N314DA

Part: SKIN — CRACKED (FS 525 S-16R) · airframe 59,766 hrs · 45,273 cycles

THE FUSELAGE SKIN WAS FOUND WITH A CRACK JUST ABOVE THE BONDED DOUBLER MILL LINE OF STRINGER 16R AT FS 525. THE CRACK WAS 1 INCH LONG AND TYPICAL OF THOSE DOCUMENTED IN AD 2004-18-06 AND BAC S/B 737-53A1210. THE CRACK WAS REMOVED WITH A CUT OUT AND REPAIRED WITH AN EXTERNAL DOUBLER PER B737 SRM AND ER/A 450574-14AD.

Part: PROXIMITY SWITCH — OUT OF ADJUST (NR 1 SLAT) · airframe 58,116 hrs · 44,049 cycles

SELECTED FLAPS AND L/E TRANSIT AMBER LIGHT ILLUMINATED. CONFIRMED BY L/E AMBER LIGHTT ON OVERHEAD PNL. FOLLOWED QRH PROCEDURES AND PLANNED FLAP 15 LANDING. ON SHORT FINAL L/E FLAP GREEN LIGHT ILLUMINATED AND SELECTED FLAPS 30. RIGGED NR 1 L/E FLAP EXTENDED PROX SWITCH, CKS GOOD.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 57,422 hrs · 43,552 cycles

INSPECTION OF THE C2 DOOR OPENING FRAME AT FS 794 PER AD 93-14-10 REVEALED CRACK IN THE DOOR FRAME WEB AND FLANGE JUST BELOW THE NR 5 DOOR STOP FITTING. THE CRACKS WERE REMOVED WITH A CUT OUT AND REPAIRED WITH AN ALUMINUM REPAIR ANGLE AND AN EXTERNAL ALUMINUM SKIN DOUBLER PER ER/A 093455 -14AD.

Part: SKIN — CRACKED (L1 DOOR CUTOUT) · airframe 57,422 hrs · 43,552 cycles

THE FUSELAGE SKIN AT THE L1 DOOR OPENING WAS FOUND CRACKED AT THE CUTOUT EDGE JUST ABOVE THE LOWER AFT CORNER. THE CRACKS WERE SMALL AND TYPICAL OF BAC S/B 737-53-1083. THE CRACKS WERE TRIMMED OUT OF THE SKIN AND REPAIRED WITH EXTERNAL ALUMINUM REPAIR DOUBLERS PER THE BAC S/B AND ER/A 093452-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 57,422 hrs · 43,552 cycles

INSPECTION OF THE STRINGER 4L SKIN LAP JOINT PER AD 2003- 08-15 REVEALED A CRACK INDICATION IN A FASTENER HOLE AT FS 690. THE CRACKED AREA WAS REMOVED WITH A SKIN CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER B737 SRM AND ER/A 093308-14AD.

Part: FITTING — GOUGED (HORIZONTAL STAB) · airframe 54,585 hrs · 41,351 cycles

THE UPPER ATTACH LUG OF THE HORIZONTAL STABILIZER CENTER SECTION WAS FOUND WITH A GOUGE FROM INTERFERENCED WITH AN IMPROPERLY INSTALLED FASTENER ON ADJACENT STRUCTURE. THE GOUGE WAS BLENDED TO A SMOOTH CONTOUR AND NDT INSPECTED. THE GOUGED FITTING WAS AUTHORIZED FOR SERVICE WITH REPETITIVE INSPECTION REQUIREMENTS PER ER/A 385224-14AD.

Part: SKIN — CRACKED (FUSELAGE) · airframe 54,585 hrs · 41,351 cycles

THE FUSELAGE SKIN AT FS 750 WAS FOUND WITH A 2 INCH CRACK RUNNING ALONG THE EDGE OF THE BONDED DOUBLER AT STRINGER 18R. THE CRACK WAS CUTOUT OF THE SKIN AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER ER/A 385222-14.

Part: BULKHEAD — CANNING (FUSELAGE) · airframe 54,055 hrs · 40,889 cycles

INSPECTION OF THE AFT P-DOME REVEALED A 10 X 8 X .25 INCH OIL CAN IN THE LOWER WEB AREA OF NEAR BL 0. THE OIL CAN WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN ALUMINUM REPAIR DOULBER PER BAC S/B 737-53A1075 AND ER/A 384318-14AD.

Part: TEE FITTING — CRACKED (NOSE WHEEL WELL) · airframe 52,495 hrs · 40,219 cycles

IRREG/ LOSS OF A SYSTEM HYDRAULIC QUANTITY FOLLOWED BY A LOSS OF PRESSURE AFTER LOWERING THE LANDING GEAR CA/ FOUND TEE FITTING IN THE NOSE WHEEL WELL CRACKED ____REPLACED SAME SERVICED SYSTEM NO LEAKS FOUND

Part: COMPRESSOR — STALLED (NR 1 ENGINE) · airframe 51,152 hrs · 39,651 cycles

IR - COMPRESSOR STALL NR 1 ENG ON TAKE TAKE OFF. INITIATED ABORT BETWEEN 70-80 KTS. DEAD HEATING CAPT REPORTED BRIGHT FLASH FROM NR 1 ENG SHORTLY AFTER T/O PWR ADDED. REPLACED ENGINE.

Part: FRAME — CRACKED (R-2 DOOR FRAME) · airframe 50,905 hrs · 39,548 cycles

1" CRACK IN R-2 DOOR CUTOUT FRAME, JUST BELOW UPPER FWD. ROLLER CASTING REMOVE & REPLACE FRAME SECTION PER DRAWING

Part: LIGHT — INTERMITTENT (COCKPIT) · airframe 48,698 hrs · 38,623 cycles

ON LANDING GEAR EXTENSION, RT MAIN LANDING GEAR GREEN LIGHT DID NOT ILLUMINATE. BULB CK WAS GOOD. CYCLED GEAR WITH SAME INDICATION. PUSHED LIGHT ASSY SEVERAL TIMES. THEN RT GEAR LIGHT CAME ON. ALL INDICATIONS GOOD. CONFIRMED GEAR DOWN WITH CONFIG HORN AND TOWER FLY BY. CKED RT GEAR DOWNLOCK SENSOR AND TARGET. CKS OK. FOUND RT GEAR GREEN LIGHT ASSY BAD. REPLACED LIGHT ASSY. ALL IND NOW NORMAL. OK FOR SVC.

Part: FAN — FAULTY (COCKPIT) · airframe 48,668 hrs · 38,610 cycles

SMOKE AND FUMES IN COCKPIT DURING PREFLIGHT. FOUND CONTROL CABIN AUGMENTATION FAN PUTTING FUMES INTO COCKPIT. FWD TO MCO AND PLACARD.

Part: SKIN — CORRODED (FUSELAGE) · airframe 48,184 hrs · 38,408 cycles

CORROSION WAS FOUND ON THE FUSELAGE SKIN AT STATION 887 AND 907 IN THE UPPER SKIN WHERE THE VERTICAL STABILIZER FAIRING ATTACHES AT ABOUT RBL 4 AND 5. THE MAXIMUM DEPTH OF DAMAGE WAS .012" CONTAINED WITHIN A 1/5" DIAMETER. THE DAMAGE WAS REMOVED AND AN EXTERNAL DOUBLER WAS INSTALLED PER ERA 396608-14 AT HMV.

Part: FITTING — CORRODED (FUSELAGE) · airframe 48,183 hrs · 38,408 cycles

THE RT FUSELAGE CLEVIS LUGS ATTACHING THE HORIZONTAL STABILIZER WERE FOUND CORRODED ON THE FACES AND BORES. THE CORROSION WAS REMOVED AND NEW BUSHINGS WERE INSTALLED PER ERA 396532-14AD AT HMV.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 48,183 hrs · 38,408 cycles

CRACKS WERE FOUND IN THE WEB, DOUBLER AND UPPER CHORD OF THE LBL 24 LONGITUDINAL FLOOR SUPPORT AT FS 675. THE CRACKS WERE REMOVED AND THE DAMAGE REPAIRED PER ERA 396570-14AD AT HMV.

Part: SKIN — CRACKED (FUSELAGE) · airframe 48,044 hrs · 38,349 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 1 INCH CRACK NEAR FS 520 AND STRINGER 16L. THE CRACK WAS ROUTED OUT AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER B737 SRM 53-30-3, FIG 1 AND ER/A 379238-14.

Part: POWER SUPPLY — FAILED (ROWS 14 & 15) · airframe 47,107 hrs · 37,931 cycles

EMERGENCY POWER SUPPLY WOULD NOT TEST AT ROWS 14, 15 DEF. REPLACED POWER SUPPLY.

Part: FUSE — BLOWN (ROW 10-18)

E-PATH LIGHTS INOP ROW 10 TO 18. REPLACED FUSE IN PWR SUPPLY.

Part: SKIN — CRACKED (BS 951)

FUSELAGE AFT GALLEY DOOR CUTOUT SKIN UPPER HINGE CUTOUT, CRACK REPAIR. THE UPPER HINGE CUTOUT OF THE AFT GALLEY DOOR CUTOUT SKIN WAS FOUND WITH A .25 LONG TYPICAL CRACK AT THE UPPER CORNER. THE CRACK WAS ROUTED OUT AND REPAIRED WITH A DOUBLER PER ER/A 367237-14, REV A AND BASED ON A REPAIR PER B737 SRM 53-30-3, FIG 21A.

Part: BLADES — DAMAGED (NR 1 ENG COMP)

AT CRUISE, CREW NOTE COMPRESSOR SURGING. DIVERTED TO BOS. FOUND NOSE BULLET LOOSE. DAMAGE INCURRED TO FIRST AND SECOND STAGE FAN BLADES, NOSE COWL ACCOUSTIC LINER AND N1 TACH GENERATOR HOUSING BULLET MOUNT STUDS. REPLACING 1ST AND 2ND STAGE FANS, INLET COWL AND N1 TACH GENERATOR GEARBOX AND NOSE BULLET.

Part: GCU — MALFUNCTIONED (LT & RT)

ON CLIMBOUT, APU OFF BOTH GEN ON, RECEIVED A SPIKE. LOST ALL ELECTRICAL PWR IN COCKPIT AND CABIN FOR A SPLIT SECOND. NO C/B POPPED, NO EQUIP LOSS. INSPECTED LT AND RT GEN HARNESS, NTF INSPEC ENG GEN AND BUSS TIE BREAKERS. NTF RAN GCU DIODE TEST, BATTERY TEST AND STB POWER TEST, ALL PASSED. REPLACED LT AND RT ENG GCU. A/C PWR CKS NORMAL. GCU NR 1 (S/N ZG623) OFF. GCU NR 2 (S/N ZB3038DH) OFF.

Part: LINE — RUPTURED (ENGINE)

LOSS OF A/B HYDRAULICS RESULTED IN DIVERSION BACK TO MCO. FOUND 01 ENG PRESS LINE RUPTURED. REPLACED SAME, LEAK CKS OK. REPLACED ALL CASE DRAIN FILTERS.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING ACCOMPLISHMENT OF SI 3-69482-12, SEVEN CRACKS WERE DISCOVERED ON THE FORWARD FACE OF THE FS 178 BULKHEAD WEB. SEVEN INDEPENDENT CUTOUTS WERE REQUIRED TO REMOVE THE CRACKS. REPAIRED PER DALA ER/A 304632-14.

Part: SKIN — CRACKED (L2 DOORWAY)

A CRACK WAS FOUND IN THE FUSELAGE SKIN AT THE L2 DOOR CUTOUT IN THE UPPER AFT CORNER. THE CRACK WAS IN THE INNER LAYER OF THE BONDED SKIN ASSEMBLY AND WAS APPROX 1.75 IN LENGTH. REPAIRED PER BACO S/B 737-53-1149.

Part: SKIN — CRACKED (R-2 DOORWAY)

FOUND A 2.25 INCH CRACK IN THE R-2 DOORWAY. REPAIRED PER B737-200 SRM 53-30-3, FIG 24.

Part: NOSE COWL — DAMAGED (NR 2 ENGINE)

DURING SHOP INSPECTION, A DEEP NICK WAS FOUND IN THE LEADING EDGE LIP OF NR 2 ENGINE NOSE COWL. REPAIRED PER SRM 54-30-3 FIG. 4.

Part: NOSE COWL — CRACKED (NR 2 ENGINE)

DURING SHOP INSPECTION, A .5 INCH CRACK WAS FOUND IN THE LEADING EDGE LIP OF NR 2 NOSE COWL. REPAIRED PER SRM 54-30-3 FIG. 4.