N331DL

Part: SKIN — CRACKED (FUSELAGE) · airframe 50,857 hrs · 40,151 cycles

A 1 INCH CRACK WAS FOUND IN THE BONDED SKIN ASSY AND UNDERLYING BEAR STRAP AT THE UPPER AFT CORNER OF THE L2 DOOR CUTOUT. THE CRACK WAS REMOVED WITH A CUTOUT AND REPAIRED WITH 3 EXTERNAL ALUMINUM REPAIR DOUBLERS PER B737 SRM AND ER/A 095399-14, REV A.

Part: HOUSING — CRACKED (SPOILER ACTUATOR) · airframe 49,514 hrs · 39,120 cycles

LOST A HYDRAULIC SYSTEM ON TAXI IN TO GATE AT ORD. FOUND NR 8 GROUND SPOILER ACTUATOR BODY CRACKED. REPLACED NR 8 GROUND SPOILER PER AMM 27-62-101, PB 401. LEAK AND OP. CHECK GOOD. RII PERFORMED.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

DURING ACCOMPLISHMENT OF INSPECTIONS IAW SB 737-55-1028 (DAL EO 3-85220-3), CORROSION WAS FOUND ON FIVE (5) VERT STABILIZER CLEVIS LUGS AND THREE (3) VERT STABILILZER ATTACH LUGS. THE BORES WERE OVERSIZED AND THE LUG FACES MACHINED TO REMOVE CORROSION. O/S BUSHINGS WERE INSTALLED IAW SB 737-55-1028. ER/A 385290-14 WAS ISSUED TO ADDRESS THESE 8 LUGS THAT WERE MACHINED BEYOND THE SERVICE BULLETIN LIMITS.

Part: SKIN — DENTED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

A SCRATCH AND DENT WAS FOUND IN THE FUSELAGE SKIN JUST BELOW THE C1 CARGO DOORWAY EXTENDING FROM FS 460 TO FS 500. AN EXISTING REPAIR WAS FOUND AT THE FORWARD LOWER CORNER OF THE DOORWAY. THIS REPAIR WAS REMOVED AND AN EXTERNAL ALUMINUM DOUBLER TRIPLER AND FILLER WERE INSTALLED OVER THE PREVIOUS REPAIR AREA AND INCORPORATING THE CUT OUT DENT/SCRATCH AREA. WORK WAS DONE IN ACCORDANCE WITH ER/A 385217-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

FUSELAGE SKIN STA 255, S-23R TO S-24R - CUTOUT: EXISTING TEMPORARY (BLIND FASTENER) SRM REPAIR REMOVED AND PERMANENT SKIN REPAIR INSTALLED IAW DAL ER/A 385263-14.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

DURING ACCOMPLISHMENT OF EO 03-062982-03AD, MTC ADDED ADDITIONAL FASTENER HOLES THROUGH THE UPPER CAP AND SPLICE ANGLES OF THE CENTER WING BOX FLOORBEAMS FROM BS 650 TO 675 AT BL 0.07. REPAIR PER ER/A 385423-14AD.

Part: SPAR — GOUGED (RT WING) · airframe 47,782 hrs · 37,739 cycles

RT WING / MLG AFT SUPPORT FITTING / WBL 157, TOOLING DAMAGE. THE MLG AFT SUPPORT FITTING ON THE RT WING SUFFERED TOOLING DAMAGE DURING REMOVAL OF FASTENERS FOR INSPECTION. THE BORE OF ONE OF THE FASTENERS WAS DAMAGED IN THE AFT FITTING, REAR SPAR UPPER CHORD, REAR SPAR WEB AND THE FWD MLG FITTING. IAW ER/A 385269-14, THE AFT FITTING WAS REPLACED, THE REMAINING LAYERS WERE BUSHED AND AN EXTERNAL STRAP WAS INSTALLED OVER THE REAR SPAR UPPER CAP.

Part: PRESSURE PANEL — CRACKED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

FUSELAGE STA 727 BLKHD, MLG WW, UPPER CHORD - REPAIR: A 0.5 INCH CRACK WAS PREVIOUSLY REPAIRED IN TEH UPPER CHORD OF THE SUBJECT BULKHEAD NEAR BL 0. THE CRACK WAS IN THE UPPER FLANGE OF THE COMPRESSION CHORD AND RAN THROUGH A FASTENER HOLE. DURING THE CURRENT HMV, THE TIME LIMITED REPAIR WAS REMOVED AND, DUE TO ADDITIONAL DAMAGE FOUND, THE COMPRESSION CHORD, THE UPPER CHORD, THE COMPRESSION STRAP AND THE LT FLOOR WEB WERE TRIMMED OUT AND A REPAIR ANGLE, WEB DOUBLER AND SPLICE STRAP WERE INSTALLED IAW DAL ER/A 368710-14.

Part: FRAME — CRACKED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

FUSELAGE SKIN STA 663, S2R TO S1 - MISALIGNMENT: DURING INSPECTION OF THE FS 663 FRAME, MTC FOUND CRACKS IN THE FRAME AT S2R AND S1R. THESE WERE WITHIN THE AREA ADDRESSED BY B737-200 SRM 53-10-4, FIG 14. DURING INSTALLATION OF SRM FRAME REPAIR, SKIN ATTACH FASTENERS NEEDED TO BE RELOCATED THROUGH THE SKIN. THEY WERE CUTOUT IN THE SKIN AND DOUBLER, AND AN EXTERNAL DOUBLER AND TRIPLER WERE INSTALLED IAW DAL ER/A 385226-14.

Part: ATTACH FITTING — CORRODED (HORIZ STAB) · airframe 47,782 hrs · 37,739 cycles

HORIZ STAB LT, RT, AND CENTER SECTIONS ATTACH FITTINGS :LUG CORROSION, INSPECTION OF THE HORIZONTAL STABILIZER ATTACH LUGS ON THE LT, RT, AND CENTER SECTIONS OF THE STAB PER BAC S/B 737-55- 1055, CORROSION WAS FOUND IN SEVERAL OF THE LUG BORES AND ON THE LUG FACES. THE CORROSION WAS REMOVED BY OVERSIZING THE BORES AND SPOTFACING THE LUG FACES. THE LUGS WERE RESTORED WITH OVERSIZED BUSHINGS. THE REPAIR WAS ACCOMPLISHED PER ER/A 385250-14AD.

Part: SILL — CRACKED (FUSELAGE) · airframe 47,782 hrs · 37,739 cycles

FUSELAGE C-2 DOOR UPPER SILL FS 818 WEB CORROSION. DURING INSPECTION OF A TIME LIMITED REPAIR TO THE C-2 DOORWAY UPPER SILL WEB, CRACKING OF THE WEB WAS NOTED AS WELL AS A SHORT ED FASTENER IN THE SILL OUTER CHORD. THE WEB WAS REPAIRED WITH A DOUBLER AND THE CHORD WITH AN EXTRUDED ANGLE PER ER/A 381103-14AD, REV C. THE REPAIR IS CENTERED APPROX ATSTA 818.

Part: SKIN — CRACKED (KEELBEAM) · airframe 47,782 hrs · 37,739 cycles

FS 661 - 727, KEEL BEAM SKIN PANEL FABRICATION: DURING INSPECTIONS PER EO 3-58542-3, THE SUBJECT PANEL WAS FOUND CRACKED. BAC SB 737-53-1104 PROVIDES REPAIR INSTRUCTIONS TO REFABRICATE THE PANEL, HOWEVER ER/A 385214-14 WAS ISSUED TO CUT AN ACCESS HOLE IN THE MOUNTING COVER BETWEEN THE HYDRAULIC PUMP AND RESERVOIR IN ORDER TO INSTALL SOLID FASTENERS IN ALL SKIN PANEL LOCATIONS.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 46,860 hrs · 37,345 cycles

THE UPPER SILL BEAM OF THE C2 DOOR CUTOUT SURROUND STRUCTURE WAS FOUND WITH A CRACK IN THE BEAM WEB AT FS 818.

Part: ANTENNA — FAILED (WX RADAR) · airframe 46,586 hrs · 37,230 cycles

WX RADAR ANTENNA FAULT. REPLACED WX RADAR ANTENNA, TEST GOOD. THIS WAS AN AIR TURNBACK.

Part: WIRE — SHORTED (NR 2 ENGINE) · airframe 44,821 hrs · 36,500 cycles

NR 2 ENG OIL TEMP IN YELLOW BAND. FOUND NR 2 FUEL HEAT VALVE C/B POPPED. FOUND WIRE 058-20 INSIDE FIREWALL CANNON PLUG SHORTED TO GROUND. REPAIRED SAME.

Part: COFFEEMAKER — SHORTED (AFT GALLEY) · airframe 44,279 hrs · 36,277 cycles

FLT ATT REPORTED STRONG ELECTRICAL SMELL IN AFT GAL. TURNED OFF AFT GALLEY PWR IN COCKPIT SMELL WENT AWAY. FOUND SHORTED AFT NR 1 COFFEE DISPENSER. REPLACED SAME, CKS OK.

Part: SKIN — GOUGED (FUSELAGE) · airframe 44,172 hrs · 36,228 cycles

THE FUSELAGE SKIN AT THE C1 DOOR CUTOUT FWD EDGE (FS 440) WAS FOUND WITH SEVERAL GOUGES AND SCRATCHES BETWEEN STRINGERS 21R & 25R. THE SKIN WAS CUT OUT TO REMOVE THE DAMAGE. THE CUTOUT WAS REPAIRED WITH AND EXTERNAL ALUMINUM DOUBLER AND TRIPLER PER ER/A 378451-14, REV A.

Part: FLOOR PANEL — CRACKED (COCKPIT) · airframe 44,172 hrs · 36,228 cycles

THE COCKPIT FLOOR WEBS AT WL 207 THAT EXTEND FROM FS 178 TO FS 188 O/B OF LBL AND RBL 24 WERE FOUND CRACKED. THE CRACKS WERE FOUND DURING INSPECTION AND MODIFICATION OF THE FS 178 BULKHEAD WEB PER BAC S/B 737-53A1173, REVISION 3. THIS ER/A INSTRUCTS TO REPLACE THE WEBS IN ACCORDANCE WITH THE S/B. ER/A 378400-14AD.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 43,309 hrs · 35,845 cycles

ON T/O ROLL, LT ENG WOULD ONLY ACHIEVE 2.02 EPR. DISCONTINUEDT/O ROLL AT 60 KTS. TRIMMED 01/02 ENGS PER PFHB. PART PWR AND T/O PWR CHECKS GOOD. ALL ENG PARAMETERS NORMAL ON ENG RUN.

Part: BALLAST — FAILED (GALLEY)

SMOKE AND FUMES IN FWD CABIN AND FLT DECK. DIVERTED TO ATL. REPLACED FWD GALLEY CEILING LIGHT BALLAST.

Part: FRAME — CRACKED (BS 616)

LT AND RT INBD CHORD OF THE FS 616 FRAME BOTH HAVE A CRACK IN THE LOWEST FASTENER HOLE BELOW THE FLOOR LINE. REPAIRED PER ERA 331885-14.

Part: SKIN — DAMAGED (BS 847)

LWR AFT CORNER OF THE C2 DOOR CUTOUT WAS ROUTED OUT TO REMOVE DAMAGE. REPAIRED PER ERA 331876-14.

Part: BULKHEAD WEB — CRACKED (BS 178)

8 CRACKS FOUND IN THE BS 178 BULKHEAD WEB. REPAIRED PER ERA 331867-14.

Part: FRAME — CORRODED (BS 800)

C2 DOOR CUTOUT FWD FRAME LWR CORNER AT FS 800 WAS FOUND CORRODED IN THE UPPER RADIUS NEAR S25R. REPAIRED PER ERA 331884-14AD.

Part: FRAME — DENTED (BS 747/827)

THE STA 747 FRAME WAS FOUND DENTED ON THE INBOARD FLANGE BETWEEN STR 24L AND 25L. THE STA 827 FRAME WAS FOUND DENTED ON THE INBOARD FLANGE AT STR 24L. THE DAMAGE WAS CAUSED IN SERVICE. REPAIRED PER ERA 331894-14.

Part: LINE — RUPTURED (NR 2 ENGINE)

SYS 'A' LOSS INDICATIONS LOW HYD QTY AND NR 2 SYS 'A' LOW PRESS LIGHT. FOUND PRESSURE LINE ON RT ENG HYD PUMP RUPTURED. REPLACED LINE. SERVICED SYS BLEED SYS. ALL CK GOOD PER M/M.

Part: INTERCOSTAL — CRACKED (BS 340)

THE R1 DOOR SURROUND AFT FRAME INTERCOSTAL AT STR 8A WAS FOUND WITH A TYPICAL CRACK PER S/B 737-53A1108. THE INTERCOSTAL WAS REPAIRED PER THE S/B AND ER/A 363174-14AD WHICH ALLOWED SUBSTITUTION OF ALODINE FOR CHROMIC ANODIZE.

Part: FAN — FAILED (AC BAY)

DURING DESCENT, A STRONG ELECTRICAL ODOR STARTED, VERY STRONG IN COCKPIT. FLT ATT REPORTED STRONG ELECTRICAL ODOR ROW 14. REPLACED GASPER FAN AND BOTH WATER SEPARATOR BAGS, CKS OK.

Part: HYDRAULIC FLUID — LOST (A-HYD SYST)

LOSS OF A-SYSTEM HYDRAULIC QTY AND PRESSURE. ACCOMPLISHED SYSTEM A-HYDRAULIC LOSS PROCEDURES PER POM. RETURNED TO ATL, LANDING WEIGHT 102,000 POUNDS.

Part: DOOR — JAMMED (L 1)

DURING EVAC OF AIRCRAFT, THE LEFT NR 1 DOOR WOULD NOT OPEN ALL OF THE WAY. DOOR CHECKS GOOD PER MM 52-11-00, OPENED DOOR DEPLOYED AND INFLATED SLIDE OPS NORMAL. REPLACED SLIDE.

Part: RELAY — INOPERATIVE (STAB TRIM)

AT ALTITUDE MAIN STAB TRIM MOTOR WOULD NOT WORK, A/P MOTOR WORKS OK. APPLICABLE C/B WERE CYCLED TO NO AVAIL, RETURNED TO ATL PER DISPATCH. INSPECTED STAB TRIM ACT, CLEANED CONNECTORS, INSPECTED LIMIT SWITHCES, CUTOUT SWITHCES AND ALL CHECK NORMAL. REPLACED R-66 DUE TO HISTORY AND ALL OPERATION NORMAL.

Part: FLOORBEAM — CRACKED (FS 661)

THE BL 0.07 FLOORBEAM OF THE WING CENTER SECTION IS CRACKED AT STA 661 AND THE UPPER CAP OF THE BEAM IS COMPLETELY CRACKED THROUGH, INCLUDING TWO FASTENER HOLES. THIS AREA WILL BE TRIMMED OUT. NO CRACKS WERE FOUND IN THE WEB. THE CRACK IS TYPICAL PER BOEING SERVICE BULLETIN 737-57-1210, ER/A 302502-14 INSTALLED THE SERVICE BULLETIN REPAIR FOR THE CONDITION.