N100WT

Part: PIN — DISENGAGED (RT MLG) · airframe 4,468 hrs · 3,797 cycles

THE CREW REPORTED THAT DURING TAXI AFTER LANDING THE ACFT EXPERIENCED POWER BRAKE FAILURE & THE LO BRK PRESS & ANTISKID INOPERATIVE ANNUNCIATORS ILLUMINATED. EMER NITROGEN BRAKE SYS WAS USED TO STOP ON PARKING RAMP. POST FLIGHT CHECKS FOUND HYD FLUID LEAKING FROM THE RT MLG WW AREA. MX VENDOR DISCOVERED THAT THE RT MLG AFT ATTACH TRUNNION PIN WAS NOT ENGAGED INTO MLG TRUNNION, CAUSING THE MLG TO SHIFT, DAMAGING THE BRAKE HYD LINES. THE MX VENDOR REPORTED THAT THE SAFETY BOLT FOR THE TRUNNION PIN WAS STILL SECURELY INSTALLED INTO THE MLG TRUNNION. INVESTIGATION FOUND THAT AN OUTSIDE MX VENDOR INADVERTENTLY IMPROPERLY INSTALLED THE TRUNNION PIN AFTER SHIMMING OF THE MLG PREVIOUSLY. INSPECTIONS & REPAIRS WERE COMPLETED & THE ACFT WAS RETURNED TO SERVICE.

Part: DISPLAY — FAULTY (COCKPIT) · airframe 4,396 hrs · 3,742 cycles

THE CREW REPORTED THAT DURING CRUISE THE STAND-BY FLIGHT DISPLAY IS INDICATING AN INCORRECT FLIGHT ATTITUDE, OVER 10 DEGREES OF ERROR. THE DEFECTIVE DISPLAY WAS REMOVED SN M002014 & AN OVERHAULED UNIT SN M002358 WAS INSTALLED.

Part: DISPLAY — FAULTY (COCKPIT) · airframe 4,393 hrs · 3,740 cycles

CREW REPORTED THAT THE NEWLY INSTALLED, OVERHAULED STAND-BY FLIGHT DISPLAY FLICKERS WHEN DIMMED. THE DEFECTIVE UNIT SN M001484 WAS REMOVED & AN OVERHAULED UNIT WAS INSTALLED SN M002014. FUNCTIONAL CHECKS SATISFACTORY.

Part: INDICATOR — FAILED (COCKPIT) · airframe 4,359 hrs · 3,713 cycles

STAND-BY ATTITUDE INDICATOR, FAILS AT THE END OF ITS INITIALIZATION. REMOVED SECONDARY FLIGHT DISPLAY SN M003002, INSTALLED EXCHANGE DISPLAY M003633. FUNCTIONAL CHECKED SATISFACTORY.

Part: DISPLAY — FAILED (COCKPIT) · airframe 4,361 hrs · 3,716 cycles

CREW REPORTED NEWLY INSTALLED, OVERHAULED STAND-BY FLIGHT DISPLAY, BECAME BLANK IN FLIGHT., AFTER SEVERAL MINUTES THE UNIT RESET THEN REINITIALIZED ITSELF. DISPLAY FUNCTION WAS NORMAL FOR THE REMAINDER OF THE FLIGHT. R & R UNIT WITH OVERHAULED UNIT REMOVED SN M003633, INSTALLED M001484.

Part: POSITION SWITCH — FAILED (THRUST REVERSER) · airframe 4,347 hrs · 3,702 cycles

FLIGHT CREW REPORTED THAT THE LT TR ANNUNCIATOR DID NOT ILLUMINATE WHEN THE LT TR WAS DEPLOYED ON LANDING. ANNUNCIATOR TEST CONFIRMED THE BULB WAS WORKING. TROUBLESHOOTING IDENTIFIED THE TR DEPLOY SWITCH TO BE DEFECTIVE. THE SWITCH WAS REPLACED WITH A NEW SWITCH & THE ACFT WAS RETURNED TO SERVICE.

Part: RELAY — DEFECTIVE (LIGHT SYSTEM) · airframe 4,320 hrs · 3,680 cycles

CREW REPORTED THAT THE RT SIDE TAIL FLOOD LIGHT WAS ILLUMINATED WHEN THE ACFT MASTER SWITCH WAS IN THE ON POSITION & THE TAIL FLOOD LIGHT SWITCH IN THE OFF POSITION. THE DEFECTIVE RELAY WAS REMOVED PN M83536 9-24 & A NEW RELAY WAS INSTALLED. FUNCTIONAL CHECKS WERE SATISFACTORY.

Part: INVERTER — FAILED (NR 1) · airframe 4,178 hrs · 3,544 cycles

CREW REPORTED NR 1 INVERTER FAILED AFTER ENGINE START DURING AVIONICS POWER UP. TROUBLESHOT & FOUND NR 1 INVERTER DEFECTIVE. INVERTER REMOVED AND REPLACED WITH A REPAIRED UNIT. OPS CHECKED SATISFACTORY.

Part: ANTI-ICE VALVE — FAILED (LEFT) · airframe 4,126 hrs · 3,496 cycles

CREW REPORTED A LEFT ANTI-ICE ANNUNCIATOR ILLUMINATED, TROUBLESHOT & IDENTIFIED LT ENGINE INLET VALVE DEFECTIVE. VALVE REMOVED AND AN O/H UNIT INSTALLED. OPS CHECKED SATISFACTORY.

Part: LINE — CHAFED (HYDRAULIC SYS) · airframe 4,031 hrs · 3,416 cycles

DURING ROUTINE MX, A HYD SEEP WAS DISCOVERED IN THE LT INBD FLAP AREA. TROUBLSHOOTING FOUND THE LT SPEED BRAKE RETRACT RIGID HYD LINE WAS BEING CHAFED BY THE MOVEMENT OF THE LT INBD FLAP PUSH/PULL ROD BONDING JUMPER. THE HYD LINE WAS REPLACED AND THE BONDING JUMPER ON THE FLAP PUSH/PULL ROD WAS REPOSITIONED TO CLEAR THE HYD LINE. REF: MM 27-60-00-710.

Part: FLOW DIVIDER — DEFECTIVE (NR 2 ENGINE) · airframe 3,844 hrs · 3,259 cycles

CREW REPORTED FUEL DRIPS FROM THE NR 2 ENGINE CASE DRAIN AT SHUTDOWN. TROUBLESHOOTING IDENTIFIED THE NR 2 ENGINE FLOW DIVIDER, PN 814900-6, SN F55971, AS DEFECTIVE. AN O/H FLOW DIVIDER WAS INSTALLED, LEAK/OPS CHECKS SATISFACTORY IAW MM 73-10-03.

Part: LINE — LEAKING (OXYGEN SYSTEM) · airframe 3,831 hrs · 3,246 cycles

THE CREW REPORTED THAT THE OXYGEN SYSTEM WAS LOOSING PRESSURE. MX LEAK CHECKED THE SYS AND FOUND THE CAPILLARY OXYGEN LINE IN THE NOSE SECTION OF ACFT WAS LEAKING. THE DEFECTIVE LINE WAS REMOVED AND A NEW LINE PN 9912057-11 WAS INSTALLED. THE OXYGEN WAS SERVICED TO FULL WITH ABO AND THE ACFT WAS RETURNED TO SERVICE.

Part: FLOW DIVIDER — LEAKING (FUEL SYSTEM) · airframe 3,806 hrs · 3,233 cycles

CREW REPORTED FUEL LEAKING FROM LT ENGINE DRAIN MAST AFTER SHUTDOWN. GAINED ACCESS AND REPLACED THE FLOW DIVIDER VALVE. FUNCTIONAL CHECKS SATISFACTORY. REF: MM 73-10-03.

Part: OXYGEN MASK — LEAKING (COCKPIT) · airframe 3,770 hrs · 3,199 cycles

THE CREW REPORTED THAT DURING THE POST FLIGHT CHECKS IT WAS NOTED THAT THE PILOTS QUICK DONNING OXYGEN MASK WAS LEAKING, REMOVED THE PILOTS MASK PN 9914067-41, SN 10647. INSTALLED AN O/H MASK. FUNCTIONAL CHECKS SATISFACTORY.

Part: OUTFLOW VALVE — DEFECTIVE (CABIN PRESSURE) · airframe 3,557 hrs · 3,031 cycles

THE CREW REPORTED THAT AFTER TAKEOFF THE CABIN ALTITUDE WOULD CLIMB UNTIL A ALTITUDE OF 4000 FT WAS REACHED AND THEN THE CABIN ALTITUDE WOULD STAY AT 4000 FT DURING CLIMB AND CRUISE. IT WAS NOTED THAT THE CABIN WOULD DESCEND NORMALLY TO THE SELECTED FIELD ELEVATION. TROUBLESHOT AND FOUND THAT THE PRIMARY OUTFLOW VALVE DEFECTIVE. R & R THE OUTFLOW VALVE PN 9912409-7, SN 548 INSTALLED A MODIFIED PRIMARY OUTFLOW VALVE. FUNCTIONAL CHECKS SATISFACTORY.

Part: FCU — FAULTY (RT ENGINE) · airframe 3,272 hrs · 2,827 cycles

DURING DECENT AT 12,000 FT, WHILE SOUTH OF WAYPOINT ON THE DUMPY ARRIVAL. THE RT ENGINE QUIT DUE TO A FAULTY FUEL CONTROL UNIT. THE CREW RAN THE CHECKLIST AND PROCEEDED VISUALLY FOR AN UNEVENTFUL FLAPS 15 LANDING.

Part: WIRE — BACKED OUT (BRAKE SYSTEM) · airframe 2,154 hrs · 1,899 cycles

DURING FLIGHT, APPROACHING KSUS (SPIRIT OF ST LOUIS AIRPORT, MO), THE CREW OBSERVED THAT THE BRAKE PRESSURE LOW AND ANTI-SKID INOP, ANNUNCIATOR LIGHTS WERE ILLUMINATED. CHECKLIST PROCEDURES WERE FOLLOWED AND ATC WAS ADVISED. ATC HAD EMERGENCY EQUIPMENT RESPOND. A NORMAL APPROACH AND LANDING WERE MADE. NORMAL BRAKING WAS AVAILABLE AFTER LANDING. THE AIRCRAFT WAS TAXIED TO PARKING AND SHUTDOWN. SYSTEM INVOLVED: TROUBLESHOOTING DETECTED A WIRING PROBLEM IN THE ANNUNCIATING SYSTEM. APPARENT CAUSE OF MALFUNCTION: PIN FF IN AMP CONNECTOR J131 WAS NOT CRIMPED. NOTE: IT APPEARS THE PIN WAS NOT CRIMPED WHEN IT LEFT THE FACTORY. OTHER PERTINENT INFORMATION. THE TERMINAL PIN IN AMP CONNECTOR J131 WAS REPLACED AND THE WIRE BUNDLE WRAPPED WITH FIBERGLASS SHEET. THE SYSTEM WAS FUNCTION CHECKED AND FOUND TO BE OPERATING NORMALLY. WORK WAS PERFORMED IAW CHAPTERS 20 AND 32 OF CESSNA 550 WIRING DIAGRAM MANUAL. AIRCRAFT RETURNED TO SERVICE MARCH 19, 2008.

Part: TRANSFORMER — CHAFED (LT PYLON)

WITH RT ENGINE RUNNING AND RT GEN ON-LINE, GEN ASSIST START WAS OPERATIONAL. IF LT ENG WAS RUNNING AND LT GEN ON-LINE, ATTEMPTING A RT START WOULD CAUSE LT GEN TO DROP OFF-LINE AND RT ENG WOULD NOT ROTATE. T/S TO A CT3 (LT GROUND FAULT XFORMER) WHICH HAD CHAFED AGAINST LT ENG COWLING ATTACH BRACKET AND HAD BEEN RENDERED USELESS. REPLACED LT PYLON CT3 GROUND FAULT XFORMER WITH NEW PART, SAME P/N, AND SYS WORKED PROPERLY. INSPECTED RT GROUND FAULT XFORMER, FOUND SIGNIFICANT CHAFING AGAINST THE RT COWLING ATTACH BRACKET. REPLACED RT PYLON GROUND FAULT XFORMER WITH NEW PART, SAME P/N, OBSERVED OTHER CHAFING OCCURRING ON BOTH COWLING ATTACH BRACKETS.