N603DL

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,502 hrs · 45,293 cycles

DURING INSPECTION, FOUND NUMEROUS BURN MARKS ON LT SKIN FROM RADOME TO NOSE GEAR AFT DOOR BELOW LAP JOINT. ALL BURNISHED MARKS WITHIN SERVICABLE LIMITS IAW SRM 53-00-00. FOUND 2 SOLID RIVETS BURNED BEYOND LIMITS, 3 INCHES ABOVE STRINGER 26L AT STATION 215.25 AND STATION 239. REPLACED BOTH SOLID RIVETS IAW SRM 53-00-01.

Part: UNKNOWN — ODOR (CABIN) · airframe 89,367 hrs · 45,229 cycles

FLIGHT DIVERTED DUE TO A STRONG BURNING ELECTRICAL ODOR FROM THE MID GALLEY. NO VISIBLE SMOKE REPORTED. MAINTENANCE INSPECTED WIRING BEHIND COFFEEMAKERS, OVENS, POWER CONTROL PANELS, AND CEILING LIGHTS WITH NO TROUBLE FOUND. R & R BOTH MID GALLEY COFFEEMAKERS.

Part: WIRE HARNESS — DAMAGED (EMERGENCY LIGHT) · airframe 89,139 hrs · 45,121 cycles

EMERGENCY LIGHT INOPERATIVE. REPLACED SEAT WIRE HARNESS. CHECKED NORMAL.

Part: GIRT BAR — DIRTY (L4 DOOR SLIDE) · airframe 88,649 hrs · 44,909 cycles

F/A REPORTS L4 DOOR SLIDE WILL NOT DISENGAGE COMPLETELY. CLEANED DEBRIS FROM GIRT BAR AND FLOOR MOUNTED HARDWARE. PERFORMED, AMM 25-66 INSP/CK OPS CHECKS NORMAL. OK FOR SERVICE.

Part: SNUBBER — DAMAGED (L4 DOOR) · airframe 87,924 hrs · 44,621 cycles

L4 DOOR VERY HARD TO OPEN. REPLACED ROTARY SNUBBER IAW MM 52-11. INSTALLED SNUBBER IAW MM.

Part: FRAME — CORRODED (BS 310 S23-24L) · airframe 87,617 hrs · 44,490 cycles

STA 310.5, CORROSION STR 23 TO 24 LT FRAME TOP LEG. REMOVED DAMAGE 1" X 4.5" UPPER LEG. INSTALL DOUBLER REPAIR IAW ERA 514386-14, REV ORG (TO 514386-14).

Part: STRUCTURE — CRACKED (FWD CARGO DOOR) · airframe 87,507 hrs · 44,439 cycles

DAMAGE ON FWD CARGO DOOR LOWER AFT CORNER. REMOVED EDGE CRACK IAW SRM 52-30-01.

Part: INLET — DAMAGED (NR 1 ENGINE) · airframe 86,438 hrs · 44,002 cycles

NR 1 ENGINE INLET COWL RT SIDE 9 OCLOCK POSITION HAS A DENT. DENT OUT OF LIMITS IAW SRM 54-11-01. R & R NR 1 ENGINE INLET COWL IAW AMM 71-11-01.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 86,290 hrs · 43,940 cycles

MX DISCOVERED THE L2 DOOR EXIT SIGN HAS MANY BULBS INOPERATIVE. R & R BULBS AT L2 DOOR EXIT SIGN IAW AMM 33-51.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 84,358 hrs · 43,100 cycles

LINE MAINTENANCE FOUND EMERGENCY PATH LIGHTS INOPERATIVE AT SEATS 1 THRU 6. REPLACED BATTERY CHARGER, OPERATION NORMAL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 83,149 hrs · 42,587 cycles

SEAT 2D EMERGENCY PROXIMITY LIGHT INOPERATIVE. REPLACED EMERGENCY PROXIMITY LIGHT ASSEMBLY AS PER B757 AMM 33-51. OPS CHECK GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 80,995 hrs · 41,695 cycles

DURING A LAYOVER CHECK, MAINTENANCE FOUND THE DOOR L2 EMERGENCY EXIT LIGHT INOPERATIVE. MAINTENANCE REPLACED THE FUSE AND LAMP. OPERATIONAL CHECK WAS GOOD. (2011-D0139)

Part: LIGHT — INOPERATIVE (CABIN) · airframe 80,995 hrs · 41,695 cycles

DURING A LAYOVER CHECK, MAINTENANCE FOUND THE EMERGENCY PATHLIGHTS AT 5D, 27D, AND 37D INOPERATIVE. MAINTENANCE RE-LAMPED ROW 5 AND 27. 37D HAD THE WIRING REPAIRED. OPERATIONAL CHECK WAS GOOD. (2011-D0137)

Part: WIRE — DISCONNECTED (EMERGENCY LIGHTS) · airframe 79,697 hrs · 41,117 cycles

WHITE EMERGENCY LIGHT AT SEAT 25D INOPERATIVE. HARNESS IS PULLED OUT. SPLICED AND SECURED WIRES UNDER SEAT 25D. OPS CHECK OK.

Part: UNKNOWN — ODOR (CABIN) · airframe 79,583 hrs · 41,076 cycles

DURING FLIGHT, F/A'S REPORTED A BURNING ODOR IN THE CABIN SO THE ACFT DIVERTED. MX CHECKED ACFT AND CABIN SYSTEMS WITH NO ODOR NOTED AND NO PROBLEMS FOUND. ACFT RETURNED TO SERVICE.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 78,793 hrs · 40,756 cycles

DURING LAYOVER CHECK, MX FOUND EMERGENCY PATH LIGHTS VERY DIM AT ROWS 19-27. MX REPLACED THE BATTERY PACK. OPS CHECK WAS GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 78,629 hrs · 40,681 cycles

DURING LAYOVER CHECK, MAINTENANCE FOUND EMERGENCY PATH LIGHT AT SEAT 5C INOPERATIVE. MAINTENANCE REPLACED THE LIGHT ASSEMBLY. OPERATIONAL CHECK WAS GOOD.

Part: WIRE — DAMAGED (EMERGENCY LIGHTS) · airframe 78,201 hrs · 40,447 cycles

ON A CHECK FOUND EMERGENCY PATH SEAT LIGHTS INOP AT ROWS 25, 26, 27, 30, 31, 39, 43-45. REPAIRED WIRING AT AFFECTED SEATS OPS CK OK.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 78,201 hrs · 40,447 cycles

DURING SERVICE CHECK AD 2 FOUND EMERGENCY PATH SEAT LIGHTS INOP AT ROWS 25, 26, 27, 30, 31, 39, 43-45. REPAIR WIRING AT AFFECTED SEATS, OPS CK OK.

Part: SPAR — CORRODED (HORIZ STAB) · airframe 77,253 hrs · 39,892 cycles

DURING PSV CHECK, MAINTENANCE FOUND THE RT HORIZONTAL STABILIZER REAR SPAR UPPER CHORD CORRODED WHERE THE UPPER T/E PANEL ATTACHES. THE CHORD WAS REPAIRED PER ERA 476883-14.

Part: RIB — CORRODED (HORIZ STAB) · airframe 77,253 hrs · 39,892 cycles

DURING PSV MAINTENANCE FOUND CORROSION ON THE RT HORIZONTAL STABILIZER RIB 11 UPPER SURFACE. CORROSION EXCEEDED SRM LIMITS. ACCOMPLISHED REPAIR PER ERA 477049-14.

Part: BUTT JOINT — CORRODED (FUSELAGE) · airframe 77,253 hrs · 39,892 cycles

DURING PSV 23 THE RT FUSELAGE SPLICE PLATE AT STATION 900 WAS FOUND TO HAVE CORROSION. THE BAC P/N IS A 144N3310-8402. CORROSION WAS VISIBLE AT THE STATION 900 SKIN BUTT SPLICE AT STRINGER 13R TO 15R. THE SPLICE PLATE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.

Part: ACTUATOR — WORN (THRUST REVERSER) · airframe 75,592 hrs · 39,130 cycles

RIGHT THROTTLE THRUST LEVER STOPPED HARD AND WOULD NOT GET TO TAKEOFF POWER. FOUND RIGHT THROTTLE PHYSICALLY STUCK AS IF HITTING A STOP INSP THROTTLE QUADRANT AREA ABOVE AND BELOW THROTTLES NO BINDING AREAS NOTED FREED THROTTLE WITH LIGHT FORCE PERFORMED MCDP TEST 2 AND 10 CHKS NML. CYCLED THROTTLES NUMEROUS TIMES COULD NOT DUPLICATE. SUSPECT THRUST REVERSER INTERLOCK ACTUATOR. REMOVED AND REPLACED RT THRUST REVERSER INTERLOCK ACTUATOR PER AMM CLOSED C/B'S PERFORMED MCDP TEST 2 AND 10 OPS GOOD. PERFORMED VISUAL INSPECTION OF THROTTLE QUADRANT CHKS GOOD.

Part: SKIN — MISREPAIRED (BS 628) · airframe 73,012 hrs · 37,917 cycles

DURING HMV AT SAA, THE FUSELAGE SKIN AT STA 628 AND S-25L WAS FOUND WITH AN EXISTING REPAIR THAT DID NOT MEET SRM REQUIREMENTS. THE REPAIR DOUBLER WAS REMOVED AND A BOEING DESIGNED REPAIR WAS INSTALLED.

Part: SKIN — DAMAGED (BS 1515 S28-29R) · airframe 73,012 hrs · 37,917 cycles

TOOLING MARKS WERE FOUND AT THE AIRPHONE ANTENNA SKIN AT FS 1515 BETWEEN S-28R AND S-29R. THE ANTENNA IS NO LONGER IN USE. BECAUSE THE ANTENNA HAD BEEN SUBJECT TO AN STC, THE ANTENNA WAS REMOVED, AND THE FASTENER PATTERN CUTOUT. AN EXTERNAL REPAIR DOUBLER WAS INSTALLED. CUTOUT WAS 8.6" BY 5.2".

Part: SKIN — DAMAGED (BS 1420 S28R) · airframe 73,012 hrs · 37,917 cycles

DURING HMV AT SAA, A CREASE WAS FOUND IN THE FUSELAGE SKIN AT STA 1420, S-28R. THE CREASE EXCEEDED THE ALLOWABLE SRM LIMIT. A REPAIR WAS ACCOMPLISHED PER BOEING INSTRUCTIONS. STARTING AT 12,000 CYCLES AFTER REPAIR INSTALLATION AND EVERY 12,000 CYCLES THEREAFTER, THE PERIPHERAL ROW OF FASTENERS COMMON TO THE REPAIR MUST BE LFEC INSPECTED FOR CRACKS.

Part: SKIN — CORRODED (FUSELAGE) · airframe 72,868 hrs · 37,849 cycles

FUSELAGE/SKIN/FS 880/STRG 28L-28R :CORROSION REPAIR. THE FUSELAGE SKIN WAS FOUND WITH AN AREA OF CORROSION AT FS 880 BETWEEN STRINGERS 28L AND 28R. THE CORROSION WAS ADJACENT TO AN AIR CONDITIONING DUCT CUTOUT. THE DAMAGE WAS REMOVED WITH A CUTOUT TO THE SKIN AND REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER AND TRIPLER PER ER/A 465214-14.

Part: BULKHEAD — GOUGED (FS 1720 S25L-25R) · airframe 70,681 hrs · 36,893 cycles

THE AFT FUSELAGE PRESSURE BULKHEAD WAS DAMAGED DURING A TAIL STRIKE. THE BULKHEAD CHORDS WERE CUT OUT AND A NEW SECTION WAS FABRICATED AND SPLICED IN. REF ER/A'S 460538-14 AND 460643-14 FOR SAME DAMAGE.

Part: AMPLIFIER — MALFUNCTIONED (PA SYSTEM) · airframe 69,120 hrs · 36,225 cycles

P/A MAKING BUZZING SOUND WITH POSSIBLE ELECTRICAL SMELL NEAR MID LAVS. REPLACED P/A AMP AND IFE CONTROLLER CHECKS OK.

Part: LINKAGE — LACK OF LUBE (NLG) · airframe 67,750 hrs · 35,734 cycles

ON TAKEOFF GEAR DOOR LIGHT ILLUMINATED. AIRCRAFT PERFORMED AIR RETURN. FOUND FOLLOW UP LINKAGE FOR MANUAL RELEASE OF NOSE GEAR DOORS STICKING. CLEANED AND LUBED SAME. CYCLED DOORS MANUALLY SEVERAL TIMES. JACKED NOSE GEAR AND PERFORMED NOSE GEAR EXTENTION/RETRACTION SWING SEVERAL TIMES. ALL OPS CHECKED NORMAL.

Part: SLIDE — OUT OF POSITION (L1 DOOR) · airframe 67,471 hrs · 35,644 cycles

L1 ESCAPE SLIDE FELL OUT WHEN DOOR WAS OPENED. REPLACED L1 DOOR SLIDE PER M/M. SAFETY PIN REMOVED AND STOWED.

Part: SKIN — CRACKED (FUSELAGE) · airframe 61,967 hrs · 33,491 cycles

FUSELAGE SKIN ASSY L1 DOOR CUTOUT UPPER FWD CORNER : CRACK REPAIR, INSPECTION OF THE FUSELAGE SKIN AT THE UPPER FWD CORNER OF THE L1 DOOR CUTOUT REVEALED A CRACK. THE CRACK IS TYPICAL OF AD 2004-09-32. THE CRACK WAS CUTOUT OF THE SKIN AND UNDERLYING BEARSTRAP. THE CUTOUT WAS REPAIRED WITH THREE EXTERNAL ALUMINUM REPAIR DOUBLERS IAW ER/A 090671-14AD.

Part: SWITCH — FAULTY (MID LAVATORY) · airframe 60,516 hrs · 32,930 cycles

CENTER LAV DOOR LATCH HOT AND EMITTING SMOKEY O-ZONE SMELL. REPLACED DOOR LATCH SWITCH.

Part: SKIN — DENTED (FS 1630, S-25R) · airframe 55,222 hrs · 30,504 cycles

FUSELAGE / SKIN / FS 1630 / STRG. 24R-26R : GROUND DAMAGE CUTOUT REPAIR THE FUSELAGE SKIN WAS DENTED AND GOUGED AT FS 1630 BETWEEN STRINGERS 24R & 26R. THE DAMGE WAS REMOVED WITH A 7" X 2" CUTOUT AND A 5" X 2" CUTOUT. BOTH CUTOUTS WERE REPAIRED WITH A SINGLE EXTERNAL ALUMINUM DOUBLER INSTALLED PER ER/A 382286-14, REV A.

Part: SKIN — CRACKED (FS 1701, S-29L) · airframe 55,222 hrs · 30,504 cycles

FUSELAGE / SKIN / FS 1701 / STRG. 29L : CRACKED HOLE REPAIR A SMALL CRACK WAS FOUND AT FASTENER HOLE DUE TO IMPROPER FASTENER INSTALLATION AT FS 1701 AND STRINGER 29L. THE CRACK WAS REMOVED WITH A .5" HOLE. THE HOLE WAS ADJACENT TO THE EDGE OF AN EXISTING INTERNAL REPAIR DOUBLER. TO REPAIR THE NEW DAMAGE, AN EXTERNAL ALUMINUM REPAIR DOUBLER WAS INSTALLED, OVERLAPPING THE EXISTING DOUBLER PER ER/A 382398-14, REV A.

Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 55,222 hrs · 30,504 cycles

OUTER CHORD AND WEB SPLICE; LOWER SILL CHORD SUBSTITUTION THE LOWER SILL OF THE C2 DOOR OPENING WAS FOUND WITH SEVERAL AREAS OF CORROSION. THE OUTER CHORD AND WEB OF THE FS 1440 OPENING FRAME WERE CUT AND THE LOWER SECTION REMOVED TO ALLOW REPLACEMENT OF THE SILL. THE SILL WAS REPLACED, THE WEB SPLICED PER B757 SRM, AND THE CHORD SPLICED WITH 2 ALUMINUM REPAIR ANGLES PER ER/A 382180-14, REV A.

Part: SKIN — GOUGED (FS 1701, S-20L) · airframe 55,222 hrs · 30,504 cycles

FUSELAGE / SKIN / FS 1701 / STRG. 20L / SKIN LAP JOINT : GOUGE CUTOUT REPAIR THE LOWER SKIN OF THE STRINGER 20L SKIN LAP JOINT WAS GOUGED BY TOOLING AT FS 1701. THE DAMAGED AREA OF SKIN WAS TRIMMED OUT. THE SKIN LAP WAS REPAIRED WITH AN EXTERNAL ALUMINUM DOUBLER PER ER/A 382287-14, REV A.

Part: TRUNNION — CORRODED (LT MLG) · airframe 55,222 hrs · 30,504 cycles

INSPECTION OF THE MLG FUSE PINS AND ADJACENT LUG BORES PER AD 2000-07-13, REVEALED CORROSION IN THE FUSE PIN LUG BORES OF THE LT MLG FWD TRUNNION BEARING SUPPORT FITTING ASSEMBLY. CLEANUP OF THE CORROSION RENDERED THE FITTING UNACCEPTABLE FOR FURTHER SERVICE. A NEW FITTING ASSEMBLY WAS INSTALLED ON THE AIRCRAFT PER ER/A 382314-14AD.

Part: SKIN — DENTED (FS 1680, S-17L) · airframe 55,222 hrs · 30,504 cycles

FUSELAGE / SKIN / FS 1620-1720 / STRG. 14A-20L : SKIN REPLACEMENT THE FUSELAGE SKIN WAS FOUND WITH NUMEROUS DENTS AND GOUGES NEAR THE L4 DOOR OPENING. THE SKIN PANEL WAS REMOVED TO ELIMINATE ALL OF THE DAMAGE LOCATIONS. A NEW SKIN PANEL WAS INSTALLED PER ER/A 382226-14.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 55,222 hrs · 30,504 cycles

THE UPPER CAP OF THE FS 1681 PASSENGER FLOORBEAM WAS FOUND WITH SEVERAL AREAS OF CORROSION. TO REMOVE THE DAMAGE, THE ENTIRE UPPER CAP WAS TRIMMED OFF. A NEW CAP WAS FABRICATED FROM ALUMINUM EXTRUSION AND INSTALLED PER ER/A 382227-14, REV A.

Part: SKIN — GOUGED (FS 1610, S-26L) · airframe 55,222 hrs · 30,504 cycles

FUSELAGE / SKIN / FS 1610 / STRG. 26L : DENT & GOUGE REPAIR THE FUSELAGE SKIN WAS DENTED AND GOUGED BY TOOLING AT FS 1610 JUST ABOVE THE STRINGER 26L SKIN LAP JOINT. THE DAMAGE WAS REMOVED WITH A 1" CUTOUT AND REPAIRED WITH AN EXTERNAL ALUMINUM REPAIR DOUBLER. THE REPAIR WAS ACCOMPLISHED PER ER/A 382233-14, REV A.

Part: BRAKE — DAMAGED (MLG) · airframe 54,664 hrs · 30,240 cycles

NR FIVE BRAKE TWISTED AND PADS COMING APART, REPLACED BRAKE.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 53,341 hrs · 29,613 cycles

FOUND ON LO FC EMERGENCY LIGHTS INOPERATIVE. REPLACED BATTERY PACK OPS NORMAL

Part: ACM — WORN (LT PACK) · airframe 52,882 hrs · 29,397 cycles

A/C WILL NOT MAINTAIN HIGHER THAN 7.2 PSID UNTIL RT RECIRC FAN TURNED OFF. WITH RT RECIRC FAN OFF PRESSURIZATION AND TEMP CONTROL WERE NORMAL. AT FL 390 RT PACK OFF LIGHT CAME ON, LATER RT ENG BLEED OFF LIGHT ON. COULD NOT RECOVER RT PK UNTIL ON GROUND AT LAX. THE LEFT PACK OPERATING ALONE WOULD NOT HOLD CABIN PRESSURE UNTIL DESCENDED BELOW FL 220. LEFT PACK WOULD NOT HOLD CABIN PRESSURE AT IDLE THRUST UNTIL BELOW FL 180. REPLACED AIR CYCLE MACHINE.

Part: TORQUE TUBE — FAILED (LT TE FLAPS) · airframe 52,135 hrs · 29,045 cycles

DURING LANDING WHEN FLAP LEVER MOVED FROM 15 TO 20 EICAS MSG FLAP ASYM AND TRAILING EDGE LIGHT ILLUM THE LEFT FLAP REMAINED AT 15 RIGHT FLAP STOPPED. LEFT INBOARD OUTBOARD TORQUE TUBE REMOVED AND REPLACED.

Part: TRANSMITTER — FAILED (TE FLAPS)

T/E FLAP ASSY LIGHT CAME ON AFTER T/O WHEN RAISING FLAPS FROM 10-15 DEG. FLAP NEEDLES SPLIT AND STOPPED. REPLACED T/E FLAP TRANSMITTER.

Part: SKIN — DENTED (BS 1665)

THE FUSELAGE SKIN AT FS 1665 AND STRINGER 25R WAS BADLY DENTED AT THE FWD END OF A DRAIN MAST. INSTALLATION DUE TO GROUND SERVICE DAMAGE. THE DAMAGED AREA WAS CUT OUT AND A SKIN DOUBLER AND TRIPLER WERE INSTALLED PER ER/A 364032-14, REV A.

Part: SKIN — DENTED (BS 1630)

THE FUSELAGE SKIN BETWEEN FS 1627 AND 1639 AND BETWEEN STR 28L AND 29L WAS DENTED AND GOUGED DUE TO GROUND DAMAGE. THE DAMAGED AREA WAS CUT OUT AND A SKIN DOUBLER WAS INSTALLED PERER/A 364038-14, REV B.

Part: SKIN — GOUGED (BS 1755)

THE FUSELAGE SKIN WAS DENTED, SCRATCHED AND GOUGED NEAR STRINGER 29R BETWEEN FS 1743 AND 1768. THE DAMAGED AREA WAS CUTOUT AND SKIN DOUBLER AND TRIPLER WERE INSTALLED PER ER/A 364040-14, REV A.

Part: SKIN — DENTED (BS 1560)

THE FUSELAGE SKIN HAD NUMEROUS GOUGES, DENTS AND SCRATCHED BETWEEN FS 1550 AND 1621 AND BETWEEN STRINGERS 26L AND 26R. THE DAMAGED SECTION OF SKIN WAS REMOVED AND A NEW SECTION WAS SPLICED IN PER ER/A 364044-14, REV B.

Part: TRANSCEIVER — FAILED (RT COCKPIT VHF)

ACFT DIVERTED WITH EICAS MESSAGE FWD EQ SMOKE DETECTOR STATUS PAGE. ALSO, HAD EQUIP OVERHEAT LIGHT ON. OVERBOARD EXHAUST VALVE OPEN. WENT TO ALTERNATE EQ COOLING OVERHEAT. RESOLVED AND A FEW MINUTES LATER SMOKE/OVERHEAT LIGHT CAME BACK OK. ALSO, PILOT REPORTED F/O VHF COMM RADIO INOP. TESTED ALL SYS AND FANS, ALL OK. FOUND F/O VHF TRANSCVR INOP AND FAILED BITE. ALSO, HAD WHAT APPEARED AS LIGHT SMOKE RESIDUE AT AIR VENT HOLES. REPLACED TRANSCVR RADIO SYS AND OVER HEAT SYS ALL CK NORMAL (P/N 39080001) (S/N 2651) OFF.

Part: SKIN — CORROSION (BS 720)

CORROSION WAS FOUND AROUND THE WING SCANNING LIGHT CUTOUT AT STA 720B+10 AND S-15L. THE CORROSION IS WITHIN THE REPAIR LIMITS OF B727 SRM 53-50-5, FIGURE 22 AND WAS BEING REPAIRED BY THAT SECTION. DURING ACCOMPLISHMENT OF THAT REPAIR SEVEN HOLES WERE DRILLED TOO CLOSE TO THE UPPER SKIN OF THE S-14L LAP JOINT FOR INSTALLATION OF FASTENERS IN THE REPAIR DOUBLER, LITTLE OR NO EDGE MARGIN.

Part: AUTO PILOT — FAILED (FLIGHT DECK)

FLT DIVERTED TO LAS WITH IN-FLIGHT EMERGENCY-SMOKE IN COCKPIT. FOUND RT A/P INOP ON ARRIVAL AND HEAVY BURNED SMELL EMANATING FROM RT SIDE OF A/P MODE CONTROL PANEL. INSTALLED NEW A/P. MCP AND PERFORMED TEST 01/04 AND 01/30 WITH MCDP. ALL NORMAL.

Part: PRESS SWITCH — FAILED (CARGO COMPT)

DURING PUSHBACK, NR 1 BTL CARGO FIRE EXT DISCHARGE WAS ILLUMINATED. DURING TOW INTO GATE NR 2 BTL DISCHARGE ILLUMINATED AND WAS ACCOMPANIED WITH CARGO BTL 1 AND CARGO BTL 2 EICAS MESSAGE. REPLACED NR 1 CARGO FIRE EXT BOTTLE AND FOUND PRESSURE SWITCH FAULTY.