N636DL

Part: SOCKET — DAMAGED (CABIN) · airframe 77,510 hrs · 36,208 cycles

LINE MAINTENANCE FOUND EMERGENCY ESCAPE PATH LIGHT AT SEAT 2D INOPERATIVE. REPLACED DAMAGED SOCKET AND AMP, OPERATION NORMAL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 77,093 hrs · 36,024 cycles

EMERGENCY LIGHT INOP AT SEAT 4C, BULB CHANGED, NO HELP. REPLACED LAMP ASSEMBLY. OPS CHECK GOOD. FLL JAN 19 239843.

Part: SKIN — DAMAGED (STA 324 STR 4R) · airframe 74,360 hrs · 35,005 cycles

DUE ERA 487716-14 AD PERM REPAIR TO FUSELAGE SKIN AT FS 324 ABOVE STR S4R. COMPLIED WITH ERA 487716-14AD.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 73,640 hrs · 34,670 cycles

DURING LAYOVER CHECK, FOUND EMERGENCY PATH LIGHT AT SEAT 6C INOPERATIVE. MX REPAIRED A BROKEN WIRE AND OPERATION OF LIGHTS NOW CHECKS NORMAL. (2010-D1415)(DL757103289)

Part: MODULE — CRACKED (ANTISKID SYS) · airframe 70,492 hrs · 33,169 cycles

REJECTED T/O. RT HYD DROPPING. ANTISKID FUSE MODULE CRACKED.

Part: SKIN — CRACKED (L1 CUTOUT) · airframe 67,363 hrs · 31,692 cycles

THE FUSELAGE SKIN WAS FOUND CRACKED AT THE UPPER FORWARD CORNER OF THE L1 DOOR CUTOUT. DAMAGE CUTOUT MEASURED 1.35 INCH WIDE BY 3 INCH LONG. AREA WAS INSPECTED AND NO ADDITIONAL CRACKS WERE FOUND. A REPAIR DOUBLER AND TRIPLER WERE INSTALLED.

Part: SKIN — CRACKED (FS 606-614 S27R) · airframe 62,871 hrs · 29,840 cycles

DURING CURRENT HMV, INSPECTION NOTED A SLIGHT GAP BETWEEN THE RIGHT RADIO ALTIMETER RECEIVER ANTENNA FAIRING AND THE FUSELAGE SKIN AT FS 610 AND S-27R. UPON REMOVAL OF THE ANTENNA FAIRING A DENT WITH CRACK WAS DISCOVERED. THE DENT AND CRACK WAS TRIMMED OUT FROM FS 606 TO 614, RIGHT ALONG THE PAD UP AT S-27R. THE TRIM OUT MEASURED 4.7 INCHES BY 8 INCHES. A BOEING APRPOVED REPAIR WAS INSTALLED PER ERA 457354-14.

Part: FRAME — CORRODED (BS 1300 S26-27R) · airframe 62,871 hrs · 29,840 cycles

FOUND CORROSION IN AFT PIT MAIN FRAME UPPER CAP AT BS 1300 S-26 27R. REPAIRED BY FABRICATING AND INSTALLING REPAIR 12 BY 2 FROM 7075-T6 .071 IAW B757 SRM 53-00-07 FIG 201.

Part: SKIN — CRACKED (FS 606-614) · airframe 62,871 hrs · 29,840 cycles

DURING CURRENT VISIT, A GAP BETWEEN THE RIGHT RADIO ALTIMETER RECEIVER ANTENNA FAIRING AND THE FUSELAGE SKIN AT APPROXIMATELY BODY STATION 610 S-27R JUST UNDER THE C1 CARGO DOOR CARGO DOOR OPENING WAS FOUND. UPON REMOVAL OF THE FAIRING, A DENT WITH GOUGES AND RESULTING CRACK WAS DISCOVERED. THIS RESULTED IN A TRIM OUT OF THE CRACKED FUSELAGE SKIN AND A BOEING APPROVED REPAIR INSTALLED PER 460758-14.

Part: TORQUE TUBE — CORRODED (FLAP ASSY) · corrosion level 2 · airframe 62,871 hrs · 29,840 cycles

FOUND CORROSION INSIDE LT I/B T/E FLAP TORQUE TUBE. REPAIRED BY REMOVING AND REPLACING TORQUE TUBE WITH P/N 117N2105-1 NSN, CARRIAGE ASSY WITH P/N 113N2100-13 S/N 248, FAIL SAFE AND P/N 113N2108-1 NSN IAW DELTA EA 06-097981-14 REV A.

Part: TORQUE TUBE — CORRODED (FLAP) · corrosion level 2

FOUND CORROSION INSIDE LT I/B T/E FLAP TORQUE TUBE. REPAIRED BY REMOVING AND REPLACING TORQUE TUBE WITH P/N 117N2105-1 NSN, CARRIAGE ASSY WITH P/N 113N2100-13 S/N 248, FAIL SAFE AND P/N 113N2108-1 NSN IAW DELTA EA 06-097981-14 REV A.

Part: SWITCH — SHORTED (LAVATORY) · airframe 52,662 hrs · 26,104 cycles

MID LAV DOOR SWITCH SHORTED. REPLACED SWITCH.

Part: LIGHT — INOPERATIVE (R2 DOOR) · airframe 51,577 hrs · 25,691 cycles

R2 EMERGENCY ESCAPE PATH LIGHT INOPERATIVE. REPLACED LIGHT ASSY, CHECKS OK.

Part: BRAKE — FIRE (MLG) · airframe 46,060 hrs · 23,087 cycles

RAMP WORKER NOTICED SMALL GREASE FIRE ON NR 7 BRAKE UPON ARRIVAL. NO ABNORMAL BRAKE TEMPS NOTED BY CREW VIA COCKPIT INDICATIONS. REPLACED BRAKE ASSY. NO DAMAGE FOUND.

Part: SKIN — GOUGED (FUSELAGE) · airframe 44,583 hrs · 22,446 cycles

INSPECTION OF AN EXISTING SKIN REPAIR BETWEEN FS 1681 & 1701 AND BETWEEN STRINGERS 18L & 19L REVEALED GOUGE DAMAGE TO THEREPAIR. THE REPAIR WAS REMOVED AND THE FUSELAGE SKIN CUT TO REMOVE ALL REPAIR FASTENER HOLES AND DAMAGE. THE FINAL CUTOUT WAS 10.5 INCHES X 10.5 INCHES. THE CUTOUT WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER AND TRIPLER PER ER/A 380355-14, REV A.

Part: ENGINE — FAILED (NR 1)

N CRUISE AT 370, LEFT ENG OIL PRESS WENT TO ZERO, STARTED LOOKING FOR QTY, SHOWED ZERO. STARTED TO THROTTLE BACK, LEFT ENG POPPED THEN SHUT ITSELF DOWN. SUDDEN FAILURE, OIL TEMP NEVER ROSE, WINDMILLED ENG AT 25 MIN.

Part: SKIN — CRACKED (NR 1 PYLON)

THE OUTBOARD STRUT SKIN OF THE NR 1 PYLON HAS 2 CRACKS IN THE UPPER CORNERS OF THE NAC STA 107 ACCESS HOLE. THE CRACK IN THE UPPER AFT CORNER IS .875 INCH LONG AND IS STOP DRILLED WITH A .25 DIAMETER STOP HOLE. THE CRACK IN THE UPPER FORWARD CORNER IS 1.625 INCH LONG, AND IT EXTENDS .375 INCH BEYOND THE MAXIMUM ALLOWABLE CRACK LENGTH. IT HAS ALSO BEEN STOP DRILLED WITH A .25 INCH HOLE. THE MAXIMUM ALLOWABLE CRACK LENGTH AREA WAS ESTABLISHED IN PREVIOUS CORRESPONDENCE WITH BAC ON THIS SUBJECT. TEMP REPAIR PER B757 SRM 54-51-01, FIG 204; PERM REPAIR PER B757 SRM 54-51-01, FIG 204.

Part: SKIN — CRACKED (NR 1 PYLON)

THE O/B STRUT SKIN OF THE NR 1 PYLON HAS TWO CRACKS IN THE UPPER CORNERS OF THE NAC STA 107 ACCESS HOLE. THE CRACK IN THE UPPER AFT CORNER IS .875 INCH AND WAS STOP DRILLED. THE CRACK IN THE UPPER FORWARD CORNER IS 1.625 INCH LONG. A TEMPORARY REPAIR WAS ACCOMPLISHED PER B757 SRM 54-51-01, FIG 204 TO FERRY THE PLANE TO ATL. A PERMANENT REPAIR WAS ACCOMPLISHED PER B757 SRM 54-51-01, FIG 203.

Part: SKIN — CRACKED (NR 2 ENGINE)

THE NR 2 ENGINE NACELLE STRUT SKIN WAS FOUND CRACKED JUST AFT OF NAC 107.7 ON THE I/B SIDE. THE CRACK WAS 1.5 INCH LONG AND EMANATES FROM THE UPPER FWD CORNER OF AN ACCESS HOLE BTW BULKHEADS AT STA 107.700 AND 116.050. THIS ER/A AUTHORIZES THE CRACK TO BE STOP DRILLED AND INSPECTED ON A TIME LIMITED BASIS. THE PERMANENT REPAIR WILL BE ACCOMPLISHED AT NEXT HMV. THE REPAIR IS ACCOMPLISHED IN ACCORDANCE WITH BAC TWX DAL-ATL-93-1337RR, DTD 04 DEC 93, B757 SRM 54-51-01, FIG 203 AND 204.

Part: FIRE BOTTLE — LEAKING (FLIGHT CABIN)

F/C HALON FIRE BOTTLE LEAKING EXTINGUISHING AGENT.

Part: EEL BULB — FAILED (CABIN)

AFT LEFT EMERGENCY LIGHT BEHIND FILLET PANEL INOP. RELAMPED, OPERATION NORMAL.

Part: PNEUMATIC SYSTEM — CONTANIMATED (AC COMP)

SHORTLY AFTER TAKEOFF HAD SMOKE AND ODOR ENTER CABIN. RETURNED ATL. FOUND PNEUMATIC SYSTEM CONTANIMATED. A WATER BASED SOLUTION WAS DRAINED FROM GROUND AIR CONNECTION. RAN BOTH ENGINES AND PACKS AFTER 1 HOUR HAD NO ODOR. RETURNED TO SERVICE.