N396QS

Part: BATTERY PACK — FAULTED (ZONE 200) · airframe 14,930 hrs · 9,777 cycles

NO EMERGENCY LIGHTS TEST WHEN THE EMER LIGHT SWITCH IS TURNED TO ON. REMOVED AND REPLACED ALL FOUR EMERGENCY LIGHTING BATTERY PACKS IAW MM 33-50-10.OPS CHECK GOOD IAW MM 33-50-00 NR 1 BATTERY PACK: NR 2 BATTERY PACK. NR 3 BATTERY PACK, NR 4 BATTERY PACK.

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 14,930 hrs · 9,776 cycles

FORWARD EMERGENCY OVERWING LIGHT INOP WHEN CHECKING EMER LIGHTS ON THE GROUND. CORRECTIVE ACTION: REMOVED AND REPLACED FWD EMERGENCY OVWING LIGHT ASSY IAW MM 33-50-00. OPS CHECK GOOD.

Part: SPAR — CORRODED (ZONE 600) · airframe 14,744 hrs · 9,636 cycles

RH WING AFT SPAR HAS 1 AREA OF CORROSION AROUND HI-LOK ON LOWER CLIP BEHIND PANEL 720DR. MECHANICALLY REMOVED CORROSION FROM RH WING AFT SPAR. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. SUBMITTED TO NJA ENGINEERING FOR REPAIR. REPAIRED AREA PER NJA ENGINEERING RFTS-114590, REV 0, TITLE:N396QS (680-0240) RH WING AFT SPAR CORROSION, DATED: 08/04/2025.

Part: SPAR WEB — CORRODED (ZONE 600) · airframe 14,744 hrs · 9,636 cycles

RH WING AFT SPAR HAS 2 AREAS OF CORROSION ON FWD FACE BEHIND PANEL 720DR. MECHANICALLY REMOVED CORROSION FROM RH WING AFT SPAR WEB. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. SUBMITTED TO NJA ENGINEERING FOR REPAIR. REPAIRED AREA PER NJA ENGINEERING RFTS-114589, REV 0, TITLE:N396QS (680-0240) RH WING AFT SPAR WEB CORROSION, DATED: 08/04/2025.

Part: COVER PANEL — DAMAGED (ZONE 800) · airframe 14,686 hrs · 9,593 cycles

COVER PANEL HAS COME APART AND IS CATCHING IN THE MED WHEN WE TRY TO CLOSE. REPLACED THE FOLLOWING HARDWARE AND BOOT AS FOLLOWS: 4419089-11 BOOT ASSEMBLY - FORWARD , MS24694-C61 SCUFF PLATE SCREW AND MS35206-230 FORWARD COVER PANEL SCREWS. ALL WORK WAS ACCOMPLISHED IN ACCORDANCE WITH AMM 52-10-20 (REV 10) CABIN DOOR STEP - MAINTENANCE PRACTICES. NO DEFECTS NOTED.

Part: MOUNT — CORRODED (ZONE 800) · airframe 14,368 hrs · 9,376 cycles

MECHANICALLY BLENDED 1 AREA PLUS 1 ADDITIONAL AREA OF CORROSION ON CABIN DOOR TOP STEP MOUNTING STRUCTURE, 1 AREA OF CORROSION ON CABIN DOOR UPPER, AFT SECTION ON INTERIOR OF DOOR AND 1 AREA OF CORROSION ON SPADE DOOR LOWER, MIDDLE SECTION NEAR HINGE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED CORROSION BLENDS IAW NETJETS REQUEST FOR TECHNICAL SERVICES REPORT BY CLEANING, TREATING AND PRIMING BLENDED AREAS.

Part: SPAR — CORRODED (WING) · airframe 14,368 hrs · 9,376 cycles

REPAIRED 5 CORRODED AREAS ON THE FWD AFT SPAR FACE INBOARD OF WS 37.00, 1 AREA INSIDE BAY 720DR UPPER SPAR CLIP, INBOARD CORNER AND 2 ADDITIONAL AREAS ON WING AFT SPAR LOWER SPAR CLIP INSIDE RH GEARWELL, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED CORROSION BLENDS PER NETJETS REQUEST FOR TECHNICAL SERVICES RFTS-112186 BY CLEANING, TREATING, PRIMING AND APPLYING CORROSION INHIBITING COMPOUND.

Part: SPAR — CORRODED (ZONE 300) · airframe 14,368 hrs · 9,376 cycles

REPAIRED 2 AREAS OF CORROSION ON VERTICAL STAB AFT SPAR AFT FACE ON LH AND RH SPAR CLIPS, LH SIDE APX 15" BELOW MIDDLE RUDDER HINGE AND RH SIDE, APX 10" BELOW LOWER RUDDER HINGE, PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. REPAIRED CORROSION BLENDS PER NETJETS REQUEST FOR TECHNICAL SERVICES RFTS-112180 BY CLEANING, TREATING, PRIMING AND APPLYING CORROSION INHIBITING COMPOUND.

Part: DUCT — DETACHED (ACM) · airframe 14,088 hrs · 9,180 cycles

LOSS OF CABIN PRESSURE AT 16,000¿ AND CABIN ALTITUDE AMBER CAS MESSAGE. AFTER DEPARTING FROM NASSAU TO MIAMI AT APPROXIMATELY 16,000 FEET, WE HEARD A LOUD BANG IN THE AIRPLANE FOLLOWED BY A LOSS OF CABIN PRESSURE SLOWLY RISING AT 500 FOOT A MINUTE AND WE STOPPED THE CLIMB. WE INFORMED ATC OF OUR SITUATION AND REQUESTED A DESCENT BACK TO 10,000 FEET AND GIVING US THE CABIN ALTITUDE AMBER CAS MESSAGE. WHILE DESCENDING WE OBSERVE THE CABIN CONTINUE CLIMBING UNTIL IT EVENTUALLY MET OUR ALTITUDE AT 10,000 FEET. APPROACHING MIAMI WE HEARD FURTHER NOISES ACCOMPANIED WITH LOUD RUSHING AIR SOUNDS. WE WEREN¿T SURE IF WE HAD A WINDOW STARTING TO GO OR SOMETHING ELSE STRUCTURAL HAPPENING TO THE AIRPLANE SO WE DECLARED AN EMERGENCY AND ASKED FOR PRIORITY HANDLING INTO MIAMI. UPON REACHING MIAMI DURING POST FLIGHT INSPECTION WE FOUND THE DUCT GOING INTO THE COOLING TURBINE HAD BLOWN OFF AND COME DISLODGED FOUND DUCTING FROM AIR CYCLE MACHINE TURBINE DETACHED. TECHS REINSTALLED DUCTING TO AIR CYCLE MACHINE IAW AMM 21-21-00. ACCOMPLISHED PRESSURIZED OPS CHECK WITH APU. OPS CHECK GOOD.

Part: BATTERY — DEFECTIVE (EMERGENCY LIGHTS) · airframe 13,631 hrs · 8,875 cycles

CABIN EMERG LIGHT: EMERGENCY LIGHT IN THE CABIN BETWEEN SEATS 3 AND 5 IS INOPERATIVE, AND THE LEFT FORWARD STEP EVACUATION PATH LIGHT IN INOPERATIVE.////SIGN-OFF REMOVED EMERGENCY LIGHTING BATTERY PACK #2 AND INSTALLED CUSTOMER SUPPLIED BATTERY PACK IS SAME LOCATION IAW CESSNA 680 AMM 3-50-10. OPS CHECK GOOD.

Part: DEFLECTOR — CORRODED (ZONE 200) · airframe 13,624 hrs · 8,871 cycles

APU STARTER INLET DEFLECTOR HAS NUMEROUS AREAS OF CORROSION. REMOVED CORRODED APU GENERATOR INLET DEFLECTOR AND INSTALLED NEW P/N: 6950610-7

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,624 hrs · 8,871 cycles

REPLACEMENT OF RUDDER MIDDLE ATTACHMENT UPPER PORTION HINGE BRACKET DUE TO LEVEL 3 CORROSION LOCATED WHERE BOND JUMPER IS ATTACHED. 6931050-60 (2EA), 6931050-60S (1 EA)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,624 hrs · 8,871 cycles

REPLACED THE RUDDER FAIRING LH AND RH ATTACHMENT ANGLES FROM THE UPPER TAIL CONE STINGER, DUE TO LEVEL 2 CORROSION. P/N: 6912630-67, AND 6912630-68

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,624 hrs · 8,871 cycles

MECHANICALLY BLENDED CORRODED AREA ON THE OUTER SKIN OF THE EMERGENCY EXIT DOOR NEAR THE FORWARD UPPER CORNER, PERFORMED NDT AND REPORTED RESULTS FOR REPAIR DISPOSITION. REPAIRED BLENDED AREA BY CLEANING, TREATING, PRIMING AND TOP COATING IN ACCORDANCE WITH TEXTRON STANDARD REPAIR.

Part: CONTROL UNIT — MALFUNCTIONED (ACTUATOR) · airframe 13,577 hrs · 8,831 cycles

AFTER TAKEOFF AND AT FRA CALL THE SIC TOLD THE AIRCRAFT WOULD NOT TRIM AND BE WAS HAVING TROUBLE KEEPING THE NOSE DOWN. RAN THE PRIMARY STAB TRIM INOP CHECKLIST. COULDN'T GET SECONDARY STAB TRIM TO WORK EITHER. REMOVED FAULTY ACTUATOR CONTROL UNIT. INSTALLED OVERHAULED CONTROL UNIT. COMPLIED WITH SATISFACTORY TESTS OF PRIMARY & SECONDAY TRIM ACTUATORS IAW MM 27-40-00. RECOMMENDATION LOOSENED THE TENSION ON CHAIN CONNECTED THE PRIMARY & SECONDARY STAB TRIM ACTUATORS. PERFORMED OPS CHECK WITH NO FAULTS. WORK DONE IAW AMM 27-40-00.

Part: LIGHT — DEFECTIVE (ZONE 100) · airframe 13,570 hrs · 8,825 cycles

POST-FLIGHT - EMERGENCY LIGHTS ARE NOT FUNCTIONING PROPERLY. WITH THE APU RUNNING AND THE EMER LTS SWITCH IN ¿ON¿ (PAX SAFETY - ON OR OFF), NONE OF THE INTERIOR OR EXTERIOR LIGHTS ILLUMINATE. WITH THE EMER LTS SWITCH IN ¿ARM¿ AND THE PAX SAFETY SWITCH ON, MOST LIGHTS ILLUMINATE EXCEPT FOR EXTERIOR AFT OVER WING AND INTERIOR AFT THREE (3) EXIT SIGNS (TWO LAV, ONE BULKHEAD) AND READ LIGHT ABOVE TOILET. FIVE (5) TOTAL FIXTURES ARE INOP. REPLACED EMER LIGHT TOGGLE SWITCH WITH REF TO CE-680 AMM 31-10-20. R & R BATTERY PACK #4 FUSE AS REQUIRED. PERFORMED OPS CHECK OF EMERGENCY LIGHTS WITH IAW AMM 33-50-00, ALL LIGHTS OPS AT THIS TIME. REINSTALLED JBOX ACCESS PANELS.

Part: PITOT SYSTEM — BLOCKED · airframe 12,462 hrs · 8,077 cycles

NOTED THE TWO PRIMARY ALTIMETERS DIFFER BUT NOT OUT OF LIMITS, AT FL320, DIFFERENCE 90 FT, OUT OF COMPLIANCE, WITH RT ALTIMETER READING HIGHER THAN LT. ON GROUND AFTER FLT, STILL DIFFERED BY ABOUT 25 FT. PURGED THE PILOT/STATIC SYSTEMS IAW MM 34-11-00. FOUND WATER IN PILOT & COPILOT PITOT & STATIC SYSTEMS. BOTH STATIC PORT OPENINGS ON BOTH SIDES BLOCKED. FOUND INSECT IN THE STATIC PORT ON PILOT'S SIDE BUT 1 LINE WILL NOT PURGE. REMOVED STATIC HARD LINE AT RT FWD BLKHD. PURGED STATIC HARD LINE. PURGED COPILOTS STATIC PORT AT STATIC PORT ELBOW, NO DEFECTS. PURGED STATIC SYSTEM CROSS OVER LINE, NO DEFECTS. PERFORMED PURGING ON PILOTS STATIC HARD LINE & STATIC PORT ELBOW, NO DEFECTS.

Part: STRUCTURE — CORRODED (BS 157-185) · airframe 10,593 hrs · 6,847 cycles

DURING CABIN INTERNAL ZONAL INSPECTION FOUND SEVERAL SPOTS OF CORROSION ON STRUCTURE UNDER THE CENTER DROP AISLE PANELS. COMPLY WITH FLOOR REPAIRS PER AQRD ERO. FABRICATED AND INSTALLED -001 DOUBLER, -002 DOUBLER, -003 SHIM, AND FORWARD WEB AT F.S. 157 IAW AQRD ERO 966824, REV IR, DATED AUG 24 2020.

Part: SKIN — CORRODED (RT WING) · corrosion level 2 · airframe 10,076 hrs · 6,503 cycles

CORROSION ON THE LH/RH WING UPPER SKIN ALONG EDGE OF WING TO FUSELAGE CARBON FAIRING.BLENDED AND REMOVED ALL VISIBLE SIGNS OF CORROSION ON LH I/B WING SKINS. REFER TO SUB 2 FOR NDT DETAILS. THE BLENDED AREAS WERE OUT OF LIMITS PER CESSNA 680 SRM 51-10-01. BLENDED AREAS WERE SUBMITTED TO TEXTRON AND A FIELD REPAIR WAS ISSUED FR-680-0240-7202 REV-.

Part: SKIN — CORRODED (TAILCONE) · corrosion level 2

CORROSION ON THE L/H AND R/H FUSELAGE AT THE EDGE OF THE AFT FAIRING.PERFORMED TAILCONE SECTION SKIN CORROSION REPAIR ON AFT FUSELAGE LH AND RH SKIN UNDER AFT FUSELAGE FAIRING. FABRICATED AND INSTALLED 4 DOUBLERS TO BLENDED AREAS USING .032" 2024T3 ALUMINUM ALLOY, NAS1097AD4 AND 5 RIVETS AND EA9309.3NA LOT#JH9DAB9142. APPLIED FILLET SEAL USING PS870B2 LOT #07290397 AROUND PERIMETER OF AFT FUSELAGE FAIRING AND ALL 4 DOUBLERS. IAW AQRD ERO-963128 REV.IR, DATED OCT 22 2019.

Part: SKIN — CORRODED (FUSELAGE) · airframe 9,948 hrs · 6,413 cycles

FOUND BUBBLING PAINT ON SKIN JUST OTBD OF RT NOSE CHIN FAIRING DURING TASK 53-10-00-2102. REPAIRED CORROSION ON RT FUSELAGE NOSE SKIN UNDERNEATH THE RT FWD FUSELAGE FAIRING(AFT OF FS 125 AND FS 136.20) IN ACCORDANCE WITH QRD ERO-959629 REV. IR, "LT/RT FORWARD FUSELAGE SKIN CORROSION DAMAGE, DATED 07/19/2019 SUPPORTED BY FAA FORM 8110-3 DATED 07/19/2019.

Part: SKIN — CORRODED (FUSELAGE) · airframe 9,948 hrs · 6,413 cycles

FOUND SUSPECTED LEVEL 1 CORROSION ON SKIN SURFACE JUST OTBD OF LT NOSE CHIN FAIRING DURING NLG AND NLG ACTUATOR HOUSING INSPECTION 53-10-00-2102. SUSPECT CORROSION FOUND TO EXTEND BENEATH FAIRING. REPAIRED CORROSION ON LH FUSELAGE NOSE SKIN UNDERNEATH THE LT FWD FUSELAGE FAIRING IN ACCORDANCE WITH QRD ERO-959629 REV. IR, "LT/RT FORWARD FUSELAGE SKIN CORROSION DAMAGE, DATED 07/19/2019 SUPPORTED BY FAA FORM 8110-3 DATED 07/19/2019.

Part: RIB — CORRODED (LT MLG WW) · airframe 9,948 hrs · 6,413 cycles

FOUND LEVEL 1 CORROSION IN THE LT WHEEL WELL CENTER SPAR #2 RIB DURING THE MLG CORROSION ZONAL INSPECTION. BLENDED CORROSION IN LT WHEEL WELL ON CENTER SPAR #2 RIB. FOUND CORROSION TO BE BEYOND CORROSION LIMITATIONS IAW SRM 51-70-02. REPAIRED CORROSION PER ENGINEERING MEMO DQ# 22016 M1 DATED 06/26/19. NDT PERFORMED EDDY CURRENT AND ULTRASONIC THICKNESS INSPECTIONS AFTER CORROSION WAS REMOVED FROM THE LT WHEEL WELL CENTER SPAR #2 RIB. INSPECTIONS REVEALED NO CRACK OR CORROSION INDICATIONS, THICKNESS READINGS AS DOCUMENTED FOR FURTHER EVALUATION.

Part: SPAR — CORRODED (WING) · airframe 7,983 hrs · 5,128 cycles

WING AFT SPARS AND INBOARD RIBS FITTING CORROSION.

Part: SPAR CAP — CORRODED (WING) · airframe 4,648 hrs · 2,980 cycles

REAR SPAR LOWER CAP CORRODED. REPAIRED IAW S-680-0240/02RD.

Part: COOLING TURBINE — FAILED (ACM) · airframe 4,361 hrs · 2,769 cycles

WITH THE LT ENGINE AND THE APU RUNNING, AFTER RT ENGINE START, HOT AIR WAS BLOWING OUT OF THE VENTS WITH THE TEMPERATURE CONTROLLER ON FULL COLD. STARTED TO GET SMOKE IN THE CABIN ON TAXI OUT. R & R AIR CONDITIONING PACK COOLING TURBINE. LEAK AND OPS CHECKED GOOD IAW MM 21-51-00.

Part: HEAT EXCHANGER — CRACKED (BLEED AIR) · airframe 3,881 hrs

DURING A SCHEDULED PRODUCT IMPROVEMENT (REPLACED DUCT ASSY 6914070-67) NOTICED THE HEAT EXCHANGER SIDE PLATE HAD A .35 INCH LONG CRACK AND THE OPPOSITE SIDE WAS CRACKED IN TWO PLACES. PREFORMED A LEAK CHECK OF THE HEAT EXCHANGER AND FOUND LEAKS NOT ONLY FROM THE VISABLE CRACKS, BUT ALSO LEAKS INTERNAL TO THE HEAT EXCHANGER IN THE COOLING FIN AREA. REPLACED WITH A NEW HEAT EXCHANGER.

Part: HEAT EXCHANGER — CRACKED (BLEED SYS) · airframe 3,881 hrs

DURING A SCHEDULED PRODUCT IMPROVEMENT (REPLACED DUCT ASSY 6914070-67) NOTICED THE LT HEAT EXCHANGER SIDE PLATE HAD A .35 INCH LONG CRACK AND THE OPPOSITE SIDE WAS CRACKED IN TWO PLACES. PREFORMED A LEAK CHECK OF THE HEAT EXCHANGER AND FOUND LEAKS NOT ONLY FROM THE VISABLE CRACKS, BUT ALSO LEAKS INTERNAL TO THE HEAT EXCHANGER IN THE COOLING FIN AREA. REPLACED WITH A NEW HEAT EXCHANGER.

Part: STEERING UNIT — UNSERVICEABLE (NLG) · airframe 3,569 hrs · 2,275 cycles

NOSE GEAR WOULD NOT RETRACT AFTER TAKEOFF. LANDING GEAR HANDLE SELECTED OVER THE GATE AND INTO UP POSITION. THE GREEN MAIN GEAR INDICATOR LIGHTS EXTINGUISHED. THE GREEN NOSE GEAR INDICATOR LIGHT REMAIN ILLUMINATED. JACKED ACFT AND ATTEMPTED GEAR SWING FOUND NOSE GEAR WOULD NOT CENTER PREVENTING IT FROM RETRACTING. REMOVED NOSE STEERING ACTUATOR. FOUND NOSE TRUNNION BEARINGS BAD. R & R NOSE TRUNNION BEARING AND RIGGED AND BLED SYS IAW MM CH 32-50-00. PERFORMED NUMEROUS GEAR SWINGS. LANDING GEAR EXTENSION AND RETRACTION OPS CHECKED GOOD.

Part: FRAME — CORRODED (PAX DOOR) · airframe 3,510 hrs · 2,228 cycles

CABIN DOOR FRAME HAS EXSTENSIVE CORROSION AROUND FORWARD SHEAR TIE. DAMAGE DEPTH MEASURES .036. REMOVED CABIN DOOR IAW MM 52-10-00. REMOVED FWD CABIN DOOR FRAME. REMOVED LATCH ARMS (FWD). INSTALLED NEW CABIN DOOR FWD FRAME IAW SRM 51-40-03. INSTALLED FWD LATCH ARMS IAW MM 52-10-40. INSTALLED CABIN DOOR IAW MM 52-10-00. INSTALLED LWR FAIRING. INSTALLED DOOR. INSTALLED DOOR FRAME. OPS CHECKED CABIN DOOR. SOLENOID OPERATIONAL CHECKED IAW MM TASK 52-10-00-700. PRESSURE & OPS CHECKED GOOD. LEAK CHECKED GOOD. C/W PAINT IAW MM 20-31-00. INSTALLED CABIN DOOR STEPS IAW MM 52-10-20.

Part: LATCH — LOOSE (E/E BAY DOOR) · airframe 3,255 hrs · 2,066 cycles

NOSE DOOR OPEN - RT AMBER CAS MESSAGE DISPLAYED, REAR LATCH IS LOOSE WHEN COMPARED TO FORWARD LATCHING MECHANISM. PERFORMED VISUAL INSPECTION OF RT NOSE AVIONICS DOOR LATCHES FOR WEAR. NO DEFECTS NOTED. ADJUSTED AFT LATCH ONE TURN. OPS CHECKED LATCH OPERATION. OPS CHECKED GOOD. COMPLIED WITH DOOR WARNING. OPS CHECK ON RT NOSE AVIONICS DOOR. OPS CHECKED GOOD. WORK PERFORMED IAW MM CHAPTER 52-70-00 (REV19).

Part: BRAKE ASSY — WEAK · airframe 10,042 hrs · 8,063 cycles

BOTH COPILOTS BRAKE PEDALS GO ALMOST TO THE FLOOR. VERIFIED NO LEAKAGE UNDER PEDALS IN COCKPIT. BLED BRAKES PER CESSNA MODEL 560 MM 32-42-00. OPERATIONAL CHECKED GOOD.

Part: ENGINE — OUT OF RIG (LEFT) · airframe 9,274 hrs · 7,417 cycles

AFTER SPEED BRAKE TEST RETARDED THROTTLE ON LT ENGINE TO THE IDLE STOP AND ENGINE QUIT ON ITS OWN. RIGGED LT ENG SO IT DOES NOT SHUTDOWN AT IDLE. ENG OPS CHECKS GOOD AT THIS TIME. ALL WORK DONE IAW CESSNA 560 M.M. CHAPTER 76-11-00.

Part: LINK ROD — OUT OF RIG (THROTTLE) · airframe 8,814 hrs · 7,044 cycles

LEFT ENGINE SHUT DOWN WHILE CHECKING SPEED BRAKE STOW. THROTTLE WAS IN FLIGHT IDLE. FOUND LT ENGINE RIGGING OFF. ADJUSTED LT ENGINE CONTROL CABLE RON END PER 560 MM CH 76-11-00. SAFETIED ALL JAM NUTS AND COTTER PINNED NUTS GROUND RAN AIRCRAFT PERFORMED BRAKE SOW TEST SEVERAL TIMES ENGINE DO NOT FLAME OUT. CHECKED THROTTLES AND VARIOUS POWER SETTINGS. NO THROTTLE SPLIT AND ENSURED LT ENGINE MAKES TAKEOFF POWER WORK PERFORMED PER IAW 750 MM CH 71-00-00 AND SEC MM CH 76-11-00.

Part: SPLICE — DISCONNECTED (MLG INDICATOR) · airframe 8,262 hrs · 6,604 cycles

UPON GEAR EXTENSION, RIGHT MAIN GEAR LIGHT WOULD NOT ILLUMINATE. BULB CHECKED GOOD ON ROTARY TEST. FOUND DME SPLICE DISCONNECTED IN ACTUATOR HARNESS RECONNECTED AND OPS CHECK GOOD IAW CE560 MM 32-31-04.

Part: SWITCH — DIRTY (MLG) · airframe 6,751 hrs · 5,383 cycles

DURING GEAR EXTENSION, HAD ONE RED AND NO GREEN INDICATION. COMPLIED WITH CHECKLIST, NOTICED CIRCUIT BREAKER DID NOT POP, MOVED HANDLE LEFT TO RIGHT SEVERAL TIMES WHICH FINALLY ACTIVATED THE GEAR EXTENSION PROCESS RESULTING IN A SAFE GEAR INDICATION. RECYCLED THE GEAR AND PROBLEM CAME BACK, ACCOMPLISHED AIR TURNBACK TO APF. OPS CHECKED LANDING GEAR AND COULD NOT GET PROBLEM TO DUPLICATE. FOUND DUST ON GEAR HANDLE, CLEARED GEAR HANDLE SWITCHES, SYSTEM OPS CHECK GOOD IAW 560 MM CHAPTER 32-01-00.

Part: LIGHT — INOPERATIVE (MLG INDICATOR) · airframe 6,497 hrs · 5,198 cycles

ON APPROACH LT MAIN LANDING GEAR GREEN LOCKED LIGHT DID NOT ILLUMINATE, EMERGENCY GEAR BLOW DOWN ACCOMPLISHED. FOUND LT MLG COCKPIT GEAR WARNING LIGHT INOP. REMOVED AND REPLACED LAMP, OPS CHECK GOOD IAW CITATION 560 MM CHAPTER 32-60-00. JACKED AIRCRAFT IAW CITATION 560 MM CHAPTER 7-10-01, CYCLED THE LANDING GEAR IAW CITATION 560 MM 32-01-00, DOWN JACKED AIRCRAFT, SERVICED HYDRAULIC RESERVOIR IAW CITATION 560 MM CHAPTER 12-12-01, SERVICED PNEUMATIC BOTTLE IAW CITATION 560 MM CHAPTER 12-13-01.

Part: ENGINE — INOPERATIVE (LEFT) · airframe 6,226 hrs · 4,959 cycles

AFTER ENGINE START HEARD LOUD POP WITH LEFT GENERATOR COMMING OFF LINE AND FOLLOWED BY ENGINE FLAMMING OUT. PERFORMED RIGGING ON LT ENGINE AFT THROTTLE CABLE TO FCU IAW CESSNA 560 MAINTENANCE MANUAL CHAPTER 76-11-00 AND PRATT WHITNEY JT15D MAINTENANCE MANUAL CHAPTER 71-00-00. PERFORMED ENGINE RUN OPERATIONAL CHECKS SATISFACTORY.

Part: DUCT — CRACKED (NACA)

DURING ROUTINE INSPECTION, LOOKED INTO NACA DORSAL SCOOP AND FOUND THE LOWER AIR VANE (PN 6512072-12) CRACKED .5000 INCH WITH CRACK STARTING FROM THE CENTER OF (V) CUT MOVING OUTBOARD. GAINED ACCESS FROM TAIL BAGGAGE AREA AND REMOVED CRACKED VANE. REMOVED EA 9309 IAW MFG STANDARD PRACTICES, UPON REMOVAL NOTICED THAT THE V CUT APPEARS TO HAVE BEEN CUT WITH HAND SNIPS AND THERE WAS NO RELIEF HOLE AT BOTTOM OF CUT, ALSO THERE WAS VERY LITTLE EA 9309 SECURING INTO PLACE. INSTALLED NEW PART AND CLOSED UP AREA. WILL SEND BAD PART TO MFG FOR EVALUATION. (SCR NR 91291)(PTRS 7647)