N311DL

Part: ENGINE — BIRD INGESTION (NR 1) · airframe 60,841 hrs · 45,419 cycles

ON T/O AT 1000 FT, HEARD LOUD BANG AND AIRCRAFT YAWED MOMENTARLLY LT AND RT. PASSENGER REPORTED BLUE FLAME FROM FWD OF LT ENGINE. FOWL SMELL IN CABIN. ENGINE PARAMETERS NORMAL. RETURNED TO CVG. FOUND EVIDENCE OF BIRD INGESTION IN NR 1 ENGINE. INSPECTED SAME. OK FOR SERVICE.

Part: FIRE LOOP — FAILED (MLG WW) · airframe 59,756 hrs · 44,602 cycles

CLIMBING THRU 18,000 FT WHEEL WELL FIRE INDICATION. LOWERED GEAR AND INDICATION REMAINED ON. REPLACED DETECTOR LOOP.

Part: SHAFT — FAILED (FUEL PUMP) · airframe 59,187 hrs · 44,190 cycles

FUEL PUMP SHAFT SHEARED AT ROTATION. RUNWAY EXCURSION ON RETURN IN BAD WEATHER. REPLACING NR 2 ENGINE FUEL PUMP AND CONTROL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,387 hrs · 43,587 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP JOINT PER AD 2003-08-15 REVEALED A CRACKED FASTENER LOCATION AT FS 700. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737-200 SRM AND PER ER/A 092798-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,387 hrs · 43,587 cycles

INSPECTION OF THE STRINGER 4R SKIN LAP JOINT PER AD 2003-08-15 REVEALED A CRACKED FASTENER HOLE AT FS 631. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737-200 SRM AND ER/A 092799-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,387 hrs · 43,587 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP JOINT PER AD 2003-08-15 REVEALED A CRACKED FASTENER LOCATION AT FS 500. THE CRACK WAS REMOVED WITH A CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737-200 SRM AND PER ER/A 092825-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 58,387 hrs · 43,587 cycles

INSPECTION OF THE STRINGER 4R SKIN LAP JOINT PER AD 2003-08-15 REVEALED A CRACKED FASTENER HOLE AT FS 848. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN ALUMINUM REPAIR DOUBLER PER B737-200 SRM AND PER ER/A 092824-14AD.

Part: PIN — BROKEN (CABIN) · airframe 57,924 hrs · 43,250 cycles

FOUND ON SERVICE CHECK, AISLE LIGHTS AT SEAT 22L AND 24L INOP. FOUND PIN BROKE ON M1136 AT STATION L753. REPLACED AND TESTED PER M/M.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 57,750 hrs · 43,116 cycles

FWD BULLNOSE EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERY. CHECKS OK.

Part: FUSE — FAILED (EMERGENCY LIGHT) · airframe 57,750 hrs · 43,116 cycles

AFT LT BULLNOSE EMERGENCY LIGHTS INOPERATIVE, REPLACED BATTERY. NO HELP. REPLACED FUSES ON CHARGER. CHECKS GOOD.

Part: FRAME — CORRODED (FUSELAGE) · airframe 56,754 hrs · 42,311 cycles

FOUND ON W2 LETTER CK, CORROSION ON FORMER STA 967 O/B OF STR 27 RIGHT. REPAIRED PER SRM 53-10-4 FIG 11.

Part: FRAME — CORRODED (FUSELAGE) · airframe 56,754 hrs · 42,311 cycles

FOUND ON W-2 LETTER CK, CORROSION ON FORMER STA 967 AT SKIN ATTACH ANGLE BETWEEN STR 27 LEFT AND 27 RIGHT. REPAIRED PER SRM 53-10-4 FIG 11.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 56,754 hrs · 42,311 cycles

FOUND ON W-2 LETTER CK, STRINGER 22RT CUT AT STA 957, 977, 996 FOR OUTFLOW VALVE DOUBLER REPLACEMENT. REPAIR PER SRM 53-10-3 FIG 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 56,754 hrs · 42,311 cycles

FOUND ON W-2 LETTER CK, SKIN BULGED/ RIVETS SHEARED AT FRAME STA 847 BETWEEN STR 27 LEFT AND 27 RIGHT. FOUND FORMER CORRODED AT THIS LOCATION. REPAIRED PER SRM 53-10-4 FIG 9A.

Part: WIRE — SHORTED (CABIN SEAT 22-25) · airframe 56,585 hrs · 42,181 cycles

ON L/O FOUND EMERGENCY LIGHTS AT SEAT ROWS 22-25 INOP AND L2 EXIT IDENTIFIER INOP. REPAIRED DAMAGED WIRE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,597 hrs · 41,457 cycles

A 3 INCH CRACK WAS FOUND IN THE FUSELAGE SKIN AT FS 525 JUST ABOVE STRINGER 16L RUNNING ALONG THE EDGE OF THE INTERNAL BONDED WAFFLE DOUBLER. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737-200 SRM AND PER ER/A 385203-14.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 55,597 hrs · 41,457 cycles

ENG FUEL FLOWS WERE 1500 SPLIT AFTER TAKEOFF. TRIED ENG ANTIICE ON AND MISMATCH ON THROTTLES REVERSED. EPR ON LEFT ENG 1.40 AND ON RIGHT ENG WAS 1.77. AFTER CONSULTATION WITH MAINTENANCE COORDINATOR AND DISPATCH, DIVERTED TO MCO. DUPLICATED ITEM ON R/U. REPLACED NR 1 ENG NOSE DOME. LEAK CHECK NBR 1 PT2 LINE, RAN ENGS 1 AND 2 PER PFHB. ALL CHECKS NORMAL.

Part: SKIN — CORRODED (FS 986.5, S-27R) · airframe 54,006 hrs · 40,814 cycles

FUSELAGE / SKIN / AFT LAV SERVICE CUTOUT / FS 986.5 / STRG. 27R : CORROSION CUTOUT REPAIR AN AREA OF CORROSION WAS FOUND IN THE SKIN AT THE FWD INBD CORNER OF THE AFT LAVATORY SERVICE DOOR CUTOUT. THE CORROSION WAS REMOVED WITH A 4" X 4" CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 384164-14, REV B.

Part: SPAR — CORRODED (HORIZ STAB) · airframe 53,888 hrs · 40,765 cycles

THE CENTER SECTION OF THE HORIZONTAL STAB WAS PREVIOUSLY REWORKED FOR CORROSION IN SEVERAL LUGS. THE REWORK WAS APPROVED FOR A 24 MONTH LIMIT WHICH HAS BEEN REACHED. THE HORIZONTAL STAB WAS REMOVED FROM THE AIRCRAFT AND THE REAR SPAR LOWER CHORD REPLACED TO RESTORE THE AIRCRAFT. THE WORK WAS ACCOMPLISHED PER BAC S/B 737-55-1056 & -1055 AND PER ER/A 383918-14.

Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT) · airframe 51,812 hrs · 39,906 cycles

LEFT WING BODY OVERHEAT LIGHT ON IN FLT. DIVERTED TO MCO. REPAIRING OVERHEAT SYSTEM. TRIED CONTROLLER AND OVERHEAD PANEL, NO HELP. RE-INSTALLED ORIGINAL. INSPECTED FOR LEAKS, NONE FOUND. INSPECTED LOOPS FROM NR 1 ENGINE TO AC PACK BAY CONNECTORS. CHECKED LOOPS WITH BREAKOUT BOX. ALL TEST OK. RAN AIRCRAFT AT TAKEOFF POWER. OPS CHECKS NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 51,697 hrs · 39,857 cycles

THE UPPER HINGE CUTOUT OF THE AFT ENTRY DOOR OPENING WAS FOUND WITH A SMALL CRACK IN THE BONDED SKIN ASSY. THE CRACK WAS REMOVED WITH A TRIM-OUT. THE DAMAGE WAS REPAIRED WITH AN EXTERNAL STEEL DOUBLER PER B737 SRM 53-30-3 AND PER ER/A 382354-14, REV A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 51,697 hrs · 39,857 cycles

THE FWD LOWER CORNER OF THE AFT GALLEY DOOR OPENING WAS FOUND WITH A CRACK IN THE SKIN AND UNDERLYING BEAR STRAP. THE CRACK WAS REMOVED WITH A 1.5 INCH X 1.5 INCH CUTOUT IN ALL LAYERS. THE CUTOUT WAS REPAIRED WITH 3 EXTERNAL ALUMINUM REPAIR DOUBLER PER B737 SRM 53-30-3 AND ER/A 382358-14, REV A.

Part: FAN — UNSERVICEABLE (COCKPIT) · airframe 50,607 hrs · 39,384 cycles

ON LANDING, COCKPIT FILLED WITH SMOKE, TURNED GASPER AND PACKS OFF. AT GATE DETERMINED SMOKE WAS COMING IN WHEN RT PACK WAS TURNED ON. CA FOUND CONTROL CABIN AIR FLOW FAN C/B POPPED. FWD TO MCO AND PLACARD PER MEL 21-00-30A

Part: PUMP — DEFECTIVE (NR 2 ENGINE) · airframe 50,362 hrs · 39,277 cycles

HYD SYSTEM A PUMP 2/ LOW PRESSURE. REMOVED AND REPLACED RT EDP, REPLACED CASE DRAIN AND A SYS FILTERS SERV HYD, LEAK CKS GOOD.

Part: CIRCUIT BREAKER — BURNED (P6-12) · airframe 50,242 hrs · 39,221 cycles

SMOKE IN COCKPIT FOUND LEFT SIDE WINDOW ANTI-ICE C/B C392 AND C848 STANBY HYD PUMP ALTERNATE C/B BURNED

Part: LIGHT — INOPERATIVE (CABIN) · airframe 49,644 hrs · 38,968 cycles

3 BULLNOSE EMERGENCY EXIT LIGHTS INOP C/A RELAMPED

Part: FRAME — WORN (FUSELAGE) · airframe 47,891 hrs · 38,227 cycles

THE FS 440 FRAME HAS A WORN AREA AT THE FORWARD LOWER CORNER OF THE C1 DOORWAY. THE WEAR IS LOCATED ON THE VERTICAL WEB OF THE Z-FRAME. THE DAMAGE WAS BLENDED SMOOTH AND A REPAIR DOUBLER WAS INSTALLED PER ERA 396283-14 AT HMV.

Part: ATTACH FITTING — CORRODED (STABILIZER) · airframe 47,859 hrs · 38,212 cycles

THE RT AND LT HORIZONTAL STABILIZER ATTACH FITTINGS WERE FOUND CORRODED. MATERIAL WAS REMOVED FROM THE FACES AND THE BORES WERE OVERSIZED TO REMOVE CORROSION. THE DAMAGE WAS FOUND AT HMV.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 47,859 hrs · 38,212 cycles

CRACK INDICATIONS WERE FOUND ON THE BL 0.07 LONGITUDINAL FLOORBEAM BETWEEN FS 700 AND FS 717. THE CRACKS WERE REMOVED AND REPAIRED SIMILIAR TO THAT OF B737 S/B 57-1210 PER ERA 396272-14 AT HMV.

Part: FRAME — CORRODED (FUSELAGE) · airframe 47,859 hrs · 38,212 cycles

CORROSION WAS FOUND ON THE INBOARD CHORD OF THE FS 500B FRAME AT STR 25R. THE DAMAGE WAS REMOVED AND A FACTORY SPLICE EXTENDED TO REPAIR THE DAMAGE. THE DAMAGE WAS FOUND AT HMV.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,859 hrs · 38,212 cycles

THE FS 400 RT SIDE FRAME WAS FOUND CRACKED IN THE SKIN ATTACH FLANGE IN THE BEND RADIUS ADJACENT TO THE FIRST FASTENER ABOVE STR 14R. THE DAMAGE WAS TRIMMED OUT AND A REPAIR INSTALLED PER ERA 396241-14 AT HMV.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 47,859 hrs · 38,212 cycles

THE FS 294 FLOORBEAM WAS CORRODED ON THE UPPER CAP AT LBL 10 AND RBL 49. REPAIRED PER ERA 396233-14AD AT HMV.

Part: FITTING — CORRODED (TAIL SECTION) · airframe 47,859 hrs · 38,212 cycles

THE RT HORIZONTAL STABILIZER CLEVIS LUG WAS FOUND CORRODED THE BORES WERE OVERSIZED AND SOME LOCAL BLENDED WAS APPLIED TO THE FACES PER ERA 396224-14 AT HMV.

Part: FITTING — CORRODED (STABILIZER) · airframe 47,859 hrs · 38,212 cycles

CORROSION WAS FOUND ON MULTIPLE LUGS ON THE VERTICAL STABILIZER ATTACHMENT LUGS AND FUSELAGE ATTACH LUGS. ALL CORROSION WAS REMOVED AND REPAIRED PER ERA 396259-14 AT HMV.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,859 hrs · 38,212 cycles

SKIN AT AFT GALLEY DOOR LWR HINGE CUTOUT CRACKED. DAMAGE IS TRIMMED OUT AND REPAIRED. ER/A 300224-14 REV.A

Part: FLOORBEAM — CORRODED (CABIN) · airframe 47,859 hrs · 38,212 cycles

STA 328 FLOORBEAM - PREVIOUS REPAIR CORROSION ON SURFACE TASK NR C53-107-02 OPN 58101AD NRC 416. FLOORBEAM REPAIRED PER SRM 53-10-9 FIG 9.

Part: FLOORBEAM — CORRODED (CABIN) · airframe 47,859 hrs · 38,212 cycles

STA 328 FLOORBEAM PREVIOUS REPAIR CORROSION ON SURFACE, TASK NR C53-107-02. REMOVED FASTENERS. TRIMMED BEAM AND PICKED UP HOLES. TREATED AND PAINTED PER SRM 53-10-9 PG 21. OK TO INSTALL. BEGAN INSTALLING REPAIR PER SRM 53-10-9 FIG 9. INSTALLED REPAIR PER SRM 53-10-9 FIG 9.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,389 hrs · 37,565 cycles

THE FUSELAGE SKIN ASSY BELOW THE L1 DOOR CUTOUT LOWER SILL NEAR THE AFT CORNER WAS FOUND WITH A 1 INCH CRACK. THE CRACK IS TYPICAL OF BAC S/B 737-53-1083. THE CRACK WAS ROUTED OUT AND REPAIRED WITH TWO REPAIR STRAPS ON A TIME-LIMITED BASIS PER THE S/B. THE REPAIR WAS DOCUMENTED PER ER/A 369780-14.

Part: FITTING — CORRODED (BS 685)

THE LT & RT MAIN LANDING GEARS SIDE STRUT SUPPORT FITTING LUGS AT FS 685 WERE FOUND WITH CORROSION IN THE LUG BORES AND ON THE LUG FACES. THE CORROSION WAS REMOVED BY OVERSIZING THE BORES AND MACHINING THE LUG FACES. REPAIR BUSHINGS WERE INSTALLED IN THE LUG BORES PER ER/A 369226-14, REV A.

Part: POWER SUPPLY — INOP (ROW 1-16)

AT DEPARTURE TIME, EMERGENCY LIGHTS ROWS 1 THRU 16 WOULD NOT TURN OFF. REPLACED POWER SUPPLY AND BATTERY LIGHTS OPERATION NORMAL.

Part: VALVE — FAILED (NR 1 ENGINE)

ENGINE OIL TEMP WAS IN THE YELLOW ZONE AROUND 150 DEG C FOR 15 MINUTES. WHEN THE ENGINE WAS IN IDLE THE TEMP WENT UP TO THE RED LINE. REPLACED NR 1 ENGINE FUEL HEAT VALVE (FOUND OPEN/CLOSE IND TANG HANGING UP ON VALVE BODY IN BOTH DIRECTIONS) PER PFHB DRAINED AND REPLENISHED OIL RESERVOIR. REPLACED MAIN OIL SCREEN. OPERATION AND LEAK CHECK GOOD ON ENGINE RUN.

Part: SKIN — CRACKED (BS 750)

THE FUSELAGE SKIN WAS FOUND WITH A 2 INCH CRACK AT FS 750 AND STRINGER 19R. THE CRACK WAS ROUTED OUT OF THE SKIN AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER. THE REPAIR WAS ACCOMPLISHED PER B737 SRM 53-30-3, FIG 6 AND ER/A 367661-14.

Part: VALVE — STUCK (NR 1 ENGINE)

NR 1 ENG OIL TEMP IN YELLOW BAND. ENG FUEL HEAT VLV STUCK IN THE OPEN POSITION. SHUT DOWN ENG AS PRECAUTIONARY. FLIGHT DIVERTED INTO CAE. VLV DEFERRED PER MEL. AT BDL LAYOVER, THE VLV WAS REPLACED.

Part: SKIN — CRACKED (BS 522)

THE FUSELAGE SKIN WAS FOUND WITH A 1 INCH LONG CRACK JUST ABOVE STRINGER 16R AT FS 522. THE CRACK WAS ROUTED OUT AND A REPAIR DOUBLER INSTALLED PER B737 SRM 53-30-3, FIG 1. BECAUSE THE REPAIR EXTENDED UNDR A WING-TO-FUSELAGE PANEL THE REPAIR WAS DOCUMENTED PER ER/A 366606-14 TO ENSURE DTA EVALUATION WILL BE PERFORMED.

Part: MODULE — FAILED (COCKPIT)

COCKPIT FIRE CONTROL PANEL SHORTED. POPPING NOISE COMING FROM PEDESTAL AREA. REMOVED AND REPLACED ENG/APU FIRE CONTROL MODULE.

Part: CONTROL CABLE — FRAYED (RT AILERON)

RT AILERON BINDING AT FULL RT TRAVEL. INSP FOUND AILERON CABLE SEGMENT ABSB-4 FRAYED. MANUFACTURED & INSTLD NEW CABLE SEGMENT ABSB-4 PER M/M. REPLD 2 EA AILERON BUS CABLE PULLEYS AT APPROX STA RBL 60. RIGGED AILERON BUS CABLES AND OPS CKD, ADJUSTED FIRST OFFICERS BODY CABLES AA AND AB AND OPS CK GOOD PER M/M.

Part: BULKHEAD WEB — CRACKED (BS 178)

THE FS 178 BULKHEAD WEB WAS FOUND WITH A CRACK AT LBL 5.7, WL 212. THE WEB HAD A PREVIOUS REPAIR IN THE AREA FOR 3 OTHER CRACKS WHICH WERE CUTUOUT OF THE WEB. THE EXISTING REPAIR DOUBLER WAS REMOVED, THE NEW CRACK CUTOUT, THE WEB INSPECTED FURTHER AND A NEW ALUMINUM REPAIR DOUBLER WAS INSTALLED TO REPAIR ALL OF THE CUTOUT LOCATIONS. THE REPAIR WAS ACCOMPLISHED PER ER/A 365817-14, REV B.

Part: HYD LINE — RUPTURED (NR 2 ENGINE)

ON EXTENSION OF FLAPS HHD LIGHT LOW PRESSURE ILLUMINATED WITH A-SYS QTY NEAR ZERO. REPLACED HYDRAULIC LINE.

Part: LIGHT — BROKEN (CABIN)

EMERGENCY LIGHT INOP ROW 17DEF. REPLACED LIGHT ASSY.

Part: LIGHT — SHORTED (CABIN)

ON PREDEPARTURE, FOUND L1063 FWD EXIT SIGN, EMERGENCY LIGHT RACK SHORTED. REPLACED RACK.

Part: ATTACH LUGS — WORN (LT/RT ELEVATOR)

RT ELEVATOR NR 3 AND NR 4 HINGE FITTING ATTACH LUGS AND LT ELEVATOR NR 4 AND NR 6 HINGE FITTING ATTACH LUGS WERE FOUND ELONGATED AND SCORED ON THE INNER CLEVIS LUG FACE. REFER TO ERA 361171-14 REV A FOR LOCATION AND REWORK DIMENSIONS. THE FITTINGS ARE MACHINED FROM 7075-T7351 BARE PLATE.

Part: PRESSURE DECK — CORROSION (BS 394)

NOSE LANDING GEAR HORIZONTAL PRESSURE DECK WAS FOUND WITH CORROSION AT FS 394 AND LBL 27 EXTENDING 0.042 DEEP. CUTOUT RESULTED IN HOLE SIZED 2.0 (I/B-O/B) BY 3.0 (FWD-AFT). THE PANEL IS M/F LS10328 AND IS 0.075 THICK LOCALLY.

Part: PRESSURE DECK — CORROSION (FS 394)

NOSE LANDING GEAR HORIZONTAL PRESSURE DECK WAS FOUND WITH CORROSION AT FS 394 AND LBL 27 EXTENDING .042 DEEP. CUT OUT RESULTED IN HOLE SIZED 2.0 (I/B-O/B) BY 3.0 (FWD-AFT). THE PANEL IS M/F LS10328 AND IS .075 THICK LOCALLY. REPAIRED PER ERA 361052-14 REV A.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING ACCOMPLISHMENT OF SI 3-69482-12, 3 CRACKS DISCOVERED ON THE FWD FACE OF THE FS 178 BULKHEAD WEB. THREE INDEPENDENT CUTOUTS WERE REQUIRED TO REMOVE THE CRACKS. FIRST CUTOUT, LOCATED I/B OF THE RBL 5.7 VERTICAL STRAP AT WL 201, MEASURES 1.6 VERTICALLY BY 1.O IB TO OB. THE 2ND CUTOUT IS LOCATED JUST BELOW 1ST CUTOUT AT WL 198 AND MEASURES 1.7 VERTICALLY BY 1.O IB TO OB. THE 3RD CUTOUT, LOCATED ON THE O/B SIDE OF THE LBL 5.7 VERTICAL STRAP AT WL 198, IS A 1.O DIAMETER CIRCLE. THE BULKHEAD WEB IS MANUFACTURED FROM 0.032 THICK 2024-T3 CLAD ALUMINUM.

Part: SKIN — CRACKED (C-2 DOOR OPENING)

AFT EDGE STA 840 OF C-2 DOOR OPENING HAS 3 SMALL CRACKS THAT ARE STOP DRILLED BETWEEN STRINGERS 21R AND 22R. THE CRACKS EXTEND THROUGH THE BONDED SKIN 0.036 + 0.036 CLAD 2024-T3 AND BEAR STRAP 0.125 2024-T3.

Part: DOORWAY FRAME — CRACKED (BS 847)

AFT FRAME ON THE C-1 DOORWAY WAS FOUND TO BE CRACKED APPROX 6 BELOW THE LOWER STOP FITTING. THE CRACK IS LOCATED WHERE FRAME WAS GOUGED. A 1.10 DIAMETER HOLE WAS REQUIRED TO CLEAN UP THE DAMAGE TO THE WEB. MATERIAL IS 0.071 7075-T6. THE CRACK WILL BE REPAIRED PER THE INSTRUCTIONS OF AD 93-14-10 AND SB 737-53-1096, REV 5 (DAL SI 3-55297-12AD).

Part: STRUCTURE — CORRODED (BS 31)

FS 31F CORRODED FROM LBL 10 TO RT SIDE OF FUSELAGE. REMOVED CORROSION PER SRM 51-10-6, CORROSION OUT OF LIMITS PER 53-10. REMOVED T-CAP AND FAB REPLACEMENT PER SRM 53-21-0, COMPLETED INSTALLATION OF REPAIR PER MM 53-21-0 FIG 803.

Part: STRUCTURE — CORRODED (BS 312)

AT MV-2, FOUND FS 312 CORRODED FROM LBL 10 TO RT SIDE OF FUSELAGE. REMOVED CORROSION PER SRM 51-10-6, CORROSION OUT OF LIMITS PER 53-10. REMOVED T-CAP AND FAB REPLACEMENT PER SRM 53-21-0 PG 803. COMPLETED INSTALLATION OF REPAIR PER MM 53-21-0 PG 803.

Part: FUEL HEAT VLV — MALFUNCTIONED (NR 1 ENGINE)

ON CLIMBOUT, NR 1 FUEL HEAT INDICATED FULL OPEN-LOSS OF EPR, SPLIT THROTTLES AND OIL TEMP WENT INTO YELLOW BAND FOR 14 MINS, RETURNED TO MSP. REPLACED FUEL HEAT VALVE PER M/M 73-14-11 PG 402. ALL TEMPERTURES WITHIN LIMITS PER M/M 71-09-100 PG 218. FOUND VALVE MISLABLED OLD VALVE.

Part: FUSE — FAILED (CABIN)

EMERGENCY TRACK LIGHTS OUT AT ROWS 1 AND 16. AISLE LIGHTS AT ROWS 11, 15, 21, 24 INOPERATIVE. RELAMPED TRACK LIGHTS, AISLE LIGHTS AT ROWS 11 AND 15. REPLACED BATTERY PACK FUSE. FOUND BATTERY PACK LOOSE FOR ROWS 21 AND 24.

Part: WIRE — BROKEN (CABIN)

EMERGENCY PATH LIGHTS IN F/C CABIN DAMAGED. REPAIRED WIRE AND OPERATION NORMAL.

Part: BULB — FAILED (CABIN)

L-1 DOOR EMERGENCY SLIDE LIGHT INOP. RELAMPED.

Part: DIFF PRESS SW — FAILED (NR 2 ENGINE)

ON CLIMBOUT, NR 2 ENG OIL PRESS BYPASS LIGHT ON. ALL OTHER IND NORMAL, DIVERTED TO MEM, LIGHT STAYED ON. NORTHWEST MTC CHECKED AND REPLACED OIL FILTER AND NO CONTAMINATION WAS FOUND. PUT THE NR 2 ENG BYPASS LIGHT ON MCO MEL 79-00-02. WHEN A/C ARRIVED ATL, MTC REPLACED DIFF PRESS SW 793701055 AND REMOVED MCO.

Part: BULB — FAILED (CABIN)

EMERGENCY FLOOR TRACK LIGHT INOP AT SEAT 23D. REPLACED LAMP, CKS NORMAL.

Part: BATTERY — DISCHARGED (CABIN)

ON PRE-FLIGHT CHECK, FWD CABIN FLOOR TRACK LIGHTS FOUND INOP. REPLACED BATTERY PACKS, OPERATION NORMAL.

Part: SKIN — CRACKED (R-1 DOORWAY)

DURING A LETTER CHECK IN TPA, A CRACK WAS FOUND IN THE R-1 DOORWAY IN THE LOWER AFT CORNER APPROXIMATELY 1.4 INCH LENGTH. THE CRACK WILL BE REPAIRED IN ACCORDANCE WITH B737-200 SRM 53-30-3 FIGURE 26.

Part: VANE — CRACKED (NR 3 TE FLAP)

DURING INSPECTION, RT WING NR 3 FLAP VANE WAS FOUND WITH CRACKED UPPER SKIN. REPAIRED PER SRM 57-53-00 FIG 806.

Part: WEB — CRACKED (NOSE W/W FS270)

DURING INSPECTION, A 6 INCH CRACK WAS FOUND AT THE RT SIDEWALL WEB OF THE NOSE WHEEL WELL AT STATION 270. IN ACCORDANCE WITH S/B 727-53-145, THE WEB WAS TRIMMED OUT AND A REPAIR DOUBLER AND FOUR STRAPS WERE INSTALLED.

Part: EEL RACK — FAILED (CABIN)

DURING INSPECTION, FOUND AFT CABIN FLOOR EMERGENCY TRACK LIGHTS INOP. REPLACED RACK M9222, OPERATION NORMAL.