N373DL

Part: FLOORBEAM — CRACKED (BS 660) · airframe 48,412 hrs · 37,830 cycles

DURING INSPECTION PER SI 3-56673-12, AN EXISTING REPAIR/MODIFICATION WAS FOUND TO BE CRACKED IN THE UPPER FORWARD HOLE OF THE WEB DOUBLER, WEB, UPPER CHORD, AND MOD CHANNEL AT RBL 24.8 AND LBL 24.8. CRACKS WERE REMOVED, WEB DOUBLERS, CHORDS, AND MOD CHANNELS WERE REPLACED AND THE WEB WAS REPAIRED WITH A DOUBLER PER ER/A'S 450662-12AD AND 450663-14AD.

Part: TIRE — DAMAGED (LT MLG) · airframe 47,443 hrs · 37,118 cycles

NR 2 MAIN TIRE LOST CAP ON OUTBOUND HOU /AFTER LOSS OF A-SYSTEM HYDRAULICS, CREW MANUALLY EXTENDED GEAR, LANDED IN ATL WITHOUT INCIDENT. TIRE REMAINED INFLATED /DAMAGE TO LEADING EDGE OF MID FLAP AND HYDRAULIC LEAK PRESENT DUE TO DAMAGED LINES IN WHEEL WELL. REPLACED WHEEL. REPAIRED DAMAGE.

Part: PUMP — FAILED (A-HYD SYSTEM) · airframe 46,647 hrs · 36,537 cycles

LOSS OF A-SYSTEM HYDRAULIC PRESSURE IN FLIGHT. REPLACED BOTH ENGINE PUMPS DUE A-SYSTEM CONTAMINATION.

Part: SOCKET — BURNED (SEAT ROW A-13) · airframe 45,920 hrs · 35,998 cycles

ON GO-AROUND IN ATL STRONG BURNING ODOR WAS DETECTED IN CABIN AND COCKPIT. ODOR DISSIPATED IN APPROX 3 MIN. REPLACED LIGHT SOCKET AT SEAT 13A.

Part: WEB — CRACKED (FUSELAGE) · airframe 45,401 hrs · 35,599 cycles

FUSELAGE SHEAR BEAM WEB CRACKED AT STRINGER 18A AND STA 727. AREA REPAIRED IAW ERA 090776-14.

Part: FITTING — CORRODED (MLG SIDE STRUT) · airframe 45,399 hrs · 35,598 cycles

CORROSION ON THE MLG SIDE STRUT ATTACH AT FUSELAGE STA 685 MLG FITTING. AREA REPAIRED IN ACCORDANCE WITH ERA 090842-14.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 45,399 hrs · 35,598 cycles

HORIZONTAL STABILIZER FRONT AND REAR SPAR ATTACH LUGS CORRODED. AREA REPAIRED IAW ERA 090805-14AD.

Part: ATTACH FITTING — DAMAGED (VERTICAL STAB) · airframe 45,399 hrs · 35,598 cycles

VERTICAL STABILIZER ATTACH LUG FOUND TO HAVE A THINNER FLANGE THAN BLUEPRINT. AREA REPAIRED IAW ERA 090968-14AD.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 45,399 hrs · 35,598 cycles

FUSELAGE CABIN FLOORBEAM AT STATION 520 FOUND WITH A CRACK AT THE UPPER CHORD. AREA REPAIRED IAW ERA 090614-14.

Part: FRAME — DENTED (FUSELAGE) · airframe 45,399 hrs · 35,598 cycles

INNER FLANGE OF FRAME AT STATION 500 DENTED BETWEEN STRINGERS 24R AND 25R. AREA REPAIRED IAW 090636-14.

Part: SKIN — CRACKED (R1 DOOR CORNER) · airframe 45,399 hrs · 35,598 cycles

FUSELAGE SKIN AT THE R1 DOOR LOWER AFT CORNER WAS FOUND WITH A FATIGUE CRACK. AREA HAD BLIND FASTENER REPAIR INSTALLED AND PERMANENT REPAIR INSTALLED PER ER/A 363957-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,399 hrs · 35,598 cycles

FUSELAGE SKIN AND STRINGER CRACKED AT STA 525 AND STR 16L. ERA 091121-14 COMPLIED WITH FOR REPAIR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 45,399 hrs · 35,598 cycles

CRACKS IN FUSELAGE SKIN AT STATION 380 BETWEEN S-17L AND 18L. AREA REPAIRED IAW ERA 090754-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 43,115 hrs · 33,752 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 3 INCH CRACK JUST BELOW STRINGER 18R AT FS 750. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER PER THE B737-200 SRM AND PER ER/A 384987-14.

Part: TRANSCEIVER — FAILED (E/E BAY) · airframe 42,120 hrs · 33,360 cycles

WX RADAR INOP. ANT FAULT MSG DISPLAYED. REPLACED RADAR TRANSCEIVER. RADAR TEST NORMAL.

Part: HYDRAULIC SYSTEM — LOW (A SYSTEM) · airframe 41,797 hrs · 33,228 cycles

SYSTEM A HYD QTY INDICATOR DROPPED TO 1.5 GALLONS FOLLOWED BY ILLUMINATION OF SYSTEM B LOW QTY LIGHT. ABNORMAL PROCEDURES FOLLOWED. A/C ARRIVED WITH A SYSTEM AT 2.5 GAL. SERVICED TO FULL EXERCISED FLAPS/SLATS AND SPOILERS OPERATED GEAR HANDLE. PERFORMED YAW DAMP TEST OPERATED RUDDER. RAN B SYSTEM FOR SEVERAL HOURS. NO LEAKS FOUND.

Part: TIRE — SEPARATED (NR 4) · airframe 41,783 hrs · 33,221 cycles

ON WALK AROUND FOUND TIRE TREAD MISSING ON NR 4 MAIN TIRE. TREAD SEPARATION CAUSED DAMAGE TO THE RT INBD UNDERWING FIXED PANEL, RT TRAILING EDGE MID FLAP AND BROKE THE INNER AND CENTER RT GEAR DOORS. REPLACED WHEEL ASSY AND REPAIRED DAMAGE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 41,524 hrs · 33,114 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 1.375 CRACK ALONG THE MILL LINE JUST ABOVE STRINGER 16L AT FS 525, AFT OF THE WING SCANNING LIGHT CUTOUT. THE CRACK WAS REMOVED WITH A CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL DOUBLER PER B737 SRM AND ER/A 383970-14.

Part: TORQUE LINK — FAILED (NLG) · airframe 39,800 hrs · 32,388 cycles

AT 100 KTS LANDING ROLLOUT, NOSE WHEEL HAD SEVERE SHIMMY. REPLACED TORQUE LINK ASSY.

Part: SKIN — CRACKED (FS 727B, S-18R) · airframe 39,297 hrs · 32,179 cycles

FUSELAGE / SKIN / FS 727B / STRG. 18R : CRACK REPAIR INSPECTION OF THE FUSELAGE SKIN REVEALED A 5" CRACK JUST ABOVE STRINGER 18R AT FS 727B. THE CRACK WAS REMOVED WITH A CUTOUT IN THE SKIN. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER THE B737 SRM AND PER ER/A 382255-14.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 39,172 hrs · 32,127 cycles

2L EMERGENCY EXIT LIGHT INOP. REPLACED POWER SUPPLY.

Part: BATTERY — DISCHARGED (CABIN) · airframe 37,115 hrs · 31,257 cycles

AFT RT SLIDE EMERGENCY LT INOPERATIVE AND 1 CABIN AISE EMER. LT I INOPERATIVE. REPLACED BATTERY

Part: LIGHT — CORRODED (ESCAPE SLIDE) · airframe 37,115 hrs · 31,257 cycles

AFT LEFT SLIDE EMERGENCY LT INOPERATIVE. REPLACED LIGHT ASSY

Part: SKIN — FATIGUED (GALLEY DOOR) · airframe 35,222 hrs · 29,790 cycles

DURING ACCOMPLISHMENT OF S/B 737-53-1116 REV 3, SEVERAL DEVIATIONS WERE REQUIRED TO ACCOMPLISH REPAIR (FASTENER SUB). ER/A 334616-14AD.

Part: FRAME — TOOL DAMAGE (FUSELAGE) · airframe 35,222 hrs · 29,790 cycles

THE SIDE FRAME AT STA 907 ON LHS SUSTAINED TOOLING DAMAGE BETWEEN THE 3RD AND 4TH FASTENERS FROM THE UPPER EDGE OF THE FRAME SPLICE. ER/A 334646-14 REV A.

Part: FRAME — TOOL DAMAGE (FUSELAGE) · airframe 35,222 hrs · 29,790 cycles

THE LT SIDE FRAME AT STA 747 WAS GOUGED DURING FASTENER REMOVAL. DAMAGE LOCATED AT THE UPPER END OF THE FRAME AND LOCATED IN THE RADIUS. ER/A 334653-14.

Part: FRAME — TOOL DAMAGE (FUSELAGE) · airframe 35,222 hrs · 29,790 cycles

PILOT HOLE FOUND IN THE I/B FLANGE OF THE FS 927 FRAME AT S-14R. HOLE COMMON TO LOWER FRAME AND STRAP. ER/A 334668-14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 35,092 hrs · 29,682 cycles

THE FUSELAGE SKIN, BONDED DOUBLER, AND BEAR STRAP WERE FOUND WITH A TYPICAL CRACK IN THE LOWER FORWARD CORNER OF THE AFT ENTRY DOOR CUTOUT (L2). THE CRACK WAS REMOVED IN ALL THREE MEMBERS WITH A 1.9 CUTOUT. THE CUTOUT WAS REPAIRED WITH THREE EXTERNAL ALUMINUM DOUBLERS PER B737 SRM 53-30-3, FIG 24 AND ER/A 377366-14, REV A.

Part: POWER SUPPLY — INOPERATIVE (ROW 16-21)

WHITE EMERGENCY TRACK LIGHTS OUT ROW 16 TO ROW 21. FOUND MID AND AFT BATTERY PACK AND PWR SUPPLY BAD. REPLACED SAME, OPS NORMAL.

Part: COFFEEMAKER — SMOKING (AFT GALLEY)

ABOUT 15 MIN AFTER T/O AT APPROX 20,000 ALT, F/A REPORTED A STRONG ELECT SMELL IN AFT LAV AREA. SHUT OFF GALLEY PWR AND PULLED AFT LAV C/B. RETURNED TO CVG. ON DESCENT, F/A REPORTED SMELL DIMINISHING. INSPECTED, SUSPECT BURNING COFFEE.

Part: HINGE — FAILED (RT LE FLAP)

RT I/B LEADING EDGE FLAP SKIN BENT/CRACKED AT UPPER I/B EDGE DUE TO FAILURE OF I/B HINGE.

Part: SKIN — CRACKED (LT COCKPIT)

THE UPPER OUTBD CORNER OF THE L1 COCKPIT WINDOW WAS FOUND WITH A .75 INCH LONG CRACK IN THE SKIN AND UNDERLYING GUSSET ALONG THE C-D WINDOW POST. THE GUSSET CRACK WAS STOP DRILLED AND THE SKIN CRACK TRIMMED OUT. AN EXTERNAL STEEL DOUBLER AND ALUMINUM TRIPLER WERE INSTALLED TO REPAIR THE DAMAGE. THE REPAIR WAS ACCOMPLISHED PER ER/A 365422-14.

Part: DNLOCK LIGHT — MALFUNCTIONED (LT MLG)

LT MAIN LANDING GEAR DOWN AND LOCKED LIGHT DID NOT ILLUMINATE ON LANDING. A/C ARRIVED GATE LT GREEN LIGHT ON. SLUGGED LEFT GEAR LIGHT, CHECKED GOOD. READJUSTED LANDING GEAR ASSY UNIT AS PRECAUTIONARY. PERFORMED TEST PFHB PER CHAPTER 32 OF M/M, ALL CHECKED GOOD.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING ACCOMP OF SI 3-69482-12, TWO CRACKS WERE DISCOVERED ON THE FORWARD FACE OF THE BS 178 BULKHEAD WEB. FIRST CRACK IS LOCATED UNDER THE RBL 5.7 VERTICAL STRAP AT APPROXIMATELY WL 202 AND THE SECOND IS LOCATED UNDER THE LBL 5.7 VERTICAL STRAP, RANGING BETWEEN WL 198 AND WL 202. THE WEB IS MANUFACTURED FROM 0.040 2024-T3 CLAD.

Part: LE SKIN — DENTED (VERT STAB)

DURING SHOP INSPECTION, VERTICAL STABILIZER L/E WAS FOUND DENTED BEYOND LIMITS. REPAIRS ACCOMPLISHED PER SRM 55-30-6.