00-06-910-801 PT 1 REV 8. BLEND FOUND TO BE WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12. INSTALLED RIVETS FR 71.2, STR 33-28S IAW SRM 51-42-05-02-01, REV 12. PRIOR TO INSTALLING RIVETS APPLIED ALODINE AND PRIMER IAW SRM 53-00-00-02-09, REV 12. APPLIED CPC IAW SRM 53-00-00-02-09, REV 12. PRIOR TO APPLYING CPC TOPCOAT APPLIED IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 489.5, STR 32-31P HAVE CORROSION. BLENDED CORROSION SRM 53-00-00-02-09, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 & 51-00-06-02-09, PT 1, REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: STRINGER CLIP — CORRODED (STRINGER 24 L) · airframe 10,385 hrs · 11,359 cycles

STRINGER CLIP FR 71.2, STR 24P HAS CORROSION. FOUND TO BE CORRODED OUT OF LIMITS IAW SRM 53-20-15-00-01, REV 12. REMOVED STRINGER CLIP IAW SRM REV 12 51-42-05-02-01. INSTALLED NEW STRINGER CLIP IAW SRM 51-42-05-02-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AND WEB OF FR 94.8 STR 33-31S HAVE CORROSION. REMOVED CORROSION FROM NR 5 SEAT TRACK IAW SRM 51-21-00-00-02, REV 12. CONTINUED REMOVING CORROSION FROM SEAT TRACK NR 5 IAW SRM REV 12 53-20-49-02-02. MECHANICALLY MEASURED SEAT TRACK NR 5 DEEPEST AREA FOUND 0.068". SEAT TRACK FOUND TO BE OUT OF LIMITS IAW SRM REV 12 53-20-49-02-02. REMAINING THICKNESS FOUND TO BE 0.026" IAW SRM REV 12 53-20-49-02-02. REMOVED DIP TRAY FOR FOM IAW SRM 51-41-00-00-01, REV 12. REMOVED SEAT TRACK NR 5 IAW SRM 51-41-00-00-01 & 51-42-05-02-01 & 51-40-15-02-01, REV 12. MATCH DRILLED SEAT TRACK IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL SEAT TRACK NR 5. INSTALLED SEAT TRACK NR 5 IAW SRM 51-42-05-02-01, 51-40-15-02-01 AND 51-41-05-00-01, REV 12. WM 20-12-10-201, REV 1. PERFORMED GROUNDING OF METALLIC COMPONENTS, CHECK SATISFACTORY AT THIS TIME (.2 M OHMS). APPLIED TOPCOAT SURFACE PROTECTION TO RIVETS IAW SRM 51-25-15-02-01, REV 12. INSTALLED DRIP TRAY IAW SRM 51-41-00-00-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 216 STR 32-29S HAVE CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6 TASK 51-00-01-250-801, REV 8. IAW SRM 53-20-15-00-01, REV 12 AND DWG 85328320 FRAME MEASURED ABOVE NOMINAL, BLENDING WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 19.4 STR 33-32S HAS CORROSION. REMOVED RIVETS TO FOM REMOVED CORROSION IAW SRM 51-42-05-02-01 AND 51-21-00-00-02, REV 12 MIN THICKNESS NOTED .038", CONFIRMED CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801, PT 1, REV 8. BLENDS WITHIN LIMITS SRM 53-00-00-02-09, REV 12. INSTALLED RIVETS IAW SRM 51-42-05-02-01, REV 12. PRIOR TO INSTALLING RIVETS, ALODINE AND PRIMED REWORKED AREA IAW SRM 51-21-10-02-01, 51-25-10-02-01, REV 12. APPLIED INTERIOR AND EXTERIOR TOPCOAT, APPLIED CIC TO REWORKED AREA IAW SRM 53-00-00-02-09, REV 12.

Part: STANCHION — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STANCHION AT FRAME -18.25 STR 31P HAS CORROSION. REMOVED FWD FITTINGS AT -18.25 AND 31P TO FOM IAW SRM 51-42-05-02-01 AND 51-41-05-00-01, REV 12. REMOVED STANTION AT FRAME -18.25 DUE TO CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-20-43-00-01, REV 12. NO DAMAGE ALLOWED. MATCH DRILLED NEW STANCHION IAW SRM 51-40-07-02-01, REV 12. REINSTALLED NEW STANTION AND FWD FITTING IAW SRM 51-42-05-02-01 AND SRM 51-40-05-02-01, REV 12. APPLIED TOP COAT AND CPC IAW SRM 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40.

Part: STANCHION — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STANCHION AT FRAME -18.25, STR 31S HAS CORROSION. REMOVED BOLT AND FWD FITTING TO FOM IAW SRM 51-41-05-00-01 AND 51-42-05-02-01, REV 12. REMOVED STANTION TO FOM STANTION FOUND TO BE OUT OF LIMITS DUE TO CORROSION NO DAMAGE ALLOWED IAW SRM 53-20-03-00-01, REV 12. MATCH DRILLED NEW STANCHION IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL FWD FITTING AND REPLACEMENT STANTION. INSTALLED NEW STANCHION AND FWD FITTING IAW SRM 51-23-00-00-01, 51-42-05-02-01, 51-40-10-02-01, 51-41-00-00-01 REV 12. APPLIED TOP COAT AND CPC IAW SRM 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 624.5, STR 33-31S HAVE CORROSION. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1 REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-40-15-00-01 AND 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 624.5, STR 33-31P HAVE CORROSION. REMOVED CORROSION IAW SRM 51-21-00-00-02-09, REV 12. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1 REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-40-15-00-01 AND 53-00-00-02-09, REV 12.

Part: SEAT TRACK — DAMAGED (NR 13) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 13 HAS AREAS OF GOUGES INSIDE THE CLAW. REMOVED CORROSION IAW SRM 53-30-49-02-01, REV 12. FOUND TO BE 0.025", TOP CLAW MATERIAL LOSS 0.012". FOUND TO BE WITHIN LIMITS IAW SRM 53-30-49-02-01 REV 12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801 PT 1 REV 8.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE AT FR 156 STR 32-30S HAS CORROSION. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6, TASK 51-00-01-250-801, REV 8. FRAME FLANGE FOUND TO BE WITHIN LIMITS IAW SRM 53-00-00-02-09 REV 12.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

SKIN STRAP AT 31P, BETWEEN FR 94.8 - 116 HAS MINOR CORROSION. REMOVED CORROSION FROM NR 5 SEAT TRACK IAW SRM 51-21-00-00-02, REV 12. CONTINUED REMOVING CORROSION FROM SEAT TRACK NR 5 IAW SRM REV 12 53-20-49-02-02. MECHANICALLY MEASURED SEAT TRACK NR 5 DEEPEST AREA FOUND 0.068". SEAT TRACK FOUND TO BE OUT OF LIMITS IAW SRM REV 12 53-20-49-02-02. REMAINING THICKNESS FOUND TO BE 0.026" IAW SRM REV 12 53-20-49-02-02. REMOVED DIP TRAY FOR FOM IAW SRM 51-41-00-00-01, REV 12. REMOVED SEAT TRACK NR 5 IAW SRM 51-41-00-00-01 & 51-42-05-02-01 & 51-40-15-02-01 REV 12. MATCH DRILLED SEAT TRACK IAW SRM 51-40-07-02-01, REV 12. OK TO INSTALL SEAT TRACK #5. INSTALLED SEAT TRACK #5 IAW BOMBARDIER Q400 SRM 51-42-05-02-01, 51-40-15-02-01 AND 51-41-05-00-01 REV 12. WM 20-12-10-201, REV 1. PERFORMED GROUNDING OF METALLIC COMPONENTS, CHECK SATISFACTORY AT THIS TIME (.2 M OHMS). APPLIED TOPCOAT SURFACE PROTECTION TO RIVETS IAW SRM 51-25-15-02-01, REV 12. INSTALLED DRIP TRAY IAW SRM 51-41-00-00-01, REV 12.

Part: ACCESS PANEL — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION AROUND SCREW HOLES OF MATING SURFACE ON PANEL 622BT. REMOVED CORROSION AS MARKED IAW SRM 57-10-35-02-02, REV 12. MECHANICALLY MEASURED, MAX MATERIAL LOSS OF .009" IS WITHIN LIMITS IAW SRM REV 12-57-10-35-02-02. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801 PT 1, REV 7. OK TO APPLY SURFACE PROTECTION. APPLIED ALODINE AND PRIMER IAW SRM REV 12 51-21-10-02-01 AND 51-25-40-02-01. APPLIED EPTFE TAPE IAW AMM 57-11-01-400-801, REV 40. RE IDENTIFIED PANEL 622BT SRM 57-10-35-02-02, REV 12.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 10,385 hrs · 11,359 cycles

SEAT TRACK NR 16 HAS AREAS OF CORROSION. REMOVED CORROSION FROM SEAT TRACK NR 16 IAW SRM 53-40-49-02-02, REV 12. SEAT TRACK FOUND TO BE OUT OF LIMITS IAW SRM 53-20-49-02-02 REV 12. FLANGES AT .046IN AND CLAW AT .0195IN. REMOVED NR 23 SEAT TRACK AND WEB FROM X698-X728 RT SIDE TO FOM IAW SRM REV 12 51-42-05-02-01, 51-41-05-00-01 AND 51-40-15-02-01. REMOVED SEAT TRACK 16 IAW IAW SRM 51-42-05-02-01, REV 12, 51-40-15-02-01 REV 12 AND 51-41-05-00-01 REV 12. MATCH DRILLED REPLACEMENT NR 16 SEAT TRACK IAW SRM REV 12 51-40-27-02-01. OK TO INSTALL SEAT TRACK AND THE ABOVE MENTIONED PARTS REMOVED TO FOM. BEGAN INSTALLING SEAT TRACK NR 16 IAW SRM 51-42-05-02-01, REV 12. INSTALLED RIVETS IN SEAT TRACK 16 IAW BOMBARDIER SRM 51-42-05-02-01, REV 12. INSTALLED HILITES IAW SRM 51-40-15-02-01, REV 12 IN SPLICE. OK TO INSTALL WEB AND SEAT TRACK 23. INSTALLED SEAT TRACK NR 23 IAW SRM 51-42-05-02-01 REV 12 AND SRM 51-41-05-00-01, REV 12. INSTALLED WEB WITH SEAT TRACK NR 23 IAW SRM 51-42-05-02-01 REV 12. INSTALLATION OF SEAT TRACK NR 16 IS COMPLETE. APPLIED PRIMER AND ALUMINIZED PAINT IAW SRM 51-25-10-02-01, 51-25-15-02-01 REV 12. PERFORMED GROUNDING CHECK OF METALLIC COMPONENTS IAW SRM 51-80-00-02-01 REV 12. CHECK SATISFACTORY AT THIS TIME. 0.00M. PRIMED AND PAINTED RIVETS IAW SRM 51-25-10-02-01 AND 51-25-15-02-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME 19.400 HAS CORROSION BETWEEN STRINGERS 30-32P. REMOVED CORROSION IAW SRM 51-42-05-02-01 AND 51-21-00-00-02, REV 12. CONFIRMED CRACK FREE CONDITION REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1, REV 8. BLENDS WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 216 STR 32-29P HAVE CORROSION. REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. VERIFIED AFFECTED AREAS CRACK FREE REF NDTM PART 6, TASK 51-00-01-250-801, REV 8. FOUND TO BE WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12.

Part: SEAT TRACK — DAMAGED (COCKPIT) · airframe 10,385 hrs · 11,359 cycles

CO-PILOTS SIDE OTBD SEAT TRACK WORN ON UPPER SURFACE. SMOOTHED DAMAGE IAW SRM 53-10-49-02-01, REV 12, CONFIRMED CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1 REV 7. BLENDS FOUND TO BE WITHIN LIMITS IAW SRM 53-10-49-02-01, REV 12.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 261LT IS CHAFED ON MATING SURFACE. REMOVED FASTENERS AS REQUIRED IAW SRM 51-44-30-02-01, REV 12. REMOVED DAMAGE SRM 53-75-06-02-01 REV 12. CONFIRMED CRACK FREE IN AFFECTED AREA REF NTM 51-00-06-910-801, PT 1, REV 7. MECHANICALLY MEASURED MIN REMAINING THICKNESS IS 0.089". IN LIMITS IAW SRM 53-75-06-02-01 REV 12. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. CAMLOC GRIP LENGTH GOOD, MIN POSSIBLE COMBINED THICKNESS .181" SRM 53-75-06-02-01, REV 12. INSTALLED FASTENERS IAW SRM REV 12 53-75-06-02-01.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGE OF FR 94.8 STR 31S HAS CORROSION. REMOVED 12 RIVETS TO FOM IAW SRM 51-42-05-02-01, REV 12, REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PT 6, TASK 51-00-01-250-801, REV 8. MIN THICKNESS REMAINING NOTED .039 BETWEEN STRINGER 31S AND 30S REF NDTM TASK 51-00-04-910-801, REV 8. ALL WORK PERFORMED IAW SRM 53-00-00-02-09, REV 12. NOMINAL THICKNESS .040" IAW SRM 53-20-15-00-01, REV 12. MATERIAL LOSS IN LIMITS IAW SRM 53-00-00-02-09, REV 12, MIN THICKNESS REMAINING NOTED .041" BETWEEN STRINGERS 30S AND 29S REF NDTM 51-00-04-910-801, PT 1, REV 8. ALODINED AND PRIMED IAW SRM 51-21-10-02-01, 51-25-10-02-01 REV 12. INSTALLED 12 RIVETS IAW SRM 51-42-05-02-01, REV 12. APPLIED TOP COAT AND CPC IAW SRM 51-25-15-02-01, REV 12 AND AMM 51-25-01-390-801, REV 40.

Part: SPAR — CHAFED (CENTER WING) · airframe 10,385 hrs · 11,359 cycles

CENTER WING FRONT SPAR UPPER CAM LOC RECEPTACLE FLANGE BETWEEN LT WING STA YW45 AND LT STA YW60 IS CHAFED. SMOOTHED CHAFE DAMAGE IAW SRM 57-10-05-02-01 R12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801 & 51-00-06-910-801, PT 1, REV 7. FOUND FLANGE TO BE WITH IN LIMITS IAW SRM 57-10-05-02-01, REV 12.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 261HT IS CHAFED ON MATING SURFACE. REMOVED FASTENERS AS REQUIRED IAW SRM 51-44-30-02-01, REV 12. REMOVED DAMAGE IAW SRM 53-75-06-02-01 REV 12. MECHANICALLY MEASURED, MIN REMAINING THICKNESS IS 0.099". DAMAGE IS IN LIMITS IAW SRM 53-75-06-02-01, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 7. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. CAMLOC GRIP GOOD, MIN POSSIBLE COMBINED THICKNESS .191 SRM 53-75-06-02-01, REV 12. INSTALLED FASTENERS IAW SRM REV 12 53-75-06-02-01.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 261FT IS CHAFED ON MATING SURFACE. REMOVED FASTENERS AS REQUIRED IAW SRM 51-44-30-02-01, REV 12. REMOVED DAMAGE IAW SRM 53-75-06-02-01, REV 12. CONFIRMED CRACK FREE REF NTM 51-00-06-910-801 PT 1, REV 7. MECHANICALLY MEASURED MIN REMAINING THICKNESS IS 0.096". IN LIMITS IAW SRM 53-75-06-02-01, REV 12. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. CAMLOC GRIP LENGTH GOOD, MIN POSSIBLE COMBINED THICKNESS IS .180" REF SRM 53-75-06-02-01, REV 12. INSTALLED FASTENERS IAW SRM REV 12 53-75-06-02-01.

Part: SPAR — CHAFED (CENTER WING) · airframe 10,385 hrs · 11,359 cycles

CENTER WING FRONT SPAR UPPER CAM LOC RECEPTACLE FLANGE BETWEEN RT WING STA YW45 AND RT STA YW60 IS CHAFED. SMOOTHED CHAFE DAMAGE IAW SRM 57-10-05-02-01, REV 12, CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-04-910-801 PTI 051-00-06-910-801, PT 1, REV 7. FOUND FLANGE TO BE WITH IN LIMITS IAW SRM 57-10-05-02-01, REV 12.

Part: SEAT TRACK — DAMAGED (COCKPIT) · airframe 10,385 hrs · 11,359 cycles

CO PILOTS SIDE INBD SEAT TRACK WORN ON UPPER SURFACE. SMOOTHED DAMAGE IAW SRM 53-10-49-02-01, REV 12. CONFIRMED CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801 PT 1 REV 7. BLENDS FOUND TO BE WITH IN LIMITS IAW SRM 53-10-49-02-01, REV 12.

Part: FRAME — CORRODED (FUELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 94.8 STR 32-29P HAVE CORROSION. REMOVED 16 RIVETS TO FAM IAW SRM 51-42-05-02-01, REV 12, REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. VERIFIED AFFECTED AREA TO BE CRACK FREE, REF NDTM PT 6, TASK 51-00-01-250-801, REV 8. MINIMUM THICKNESS REMAINING NOTED, .038, REF NDTM PART 1, TASK 51-00-04-910-801, REV 8. WORK PERFORMED IS IAW SRM 53-00-00-02-09, REV 12. NOMINAL THICKNESS .040" IAW SRM 53-20-15-00-01, REV 12. MATERIAL LOSS IN LIMITS IAW SRM 53-00-00-02-09, REV 12. RESTORED SURFACE PROTECTION IAW SRM 51-21-10-02-01 & 51-25-10-02-01, REV 12. INSTALLED (16) EA RIVETS IAW SRM 51-42-05-02-01 & 51-23-00-00-01, REV 12. APPLIED TOP COAT SRM 51-25-15-02-01, REV 12. APPLIED CPC IAW AMM 51-25-01-590-801, REV 40.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER TIE HARDWARE AT FR -18.25, STR 31P IS CORRODED. REMOVED HARDWARE IAW AMM 20-10-01-430-801, REV 40. INSTALLED NEW HARDWARE IAW AMM 20-10-01-430-801, REV 40.

Part: SEAT TRACK — DAMAGED (COCKPIT) · airframe 10,385 hrs · 11,359 cycles

PILOTS SIDE INBD SEAT TRACK WORN ON UPPER SURFACE. SMOOTHED DAMAGE IAW SRM 53-10-49-02-01, REV 12. CONFIRMED CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801, PT 1, REV 7. BLENDS FOUND TO BE WITHIN LIMITS IAW SRM 53-10-49-02-01, REV 12.

Part: FAIRING — CHAFED (WING-BODY) · airframe 10,385 hrs · 11,359 cycles

UPPER WING TO FUSELAGE FAIRING PANEL 261CT IS CHAFED ON MATING SURFACE. REMOVED FASTENERS AS REQUIRED IAW SRM 51-44-30-02-01, REV 12. REMOVED DAMAGE IAW SRM 53-75-06-02-01, REV 12. MECHANICALLY MEASURED, MIN REMAINING THICKNESS IS 0.092" IN LIMITS IAW SRM 53-75-06-02-01, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT 1, REV 7. ALODINED AND PRIMED IAW SRM 51-21-10-02-01 AND 51-25-10-02-01, REV 12. CAMLOC GRIP LENGTH GOOD, MIN POSSIBLE COMBINED THICKNESS .176 SRM 53-75-06-02-01, REV 12. INSTALLED FASTENERS IAW SRM REV 12 53-75-06-02-01.

Part: SEAT TRACK — WORN (COCKPIT) · airframe 10,385 hrs · 11,359 cycles

PILOTS SIDE OTBD SEAT TRACK WORN ON UPPER SURFACE. SMOOTHED DAMAGE IAW SRM 53-10-49-02-01, REV 12, CONFIRMED CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1 REV 7. BLENDS FOUND TO BE WITHIN LIMITS IAW SRM 53-10-49-02-01, REV 12.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

STRINGER 26S HAS 1 CORRODED RIVET FORWARD OF FR196. REMOVED RIVET IAW SRM 51-24-05-02-01, REV 12. INSTALLED RIVET IAW SRM 51-42-05-02-01, REV 12. PRIMED RIVETS AND TOP COATED IAW SRM 51-25-10-02-01 AND 51-25-15-02-01, REV 12. APPLIED EXT TOP COAT IAW SRM 51-25-15-02-01 REV 12. CPC TO BE APPLIED ON TC 531000Q01-60176-QMBD, WO 144032.

Part: ATTACH BRACKET — BROKEN (LT WING) · airframe 10,385 hrs · 11,359 cycles

LT CANOE PANEL 527AB AFT INBD ATTACH BRACKET IS BROKEN. REMOVED BRACKET IAW SRM 51-41-05-00-01, REV 12. INSTALLED NUTPLATES ON NEW BRACKET IAW SRM 51-42-05-02-01, REV 12. REINSTALLED BRACKET IAW SRM 51-41-05-00-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 155 STR 32-30P HAVE CORROSION. REMOVED 1 EA RIVET TO FOM AND REMOVED CORROSION IAW 51-42-05-02-01 AND 53-00-00-02-09, REV 12. REMOVED ADDITIONAL RIVETS TO FOM IAW SRM 51-42-05-02-01, REV 12. VERIFIED AFFECTED AREAS TO BE CRACK FREE NDTM PART 6, TASK 51-00-01-250-801, REV 8 MIN THICKNESS NOTED, .043" REF NDTM PART 1 TASK 51-00-04-910-801, REV 8. NOMINAL THICKNESS IS .040" REF DWG 85328143, FOUND TO BE WITHIN LIMITS IAW SRM 53-20-15-00-01, REV 12. ALODINE AND PRIMER REWORKED AREA IAW SRM 51-21-10-02-01, 51-25-10-02-01 REV 12. INSTALLED RIVETS IAW SRM 51-42-05-02-01, REV 12. APPLIED TOP COAT SRM 51-25-15-02-01 REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 196 STR 32-30S HAVE CORROSION. REMOVED 11 RIVETS AND REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6, TASK 51-00-01-250-801, REV 9. MINIMUM THICKNESS REMAINING NOTED BETWEEN STRINGER 31S AND 30S .044 ON THE FLANGE AND .046 ON THE WEB, AND BETWEEN STRINGER 31S AND 32S, .044 ON THE FLANGE AND .047 ON THE WEB REF Q400 NDTM PART 1 TASK 51-00-04-910-801 REV 8. NOMINAL THICKNESS OF FRAME IS .040IN IAW SRM 53-20-15-00-01, ITEM 432, REV 12 AND DWG 85328121. CORROSION REMOVAL IS WITHIN LIMITS IAW SRM 53-00-00-02-09, REV 12. ALODINED AND PRIMED RIVET HOLES AND INSTALLED REMOVED RIVETS AS REQUIRED IAW SRM 51-21-10-02-01, 51-25-02-01 AND 51-42-05-02-01 REV 12. APPLIED ALODINE PRIMER AND TOP COAT IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01 REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME FLANGES AT FR 196 STR 32-30P HAVE CORROSION. REMOVED 10 RIVETS AND REMOVED CORROSION IAW SRM 53-00-00-02-09, REV 12. VERIFIED AFFECTED AREAS TO BE CRACK FREE REF NDTM PART 6, TASK 51-00-01-250-801, REV 8. MINIMUM THICKNESS REMAINING NOTED BETWEEN STRINGER 31P AND 30P .043 ON THE FLANGE AND .044 ON THE WEB AND BETWEEN 32P AND 31P, .042 REF NDTM PART 1 TASK 51-00-04-910-801 REV 8. NOMINAL THICKNESS OF FRAME IS .040 IAW SRM 53-20-15-00-01, ITEM 432, REV 12 AND DWG 85328121. CORROSION REMOVAL IS WITHIN LIMITS OF SRM REPAIR 53-00-00-02-09, REV 12. ALODINED AND PRIMED RIVET HOLES AND INSTALLED REMOVED RIVETS AS REQUIRED IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-42-05-02-01, REV 12. APPLIED ALODINE PRIMER AND TOP COAT TO REPAIR AREAS IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01 REV 12. APPLIED CPC AMM 51-25-01-390-801, REV 40.

Part: SKIN — CORRODED (LT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON LT WING LANDING INBD AND OTBD SIDE FOR PANEL 524AT. REMOVED DAMAGE IAW SRM 57-20-35-02-05, REV 12. MIN THICKNESS NOTED .079" CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT 1 AND 51-00-04-910-801, PT 1 REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINE AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: SKIN — CORRODED (RT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON RT WING LANDING INBD SIDE FOR PANEL 624CT. REMOVED CORROSION IAW SRM 57-20-35-02-05, REV 12 MIN THICKNESS NOTED .084", CONFIRMED AFFECTED AREA CRACK FREE NTM 51-00-04-910-801 AND 51-00-06-910-801 PT 1, REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINE AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: NUT PLATE — CORRODED (WINDSHIELD) · airframe 10,385 hrs · 11,359 cycles

FOUND ONE CORRODED NUT PLATE FOR CO PILOT WINDSHIELD. R & R OLD NUTPLATE WITH A NEW 1 SRM 51-42-35-02-01 AND 51-42-05-02-01, REV 12. APPLIED SURFACE PROTECTION TO RIVETS IAW SRM 51-25-10-02-01, REV 12. PERFORMED RII INSPECTION OF INSTALLATION OF NUT PLATE & NUT PLATE STRIP TO CO-PILOT'S WINDSHIELD FRAME.

Part: SKIN — CORRODED (LT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON LT WING LANDING INBD SIDE FOR PANEL 524DT. REMOVED CORROSION AS MARKED IAW SRM 57-20-35-02-05, REV 12 MIN THICKNESS NOTED .079" CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801 PT 1 AND 51-00-06-910-801, PT 1 REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINE AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

FRAME WEB AREA OF FR 236, STR 30P HAS CORROSION. REMOVED CORROSION IAW SRM 51-21-00-00-02, REV 12. VERIFIED AFFECTED TO BE CRACK FREE REF NDTM PART 6, TASK 51-00-01-250-801, REV 8. MINIMUM THICKNESS NOTED, .043 REF NDTM PART 1, TASK 51-00-04-910-801, REV 8. NOMINAL THICKNESS OF FRAME IS .040IN IAW DWG 85361310 AND SRM 53-30-15-00-01, ITEM 4, REV 12. CORROSION BLEND IS IN LIMITS IAW SRM 53-00-00-02-09, REV 12. APPLIED ALODINE PRIMER AND PAINT IAW SRM 51-21-10-02-01, 51-25-10-02-01 AND 51-25-15-02-01 REV 12.

Part: ACCESS PANEL — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION AROUND SCREW HOLES OF MATING SURFACE ON PANEL 522BT. REMOVED CORROSION AND ALODINED MIN THICKNESS REMAINING .217, PANEL IS WITHIN LIMITS IAW SRM 57-10-35-02-02, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT 1, REV 7. APPLIED ALODINE AND PRIMED REWORKED AREAS IAW SRM REV 12 57-10-35-02-02. COMPLIED WITH STEP 7 OF SRM 57-10-35-02-02, REV 12.

Part: SKIN — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 524DT MATING SURFACE. REMOVED CORROSION AND BLENDED IAW SRM REV 12 57-20-35-02-02. MIN THICKNESS REMAINING .118 IS WITHIN LIMITS IAW SRM REV 12 57-20-35-02-02. ALODINED, PAINTED AND RE IDENTIFIED IAW SRM REV 12 57-20-35-02-02. CONFIRMED CRACK FREE IN AFFECTED AREAS REF NTM 51-00-06-910-801, PT 1, REV 7.

Part: ACCESS PANEL — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON ACCESS PANEL 624BT MATING SURFACE. REMOVED CORROSION IAW SRM 57-20-35-02-02, REV 12. WITHIN LIMITS IAW SRM 57-20-35-02-02, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 7. INSTALLED NEW OUTER SEAL IAW SRM REV 12 57-20-35-02-02. ALODINED AND PRIMED AND RE IDENTIFIED IAW SRM REV 12 57-20-35-02-02.

Part: SKIN — CORRODED (RT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON RT WING LANDING INBD AND OTBD SIDE FOR PANEL 624AT. REMOVED CORROSION IAW SRM 57-20-35-02-05, REV 12 MIN THICKNESS NOTED .005" CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801, PT 1, REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINE AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: SKIN — CORRODED (LT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON LT WING LANDING INBD SIDE FOR PANEL 524CT. REMOVED CORROSION ON LANDING IAW SRM 57-20-35-02-05, REV 12 MIN THICKNESS NOTED .081" CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1, REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINED AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: SKIN — CORRODED (LT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON LT WING LANDING INBD SIDE FOR PANEL 524BT. REMOVED DAMAGE IAW SRM 57-20-35-02-05, REV 12 MIN THICKNESS NOTED .085", CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1, REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINE AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: SKIN — CORRODED (LT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON LT WING LANDING INBD SIDE FOR PANEL 524ET. REMOVED CORROSION IAW SRM 57-20-35-02-05, REV 12 MIN THICKNESS NOTED .085" CONFIRMED CRACK FREE IN AFFECTED AREA REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1, REV 7. FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINED AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: SKIN — CORRODED (LT WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON RT WING LANDING INBD AND OTBD FOR PANEL 624BT. REMOVED CORROSION IAW SRM 57-20-35-02-05, REV 12. MIN THICKNESS NOTED .085", CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-04-910-801, PT 1 AND 51-00-06-910-801 PT 1, REV . FOUND BLENDS TO BE WITHIN LIMITS IAW SRM 57-20-35-02-05, REV 12. APPLIED ALODINE AND PRIMER IAW SRM 51-21-10-02-01 AND 51-25-40-02-01, REV 12.

Part: ACCESS PANEL — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 624AT MATING SURFACE. REMOVED CORROSION FROM PANEL 624AT IAW SRM 57-20-35-02-02, REV 12. MINIMUM REMAINING ON PAD IS .115 IS WITHIN LIMITS IAW SRM 57-20-35-02-02, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT1, REV 7. PRIOR TO BLENDING CORROSION OUTER SEAL WAS REMOVED IAW SRM REV 12 57-20-35-02-02. ALODINED REWORK AREAS AND INSTALLED NEW OUTER SEAL AND RE-IDENTIFIED IAW SRM REV 12 57-20-35-02-02. PRIMERED BARE METAL AREAS IAW SRM 51-25-10-0201, REV 12.

Part: SKIN — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 524CT MATING SURFACE. REMOVED CORROSION AND BLENDED IAW SRM REV 12 57-20-35-02-02 MIN REMAINING THICKNESS .116 WITHIN LIMITS IAW SRM REV 12 57-20-35-02-02. ALODINED AND RE IDENTIFIED PANEL IAW SRM REV 12 57-20-35-02-02. CONFIRMED CRACK FREE IN AFFECTED AREAS REF NTM 51-00-06-910-801, PT 1, REV 7.

Part: SKIN — CORRODED (FUSELAGE) · airframe 10,385 hrs · 11,359 cycles

EXTERNAL FUSELAGE SKIN HAS CORROSION STA X49.500 AND STRINGER 31P. REMOVED PAINT FROM MARKED AREA AT STA X49.500, STR 31P IAW SRM 51-26-10-02-01, REV 12. REMOVED RIVET IAW SRM 51-42-05-02-01, REV 12. REMOVED CORROSION IAW SRM 53-20-31-02-01, REV 12. MIN THICKNESS NOTED .063", CONFIRMED CRACK FREE REF NTM 51-00-01-250-801 PT6 & 51-00-04-910-801 PT1 REV 7. NORMINAL THICKNESS .060". NO MATERIAL LOSS NOTED. THICKNESS IAW DWG 85327133 SH1, REV C. OK TO TREAT PRIMER AND INSTALL RIVET. ALODINED, PRIMED AND INSTALLED RIVET IAW SRM 51-21-10-02-01, 51-25-45-02-01 AND 51-42-05-02-01, REV 12. PRIMED RIVET TAIL AND TOP COATED IAW SRM 51-25-10-02-01 AND 51-25-15-02-01 TOP COATED EXT IN AW 51-25-15-02-01, REV 12. APPLIED CPC IAW AMM 51-25-01-390-801, REV 40.

Part: BEARING — CORRODED (CARGO DOOR) · airframe 10,385 hrs · 11,359 cycles

FORWARD BAGGAGE DOOR, SECOND FROM AFT LEFT AND LATCH BEARING IS CORRODED. REMOVED CORRODED BEARING IAW NR 652574-3, ISSUE NR 01, DATED 7-27-12, STEPS 1 THROUGH 9. INSTALLED NEW BEARING IAW MCN NR 652574-3 ISSUE NR 01 DATED 7-27-12, STEPS 10 THROUGH 14.

Part: ACCESS PANEL — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 624CT MATING SURFACE. REMOVED CORROSION FROM PANEL 624CT IAW SRM 57-20-35-02-02, REV 12. MINIMUM REMAINING ON PAD IS .1195 IS WITHIN LIMITS IAW SRM 57-20-35-02-02, REV 12. CONFIRMED AFFECTED AREAS CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 7. PRIOR TO BLENDING OUTER SEAL WAS PARTIALLY REMOVED IAW SRM REV 12 57-20-35-02-02. REINSTALLED PARTIALLY REMOVED OUTER SEAL IAW SRM REV 12 57-20-35-02-02. ALODINED AND PRIMED AND REIDENTIFIED IAW SRM REV 12 57-20-35-02-02.

Part: SKIN — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 524ET MATING SURFACE. REMOVED CORROSION FROM PANEL 524ET IAW SRM 57-20-35-02-02, REV 12. MINIMUM REMAINING ON PAD IS .119 IS WITHIN LIMITS IAW SRM 57-20-35-02-01, REV 12. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801, PT 1, REV 7. OUTER SEAL WAS REMOVED PRIOR BLENDED IAW SRM REV 12 57-20-35-02-02. REINSTALLED PARTIALLY REMOVED OUTER SEAL IAW SRM REV 12 57-20-35-02-01. ALODINED AND PRIMED AND REIDENTIFIED IAW SRM REV 12 57-20-35-02-02.

Part: NUT PLATE — CORRODED (AFT SERVICE DOOR) · airframe 10,385 hrs · 11,359 cycles

AFT SERVICE DOOR, FWD FRAME, 2ND DOOR STOP FROM THE TOP HAS A CORRODED NUTPLATE, VIEWED FROM 3RD LIGHTNING HOLE FROM THE TOP. (80) RIVETS WERE REMOVED FROM FWD INNER SKIN FOR FOM, IAW SRM 51-42-45-02-01, REV 12. (2) NUTPLATES REMOVED BECAUSE OF CORROSION AND REPLACED WITH M521042 L3 NUTS AND AN960D10 WASHERS AT AFT SERVICE DOOR STOP NR 19, HOLES D+B. ALL WORK WAS IAW SRM 52-00-00-01-01, PAGES 102-103, FIG 101. OK TO REINSTALL FASTENERS ON INNER SKIN. REPLACED (80) RIVETS REMOVED FOR FOM IAW SRM 51-42-45-02-01, REV 12. REPLACED (2) HUCK BOLTS THAT HAD BEEN REMOVED FOR FOM IAW SRM 51-42-15-02-01 REV 12. RESTORED SURFACE PROTECTION IAW SRM 51-25-10-02-01 + AMM 51-25-01-390-801, REV 40.

Part: SKIN — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 524BT MATING SURFACE. REMOVED CORROSION AND BLENDED IAW SRM REV 12 57-20-35-02-02. MIN REMAINING THICKNESS .118 WITHIN LIMITS IAW SRM REV 12 57-20-35-02-02. ALODINED, PAINTED AND RE-IDENTIFIED IAW SRM, REV 12 57-20-35-02-02. CONFIRMED AFFECTED AREA CRACK FREE REF NTM 51-00-06-910-801 PT 1 REV 7. OUTER SEAL WAS REMOVED PRIOR TO BLENDING IAW SRM 57-20-35-02-02, REV 12. INSTALLED NEW OUTER SEAL IAW SRM REV 12 57-20-35-02-02.

Part: DOOR FRAME — CORRODED (SERVICE DOORWAY) · airframe 10,385 hrs · 11,359 cycles

AFT SERVICE DOOR FWD FRAME HAS CORRODED NUT PLATE VIEWED FROM 3RD LIGHTNING HOLE FROM THE TOP. REMOVED NUT PLATE BRACKET FOR FOM, IAW SRM 51-42-05-02-01 & 51-41-00-00-01 REV 12. R & R 2 NUTPLATES IAW SRM 51-42-75-02-01, REV 12. REINSTALLED NUTPLATE BRACKET IAW SRM 51-42-05-02-01 + 51-41-00-00-01, REV 12.

Part: SKIN — CORRODED (WING) · airframe 10,385 hrs · 11,359 cycles

CORROSION ON PANEL 524AT MATING SURFACE. REMOVED AND BLENDED CORROSION IAW SRM R12 57-20-02-02 MIN REMAINING THICKNESS .115 WITHIN LIMITS IAW SRM REV 12 57-20-35-02-02. ALODINED, PAINTED AND RE-IDENTIFIED IAW SRM 57-20-35-02-02, REV 12. CONFIRMED CRACK FREE IN AFFECTED AREAS REF NTM 51-00-06-910-801, PT 1, REV 7. PRIOR TO BLENDING OUTER SEAL WAS REMOVED IAW SRM REV 12 57-20-35-02-02. INSTALLLED NEW OUTER SEAL IAW SRM REV 12 57-20-35-02-02.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 9,751 hrs · 10,681 cycles

NORMAL BACKLIGHTING DIM IN THE F/A EMERGENCY LIGHT SWITCH. LAMPED. OPS CHECKED GOOD.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 9,180 hrs · 10,068 cycles

CENTER AND FORWARD CABIN OVERHEAD INFORMATION SIGNS HAS INOPERATIVE LAMPS. REPLACED LAMPS.

Part: BLEED AIR SYS — SMOKE (APU) · airframe 8,906 hrs · 9,765 cycles

WHILE WAITING TO REFUEL, SMOKE APPEARED AT EYEBALL VENTS AND BEGAN TO FILL CABIN, AFTER TURNING APU OFF, SMOKE DISSIPATED. OBTAINED "AIR CONTAMINATION CHECKLIST" DATA FROM FLIGHT CREW PERFORMED GVI OF APU FOR EXTERNAL OIL LEAKAGE, NONE NOTED. PERFORMED OIL LEVEL CHECK OF APU IAW AMM TASK 12-10-49-210-802, NO OIL ADDED. PERFORMED OPS TEST OF THE APU IAW AMM TASK 49-00-00-710-801. AS SOON AS APU BLEED AIR WAS TURNED ON, OIL SMOKE EMITTED FROM GASPERS. PERFORMED "REMOVAL OF ODOR FROM THE AIR CONDITIONING DUCT" IAW AMM TASK 21-00-00-160-801, NO OIL SMOKE NOTED FROM GASPERS. RETURNED ACFT TO SERVICE.

Part: UNKNOWN — ODOR (CABIN) · airframe 8,730 hrs · 9,598 cycles

LOW BLEED AIR FLOW AND MUSTY ODOR. INTERAGATED CDS AND FOUND NO FAULT CODES C/W OPS TEST OF BLEED AIR SYS IAW AMM 36-11-00-710-802, NO DEFECTS NOTED. COULD NOT DUPLICATE. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: UNKNOWN — MULTIPLE FAIL · airframe 8,672 hrs · 9,540 cycles

ON DESCENT, PFD1 MON FAIL ON ED. AFCS FAIL ON PFD1. CAS INSTRUMENTS ALL HAVE RED FLAGS. ATT FAIL. ALT FAIL. IVSI FAIL. IAS FAIL. HDG FAIL. RETURNED TO FIELD. LANDING UNEVENTFUL. FOUND ACFT POWERED DOWN UPON OUR ARRIVAL. POWERED ACFT UP AND NO FAIL MESSAGES WERE SHOWN ON DISPLAYS. PERFORMED OPS TEST OF AHRS IAW MX 6342101, OPS TEST GOOD. PERFORMED OPS TEST OF ADU IAW MX 6341101, OPS TEST GOOD. PERFORMED FUNCTIONAL TEST OF FGM IAW MX 6221101, OPS TEST GOOD. NO FAULTS LOGGED IN CDS. AS PRECAUTIONARY MEASURE, R & R AHRS NR 1 IAW MX 6342101. OPS TEST GOOD. HGS RETURN TO SERVICE OPS TEST IAW MX 6343510. OPS TEST GOOD. ACFT REMAINS CAT III AS REFLECTED ON PLACARD. COULD NOT DUPLICATE. RETURNED TO SERVICE.

Part: CONNECTOR — LOOSE (FIRE DECTECTOR) · airframe 8,521 hrs · 9,363 cycles

ENROUTE, RECEIVED A CHECK FIRE DET WARNING LT IT WOULD COME ON INTERMITTENTLY. RAN CHECK LIST AND RECEIVED A BTL LOW LIGHT. THAT LIGHT WAS ALSO COMMING ON AND OFF IT WENT OFF FOR ABOUT 5 FULL MINUTES AND RECEIVED LIGHT AGAIN IN THE DESCENT, ALL THE WAY TO THE GROUND. FOUND CONNECTOR 2600-P26 (APU FIRE DETECTOR) EXTREMELY LOOSE. RE-SECURED CONNECTOR. REF MEL 26-20-1. REMOVED JUMPER WIRES FROM PINS A & B ON APU FIRE BOTTLE CONNECTOR 2600-P12. RE-CONNECTED CONNECTOR 2600-P12 TO APU FIRE BOTTLE. PERFORMED OPS TEST OF APU FIRE DETECTION SYS IAW AMM TASK 26-13-00-710-801. OPS TEST GOOD. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: DEICE SYSTEM — MALFUNCTIONED (WING) · airframe 8,207 hrs · 9,025 cycles

DE-ICE PRESSURE CAUTION AFTER TAKEOFF. BOOT SET SECOND FROM RT WING TIP REMAINED INFLATED, ADVISORY LIGHT STAYED ON. BOOTS DEFLATED AFTER APPROX 20 MINUTES. RETURNED TO THE FIELD AND ACCOMPLISHED A UNEVENTFUL LANDING. PERFORMED OP'S CHECK OF DDV SYS IAW AMM TASKS 30-11-16-710-801. ALSO PERFORMED TACTILE INSPECTION OF ALL BOOTS. NO ISSUES OR DESCREPANCIES REGARDING BOOT SET SECOND FROM RT WING TIP, INTERROGATED CDS, FOUND " LOW PRESS 6B". R & R NR 6 DDV, IAW AMM TASKS 30-11-16-000-801, 30-11-16-400-801. OP'S CHECKED GOOD. NO CAUTIONS OR FAULTS RETURNED. NO OTHER DEFECTS NOTED. PERFORMED FUNCTIONAL TEST OF THE AIRFRAME PNEUMATIC DEICING SYS IAW AMM TASK 30-11-00-720-801. COULD NOT DUPLICATE. RETURNED TO SERVICE.

Part: SEAL — FROZEN (PAX DOOR) · airframe 7,823 hrs · 8,631 cycles

MAIN CABIN DOOR HARD TO OPEN. INSPECTED AND FOUND ICE BUILD UP ON LOWER SEAL THRESHOLD. REMOVED ICE AND CLEANED SEAL MATING AREA. DOOR OPENS AND CLOSES NORMAL. OK FOR CONTINUED SERVICE. NO PARTS REPLACED.

Part: DOOR — BINDING (MAIN PAX) · airframe 7,421 hrs · 8,207 cycles

A F/A REPORTS MAIN CABIN DOOR LEVER VERY HARD TO OPERATE TO OPEN DOOR. GVI FWD PASSENGER DOOR MECHANISM IAW AMM TASK 52-11-00-210-801, NO OBIOUS DEFECT NOTED, OPS CHECK FWD PASSENGER DOOR IAW 52-11-00-710-802 FEW TIMES, NO DEFECT NOTED. COULD NOT DUPLICATE. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHT) · airframe 6,034 hrs · 6,779 cycles

EMERGENCY LIGHTS WILL NOT STAY ON WHEN SWITCH SELECTED ON. FERRY FOR REPAIRS. REPLACED EMERGENCY LIGHTS BATTERY PACKS. ALL OPS CHECKS GOOD. ACFT OK FOR CONTINUED SERVICE.

Part: UNKNOWN — ODOR (CABIN) · airframe 5,911 hrs · 6,645 cycles

F/A'S REPORTED BURNING PAPER ODOR VICINITY OF ROW 12. INSPECTED CABIN, CARGO PITS, LAV AREAS, SEATS, CEILING AND FLOOR AREAS WITH AND WITHOUT RECIRC FAN AND APU BLEED AIR. NO BURNING ODORS OR DEFECTS NOTED. OK FOR CONTINUED SERVICE. COUND NOT DUPLICATE. NO PARTS REPLACED.

Part: HANDLE — LACK OF LUBE (SERVICE DOOR) · airframe 5,886 hrs · 6,618 cycles

AFT SERVICE DOOR WILL NOT OPEN FROM THE INSIDE OF THE ACFT. LUBED AFT SERVICE DOOR HANDLE AS REQUIRED. OPERATED SEVERAL TIMES WITH NO FURTHER DEFECTS NOTED. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: DOOR — BINDING (MAIN PAX) · airframe 5,670 hrs · 6,403 cycles

F/A REPORTS THAT THE MAIN CABIN DOOR IS DIFFICULT TO OPEN. CYCLED THE MAIN CABIN DOOR SEVERAL TIMES, DOOR OPERATES NORMALLY. DOOR HAD A LARGE AMOUNT OF WATER ALL OVER. SUSPECT ICE BUILD UP FROM THE PREVIOUS FLIGHT. NO OTHER DEFECTS NOTED. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: FEEL SENSOR — MALFUNCTIONED (RUDDER) · airframe 5,234 hrs · 5,931 cycles

ON DECENT F/O LEG, RUDDER JAMMED UNTIL F/O APPLIED ENOUGH FORCE TO FREE RUDDER. DVI OF ALL RUDDER CABLE RUNS, RIGGING OF CABLE RUNS, AND REPLACEMENT OF RUDDER FEEL AND SUMMING UNIT. ALL RIG CHECKS AND OPS CHECKS NOW PASS. C/W FREEDOM OF MOVEMENT OF RUDDER IAW GPM 9.2.5. ENSURED FULL TRAVEL AND VERIFIED PROPER DIRECTION OF MOVEMENT - NO DEFECTS NOTED. CHECK FLIGHT GOOD. RETURNED TO SERVICE.

Part: SENSOR — MALFUNCTIONED (LT MLG) · airframe 4,669 hrs · 5,332 cycles

AFTER TAKEOFF FROM LT MAIN GEAR UNSAFE (RED) LIGHT STAYED ON AND STARTED FLASHING. GEAR HANDLE UNSAFE LIGHT ILLUMINATED THE SAME AS THE GEAR HANDLE AMNUNCIATOR LIGHT. RETURNED TO FIELD. LANDING UNEVENTFUL. REMOVED LT MLG PROXIMITY SENSORS IAW AMM 32-61-06-000-802. INSTALLED NEW FROM STOCK LT MLG BOTH PROXIMITY SENSORS. IAW AMM TASK 32-61-06-400-802 PARA 1-4A. STEPS (1)J AND (8) THRU (16). STEPS (2) THRU (7) NOT REQUIRED HARNESS ALREADY MADE UP. PARA 5 A.B.C., PARA D NOT REQUIRED ONLY DOWN LOCKS REPLACED. RETURNED TO SERVICE.

Part: SKIN — CHAFED (LT WING TE FLAP) · airframe 4,459 hrs · 5,085 cycles

C-CHECK- LT WING OB FLAP UPPER SKIN HAS 64IN OF CHAFING FROM WING T/E SHROUD. BLENDED FLAP SKIN IAW SRM 57-52-30-02-01. MEASURED AFFECTED AREA MIN MATERIAL REMAING .029 REF HORIZ NTM 4.2.0-1. THICKNESS IS WITHIN LIMITS IAW HORIZ RD 8/4-57-1428. REWORKED AREA USING EDDY CURRENT, NO CRACKS NOTED AT THIS TIME IAW HORIZON RD 8/4-57-1428, NDTM SEC 6. ALODINED, PRIMED AND PAINTED REF RD 8/4-57-1428 AND SRM 51-25-15-02-01. FABRICATED SHIMS, ALODINED, PRIMED AND PAINTED IAW RD8/4-57-016 AND SRM 51-21-10-02-01, 51-25-10-02-01. INSTALLED SHIMS IAW RD 8/4-57-016 AND RD 8/4-57-1428.

Part: SKIN — CHAFED (LT WING TE FLAP) · airframe 4,459 hrs · 5,085 cycles

C-CHECK - LT WING OTBD FLAP L/E INBD END HAS CHAFING .2500 IN BY .1250 IN WIDE. BLENDED DAMAGE IAW SRM 51-14-00. MEASURED AFFECTED AREA MIN MATERIAL REMAINING .052 REF HORIZON AIR NTM 4.2.0-1. REMAINING THICKNESS IS WITHIN LIMITS IAW RD 8/4-57-1427. INSPECTED REWORKED AREA USING EDDY CURRENT WITH NO CRACKS NOTED AT THIS TIME PER RD 8/4-57-1427 AND HORIZON NDTM SEC 6. ALODINED, PRIMED AND PAINTED IAW RD 8/4-57-1427 AND SRM 51-25-15-02-01. COMPLETED REPAIR IAW RD 8/4-57-1427.

Part: STRUCTURE — CRACKED (W-B FAIRING) · airframe 4,459 hrs · 5,085 cycles

WING TO BODY FAIRING 264AR UPPER HORIZ SUB STRUCTURE CRACKED AT THE AFT END. REMOVED DAMAGED SECTION AT RT UPPER CHANNEL PN 85357153 IAW AD 8/4-53-3330 ISSUED 02 SEPT 10. USED EDDY CURRENT TO INSPECT REPAIR NO CRACKS FOUND. TREATED AREA AND APPLIED PAINT.

Part: STRUCTURE — CHAFED (TE FLAP) · airframe 4,459 hrs · 5,085 cycles

C-CHECK - LT WING OTBD FLAP, L/E INBD END HAS CHAFING .2500 INCH BY .1250 INCH WIDE. BLENDED DAMAGE IAW SRM 51-14-00, REV 7. MEASURED AFFECTED AREA MIN MATERIAL REMAINING .052" REF HORZ. AIR NTM 4.2.0-1 REV 13.

Part: SKIN — CHAFED (TE FLAP) · airframe 4,459 hrs · 5,085 cycles

C-CHECK - LT WING OTBD FLAP, UPPER INBD SKIN HAS 64IN OF CHAFING FROM WING T/E SHROUD. BLENDED FLAP SKIN IAW SRM 57-52-30-02-01, REV 05, APR 07. MEASURED AFFECTED AREA MIN MATERIAL REMAINING .029 REF HORZ NTM 4.2.0-1.

Part: LANDING GEAR — MALFUNCTIONED · airframe 4,387 hrs · 4,999 cycles

ON GEAR RETRACTION FROM FCA, NOSE & RT MAIN RETRACTED NORMALLY. THE LT MAIN RED UNSAFE & DOOR CAUTION LIGHT REMAINED ILLUMINATED FOR 20 SECS LONGER THEN NORMAL & THEN RETRACTED. GEAR EXTENTED NORMALLY. PERFORMED GVI OF NLG, AND BOTH MLG'S, NO DEFECTS NOTED. INTERROGATED PSEU, FOUND RGDRCL FAULT UNREASONABLE FAR-09, LGDRCL FAULT UNREASONABLE FAR-09, NGDRCL FAULT UNREASONABLE FAR-09, IN FAULT HISTORY, NO PRESENT FAULTS FOUND. FERRY TO PDX. COMPLIED WITH RIGGING OF MLG RETRACTION ACTUATOR FOR LT MLG IAW AMM TASK 32-31-11-830-801. ADJUSTED ACTUATOR ROD END ALL OPS CHECKS GOOD. RETURNED TO SERVICE.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 3,242 hrs · 3,741 cycles

SEA - CLIMBING THROUGH 20,000 FT REAR OUTFLOW VALVE DUMPS. DESCENDING BELOW 20,000 FT PRESSURIZATION WORKS NORMALLY. RETURNED TO FIELD. LANDING UNEVENTFUL. FOUND "CPC/OF VALVE DATA FAIL" IN CDS. REMOVED AND REPLACED AFT OUTFLOW VALVE IAW Q400 AMM TASK 21-31-16-000-801 AND 21-31-16-400-801. FUNCTIONAL TEST OF THE PRESSURIZATION CONTROL IS GOOD. FAULT CODE CLEARED AND DID NOT REAPPEAR. RETURNED TO SERVICE.

Part: SWITCH — MALFUNCTIONED (BLEED OVERTEMP) · airframe 2,499 hrs · 2,858 cycles

ON CLIMB OUT "NR 2 BLEED HOT" CAUTION LIGHT CAME ON CAUTION LIGHT STAYED ON FOR ABOUT 20 MINUTES, THE WENT OUT DURING APRPROACH. BLEED WAS SWITCHED OFF IAW CHECKLIST ON ILLUMINATION OF CAUTION LIGHT. DIVERTED AND ACCOMPLISHED A UNEVENTFUL LANDING. INTERROGATED CDS. FOUND FAULT CODE 7005 RT BLD OVERTEMP SWICH FAULT. REMOVED AND REPLACED RT BLEED OVERTEMP SWICH IAW TASK NR 36-11-16-000-801 AND TASK NR 36-11-16-400-801. PERFORMED OPS TEST OF THE BLEED AIR SYS IAW AMM TASK NR 36-11-00-710-802. NO FURTHER DEFECTS NOTED. OPS CHECK GOOD. RETURNED TO SERVICE.

Part: DOWNLOCK SENSOR — OUT OF RIG (LEFT) · airframe 166 hrs · 175 cycles

SEA -L GEAR DOOR AMBER LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION F/A REPORTED BOTH REAR DOORS OPEN. RIGGED LEFT GEAR DOWNLOCK NR 2 SENSOR. PERFORMED GEAR RETRACTION CHECK OPS CHECK GOOD A/C OK FOR CONT SERVICE. NO PARTS REPLACED.

Part: UNKNOWN — UNKNOWN (AUTOFEATHER SYS) · airframe 85 hrs · 89 cycles

SEA - ABORTED TAKEOFF AT 90 KNOTS DUE TO FAILURE OF AUTOFEATHER TO ARM (THERE WAS NO ANNUNCIATION ON ED). RETURNED TO THE GATE. COMPLIED WITH OPS TEST OF PROP AUTOFEATHER AND UPTRIM SYSTEM IAW AMM TASK 61-20-00-710-801. TEST IS GOOD. GROUND RAN ACFT AT RATING, AUTOFEATHER ARMED AS REQUIRED. PERFORMED HIGH SPEED TAXI WITH NO DEFECTS NOTED. ARMED AT 45 KNOTS. COULD NOT DUPLICATE. RETURNED TO SERVICE. NO PARTS REPLACED.

Part: PROXIMITY SENSOR — OUT OF RIG (LT MLG DOOR) · airframe 23 hrs · 12 cycles

STS - LEFT MAIN GEAR UNSAFE INDICATION AND LT MLG DOOR OPEN INDICATION AFTER GEAR SELECTED DOWN ON APPROACH. FERRY TO PDX FOR REPAIRS. INTERROGATED OF PSEU FOUND PRESENT FAULT LGDLK 1 UNREASONABLE FAR. INDUCTANCE VALUE OF LGDLK1 SENSOR WAS AT 7.960 MH BEFORE ADJUSTMENT. RIGGED THE PROXIMITY SENSOR IAW AM TASK 32-61-06-830-801. CHECKED THE INDUCTANCE VALUE OF PROXIMITY SENSOR IAW TASK 32-61-00-280-801, CURRENTLY AT 8.296MH. OP'S TESTED OF THE LANDING GEAR PRIMARY EXTENSION/ RETRACTION SYSTEM IAW TASK 32-31-00-710-801. OP'S CHECKED GOOD. RETURNED TO SERVICE. NO PARTS.