N376DL

Part: FILTER — BYPASSING (NR 2 ENGINE) · airframe 48,284 hrs · 38,289 cycles

NR 2 ENG FILTER BYPASS LIGHT ILLUM IN FLT. ALL ENG PARAMETERS NORMAL. PRESS STAYED GOOD WITH ENG SHUT DOWN. REPLACED FILTER AND DIFF PRESSURE SWITCH.

Part: SKIN — CRACKED (BS 525) · airframe 47,790 hrs · 37,959 cycles

A CRACK WAS FOUND IN THE FUSELAGE SKIN AS A RESULT OF INSPECTION PER DAL OPN 57546. THE CRACK IS APPROX 1.5 INCH LONG AT BS 525 ABOVE STRINGER 16L. INSTALLED DOUBLER REPAIR PER B737-200 SRM 53-30-3, FIG 48, DETAIL XI AND ER/A 450994-14AD.

Part: FITTING — CORRODED (HORIZONTAL STAB) · airframe 45,705 hrs · 36,389 cycles

HORIZONTAL STABILIZER RT AND LT CENTER AND OUTBOARD SECTION LUG FITTINGS AT THE FRONT AND REAR SPAR CORRODED AND DAMAGE. REPAIRED IAW ER/A 094975-14AD & 094865-14AD.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 45,703 hrs · 36,388 cycles

STRINGER 5L AND AFT ENTRY BEAR STRAP SUFFERED DAMAGE. REPAIRED IAW ERA 094945-14.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · airframe 45,703 hrs · 36,388 cycles

STATION 927 WEB AND SHEAR TIE REPAIRED AT STRINGER 5L DUE TO TOOLING DAMAGE. REPAIRED IAW ERA 095091-143.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 45,703 hrs · 36,388 cycles

VERTICAL STABILIZER ATTACH FITTINGS NR 3 AND NR 6 LUGS WORN ON THE AFT FACES DUE TO CORROSION. REPAIRED IAW ERA 095030-14.

Part: SKIN — WORN (LT WING) · airframe 45,703 hrs · 36,388 cycles

LT LOWER WING SKIN WORN AT FUEL TANK ACCESS DOOR CUTOUT. REPAIRED IAW ERA 094867-14.

Part: SHEAR BEAM — CRACKED (FUSELAGE) · airframe 45,703 hrs · 36,388 cycles

STRINGER 18A SHEAR BEAM WEB CRACKED AT STA 727 ON BOTH THE LT AND RT SIDES. REPAIRED IAW ERA 094822-14.

Part: ATTACH FITTING — CORRODED (VERT STAB) · airframe 45,703 hrs · 36,388 cycles

BODY CLEVIS LUGS FOR VERTICAL STABILIZER ATTACH FITTINGS CORRODED. REPAIRIED IAW ERA 095009-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 45,703 hrs · 36,388 cycles

FUSELAGE SKIN DAMAGED AT THE C1 DOOR CUTOUT AT STATION 440 AND STR 23R - 24R. REPAIRED IAW ERA 257313-14 REV E.

Part: LIGHT — BURNED (INDICATOR) · airframe 44,117 hrs · 35,175 cycles

WHILE WORKING MCO ON ANTI SKID LIGHTS STAYING ON DIM. FOUND WINDSHEAR AND ALTITUDE ALERT LIGHT ASSEMBLIES WITH ELECTRICAL BURNS AND ODOR. REPLACED ASSEMBLIES.

Part: FIRE DETECTOR — MALFUNCTIONED (APU BAY) · airframe 43,563 hrs · 34,754 cycles

PRIOR TO TIME OF DESCENT, APU FIRE WARNING. ACCOMPLISHED EMERGENCY PROCEDURES. BOTTLED DISCHARGED. LIGHT REMAINED ILLUMINATED. INSPECTED APU EXHAUST AND APU COMPARTMENT FOR DAMAGE OR EVIDENCE OF FIRE, NONE FOUND. APU WAS NOT RUNNING AT TIME OF FIRE WARNING. SUSPECT DETECTION SYSTEM FAULT.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 41,648 hrs · 33,510 cycles

CORROSION DAMAGE ON STA 986.5 FLOORBEAM UPPER CHORD AT LBL 6 AND RBL 6. REPAIRED PER SRM DRD 53-20-1D FIG 803D, UPPER CHORD REPLACEMENT.

Part: CLAMP — LOOSE (LT AIR CLEANER) · airframe 41,122 hrs · 33,297 cycles

ON T/O ROLL RECEIVED A PACK TRIP OFF INDICATION. CONTINUED TAKEOFF. ONCE AIRBORNE PERFORMED PROCEDURE PER POM. WHEN THE PACK WAS RESET THE PRESSURE PEGGED TO TOP OF SCALE. WING BODY OVERHEAT ILLUMINATED FOLLOWED BY A BLEED TRIP OFF INDICATION. ALL INDICATIONS OCCURRED ON THE LEFT SIDE OF SYSTEM. OPENED NR 1 ENG COWLS AND LT PACK BAY DOOR. INSPECTED AIR DUCTS FROM ENG TO PACK BAY AND DUCTS IN PACK BAY. NO DEFECTS. FOUND AIR LEAKING FROM INBOARD CLAMP OF LT AIR CLEANER HOT AIR BLOWING DIRECTLY ON OVERHEAT LOOP. SECURED CLAMP NO LEAKS. PERFORMED T/O POWER CHECK FOR 3 MIN DUCT PRESS AND PACK OPERATION NORMAL.

Part: SKIN — GOUGED (NO 2 FOREFLAP) · airframe 41,115 hrs · 33,293 cycles

UPPER SKIN WORN THROUGH AT NO 2 T/E FOREFLAP REPAIRED PER SRM 51-40-20 FIG 12

Part: WEB — CHAFED (HORIZ STAB) · airframe 41,115 hrs · 33,293 cycles

FOUND ON Q1 LETTER CK RT AND LT INBD BALANCE BOARD PANELS CHAFING THROUGH THE INBD WEBS. REPAIRED PER SRM 51-40-20 AND OPERATION 1000

Part: DOOR FRAME — CRACKED (C2 CARGO DOOR) · airframe 39,942 hrs · 32,802 cycles

DOORS / C2 CARGO DOOR / FWD FRAME / LAP SPLICE : CRACK REPAIR THE FWD FRAME OF THE C2 CARGO DOOR WAS FOUND WITH 2" CRACK IN THE UPPER FRAME AND A FASTENER HOLE CRACK IN THE LOWER FRAME AT FRAME LAP JOINT BETWEEN DOOR STOPS #3 & #4. THE CRACKED FRAMES WERE REPAIRED WITH 2 TITANIUM REPAIR ANGLES OVERLAPING THE EXISTING FRAME LAP PER ER/A 383269-14, REV A.

Part: CAP — SPLIT (SPOILER ACTUATOR) · airframe 39,738 hrs · 32,713 cycles

HYDRAULIC SYSTEM A FAILURE IMMEDIATELY FOLLOWING TAKEOFF. FOUND CAP ON NR 7 SPOILER HAD SPLIT. REPLACED CAP AND O-RING. INSPECTED AND REPLACED CASE DRAIN AND PRESSURE FILTERS. SERVICED HYDS TO FULL. LEAK AND OPS CHECKS OK.

Part: DOOR — DAMAGED (APU) · airframe 38,329 hrs · 32,125 cycles

APU DOOR HOLE IN OUTER SKIN. REPAIRED PER SRM 52-00-3 FIG 6.

Part: SLIDE — OUT OF POSITION (L1 DOOR) · airframe 37,535 hrs · 31,780 cycles

L1 DOOR SLIDE CAME OUT OF CASE. C/A REPLACED SLIDE.

Part: LOOP — INTERMITTENT (FUSELAGE) · airframe 36,414 hrs · 30,991 cycles

AFTER T/O LEFT BODY OVERHEAT LIGHT ILLUMINATED AND REMAINED ON THEN FLICKERD AFTER POM. DROPPED ECS BAY LEADING EDGE FLAPS, SHOOK DOWN WIRES TO THERMOCOUPLES (FOUND NO INTERMITTENT LIGHT) REP COMPONENT OVERHEAT UNIT AND TESTED GOOD.

Part: FRAME — CRACKED (BULKHEAD) · airframe 36,182 hrs · 30,791 cycles

DURING INSPECTIONS OF THE FS 178 BLKHD CRACKS WERE FOUND IN THE LT AND RT SIDE CHORDS AND IN THE BULKHEAD WEB AT RBL 10 WL 233.5. THE CHORDS WERE REPLACED AND THE WEB REPAIRED PER ERA 396656-14AD AT MV.

Part: SKIN — WORN (WING) · airframe 36,182 hrs · 30,791 cycles

THE INNER SURFACE OF THE LOWER WING SKIN WAS FOUND WORN AT THE BOOST PUMP ACCESS HOLE AT WBL 148. THE DAMAGE CLEAN UP WAS APPROXIMATELY 1.5 X 1.5 X .061 INCH. THE DAMAGE WAS REPAIRED PER ERA 396660-14 AT MV.

Part: TIRE — FAILED (LT MLG) · airframe 36,172 hrs · 30,786 cycles

NR 1 MAIN TIRE BLEW ON TAKEOFF AT 150 KNOTS. LANDING WEIGHTWAS 105.5K. RATE OF DESCENT AT LANDING WAS 100FT/MIN. C/A R/R NBR 1 MAIN TIRE PER MM. PERFORMED OVER WEIGHT LNDG INSP PER MM 05-51-51. N.T.F.

Part: STRUCTURE — CRACKED (CARGO DOOR) · airframe 35,636 hrs · 30,376 cycles

RUMBLING NOISE EN ROUTE DFW - AUS AT 18000 MSL. FWD OUTFLOW VALVE CLOSED, MAIN OUTFLOW VALVE FULL CLOSED ALL DOOR LIGHTS CHECKED AND TESTED. F/A CHECKED ALL DOORS FOR NOISE AND STRAPS. REPLACED FWD CARGO DOOR FOR CRACK.

Part: SKIN — CRACKED (FUSELAGE) · airframe 34,551 hrs · 29,497 cycles

THE LOWER FWD CORNER OF THE AFT GALLEY DOOR (R2) CUTOUT WAS FOUND WITH A TYPICAL CRACK IN THE SKIN ASSY AND UNDERLYING BEARSTRAP. THE CRACK WAS REMOVED WITH A 1 INCH CUTOUT IN ALL MEMBERS AND REPAIRED WITH THREE EXTERNAL ALUMINUM DOUBLERS PER B737 SRM 53-30-3, FIG 24 AND ER/A 369784-14, REV A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 34,551 hrs · 29,497 cycles

THE LOWER AFT CORNER OF THE FWD GALLEY DOOR CUTOUT (R1) WAS FOUND WITH A TYPICAL CRACK IN THE SKIN ASSY. THE UNDERLYING BEARSTRAP WAS NOT CRACKED. THE CRACK WAS ROUTED OUT WITH A 1 INCH CUTOUT AND REPAIRED WITH TWO INCH EXTERNAL ALUMINUM DOUBLERS PER B737 SRM 53-30-3, FIG 26 AND ER/A 369783-14, REV A.

Part: POWER SUPPLY — INOPERATIVE (CABIN EEL)

EMERGENCY LIGHTS INSIDE AND OUT - AFT SVC DOORS LT AND RT INOPERATIVE. REPLACED BATTERY POWER SUPPLY RT SIDE AFT B/B AND POWER SUPPLY ABOVE AFT GALLEY. ALL EMERGENCY LIGHTS CHECK OK.

Part: BULKHEAD WEB — CRACKED (BS 178)

DURING INSPECTIONS PER SI 3-69482-12, THE STATION 178 BULKHEAD WAS FOUND CRACKED IN ONE LOCATION APPROXIMATELY AT RBL 4 AND WL 200. THE RESULTING DAMAGE CUTOUT IS 1 WIDE AND 4.75 LONG. THE BULKHEAD WEB IS FABRICATED FROM 0.032 CLAD 2024-T3.

Part: INTERCOSTAL — CRACKED (BS 328)

FOUND CRACK IN THE R1 DOOR FRAME INTERCOSTAL AT STR 8A. REPAIRED IN ACCORDANCE WITH S/B 737-53A1108 AND AD 88-03-03.

Part: RIB — CRACKED (BS 851)

THE WING RIB UPPER CHORD AT RBL 70.5 AND BS 851 HAS TWO CRACKS IN THE VERTICAL FLANGE. ONE CRACK EXTENDS FROM THE AFT END OF THE PART IN THE BOTTOM FASTENER ROW. THE SECOND CRACK EXTENDS FROM THE MIDDLE OF THE AFT EDGE OF THE VERTICAL FLANGE TO THE END FASTENER IN THE UPPER ROW. IN ADDITION, CORROSION WAS FOUND AT THE UPPER FLANGE OF THE RIB CHORD AT BS 846. THE CORROSION IS .050 DEEP AND IS APPROXIMATELY 1 INCH OUTBOARD OF THE VERTICAL FLANGE OF THE RIB CHORD. THE BLENDED AREA MEASURES APPROX 3 FWD/AFT AND 1.5 INBD/OUTBD. REPAIRED PER DALA ER/A 304296-14, REV A.

Part: BATTERY PACK — DISCHARGED (CABIN)

EMERGENCY LIGHTS OUT AT LT OVERWING RT SIDE ABOVE WING EXIT HATCH, AND OVERHEAD BINS 13C, 11D, AND 10C. REPLACED BATTERY PACK.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

RIGHT AFT EXIT DOOR SLIDE LIGHT FOUND INOP ON SERVICE CHECK. ALSO, LEFT FWD SLIDE LIGHT INOP. RELAMPED LEFT FWD SLIDE LIGHT WITH BULB 1519. REPLACED FAULTY POWER SUPPLY FOR AFT RIGHT SLIDE LIGHT.

Part: DN SWITCH — FAILED (LANDING GEAR)

WHEN LANDING GEAR WAS PLACED DOWN, ALL 3 GREEN AND ALL 3 RED LIGHTS ILLUMINATED. REPLACED GEAR HANDLE DOWN SWITCH (S-78), OPERATION NORMAL.

Part: BULB — FAILED (NLG)

ON APPROACH TO ATL, LANDING GEAR EXTENDED, NOSE GEAR DID NOT HAVE GREEN LIGHT. CYCLED GEAR, NO CHANGE. ACCOMPLISHED MISSED APPROACH. REPLACED BOTH INDICATOR BULBS, LOWERED GEAR GOT GREEN LIGHT AND LANDED NORMALLY.

Part: SKIN — DELAMINATED (RUDDER)

FOUND ON LTR CK, DAMAGE TO TRAIL EDGE RUDDER. REPAIRED PER SRM 55-40-5 FIG 1.

Part: SKIN — CRACKED (L1 DOOR)

FOUND ON LTR CK, L1 DOOR LOWER HINGE CUTOUT LWR AFT CORNER .3125 INCH CRACK. REPAIRED PER SRM 52-00-3.

Part: NOSE COWL — CRACKED (NR 1 ENGINE)

DURING SHOP INSPECTION, FOUND NR 1 ENGINE NOSE COWL WITH CRACKED FRAME AT THE 9 O'CLOCK POSITION. REPAIRED PER SRM 54-1-3.