N720QS

Part: WIRE HARNESS — CORRODED (PROXIMITY SENSOR) · airframe 7,450 hrs · 4,589 cycles

FL 260, CLIMBING AT 300KTS, RT RED BOX SLASH GEAR UNSAFE INDICATION APPEARED. SPEED TAPE TURNED RED. AFTER SLOWING TO ABOUT 270KTS GEAR INDICATION RETURNED TO NORMAL AND REMAINED NORMAL. FLT WAS SMOOTH, NO VIBRATIONS. FOUND CORROSION ON RT MLG PROXIMITY SWITCH CABLE ASSY. REMOVED AND REPLACED HARNESS WITH NEW IAW 32-30-00. PERFORMED LANDING GEAR CYCLING AND VERIFIED INDICATION ON EICAS ALL OPS TESTED SATISFACTORY. IAW 32-10-11.

Part: HYDRAULIC LINE — LEAKING · airframe 7,069 hrs · 4,331 cycles

FL390, RT HYD LOW LEVEL, HYD EICAS MESSAGE CAME ON. QTY SHOWING 24. RAN CHECKLIST. RT HYDRAULIC LOW PRESSURE EICAS MESSAGE CAME ON. RAN CHECKLIST, DECLARED AN EMERGENCY, DIVERTED. HYD FLUID LEAKING FROM THE BELLY. REPLACED CHAFED HYD LINES IN AFT COMPARTMENTS ONLY. CLEANED RESIDUE IN AFT COMPARTMENT. OPERATED AUXILARY PUMP AND CYCLED FLIGHT CONTROLS, NO DEFECTS OR LEAKS NOTED. ALL WORK DONE IAW AMM 20-10-12 AND 20-10-13, REF GAMPS 2507, REV B.

Part: WEB — GOUGED (PAX DOOR) · airframe 6,578 hrs · 4,033 cycles

THE MAIN ENTRY DOOR DAMPER LOWER ARM HAS BEEN CONTACTING WEB AT FS 5727 DURING NORMAL OPERATION OF MED, RESULTING IN GOUGES ON THE WEB AND A CRACK EMANATING FORWARD OT THE EDGE OF THE WEB. ARE REQUESTING AN ENGINEERING DISPO TO REPAIR THE WEB. IF A REPAIR DOUBLER IS GOING TO BE REQUIRED, WE REQUEST IT BE INSTALLED ON THE INBD SIDE OF THE WEB, DUE TO THE CLOSE TOLERANCE BETWEEN THE MED DAMPER ARM AND THE WEB.

Part: FIRE LOOP — CHAFED (NACELLE) · airframe 6,064 hrs · 3,723 cycles

APPROX 30 MIN FROM DESTINATION, NOTED LT ENGINE FIRE WARNING LIGHT DIMLY ILLUMINATED. ALL ENGINE PARAMETERS WERE NORMAL, REDUCING THRUST LEVER ON AFFECTED SIDE, NO CHANGE. PERFORMED INSPECTION OF FIRE LOOP ZONE 1. FOUND LOOP CHAFING ON GEARBOX, NO DAMAGE OR DEFECTS NOTED ON LOOP, REPOSITIONED LOOP AND PERFORMED OPS CHECK WITH NO DEFECTS NOTED. REF MM 26-10-00 AND WIRE DIAGRAM- 26-20-11.

Part: ACTUATOR — LOCKED (NR 2 SLATS) · airframe 5,877 hrs · 3,603 cycles

SLAT / FLAP MAINTENANCE LIGHT ON. NO SLAT OR FLAP MOVEMENT. FOUND NR 2 SLAT ACUTATOR LOCKED UP AND WOULD NOT MOVE. REMOVED NR 2 RT SLAT ACTUATOR AND INSTALLED A MODIFIED ACTUATOR. RIGGED ON SLAT SYS AND PERFORMED SATISFACTORY FLAP/SLAT CONTROL AND DRIVE SYS FUNCTIONAL TEST WITH NO FAULTS FOUND. FOR ALL WORK REF MM 27-51-45 27-80-00 AND 27-80-10.

Part: PROXIMITY SWITCH — OUT OF ADJUST (MLG) · airframe 4,370 hrs · 2,699 cycles

LT MAIN GEAR ON RETRACTION RED CROSS HATCHES RAN QRH RETURNED TO PBI NORMAL 3 GREEN DOWN AND LOCKED LANDING. READJUSTED FWD LT MGL PROX SWITCH TO .037 INCH (WITHIN LIMITS) AND ADJUSTED LT MLG DOOR CONNECTING ROD .5 TURN TIGHT WITHIN LIMITS. CYCLED GEAR, OPS CHECK GOOD ON GROUND. ALL WORK PERFORMED IAW MM CH 32-10-11, 32-10-10, 32-60-00.

Part: INDICATION SYS — ILLUMINATED (LT MLG) · airframe 4,370 hrs · 2,699 cycles

LEFT MAIN GEAR RED CROSS HATCHES ON RETRACTION

Part: UPLOCK SWITCH — INOPERATIVE (LT MLG) · airframe 4,370 hrs · 2,698 cycles

UPON GEAR RETRACTION, LT MAIN GEAR INDICATION WAS AMBER CROSS HATCHED THEN RED CROSS HATCHED AND STAYED THAT WAY. GEAR SOUNDED TO HAVE RETRACTED NORMALLY. FOLLOWING QRH DID NOT FIX THE PROBLEM. UNEVENTFUL LANDING FOLLOWED. HYD RESS WAS NORMAL. RECEIVED 3 GREEN DOWN INDICATIONS. REMOVED AND REPLACED LT FWD AND AFT UPLOCK PROXIMITY SWITCHES. WORK DONE IAW MM 32-10-11 AND CMP 326020. PART SN OFF: 4AS8135500-503 SN: OFF NA SN ON: N/A PN ON: 4AS8135500-503 (AFT)

Part: INDICATOR — MALFUNCTIONED (MLG) · airframe 4,370 hrs · 2,698 cycles

UPON GEAR RETRACTION LEFT MAIN GEAR INDICATION WAS AMBER CROSS HATCHED THEN RED CROSS HATCHED AND STAYED THAT WAY.

Part: PUMP — INOPERATIVE (HYD SYSTEM) · airframe 4,369 hrs · 2,697 cycles

WE GOT THE RT HYD LEVEL LOW CAS MESSAGE. LATER WE GOT THE RT HYD PUMP PRESS LOW MESSAGE. GEAR CAME DOWN AND WE DID THE EMERGENCY GEAR EXTENSION IAW CHECK LIST. REST OF RT HYD SYS WORKED NORMAL. AFTER LANDING PSI STAYED AMBER 2800 PSI AND QUANTITY WAS 38. REMOVED AND REPLACED RT PUMP PN 4018301, SN OE53AB. ALL PERFORMED IAW AMM 29-10-03. REMOVED L/LT MLG SIDE BRACE ACTUATOR PN 26300-000-04 S/N IL-020. CYCLED GEAR SEVERAL TIMES AND SYSTEM OPERATES AS NORMAL. IAW 32-10-20

Part: HYDRAULIC SYSTEM — LOW · airframe 4,369 hrs · 2,697 cycles

AT FL350 WE GOT THE RT HYD LEVEL LOW CAS MESSAGE. DID THE EMERGENCY GEAR EXTENSION PER CHECK LIST.

Part: UNKNOWN — UNKNOWN (ELEVATOR FEEL) · airframe 2,666 hrs · 1,611 cycles

ELEVATOR FEEL FAIL LIGHT CAME ON IN CLIMBOUT. REMAINED ON, THE ENTIRE FLIGHT. UPON A/C ARRIVAL VERIFIED DISCREPANCY AND NOTED THAT THE SPQC WAS NOT FULLY INSTALLED IN RACK, RERACKED SPQC AND MESSAGE EXTINGUISHED. PERFORMED A SPQC DOWNLOAD AND OPS CHECK WITH NO FURTHER DEFECTS NOTED. COPIED DOWNLOADED INFORMATION TO DISK. ALL WORK PERFORMED IAW WATCH SPQC TOOL KIT USERS GUIDE D9520200 REV B.

Part: FIRE LOOP — FAILED (LT ENGINE) · airframe 1,826 hrs · 1,152 cycles

DURING CLIMB THRU RECEIVED LT ENG FIRE DETECT MSG ON EICAS. RETURNED WITH NO PROBLEM. ACCESS EXTERNAL AND INTERNAL BYPASS DUCT ON LT ENGINE VISUALLY INSPECTED INTERNAL ZONE 2 FIRE DETECTOR ALSO EXTERNAL ZONE 1 FIRE DETECTOR. NO DEFECTS FOUND. REMOVED LOWER PYLON PANELS FOR ACCESS TO CONNECTOR TROUBLESHOT SYSTEM AND FOUND ZONE 2 OVERHEAT LOOP TO BE BAD. REPLACED ZONE 2 FIRE LOOP, OPS CHECKS GOOD. ALL WORK DONE IAW MM 21-10-10.

Part: ACTUATOR — INOPERATIVE (NR 3 FLAP) · airframe 1,405 hrs · 866 cycles

AFTER TAKEOFF FROM SUX, SLATS AND FLAPS WOULD NOT RETRACT. SLAT/FLAP MAINTEN ICAS MESSAGE CAME ON. TRIED TO RECYCLE SEVERAL TIMES BUT THE PROBLEM WOULD NOT CLEAR. REPLACED NR 3 RT FLAP (OUTBD) ACTUATOR. IAW A/C MM CHAPTER 27 AND CMP 275215 COMPLETED FLAP/SLAT CONTROL AND DRIVE SYSTEM - FUNCTIONAL TEST IAW CMP 275101 NO DEFECTS NOTED. FLAP CONTROL SURFACES CHECK WITH CLINOMETER ALL DEG WITHIN LIMITS, 12 DEGREES, 20 DEGREES, 40 DEGREES NO DEFECTS.

Part: CONNECTOR — SHORTED (VIDEO MONITOR) · airframe 1,029 hrs · 637 cycles

VIP SEAT VIDEO MONITOR PORT SHORTED OUT. SMOKE AND ACID SMELL WAS OBSERVED COMING FROM THE MONITOR PORT. - VERIFIED DISCREPANCY, FOUND VIP VIDEO MONITOR CONNECTOR TO BE BAD. DISABLED AND STOWED VIP VIDEO MONITOR CONNECTOR CANNON PLUG. ALL OTHER VIDEO MONITOR OPS CHECK GOOD. NO SMOKE OR ACID SMELL OBSERVED. OP CHECK GOOD IAW G200 COMPLETION MANUAL 23-50-00.

Part: PANEL — LEAKING (FUEL VENT) · airframe 772 hrs · 483 cycles

FUEL LEAKING OUT OF RT WING IN FRONT OF AILERON ON TOP. AIRCRAFT WAS INFLIGHT FOR 1.4 HRS AND LOST APPROX 1000 LBS OF FUEL OVER THE NORMAL BURN. INSPECTED RT WING FOUND SEEPAGE FROM RT BOTTOM WING VENT (NACA SCOOP). OPEN WING PANEL 640UT, REMOVED OLD SEALANT AROUND VENT SCOOP, CLEANED AREA PER G200 MM 28-10-00 PG 201 TASK 28-10-00-1410-801. SEALED AREA TASK 28-10-0-390-801 PARA G PG 206 WITH PR1440 B1/2 (MIL SPEC 8802). CLOSED PANEL 640NT. COMPLIED WITH LEAK CHECK OF PANEL AND SCOOP, LEAK CHECKED GOOD.

Part: CONTROLLER — MALFUNCTIONED (CABIN COOLING) · airframe 88 hrs · 61 cycles

DURING FLIGHT THE COCKPIT AUTO TEMP MESSAGE ILLUMINATED, AFTER SWITCHING COCKPIT TEMP CONTROLLER TO MANUAL, SYSTEM WAS NORMAL AS LONG AS THE TEMP CONTROL KNOB WAS FULL COLD. PLACED TEMP CONTROL KNOB TO WARM AND NOTICED FUMES OF HOT MELTING PLASTIC, FOLLOWED BY THE COCKPIT DUCT TEMP, HI MESSAGE. RETURNED COCKPIT TEMP CONTROL KNOB TO FULL COLD AND THE WARNING WENT OUT. ITEM IS UNDER INVESTIGATION.