N376QS

Part: SUPPORT BRACKET — CORRODED (ZONE 300) · airframe 15,385 hrs · 10,260 cycles

REMOVED THE CORRODED UPPER RUDDER SUPPORT UPPER BRACKET, RECEIVED FABRICATED NEW BRACKET PART NUMBER AQRD-6931050-64 AND INSTALLED PER TEXTRON 680 SRM 51-40-03 AND AEROSPACE QUALITY RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER AND NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED · airframe 15,385 hrs · 10,263 cycles

BLENDED CORRODED AREA LOCATED ON THE UPPER INBOARD WING SKINS ALONG THE DRAG ANGLES (WING-TO-FUSELAGE FAIRING STRUCTURE) REMOVED THE MIDDLE AND AFT DRAG ANGLES FOR ACCESS AND BLENDED ADDITIONAL AREAS. PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED BLENDED AREA BY FABRICATING AND INSTALLING REPAIR DOUBLERS AND SHIM IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER.

Part: HINGE — CORRODED (ZONE 500 AILERON) · airframe 15,385 hrs · 10,260 cycles

BLENDED AREA OF CORROSION LOCATED ON LH AILERON, INBOARD HINGE, INBOARD SIDE WHERE BOND JUMPER ATTACHES, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREA PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED (ZONE 600) · airframe 15,385 hrs · 10,260 cycles

BLENDED MULTIPLE CORRODED AREAS OF THE RH WING UPPER INBOARD SKINS LOCATED ALONG THE AFT DRAG ANGLE (WING-TO-FUSELAGE FAIRING STRUCTURE), PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED BLENDED AREAS BY TREATING, PRIMING AND TOP COATING AREAS PER TEXTRON STANDARD REPAIR.

Part: SKIN — DAMAGED · airframe 15,385 hrs · 10,260 cycles

MECHANICALLY REMOVED CORROSION ALONG LH AND RH WING LOWER TRAILING EDGE SKIN NEAR THE AFT DRAG ANGLE OUTBOARD EDGES, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED CORROSION BLEND BY CLEANING, TREATING AND PRIMING PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED (ZONE 300) · airframe 15,385 hrs · 10,263 cycles

BLENDED CORRODED AREA LOCATED SKIN OF THE VERTICAL STABILIZER AT THE TRAILING EDGE UPPER END, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED BLENDED AREA BY FABRICATING AND INSTALLING REPAIR DOUBLER IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER.

Part: STRUCTURE — CORRODED (LT MLG WW) · airframe 15,385 hrs · 10,263 cycles

BLENDED CORRODED AREA LOCATED IN THE LH MAIN LAND GEAR WHEEL WELL LOCATED UNDER THE EMERGENCY BRAKE FEED THRU FITTING AT WS37, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED BLENDED AREA BY FABRICATING AND INSTALLING REPAIR DOUBLER IN ACCORDANCE WITH AEROSPACE QUALITY RESEARCH AND DEVELOPMENT MRO ENGINEERING REPAIR ORDER. BLENDED CORRODED AREA LOCATED RH MAIN LAND GEAR WHEEL WELL LOCATED UNDER THE EMERGENCY BRAKE FEED THRU FITTING AT WS37, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED TREATED AND PRIMED AREA PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — DAMAGED (ZONE 800) · airframe 15,385 hrs · 10,263 cycles

BLENDED 5 AREAS OF CORROSION LOCATED ON THE OUTER SKIN OF THE EMERGENCY EXIT DOOR, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED TREATED AND PRIMED BLENDED AREA PER TEXTRON STANDARD REPAIR.

Part: SHUTOFF VALVE — MALFUNCTIONED (LT ENGINE) · airframe 15,346 hrs · 10,235 cycles

LEFT ENGINE ITT EXCEEDANCE. WHILE IN CLIMB ABOUT 38,000 FEET WITH THRUST SET AT MCT, THE LEFT ENGINE ITT WENT INTO THE YELLOW BAND. AFTER 20 SECONDS THE YELLOW BAND TURNED RED AND THEN WE PULLED THE POWER BACK TO REDUCE THE ITT. HIGHEST ITT OBSERVED WAS 930, AND I PUSHED THE EVENT MARKER BUTTON. CORRECTIVE ACTION; REMOVED LH/RH HP PRSOV AND INSTALLED IN TRANSPOSED POSITION. REPLACED ALL DISTURBED BLEED SEALS IN LH/RH ENGINE BLEED DUCTS. ALL WORK PERFORMED IAW CE680 AMM 36-10-00. PERFORMED LH/RH ENGINE RUNS TO TAKEOFF POWER IN DIFFERENT BLEED CONFIGURATIONS. ENGINE PERFORMANCE IS SATISFACTORY. LEAK CHECKS OF LH/RH BLEED DUCTS GOOD.

Part: ENGINE — OVERTEMP (LEFT) · airframe 15,346 hrs · 10,235 cycles

LEFT ENGINE ITT EXCEEDANCE. WHILE IN CLIMB ABOUT 38,000 FEET WITH THRUST SET AT MCT, THE LEFT ENGINE ITT WENT INTO THE YELLOW BAND. AFTER 20 SECONDS THE YELLOW BAND TURNED RED AND THEN WE PULLED THE POWER BACK TO REDUCE THE ITT. HIGHEST ITT OBSERVED WAS 930, AND I PUSHED THE EVENT MARKER BUTTON.

Part: FUSE — INOPERATIVE (ZOEN 200) · airframe 15,205 hrs · 10,136 cycles

EMERGENCY LIGHTING: ALL EMERGENCY LIGHTS INOP WITH SWITCH IN ARM, WORKS MORMALLY WITH SWITCH ON CORRECTIVE ACTION: REPLACED FUSE IN #1 EMERGENCY BATTERY PACK. OPS CHECK GOOD. IAW CE-680 AMM 33-50-00.

Part: FUSE — DEFECTIVE (ZONE 200) · airframe 15,160 hrs · 10,113 cycles

MAIN EXIT SIGN/LIGHT: THE MAIN CABIN DOOR EMERGENCY EXIT SIGN IS INOP ALONG WITH THE EXIT SIGNS ON EACH SIDE OF THE DOOR WITH BATTERIES OFF AND EMERGENCY LIGHT SWITCH ON. THEY ARE ALSO INOP WITH THE APU RUNNING, EMERGENCY LIGHT SWITCH SET TO ARM AND PAX SAFETY SWITH ON. REPLACED #1 EMERGENCY LIGHTING BATTERY FUSE AND PERFORMED OPS CHECKS WITH NO DEFECTS NOTED. SWAPPED #1 BATTERY PACK WITH #3 BATTERY PACK IAW AMM 33-50-10

Part: FUSE — BLOWN (ZONE 200) · airframe 15,160 hrs · 10,113 cycles

SAW RT WING INSPECTION LIGHT GO OFF. IT SHOULD BE ON WITH THE EMERGENCY LIGHTS ARMED & PAX SAFETY SWITCH ON. ON INVESTIGATION, MAIN CABIN ENTRY DOOR EMERGENCY LIGHT WAS OFF ALONG WITH LAV BULKHEAD EMERGENCY LIGHT, WITH THE APU RUNNING, EMERGENCY LIGHTS ARMED & PAX SAFETY SWITCH ON. SHUT DOWN ACFT, BATTERIES OFF. WITH THE EMERGENCY LIGHT SWITCH ON, EXTERIOR LIGHTS WORKED NORMAL AND LAV BULKHEAD EMERGENCY LIGHT WAS ON. ONLY LIGHT OUT WAS CABIN ENTRY EMERGENCY LIGHT. STARTED APU & AGAIN FAILED. REMOVED FUSE AND REPLACED WITH A NEW FUSE. PERFORMED A SATISFACTORY OPS CHECK. WORK PERFORMED IAW AMM 33-50-10

Part: BATTERY PACK — DEFECTIVE (ZONE 200) · airframe 15,135 hrs · 10,096 cycles

EMERGENCY SWITCH ON POSITION NO EMERG EXIT SIGN/ LIGHT. REMOVED AND REPLACED EMER BATTERY, P.ERFORMED CONTINUITY CHECKS ALONG WITH CHARGING OF THE EMER BATTERY FOR TWO HOURS. OPERATIONAL CHECKS GOOD, RETURNED AIRCRAFT TO ORIGINAL CONFIGURATION. NO FURTHER MAINTENANCE REQUIRED AT THIS TIME, ALL WORK DONE IAW CE-680 MM 33-50-10.

Part: BATTERY — DEFECTIVE (ZONE 200) · airframe 15,133 hrs · 10,095 cycles

EMERGENCY LIGHTS NOT TURNING ON WHEN PAX SAFTEY BUTTON IS SELECTED ON. EMERGENCY LIGHTS DO TURN ON WHEN EMER LTS SWITCH IS SELECTED TO ON ARRIVED AT AC AND TURNED ON ERNER LIGHTS AND FOUND THAT THE ONLY EMER LIGHTS THAT DID NOT ILLUMINATE WERE THE FWD MOST LIGHTS, ERNER SIGN JUST INSIDE MED, FIRST READING LIGHT. ALL OTHER EMER LIGHTS WORKED AS THEY SHOULD, T/S AND FOUND THAT THE # I EM.ER LIGHT BATT IS DEFECTIVE. REMOVED DEFECTIVE # L EMERGENCY BATT AND INSTALL~ A REPAIRED WITH IA W CE-680 MM CH 33-50-L 0 / OP'S CK GOOD.

Part: SKIN — CORRODED (ZONE 600) · airframe 15,075 hrs · 10,058 cycles

LOWER WING SKIN CORROSION REF (ENGINEERING REPAIR ORDER ERO-979789)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 14,723 hrs · 9,830 cycles

MAIN DOOR: MAIN CABIN DOOR IS VERY DIFFICULT TO PULL CLOSED FROM INSIDE. IT ALSO SWINGS DOWN AGGRESSIVELY WHEN OPENING. REMOVED MED STEPS, INSPECTED ALL MED LINKAGES. NO DEFECTS NOTED. INSPECTED MED CABLES, FOUND CABLES TO BE SERVICEABLE AND CABLES AT PROPER TENSIONS. REINSTALLED MED STEPS. ALL OPERATIONAL CHECKS GOOD. IAW: CE-680 MM 52-10-00.

Part: RUDDER — DAMAGED (ZONE 300) · airframe 14,404 hrs · 9,599 cycles

TOP OF THE RUDDER IN THE RUDDER CAP HAS SMALL BURN HOLE FROM POSSIBLE LIGHTING STRIKE.

Part: WING — CORRODED (ZONE 700) · airframe 13,983 hrs · 9,286 cycles

EXFOLIATION FOUND IN FOUR LOCATIONS ALONG THE REAR AFT SPAR OF THE LH & RH MLG. REQUIRES HI-LOK REMOVAL, CORROSION REMOVAL AND MAPPING

Part: SPAR — CORRODED (UNKNOWN) · airframe 13,983 hrs · 9,286 cycles

FOUND DURING MM TASK 57-00-00-2200: EXFOLIATION FOUND IN FOUR LOCATIONS ALONG THE REAR AFT SPAR OF THE LH & RH MLG.

Part: DOWNLOCK SWITCH — FAILED (RT MLG) · airframe 13,963 hrs · 9,267 cycles

MAIN RIGHT GEAR WOULD NOT RETRACT. AFTER GEAR RETRACTION NOSE AND LEFT MAIN RETRACTED. RIGHT MAIN REMAINED DOWN AND LOCKED (GREEN). ALSO CONFIRMED BY TOWER ON DEPARTURE NOSE AND LEFT RETRACKED, RIGHT MAIN DOWN. NO RED UNLOCK LIGHT. PER QRH LOWERED GEAR , 3 GREEN NO RED. LANDED UNEVENTFULLY. PERFORMED REMOVAL AND INSTALLATION OF RH MAIN LANDING GEAR DOWN LOCK SWITCH. WORK DONE IAW AMM CH 32-60-00. PERFORMED MAIN LANDING GEAR SWINGS AND OPERATIONAL TEST IAW AMM CH 32-60-0ALL OPS CHECK GOOD.

Part: LIGHT — INOPERATIVE · airframe 13,939 hrs · 9,247 cycles

CABIN EMERG LIGHT: REPEAT WRITE UP (6TH THIS MONTH). CABIN EMERGENCY LIGHTS INOP IN ARM POSITION (NOTICED DURING PREFLIGHT). MOST LIGHTS COME ON WITH SWITCH IN 'ON' POSITION. WITH EMER LIGHT SWITCH IN 'ARM' POSITION AND THEN SELECTING PAX SAFETY SWITCH TO ON, THE EMERGENCY LIGHTS FAIL TO ILLUMINATE. EXIT LIGHT ABOVE THE MAIN ENTRY DOOR NEVER ILLUMINATES NO MATTER WHAT SWITCH POSITION IS SELECTED. SAME FOR THE TABLE EMER LIGHT ACROSS FROM MAIN DOOR.//SIGNOFF// INSPECTED OVERHEAD EMER LIGHT HARNESS AND FOUND DAMAGED WIRE FROM J1O1SV GOING TO THE OVERHEAD EMER LIGHT. ACCESSED ALL EMER LIGHTS AND INSPECTED WIRING. DURING INSPECTION FOUND OVERHEAD EMER LIGHT WIRE HARNESS DAMAGED. REPAIRED DAMAGED WIRE AND PERFORMED SATISFACTORY OPS CHECK OF THE EMER LIGHTS. REF CE-600 WDM 33-50-01 AND MM 33-50-00

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 13,935 hrs · 9,243 cycles

EMERGENCY LIGHTING: WHILE EXECUTING THE POWER ON CHECKLIST, WE DISCOVERED THE EMER LIGHTS WILL NOT ILLUMINATE IN THE ARM POSITION, BUT SOME WILL ILLUMINATE IN THE ON POSITION. REMOVED AND REPLACED ALL 4 EMERGENCY BATTIERES IAW MM 33-50-10.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 13,914 hrs · 9,230 cycles

EMERGENCY LIGHTING: WHILE CONDUCTING THE POWER ON CHECKLIST WE DISCOVERED WHEN THE EMER LTS ARE PLACED IN THE ARM POSITION, THE LIGHTS DO NOT ILLUMINATE. WHEN THE SWITCH IS PLACED IN THE ON POSITION, THE LIGHTS WORK. // SIGNOFF // TROUBLESHOT AND DETERMINED FAULT TO BE CAUSED BY A FAILED #1 EMERGENCY LIGHT BATTERY PACK. REMOVED P/N CBS28·1 S/N·598SM AND INSTALLED REPAIRED P/N·CBS28·1 S/N-007288 IAW CESSNA 680AMM 35-50-10. OPS CHECKS OK

Part: FUSE — BLOWN · airframe 13,903 hrs · 9,223 cycles

CABIN EMERG LIGHT: DURING POWER ON CHECKS WITH EMERGENCY LIGHTS SWITCH TO ARM, NONE OF THE EMERGENCY LIGHTS ILLUMINATE. WITH THE SWITCH TO ON, ALL ILLUMINATE EXCEPT THE WORK TABLE LIGHT, THE EXIT SIGN OVER MAIN CABIN DOOR AND THE 2 RED EXIT SIGNS ON EITHER SIDE OF CABIN DOOR. ALSO, ON APU POWER THE PAX SAFETY SWITCH SHOULD ILLUMINATE ALL EMER LIGHTS AND IT DOESN'T. THIS IS A REPEAT WRITE-UP. "CORRECTIVE ACTION" FOUND #1 BATTERY PACK FUSE BLOWN. CHECKED GROUND STUDS ON #1 BATTERY PACK, NO DEFECTS. CHECKED SPLICE CONNECTIONS AND PIN SECURITY ON CONNECTOR, NO DEFECTS, ON LH CIRCUIT BREAKER, WE TESTED DIOD DC021, DC022, AND DC023, NO DEFECTS, CHECKED CONTINUITY OF ON/ARM SWITCH THROUGH PINS C & S OF PC045, NO DEFECTS. REMOVED RELAY KC006 AND TRANSSORB DC029 AND REPLACED WITH NEW COMPONENTS. INSTALLED NEW FUSE IN BATTERY PACK #1. REINSTALLED LH CIRCUIT BREAKER PANEL. COMPLIED WITH OPERATIONAL CHECK OF THE EMERGENCY LIGHTING WITH NO DEFECTS. WORK PERFORMED IAW CE-680 AMM 30-30-00, 33-50-00. NO FURTHER DEFECTS NOTED.

Part: FUSE — BLOWN (EMERGENCY LIGHTS) · airframe 13,896 hrs · 9,219 cycles

DURING THE POWER ON CHECKLIST, WITH THE EMERGENCY LIGHTS SWITCH ARMED AND THE BATTERY SWITCHES OFF, NONE OF THE EMERGENCY LIGHTS ILLUMINATE. WITH THE EMERGENCY LIGHTS SWITCH IN THE ON POSITION AND THE THE BATTERY SWITCHES STILL OFF, ALL OF THE EMERGENCY LIGHTS EXCEPT THE EXIT LIGHT ABOVE THE ENTRY DOOR ILLUMINATE. CHECKED BATTERY PACK, FOUND FUSE BURNED OUT. REMOVED AND REPLACED THE FUSE. RESET INERTIAL SWITCH, OPS CHECK FAILED. ACCESSED NR 2, 3, AND 4 INTERIAL SWITCHES & RESET. OPS CHECKED GOOD. NO DEFECTS. WORK PERFORMED IAW AMM 33-50-10, AND WDM 33-50-01.

Part: CIRCUIT BREAKER — TRIPPED (EMERGENCY LIGHTS) · airframe 13,886 hrs · 9,192 cycles

EMERGENCY LIGHTING: WHEN THE EMER LIGHTS ARE TESTED (EMER SWITCH IN ON POSITION, PASS SAFETY SWITCH OFF) ALL EMER LIGHTS WORK CORRECTLY, INTERIOR AND EXTERIOR. WHEN THE EMER LIGHT SWITCH IS IN THE ARM POSITION AND THE PASS SAFETY SWITCH IS ON, ALL THE INTERIOR AND EXTERIOR LIGHTS SHOULD ILLUMINATE, BUT NONE OF THEM ILLUMINATE. FOUND CB (HT035) BREAKER HAD POPPED IN EMER POWER J·BOX, RESET BREAKER AND OPS CHECKS NORMAL.CHARGED EMER BATTERIES FOR A WHLE, REINSTALLED ALL PREVIOUSLY REMOVED ACCESS PANELS AND CABIN CARPET TRIM, IAW AMM 33-50-10,

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 13,814 hrs · 9,163 cycles

MAIN EXIT SIGN/LIGHT: EMERGENCY EXIT LIGHT ABOVE MCD WILL NOT ILLUMINATE. REMOVED FAULTY #1 EMERGENCY BATTERY AND INSTALLED A REPAIRED BATTERY AND COMPLETED OPS CHECKS WITH NO DEFECTS NOTED IAW AMM 33-50-10 AND 33-50-00.

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 13,773 hrs · 9,136 cycles

WITH EMER LTS SWITCH IN "ARM" POSITION AND PAX SAFETY SWITCH ON (BATTS ON), NONE OF THE 17 LIGHTS WILL ILLUMINATE. WITH THE EMER LTS SWITCH IN THE "ON" POSITION, REGARDLESS OF BATTS OR PAX SAFETY SWITCH, ALL LIGHTS ILLUMINATE EXCEPT FOR THE THREE INTERIOR MAIN CABIN DOOR EXIT SIGNS. TROUBLESHOOTING EMERGENCY LIGHTS. REMOVED EMERGENCY LIGHT SWITCH PANEL. OHMEO OUT EMERGENCY LIGHT SWITCH AND FOUND BROKEN WIRE TO SWITCH CONTACT 1C. RESOLDERED WIRE TO SWITCH IAW CE-680WDM 33-50-01. SWITCH OHMS OUT NORMALLY. REINSTALLED SWITCH PANEL, EMERGENCY LIGHT ISSUE STILL REMAINS. REMOVED #1 BATTERY PACK AND INSTALLED CUSTOMER SUPPLIED REPAIRED UNIT. C/W OPS CHECKS OF EMERGENCY LIGHT SYSTEM. CLOSED ALL PREVIOUSLY OPENED ACCESS. ALL CHECKS GOOD. REF CE-680 AMM 33-50-00. ORIG SUB DATE: 10/27/2022

Part: NONE — NONE · airframe 13,683 hrs · 9,070 cycles

MAIN DOOR: MAIN DOOR FREE FALLS OPEN WHEN UNLATCHED. BOTH DAMPENERS ON DOOR ARE WEAK AND MAY REQUIRE REPLACEMENT. //SIGNOFF// OPERATED DOOR MULTIPLE TIMES AND NOTED NO FREEFALL, SUBMITTED VIDEO TO MCC. DOOR REQUIRED ASSISTANT TO COME DOWN INTO THE LOCKED POSITION AS PER NORMAL OPERATION IAW CESSNA680 AMM TASK 52-10-30.

Part: NONE — NONE · airframe 13,680 hrs · 9,068 cycles

EMERG EXIT SIGN/LIGHT: WHEN THE EMERGENCY LIGHTS TOGGLE IS SWITCHED TO ON, ABOUT HALF OF THE EXIT LIGHTS ILLUMINATE. WHEN THE TOGGLE IS IN THE ARMED POSITION AND THE PAX SAFETY SWITCH IS ACTIVATED THE CHIME SOUNDS BUT NONE OF THE EMERGENCY EXIT SIGNS ILLUMINATE.

Part: NONE — NONE · airframe 13,663 hrs · 9,056 cycles

CABIN EMERG LIGHT: CABIN EMERGENCY LIGHTS INOP. REPEAT WRITE-UP. NO MAIN DC, EMER LIGHTS ON/ARM FORWARD DOOR EXIT, OVER GALLEY AND DOOR LIGHTS INOP. MAIN DC ON, EMER LIGHTS ON OR ARM AND PAX SAFETY ON ALL CABIN EXIT/EMER LIGHTS INOP. CHIME AND NO SMOKING LIGHTS DO COME ON THOUGH.

Part: NONE — NONE · airframe 13,662 hrs · 9,055 cycles

EMERGENCY LIGHTING: CANIN EMERGENCY LIGHTS INOP. NO MAIN DC, EMER LIGHTS ON/ARM FORWARD DOOR EXIT, OVER GALLEY, AND DOOR LIGHTS INOP. MAIN DC ON, EMER LIGHTS ARM, PAX SAFETY ON, ALL CABIN EXIT/EMER LIGHTS INOP. CHIME AND NO SMOKING LIGHTS DO COME ON THOUGH.//CORRECTIVE ACTION//REMOVED FUSE AND FOUND BLOWN. INSTALLED NEW FUSE AND COMPLIED WITH OPS CHECK WITH NO DEFECTS NOTED. REF CE-680 AMM 33-50-10

Part: NONE — NONE · airframe 12,954 hrs · 8,585 cycles

PRIMARY STAB TRIM FAIL AMBER CAS: WE INTIALLY INCURRED A AMBER PRIMARY STAB TRIM FAIL MESSAGE FOLLOWED BY A AMBER SECONDARY STAB TRIM FAIL CAS MESSAGE. BEFORE THE MESSAGE WE COULD TRIM UP BUT NOT DOWN BELOW 1.5 ON THE STAB TRIM INDICATOR. // SIGNOFF // ONCE ARRIVED TO THE A/C FOUND THE PRIMARY STAB TRIM CB PULLED. WETHEN PUSHED THE CB IN AND PERFORMED OPERATIONAL CHECKS ON THE PRIMARY TRIM AND FOUND THE OPERATIONAL CHECK TO BE SATISFACTORY. ALSO PERFORMED OPERATIONAL CHECK OF THE SECONDARY TRIM SYSTEM AND OPERATION~L CHECK WAS GOOD PER CE680 AMM 27-40-00. THE MACH TRIM ACUATOR WAS INSTALLED BEFORE THE FUGHT AND PER THE AMM THE PRIMARY STAB TRIM CB DOES-NOT NEED TO BE PULLED. SPOKE TO TECH WHO PERFORMED THIS MX AND HE STATED HE DID NOT PULL THAT BREAKER. WE THEN REACHED BACK OUT TO MCC AND ASKED FOR FURTHER INVESTIGATION TO SEE IF THE CREW HAD PULLED IT AFTER LANDING. FINDINGS WERE THE CREW DID PULL THE BREAKER. PER MCC THEY WANT TO FURTHER INVESTIGATE THIS SITUATION AND REACH OUT TO TEAM 680 TO SEE IF THEY HAVE ANY RECOMENDATIONS. WE ALSO GAINED ACCESS TO THE MACH TRIM ACTUATOR TO CONFIRM PROPER INSTALLATION IN WHICH WE CONFIRMED THAT THE ACTUATOR IS PROPERLY INSTALLED PER CE-680 AMM 27-40-00. THEN AFTER SPEAKING WITH TECH SUPPORT AND EXPLAINING THE SITUATION AND SENDING PICTURES OF THE INTEROGATION THAT WAS PERFORMED THROUGH THE CMC. TECH SUPPORT THEN ADVISED TO GET THE TEAM 680 TOGETHER IN THE MORNING AND DELVLOPE A PLAN FOR THIS NC. TALKED TO TEAM 680 TECH SUPPORT TROY AND AFTER EVAILUATING THE DISCREPACY HE WAS CONCERNED WITH THE 1.5 INDICATION. PERFORMED OPS CHECK AGAIN AND CONFIRMED THE ANGLE INDICATION WAS WAS WITHIN AMM SPECS (1.2 NOSE DOWN, -6.9 NOSE UP FOR THE PRIMARY TRIM. SECONDARY TRIM WAS FROM 1.5 TO -7.3 WHICH IS NORMAL TALKED TO MCC DAVE AND ERIC HOLCOMB AND THEY WANTED THE TORQUE CHECK DONE ON THE ACTUATOR, CHECK PLUGS ON ACTUATOR AND CHECK PCB'S IN NOSE. NO DEFECTS WERE NOTED. TALKED THE ERIC AGAIN AND HE SUGGESTED TO RELEASE AIRCRAFT AND MAYBE DO

Part: MODULE — DEFECTIVE (TE FLAP) · airframe 11,602 hrs · 7,670 cycles

FLAP POSITION INDICATION - AFTER DEPARTURE THE FLAPS WERE RAISED AT 400'. AT THAT POINT THE FLAP RESET AMBER LIGHT CAME ON. USING THE QRC. IT WOULDN'T RESET. A FLAP-LESS LANDING WAS MADE AT DENVER ///SIGN-OFF///REMOVED FAULTY SOFT START MODULE, PIN 6238405-30, S/N 0324. REMOVED START MODULE, P/N 6238405-34, S/N 0849 IN NEW CONDITION AND INSTALLED. REMOVED AND LNSTALLED NOW FLAP RELAY BOX CAPACITOR, PIN S2047-3. NO S/N. FLAP SYSTEM OPS CHECK GOOD. ALL WORK PERFORMED IAW CE 680 MM 27-51-00 AND CE 680 WM 27-50-01

Part: SPAR — CORRODED (VERTICAL STAB) · airframe 11,565 hrs · 7,643 cycles

MECHANICALLY BLENDED CORRODED AREA FROM THE VERTICAL STABILIZER LH SPAR CLIP, APPROXIMATELY FOUR INCHES BELOW THE MIDDLE RUDDER HINGE, PERFORMED EDDY CURRENT CRACK AND ULTRASONIC THICKNESS INSPECTIONS AND REPORTED TO TEXTRON FOR REPAIR DISPOSITION. CLEANED, TREATED, AND TOP COATED REPAIR AREA PER TEXTRON REPAIR MEMO.

Part: DOUBLER — CHAFED (FUSELAGE) · airframe 11,188 hrs · 7,386 cycles

REPAIRED CHAFE HOLE IN THE INNER DOUBLER OF THE E-EXIT SURROUND NEAR FS 409.26 BY BLENDING, PERFORMING NDT, FABRICATING AND INSTALLING REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING REPAIR ORDER.

Part: DOUBLER — CHAFED (FUSELAGE) · airframe 11,188 hrs · 7,386 cycles

REPAIRED CHAFE HOLE IN THE INNER DOUBLER OF THE E-EXIT SURROUND NEAR FS 409.26 BY BLENDING, PERFORMING NDT, FABRICATING AND INSTALLING REPAIR DOUBLER IN ACCORDANCE WITH ENGINEERING REPAIR ORDER.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 11,188 hrs · 7,386 cycles

REPAIRED CORRODED AREAS OF THE CENTER DROPPED AISLE FLOOR FROM FS 164 TO FS 202 BETWEEN STRINGERS 16L AND 16R BY BLENDING CORRODED AREAS, PERFORMING NDT, TREATING , PRIMING, AND INSTALLING REINFORCEMENT AS REQUIRED IN ACCORDANCE WITH FIELD REPAIR.

Part: RIB — CRACKED (RUDDER) · airframe 11,188 hrs · 7,386 cycles

REPAIRED RUDDER BY REPLACING CRACKED LOWER AFT RIB AND CLIP WITH NEW RIB P/N 6933160-3 AND CLIP P/N 6933160-2 PER SRM 51-40-03, 51-40-06, 51-40-09, AND CSPM 20-40-20.

Part: DRAG ANGLE — NOT REPORTED (LT WING) · airframe 11,188 hrs · 7,386 cycles

R&R THE LT FORWARD, MIDDLE, AND AFT WING/FUSELAGE DRAG ANGLES AND BLENDED CORRODED AREAS OF THE LT UPPER WING SKIN, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. TREATED AND PRIMED ALL REPAIR AREAS PER FIELD REPAIR.

Part: CONTROL VALVE — UNSERVICEABLE (ZONE 100) · airframe 10,821 hrs · 7,110 cycles

CAN NOT CONTROL COCKPIT TEMP IN MANUAL OR AUTOMATIC MODE. COULD NOT SELECT A CABIN TEMP COOLER THAN 85 DEGREES. AT ONE POINT IT GOT SO HOT SMOKE WAS COMING OUT OF THE COCKPIT AREA. SUPPLY TEMP WAS STEADY AT 210 DEGREES. //SIGNOFF// REMOVED AND REPLACED TEMP CONTROL VALVE AND CLEANED COCKPIT O-ZONE TEMP PROBE IAW AMM REF 21-60-00 OPS CHECK GOOD.

Part: SKIN — CORRODED (TAILCONE) · airframe 10,401 hrs · 6,842 cycles

FOUND CORRODED AREA ON THE BELLY SKIN OF THE TAILCONE, JUST FORWARD OF THE AIRCRAFT MANUFACTURE'S DATA TAG. REMOVED THE AFT TAILCONE/MAINTENANCE DOOR FAIRING FOR ACCESS. REPAIRED LT & RT LOWER TAILCONE SKIN CORROSION BY BLENDING, TREATING, AND INSTALLING REINFORCING DOUBLER REFERENCING AQRD ENGINEERING REPAIR ORDER APPROVED BY FAA FORM 8110-3.

Part: DOOR — CORRODED (EMEGENCY EXIT) · airframe 9,980 hrs · 6,526 cycles

MECHANICALLY BLENDED CORRODED AREA ON THE LOWER SIDE OF THE EMERGENCY EXIT DOOR. REMOVED CONTOUR RINGS AND FOUND ADDITIONAL CORROSION. BLENDED AREA FOUND UNDER CONTOUR RINGS AND FOUND ONE AREA CORRODED THROUGH. REPLACED THE EMERGENCY EXIT DOOR WITH A NEW ONE.

Part: BELLMOUTH — CORRODED (APU) · airframe 9,980 hrs · 6,526 cycles

BLENDED CORRODED APU EXHAUST DUCT BELL MOUTH, PERFORMED ULTRASONIC THICKNESS AND EDDY CURRENT CRACK INSPECTION AND REPORTED TO TEXTRON FOR DISPOSITION. REINSTALLED DUCT PER TEXTRON MEMO.

Part: DEFLECTOR — CORRODED (APU) · airframe 9,980 hrs · 6,526 cycles

BLENDED CORRODED APU COOLING DUCT INLET DEFLECTOR, PERFORMED ULTRA SONIC THICKNESS AND EDDY CURRENT CRACK INSPECTION AND REPORTED TO TEXTRON FOR DISPOSITION. TREATED, PRIMED AND PAINTED AND REINSTALLED PART PER TEXTRON MEMO.

Part: SKIN — CORRODED (ZONE 200) · airframe 9,289 hrs · 6,078 cycles

UPPER TAILCONE SKIN CORRODED. REPAIRED.

Part: UNKNOWN — ODOR (CABIN) · airframe 8,806 hrs · 5,789 cycles

ENROUTE AT FL430 AFTER 20 MINUTES OF FLIGHT TIME, BEGAN TO DETECT A WARM ELECTRICAL ODOR. TURNED OFF INTERIOR SWITCH AND ODOR APPEARED TO GO AWAY. NEVER SAW ANY VISUAL CLUES OF SMOKE OR HAZE. THERE WERE NO INCREASE OR ABNORMAL GENERATOR AMPS ETC. NEVER HAD COFFEE POTS ON THIS LEG OR THE VANITY HEATER. HAD SEVERAL CHARGERS PLUGGED IN BUT NONE OF THOSE WERE WARM OR HOT. FO WENT TO CABIN AND SEEMED TO THINK IT WAS STRONGER THERE. DIVERTED TO AIRPORT AND LAND WITHOUT INCIDENT. CHECKED AIRCRAFT, COULD NOT FIND WHERE ODOR ORIGINATED AND COULD NOT DUPLICATE.

Part: CIRCUIT BREAKER — TRIPPED (LANDING GEAR) · airframe 8,183 hrs · 5,395 cycles

THE CIRCUIT BREAKER LG CONT 2 POPPED AT TAKEOFF & GEAR UP. THE GEAR SPEED OF 210 WAS EXCEEDED BY 40K UNTIL WE DETERMINED THE GEAR NEVER RETRACTED. WE ACCOMPLISHED THE CHECKLIST BLOW DOWN PROCEDURE, INCLUDING THE MAIN GEAR & NOSE GEAR MANUAL UNLOCK RELEASE PROCEDURE. LANDED WITHOUT INCIDENT. RELEASED PRESSURE, RESET & SERVICED NLG BLOW DOWN BOTTLE, RESET LG CONTROL VLV & PERFORMED 25 FULL LG CYCLES IAW MM 32-00-00. NO DISCREPANCIES NOTED. REPOSITIONED PCB ASSEMBLY, LANDING GEAR CONTROL, PERFORMED SEVERAL GEAR SWINGS. OPERATION CHECKS GOOD. WORK DONE IAW MM CH24-60-10 REV 24.

Part: DATA UNIT — FAILED (COCKPIT) · airframe 7,290 hrs · 4,781 cycles

TEN SECS AFTER RT ENGINE START, LT ENGINE RUNNING, EICAS RT WINDSHIELD HEAT INOP AMBER MESSAGE ILLUMINATED FOLLOWED BY AN ELECTRICAL ODOR & LIGHT SMOKE IN COCKPIT. ENGINES & APU SHUTDOWN. POWERED ACFT, STBY SFD POWERS UP BOTH AIRSPEED & ALT TURNED RED & FAILED. POWERED FAILURES STOPPED & DID NOT RETURN. TROUBLESHOT SFD & ADU IAW MM 34-00-00-910-901. DURING BIT TEST, SFD & ADU PASSING SELF-TEST BUT BOTH SFD & ADU FAILED. PURGED STBY PITOT SYS. REMOVED FAILED SFD & INSTALLED REPAIRED UNIT IAW MM 34-23-01-900-801. REMOVED FAILED ADU & INSTALLED REPAIRED UNIT IAW MM 34-23-05-900-801. BIT TESTED IAW MM 34-00-00-910-901. ADU & SFD SELF-TESTS PASSED. LEAK TESTED STBY AIR DATA SYS IAW MM 34-11-00-790-801.

Part: RIB — CRACKED (LT WING) · airframe 6,270 hrs · 4,124 cycles

CORROSION AT TOP, FWD OF LT WW WHERE BRAKE LINES FEED THROUGH LWS 52 RIB. ACCOMPLISHED REPAIR DEFINITION NR S-680-0180 05RD, MAJOR REPAIR, REPAIR OF CORROSION ON LWS 52 RIB DATED JULY 22, 2014 & FAA FORM 8100-9 DATED 7/25/2014. WEIGHT & BALANCE WAS NOT AFFECTED. PERTINENT DETAILS OF THE REPAIR ARE ON FILE AT THIS REPAIR STATION CRS CNQR91BC UNDER SERVICE ORDER 2-98144.

Part: HYDRAULIC SYSTEM — UNKNOWN · airframe 5,061 hrs · 3,336 cycles

WHILE DROPPING THE LANDING GEAR, THE HYD VOLUME LOW CAS MESSAGE ILLUMINATED AND THE HYD VOLUME DROPPED TO ZERO. THE LANDING GEAR INDICATED THREE GREEN, CONDUCTED THE HYD VOLUME LOW CHECKLIST, AND LANDED WITHOUT INCIDENT.

Part: HEAT EXCHANGER — CRACKED (CABIN AIR) · airframe 4,699 hrs

DURING A SCHEDULED INSPECTION, REPLACED A DUCT ASSY OFF OF THE HEAT EXCHANGER WITH AN IMPROVED DUCT ASSY. AT DISASSEMBLY, DISCOVERED THAT RIGHT HEAT EXCHANGER HAD CRACKS FROM THE BOLT ATTACH POINTS. THE CRACKS WERE FROM .25 TO .75 IN LENGTH. IT APPEARS THE CRACKS ARE FROM ALL 4 CORNERS OF THE MOUNTING BACK PLATE ON THE HEAT EXCHANGER, THE CORNERS SHOULD HAVE BEEN RADIUSED DURING PRODUCTION. THIS HAS BEEN REPORTED TO MFG ON SCR 648257.

Part: GENERATOR — INOPERATIVE (LEFT AC) · airframe 2,904 hrs · 1,921 cycles

WHEN THROTTLES WERE ADVANCED FOR T/O THE LT WINDSHIELD INOPERATIVE CAS MESSAGE POSTED. TOWER REPORTED SEEING SMOKE COMING FROM THE REAR OF THE ACFT. VERIFIED A SMALL AMOUT OF SMOKE COMING FROM THE LT AC GENERATOR EXHAUST. INSPECTED LT ACFT GENERATOR AND FOUND BURNED WINDING THRU VENT. REMOVED THE FAULTY AC GENERATOR AND CLEANED SMOKE RESIDUE. INSTALLED EXCHANGE UNIT AND PERFORMED OPS CHECK SATISFACTORY. WORK DONE IAW MM CHAP 24-20-20 (REV 17).

Part: PUMP — LEAKING (HYD SYSTEM) · airframe 2,531 hrs · 1,706 cycles

DURING UNSCHEDULED MX, THE RT ENGINE HYD PUMP WAS REPLACED DUE TO INTERNAL LEAKAGE.

Part: PUMP — LEAKING (HYD SYSTEM) · airframe 2,531 hrs · 1,706 cycles

DURING UNSCHEDULED MX, THE LT ENGINE HYD PUMP WAS REPLACED DUE TO INTERNAL LEAKAGE.

Part: STRUT — LEAKING (NLG) · airframe 2,488 hrs · 1,683 cycles

ON DEPARTURE RT MAIN GEAR DID NOT RETRACT. JACKED ACFT CHECKED RT MAIN WOW SWITCH OK. NOSE GEAR IAW CMC SHOWED ON GROUND. DETERMINED NOSE GEAR LEAKING INTERNALLY. DISASSEMBLED NOSE GEAR, FOUND METAL IN FLUID. INSTALLED AND SERVICED WITH N2. OPS CHECKED SATISFACTORY, ALL WORK IAW CMM 32-20-01.

Part: ACTUATOR — INOPERATIVE · airframe 2,234 hrs · 1,511 cycles

ROLL SYSTEM CONTROL FAULT AMBER CAS ILLUMINATED IN FLIGHT. ACCESSED THE ROLL RATIO CHANGER ACTUATOR. NOTED GOOD CONNECTIVITY. ACTUATOR & AREA CLEAN. CONNECTED PITOT/STATIC. PERFORMED THE RAIO CHANGER POSITION CHECK. AT 300 KNOTS DIMENSION OF MALMENT IS IN SPEC. AT 300 KTS ACTUATOR MADE AN UNCOMMANDED UNDEMENT WITH STEADY AIRSPEED. MONITORED CMC FOR ASSOCIATED PCB. NOTED THAT IMPORTANT PARAMETERS ARE ALL XXX'D OUT. REMOVED ACTUATOR AND INSTALLED O/H UNIT. OPS CHECK DUE. PERFORMED OPS CHECKS. NOTED SMOOTH OPERATION WITH NO UNCOMMANDED MOVEMENTS. TRAVEL DISTANCE CHECKED GOOD. OPS CHECKED GOOD. PERFORMED OPS CHECK OF TCAS AND COM2 SYS. OPS CHECKED OK. WORK PERFORMED IAW MM 27-10-00.

Part: STRUT — DISCHARGED (NLG) · airframe 1,698 hrs · 1,137 cycles

WHEN GEAR HANDLE RAISED, RED UNLOCK ILLUMINATED, NOSE WHEEL DOWN AND LOCKED EXTINGUISHED, BOTH MAIN GEAR DOWN & LOCKED REMAINED ILLUMINATED AND AFTER 15 SECONDS GEAR RAISED NORMALLY. JACKED AIRPLANE, CONNECTED HYD GEAR HANDLE WOULD NOT ALLOW GEAR TO RETRACT INSPECTED FOUND LOWER STRUCT CAMBER AT ZERO PSI RESERVICED NOSE STRUT IAW MM 32-20-00 PERFORMED GEAR SWING OPS CHECK GOOD IAW MM 32-20-00.

Part: WIRE — CHAFED (TE FLAPS) · airframe 1,613 hrs · 1,092 cycles

AFTER T/O, FLAP INDICATOR SHOWED FLAPS AT 7 DEGREES. FLAP RESET WOULD NOT WORK. FLAPS VISUALY CHECKED UP IN FLIGHT. ON GROUND FLAPS WOULD NOT RESET OR TRAVEL UP/DOWN. EMERGENCY DECLARED. TROUBLESHOT TO A CHAFED TWISTED SHIELDED PAIR OF CONDUCTORS. REPAIRED THE WIRING AND TEST THE WIRING OK. COMPLETED FLAP ELECTRICAL RIG TESTS AND FUNCTIONAL TESTS OF THE FLAP SYS. ALL OK NEW WORK HAS BEEN COMPLETED IAW MM 27-50-00.

Part: WARNING LIGHT — ILLUMINATED · airframe 1,219 hrs · 802 cycles

ON CLIMB OUT IN ICING AT 35,000 FT " SUPPLY BLEED LEAK- R " CAS MESSAGE ILLUMINATED COMPLETED CHECKLIST L-10 IAW ABNORMAL PROCEDURES AND LIGHT WENT OUT AFTER STEP NR 2 ON DESCENT WITH ALL ANTI-ICING ON FROM FL 350 TO 10,000 FT. NO REOCCURENCE OF CAS MESSAGE. PERFORMED RT ENG RUN UP CHECK. RT ANIT-ICE SYS AND NOT CAS MESSAGES DISPLAYED AT THIS TIME. CALLED MFG AND ASKED TO CHECK CMC DIAGNOSTIC AND NO FAULT REPORTS FOUND. INFORMED MCC AND ASKED TO REPOSTION BLEED LEAK DETECTED BOXES AS REQUIRED PERFORMED LT AND RT ENGINE RUN UP AND NO CAS MESSAGES DISPLAYED AT THIS TIME BLEED LEAK DETECT BOXES REMAINING REPOSITION. ALL WORK PERFORMED IAW MM CHAPTER 26-10-20 PN ON RT 35009-20 SN D4145 PN ON LT 35009-20 SN D4117.

Part: STRUT — DISCHARGED (NLG) · airframe 946 hrs · 614 cycles

FOUND NOSE STRUT NOT FULLY EXTEND WITH ACFT ON JACKS. FOUND NO AIR IN LWR NOSE STRUT CHAMBER. FOUND CAUSE TO BE 2 O-RINGS INSTALLED ON LWR CHAMBER SHREADER VALVE. SERVICED NOSE STRUT WITH FLUID AND IAR. REPLACED O-RING ON LWR SHREADER VALVE WITH SINGLE O-RING. LEAK CHECKS SATISFACTORY. PERFORMED LANDING GEAR SWING CHECKS. FOUND TO BE SATISFACTORY. WORK WAS ACCOMPLISHED IAW MM CHAP 32-20-00.

Part: LANDING GEAR — MALFUNCTIONED · airframe 946 hrs · 614 cycles

AFTER TAKEOFF LANDING GEAR WOULD NOT RETRACT. WOW MISCOMPARE CAS MSG CAME ON.

Part: UPLOCK SWITCH — DEFECTIVE (NLG) · airframe 9,137 hrs · 8,334 cycles

LEFT MAIN GEAR WOULD NOT RETRACT AFTER T/O LEFT GEAR LOCK LIGHT AND GEAR UNSAFE. EXTENDED GEAR AND HAD THREE GREEN DOWN AND LOCKED. RANG OUT UPLOCK SWITCH NLG HIGH RESISTANCE THROUGH CLOSED CONTACTS OF SWITCH AS WELL THROUGH OPEN CONTACTS ALSO CHECKED WOW SWITCH AND FOUND DEFECTIVE. REPLACED UPLOCK AND WOW SWITCH AND ACCOMPLISHED SEVERAL OPS CHECKS OF LANDING GEAR NO DEFECTS WERE NOTED PER 560 MM 32-61-00.

Part: PICCOLO TUBE — BROKEN (WING)

DURING PHASE 1-4 INSP. MECH GRABBED THE TIP BLEED AIR FEED TUBE AND APPLIED PRESSURE BACK AND FORTH, A NOISE WAS HEARD BANGING AT EACH STROKE. AFTER DISASSEMBLY (REMOVAL OF LIP) FOUND THE 6552502-4, PICCOLO ASSY ATTACH LEGS (3 EA) .8750 CRACKED, ALMOST BROKEN. ALSO THE LIP NOSE CAP PN 65525051 WAS CHAFFED PAST 50 PERCENT OF MATERIAL THICKNESS. BOTH THE PICCOLO ASSY AND THE NOSE CAP (LIP) WERE REPLACED, USING SAME TYPE FASTENERS REMOVED. ATTACHED PICTURES.

Part: WHEEL — FAILED (MLG) · airframe 6,916 hrs · 6,509 cycles

SHORTLY AFTER LANDING BOTH MAIN TIRES BLEW OUT ON LANDING. AIRCRAFT CAME TO A COMPLETE STOP ON ACTIVE RUNWAY AND NEEDED TO BE REMOVED BY AIRPORT OPERATIONS. PEFORMED FOD, HIGH DRAG SIDE LOAD AND HARD LANDING INSPECTION, FOUND AIRCRAFT HAD BOTH MLG DOORS AND LIGHTS DAMAGED, BOTH WING TIPS DAMAGED. REMOVED AND REPLACED BOTH MLG WHEEL AND BRAKE ASSEMBLIES. PERFORMED INTERIM REPAIR, SECURED AIRCRAFT FOR A ONE TIME FERRY FLIGHT TO ICT FOR PERMANENT REPAIR.

Part: VANE — CRACKED (NACA SCOOP)

DURING ROUTINE INSP LOOKED INTO DORSAL NACA SCOOP AND SAW THE UPPER AIR VANE PART NR 651207212 WITH A 2 INCH PIECE MISSING. GAINED ACCESS THROUGH BAGGAGE AREA, REMOVED BROKEN VANE ALSO LOCATED MISSING PART DOWN STREAM PAST ACM AND FRESH AIR CHECK VALVE AND OVERHEAD BLOWER WEDGED IN DUCT WORK ON AFT BULKHEAD. NO DAMAGE WAS NOTICED ON BLOWER FAN OR CHECK VALVE. FIT AND INSTALLED NEW AIR VANE WITH RELIEF HOLE PLACED AT INTERSECTION OF V CUT. IAW 560 SRM WITH LIBERAL AMOUNTS OF EA 9309. REINSTALLED ITEMS REMOVED FOR ACCESS AND LOCATION OF MISSING PART. CLOSED UP BAGGAGE AREA.