N309DL

Part: COFFEEMAKER — ARCED (GALLEY) · airframe 59,844 hrs · 45,052 cycles

SPARK JUMPED OUT IN FRONT OF AFT GALLEY, NR 2 POSITION COFFEEMAKER. REPLACED SAME.

Part: SKIN — CRACKED (BS 525 STR 16L) · airframe 59,783 hrs · 45,010 cycles

FUSELAGE SKIN CRACKED AT BS 525, JUST ABOVE STR 16L. INSTALLED DOUBLER PER ER/A 451518-14AD, REF AD 2004-18-06, S/B 737-53A1210.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 59,174 hrs · 44,598 cycles

AFTER PUSHBACK AND NR 2 ENGINE START FLT ATTEND INFORMED US THAT CERTAIN EMERG LIGHTS WERE ILLIMINATED. CYCLED COCKPIT AND AFT FLT ATTEND SWS. LIGHTS REMAINED ON. REPLACED FWD POWER SUPPLY M1132. ALL CKS GOOD.

Part: OUTFLOW VALVE — FAILED (CABIN PRESSURE) · airframe 57,495 hrs · 43,307 cycles

ACFT UNABLE TO PRESSURIZE IN STBY MODE. REMOVED AFT OUTFLOW VALVE. INSTALLED NEW VALVE PER MAINTENANCE MANUAL. ALSO REPLACED CONTROLLER AND PANEL TEST SYS PER MAINTENANCE MANUAL.

Part: FUSE — FAILED (EMERGENCY LIGHT) · airframe 57,295 hrs · 43,163 cycles

EMERGENCY LIGHTS AT R2 DOOR AND AFT AISLE EXIT INOPERATIVE. REPLACED BLOWN FUSES IN POWER SUPPLY FOR LIGHTS.

Part: WIRE — BROKEN (COCKPIT) · airframe 57,198 hrs · 43,095 cycles

WHILE TURNING NR 1 ENG START SWITCH TO START ENG GOT LOUD POP ALONG WITH SPARK FROM BEHIND OVERHEAD PANEL. MTC FOUND 2 BROKEN WIRES BEHIND PANEL THAT CHAFED FROM RUBBING WHISKEY COMPASS EACH TIME IT IS STOWED. REPAIRED WIRES AND REPLACED SWITCH AS PRECAUTION.

Part: BULKHEAD — CANNING (FUSELAGE) · airframe 55,651 hrs · 41,919 cycles

THE WEB OF THE FS 1016 AFT P-DOME WAS FOUND WITH AN OIL-CAN CONDITION BETWEEN S-3L & S-5L. THE DAMAGED AREA OF WEB WAS CUTOUT AND REPAIRED WITH AN ALUMINUM REPAIR DOUBLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 088351-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,602 hrs · 41,878 cycles

THE UPPER AFT CORNER OF THE L2 DOOR CUTOUT WAS FOUND WITH 2 SMALL CRACKS IN THE BONDED SKIN AND UNDERLYING BEAR STRAP. THE CRACKS WERE REMOVED WITH 1 INCH CUTOUTS. THE CUTOUTS WERE REPAIRED WITH 3 EXTERNAL ALUMINUM REPAIR DOUBLER PER B737 SRM 53-30-3 AND ER/A 088350-14, REV A.

Part: ENGINE — FAILED (NR 2) · airframe 55,512 hrs · 41,813 cycles

AT CRUISE FROM YYZ - ATL NR 02 ENGINE OIL PRESS DROPPED TO 28 PSI ALL OTHER INDICATIONS NORM. NR 02 OIL QTY ON MCO NO LOW OIL PRESS LIGHT. AFTER CONSULTING WITH ATL DIVERT TO CVG AND NR 02 ENGINE SHUTDOWN. ENGINE SHUTDOWN REPORT COMPLETED. CHECKED OIL QTY AND OIL CAP FOUND FULL AND CAP IN PLACE. REPLACED ENGINE OIL FILTER INSP OIL FILTER AND CHIP DETECTORS ALL CLEAN. OIL PRESS LIGHT NEVER CAME ON UNTIL AFTER LANDING. CLEAN O/P ORFICE AND REPLACED O/P XMTR. RAN ENGINE TO TAKEOFF PWR AND O/P STAYED 48 PSI. ENGINE OK FOR SERVICE.

Part: CIRCUIT BREAKER — FAILED (COCKPIT) · airframe 49,629 hrs · 38,757 cycles

DURING T/S FOR ITEM ON LT AC BUS WOULD NOT COME ON LINE. FOUND APU GEN C/B WITH BURNED / SCORCHED TERMINALS AT THE B-1/2/3 POSITIONS. REPLACED APU GEN C/B AS PRECAUTION.

Part: FAN — ODOR (CABIN) · airframe 49,094 hrs · 38,535 cycles

DURING LANDING A LINE F/A SMELLED STRONG ODOR IN FWD PORTION OF CABIN. SMELLED LIKE BURNING PLASTIC. RAN BOTH ENGS AND PACKS, NO ODORS NOTED. FWD GASPER FAN TO MCO AND PLAC MEL 21-00-24. DUE TO HISTORY OF C/B POPPING C/B PULLED AND COLLARED E/E COMPTS AND BAGBINS, ALL NORMAL.

Part: REGULATOR — FAILED (NR 1 ENGINE) · airframe 48,713 hrs · 38,375 cycles

A/C FAILED TO PRESSURIZE_,AUTO STBY MANUAL CORR.ACT.FND PRESS LOW OFF NR 1 ENG ,REP NR 1 ENG PILOT PRESS REG PRESS A/C IN ALL POS .CK GOOD

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,936 hrs · 38,051 cycles

TIME LIMITED REPAIR REMOVED AT THE AFT ENGRY DOOR LOWER HINGE CUTOUT AND NEW REPAIR INSTALLED WITH SOLID FASTENERS. ER/A 301124-14 REV C.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,826 hrs · 38,008 cycles

THE FS 947.5 FRAME WAS FOUND CRACKED AT THE CUTOUT FOR S-19R. THE DAMAGE WAS REMOVED WITH A 1.25 X 1.0 INCH CUTOUT IN THE FRAME VERTICAL WEB. THE DAMAGE WAS REPAIRED PER ERA 334913-14 AT HMV.

Part: FRAME — CORRODED (FUSELAGE) · airframe 47,826 hrs · 38,008 cycles

THE FS 400 FRAME WAS FOUND CORRODED ABOVE STR 26R, 3.5 INCHES BELOW THE EXISTING FACTORY SPLICE. THE CORROSION WAS FOUND IN THE TOP OF THE INBOARD FLANGE. THE DAMAGE CUTOUT EXTENDED INTO THE VERTICAL WEB OF THE FRAME. THE DAMAGE WAS REPAIRED PER ERA 334912-14 BY REMAKING THE FACTORY SPLICE TO EXTEND BEYOND THE DAMAGE. THE DAMAGE WAS FOUND DURING HMV.

Part: STRAP — CORRODED (FUSELAGE) · airframe 47,826 hrs · 38,008 cycles

THE INBOARD STRAP ON THE FORWARD FRAME OF THE C2 DOOR CUTOUT WAS FOUND CORRODED. THE STRAP WAS CUT AT RBL 25 AND A NEW INBOARD END WAS SPLICED IN. THE DAMAGE WAS REPAIRED PER ERA334883-14 AT HMV.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 47,826 hrs · 38,008 cycles

THE UPPER CHORD, WEB AND DOUBLER OF THE RBL 24.8 FLOORBEAM WAS FOUND CRACKED AT FS 675. THE CHORD WAS SPLICED AND THE WEB AND DOUBLER WERE REPAIRED PER ERA 334875-14. THE DAMAGE WAS FOUND DURING INSPECTION AT HMV.

Part: FITTING — CORRODED (HORIZONTAL STAB) · airframe 47,826 hrs · 38,008 cycles

THE HORIZONTAL STABILIZER ATTACH LUGS WERE FOUND CORRODED. THE DAMAGE WAS REMOVED BY OVERSIZING THE BORES AND BLENDING SOME OF THE FACES. THE DAMAGE WAS REPAIRED AT HMV PER ERA 334874-14.

Part: FITTING — CORRODED (FUSELAGE) · airframe 47,826 hrs · 38,008 cycles

THE RT AND LT FUSELAGE CLEVIS LUGS THAT ATTACH THE HORIZ STABILIZER WERE FOUND CORRODED. SEVERAL BORES WERE OVERSIZED AND SOME OF THE FACES WERE BLENDED. THE REPAIR WAS ACCOMPLISHED AT HMV PER ERA 334873-14.

Part: FASTENER — WRONG PART (FUSELAGE FRAME) · airframe 47,826 hrs · 38,008 cycles

DURING ACCOMPLISHMENT OF THE FUSELAGE FRAME SPLICE AT FS 440 PER S/B 737-53-1125 IT WAS NOTED THAT FIVE FASTENERS WERE INSTALLED AT THE FACTORY WERE .25 INCHES IN DIAMETER. THE S/B CALLS FOR .2187 INCH FASTENERS. ERA 334853-14 ALLOWS FOR THE .25 INCH FASTENERS. THE MODIFICATION WAS ACCOMPLISHED AT HMV.

Part: ATTACH FITTING — WORN (VERTICAL STAB) · airframe 47,826 hrs · 38,008 cycles

VERTICAL STAB MOVES UP AND DOWN WHEN PUSHING ON UPPER TRAILING EDGE AREA. FOUND ATTACH FITTINGS WORN. REPAIRED SAME.

Part: SKIN — CRACKED (PAX DOOR) · airframe 46,378 hrs · 37,385 cycles

THE LOWER FWD CORNER OF THE AFT GALLEY DOOR CUTOUT WAS FOUND WITH A 1 INCH TYPICAL CRACK THROUGH THE SKIN, BONDED, DOUBLER, AND BEAR STRAP. THE CRACK WAS ROUTED OUT OF ALL MEMBERS AND REPAIRED WITH THREE ALUMINUM DOUBLERS PER ER/A 369515-14, REV A.

Part: FIRE LOOP — MALFUNCTIONED (APU BAY)

ATTEMPTED APU START PRIOR TO LANDING, HAD INDICATION OF APU FIRE (LIGHTS AND BELLS). FIRE HANDLE PULLED, BOTTLE DISCHARGED AND LIGHT EXTINGUISHED. INSPECTED APU AREA AND EXHAUST, SUSPECT FALSE INDICATION. REPLACED LOOP.

Part: FIRE DETECTOR — MALFUNCTIONED (E & E BAY)

APU FIRE INDICATION AFTER START AT 12,000 FT. PULLED FIRE HANDLE AND THE LIGHT REMAINED ON. AFTER FIRING THE BOTTLE THE FIRE HANDLE LIGHT WENT OUT IN ABOUT 2 SEC. APU HAD BEEN RUNNING FOR ABOUT 1 MIN WHEN THE FIRE INDICATION CAME ON. TROUBLESHOOT SYSTEM, NO TROUBLE FOUND.

Part: SKIN — CRACKED (BS 767)

A 2.25 INCH CRACK IN FUSE SKIN STA 767 ABOVE STR 19 RT. INSTALLED DOUBLER PER SRM 53-30-3 F1.

Part: SKIN — CRACKED (FUSELAGE)

A .125 INCH CRACK AT FUSE SKIN AT L-1 WINDOW UPPER O/B CORNER. INSTALLED DOUBLER PER SRM 53-30-3 REPAIR II FIG 11.

Part: SKIN — CRACKED (BS 727)

A 2.25 INCH CRACK IN FUSE SKIN STA 727B STR 18 RT. INSTALLED DOUBLER PER SRM 53-30-3 F1.

Part: OUTFLOW VALVE — FAILED (CABIN)

AT LEVEL OFF AT 37,000 ALTITUDE WARNING HORN SOUNDED AND CABIN ALTITUDE CLIMBING TO 10,000. DESCENDED TO MAINTAIN 10,000 CABIN ALTITUDE AND SELECTED MANUAL AC & DC WORKED OK NO FAIL LIGHT. FOUND FWD OUTFLOW VALVE STUCK OPEN. REPLACED VALVE. ALSO, OVHD PANEL WOULD NOT TEST PROPERLY. REPLACED PANEL.

Part: POWER SUPPLY — INOP (L1 DOOR)

ON NR 4 SERVICE CHECK, L1 DOOR OVERHEAD EMERGENCY LIGHT EXIT SIGN INOP. REMOVED AND REPLACED POWER SUPPLY M1133, OPN CHECK NORMAL.

Part: SKIN — CRACKED (BS 380)

A .75 INCH CRACK WAS FOUND EMANATING FROM THE FWD END OF THE AVIONICS EXHAUST CUTOUT IN THE FUSELAGE BELLY SKIN. ANOTHER 1.25 INCH CRACK WAS EMANATING FROM THE AFT END OF THE CUTOUT. THE CRACKS WERE STOP DRILLED AND AN ALUMINUM DOUBLER INSTALLED AROUND THE CUTOUT PER ER/A 367484-14, REV A.

Part: LINE — LEAKING (NR 1 ENG HYD)

HYD LEAK A-SYS TOTAL LOSS. FOUND LEAK NR 1 ENG. REPLACED HYD PUMP PRESS AND CASE DRAIN LINES. REPLACED HYD PUMP AS PRECAUTION. CHECKED CASE DRAIN FILTER FOR CONTAMINATION, NONE FOUND. REPLACED SAME. SERVICED SYS RAN ENGS AND FLT CONTROLS TO BLEED. ALL CKS NORMAL.

Part: LIGHTS — ILLUMINATED (CABIN)

EMERGENCY EXIT ROW LIGHTING ROWS 5 TO 20 ILLUMINATED WITH EMERGENCY EXIT LIGHTS SWITCH IN COCKPIT IN ARMED POSITION. F/A SWITCH IS OFF. OPERATIONAL TEST OF EMERGENCY LIGHTS OK.

Part: CHARGER — FAILED (CABIN)

SEVERAL EMERGENCY OVERHEAD ASILE LIGHTS INOP. REPLACED CHARGER ASSEMBLY

Part: POWER SUPPLY — INOPERATIVE (CABIN)

AFT CABIN EMERGENCY FLOOR TRACK INOPERATIVE. C/A: REPAIRED WIRE ON TRACK AND REPLACED BATTERY AND POWER SUPPLY FOR AFT TRACK POWER SUPPLY, MFG NR BPS7-3. BATTERY MFG NR 2013-1A.

Part: WIRE — BROKEN (CABIN)

EMERGENCY LIGHT AT SEAT 19 INOPERATIVE. REPLACED LIGHT ASSY WIRE HARNESS AND LIGHT OPS CK NORMAL.

Part: SEAL — FAILED (CARGO DOOR)

FL 330 CABIN STARTED CLIMBING 2,000 FPM, EMERGENCY DESCENT TO 10,000 FT. FOUND FWD CARGO DOOR SEAL BLOWN OUT. REPLACED SEAL RETURNED TO SERVICE.

Part: SKIN — CRACKED (R-1 DOOR CUT OUT)

DURING LETTER CHECK, THE R-1 DOORWAY FRAME WAS FOUND CRACKED AT LOWER AFT CORNER APPROXIMATELY 1.75 INCH. THE CRACK ENDS IN A NUTPLATE HOLE. REPAIRED PER ERA, 301125-14.