N361QS

Part: BATTERY — DISCHARGED (ZONE 200) · airframe 14,404 hrs · 9,762 cycles

RIGHT REAR CABIN, EXTERIOR FORWARD WING AND WING INSPECTION EMERGENCY LIGHTS WOULD NOT ILLUMINATE AFTER 30 MINUTE CHARGE APPLIED AND POWER REMOVED. PERFORMED OPERATIONAL CHECK OF INTERIOR AND EXTERIOR EMERGENCY LIGHTS IAW CE-680 AMM 33-50-10. SOPS CHECK GOOD. NO OTHER DEFECTS NOTED AT THIS TIME.

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 14,404 hrs · 9,762 cycles

CABIN EMERG LIGHT: RIGHT REAR CABIN LIGHT DID NOT ILLUMINATE AFTER CHARGING FOR 30 MINUTES CORRECTIVE ACTION; C/W TC-FLT-33-1001 CESSNA 680 EMERGENCY LIGHTING POWER SUPPLY BATTERY EXERCISE PROCEDURE. OPS CHECK GOOD IAW CE-680 MM 33-50-00.

Part: SPAR — CORRODED (SPOILER) · airframe 14,111 hrs · 9,566 cycles

FOUND AREA OF CORROSION AROUND SPOILER EXTEND HYDRAULIC LINE FITTING ON RH WING AFT SPAR. MECHANICALLY REMOVED CORROSION WHERE SPOILER AND SPEED BRAKE HYD LINES WERE DISCONNECTED AT CARRY THRU FITTING ON AFT FACE OF AFT SPAR LOCATED ON RH WING IN INBD FLAP COVE 2 OUTBD POSITIONS IAW C680 SRM 51-70-02. REPAIRED CORRODED AREA ON RH AFT WING SPAR AT HYDRAULIC FEEDTHROUGHS PER AQRD ERO-982770 REV IR TITLED "N361QS RH WING AFT SPAR WEB CORROSION" DATED JAN 28, 2025. SUPPORTED BY FAA FORM 8110-3 DATED 1/28/2025.

Part: SPAR CAP — CORRODED (ZONE 500) · airframe 14,111 hrs · 9,566 cycles

REPAIRED CORRODED AREA ON THE LH LOWER WING SPAR CAP LOCATED IN THE LH MLG WHEEL WELL BEHIND PANEL 730DL, BY R&R FASTENERS AS NEEDED, MECHANICAL BLENDS, PERFORMING NDT AND REPORTING FOR REPAIR DISPOSITION. CLEANED, TREATED, PRIMED AREAS ACCEPTABLE AREAS AS-IS. APPLIED EA 9394 ADHESIVE TO TWO AREAS SLIGHTLY PROUD AND SANDED SMOOTH. ALL WORK COMPLETED PER NETJETS REQUEST FOR TECHNICAL SERVICES REPORT.

Part: SKIN — CORRODED (ZONE 300) · airframe 14,111 hrs · 9,566 cycles

REPAIRED SEVERAL CORRODED AREAS OF THE UPPER AND LOWER TRAILING EDGE SKINS OF THE RH HORIZONTAL STABILIZER BY BLENDING, PERFORMED NDT, AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED BLENDED AREAS IAW REQUEST FOR TECHNICAL SERVICES

Part: THROTTLE CONTROL — FAULTED (ZONE 200) · airframe 14,077 hrs · 9,537 cycles

DURING TAXI OUT AND RUDDER BIAS CHECK NOTICED RIGHT THROTTLE CATCHING AS ITS ADVANCES. FEELS LIKE IT IS BINDING ON ITSELF. CORRECTIVE ACTION; ACCESSED THROTTLE QUADRANT, REMOVED DUST COVER PLATE TO ACCESS FRICTION PLATE MECHANISM. CLEANED THROTTLE FRICTION LEVER MECHANISM AS REQUIRED FOR SMOOTH OPERATION OF RH THROTTLE LEVER. MX PERFORMED IAW CE-680 MM 20-40-10 & 76-10-00. OPS CHECK GOOD AT THIS TIME.

Part: DOOR — MALFUNCTIONED (MAIN) · airframe 13,921 hrs · 9,412 cycles

ENTRANCE STAIR: MAIN CABIN DOOR VERY HEAVY WHEN CLOSING AND WHEN OPENING FALLS TO FALLS OPEN WITHOUT ANY FORCE OF THE LOCKING HANDLE. MADE ADJUSTMENST TO MED COUNTER BALANCE SYSTEM, FWD/AFT SUPPORT STRUTS, MED CLOSING HANDLE AND PUSH ROD AS REQUIRED. OPS CHECKS GOOD. RE-INSTALLED MED STEP ASSY AND COVER PANELS AS REQUIRED, ALL CHECKS GOOD. REF CE-680 AMM 52·10·30 AND 52-10-50. PUSH/PULL SCALE: JE3471 CABLE TENTIOMETER: TL-106166

Part: SKIN — CORRODED (EMERGENCY EXIT) · airframe 13,715 hrs · 9,255 cycles

MECHANICALLY REMOVED 9 AREAS OF CORROSION LOCATED ON E-EXIT DOOR OUTER SKIN SURFACE. NDT VERIFIED CORROSION REMOVAL AND REMAINING THICKNESS. EVALUATED BLENDED AREAS AND FOUND CORROSION BLENDS TO BE WITHIN LIMITS IAW ENGINEERING FIELD REPAIR SR-680-ATA52-18636 REV- , STANDARD REPAIR-CORROSION, ESCAPE HATCH DOOR SKIN,REFERENCE FAA FORM 8100-9.

Part: SKIN — CORRODED (RT WING) · airframe 13,715 hrs · 9,255 cycles

MECHANICALLY REMOVED 3 AREAS OF CORROSION LOCATED ON RH WING UPPER BONDED SKIN FWD END OF AFT DRAG ANGLE, AFT END OF MIDDLE DRAG ANGLE AND MID AREA OF MIDDLE DRAG ANGLE. FOUND 2 AREAS OF CORROSION BLENDS LOCATED AT AFT END OF MIDDLE DRAG ANGLE TO BE BEYOND LIMITS IAW FIELD REPAIR SR-680-ATA57-27245 REV-. FOUND 1 AREA OF CORROSION BLEND LOCATED AT MIDDLE AREA OF MIDDLE DRAG ANGLE TO BE WITHIN LIMITS IAW FIELD REPAIR SR-680-ATA57-27245 REV- 0. PROTECTED BARE METAL WHERE CORROSION BLEND WAS WITHIN LIMITS IAW SRM 51-20-01. REPAIRED 2 AREAS OF CORROSION BEYOND LIMITS IAW ENGINEERING FIELD REPAIR: FR-680-0235-12939 REV-.

Part: BELLCRANK — DEFECTIVE (ZONE 100) · airframe 13,417 hrs · 9,033 cycles

REPEAT WRITE UP, MAIN CABIN DOOR PRE CATCH RELEASE LEVER WILL NOT STOW. REMAINS IN A 90 DEGREE POSITION WITH THE MAIN HANDLE IN THE LOCKED POSITION. WITH THE HANDLE IN THE OPEN POSITION, PRE CATCH MOVES TO A 70 DEGREE POSITION. FOUND DOOR PRE CATCH LATCH HANDLE CLOCKED OUT OF THE RIGGED POSTION. REMOVED DOOR PANELS AND GAINED ACCES TO DOOR PRE CATCH ASSY. FOUND WORN OUT HARDWEAR THAT CAUSED SLOP IN ASSY AND ALLOWED LATCH HANDLE TO TRAVEL OVER CENTER PAST LOCK/ OPEN POSTION. REMOVED WORN OUT HARDWARE AND BELLCRANK ASSY. INSTALLED CUSTOMER SUPPLIED NEW HARDWARE AND BELLCRANK ASSY. PERFORMED FUNCTIONAL CHECK OF THE DOOR PRE CATCH ASSY WITH NO DEFECTS NOTED AT THIS TIME. WORK PERFORMED IAW AMM 52· 10·40.

Part: SPAR CAP — CORRODED (RT WING) · airframe 13,317 hrs · 8,962 cycles

MINOR CORROSION FOUND ON RH WING AFT SPAR CAP IN THE WHEEL WELL AREA. ACCOMPLISHED RH WING AFT SPAR CORROSION REPAIR IAW TEXTRON AVIATION REPAIR LETTER DQ40332M1DATED JULY 12,2023.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,317 hrs · 8,962 cycles

MINOR CORROSION FOUND ON LH VERTICAL STAB REAR SPAR CAP. ACCOMPLISHED VERTICAL STAB AFT SPAR CORROSION REPAIR IAW TEXTRON AVIATION REPAIR LETTER DQ40368.

Part: SOCKET — DAMAGED (EMERGENCY LIGHT) · airframe 12,106 hrs · 7,992 cycles

CABIN EMERG LIGHT: C. BETWEEN SEAT 8 AND 10. WHILE PERFORMING BATTERY EXERCISE PROCEDURE AND PERFORMING OTHER MX ON AIRCRAFT, NOTED EMER LIGHTS CONNECTED TO #3 BATTERY WENT OUT. CHECKED FUSE ON PACK #3, NEW FUSE FOUND BLOWN.REMOVED RH FWD EXTERIOR EMER LIGHT AND CHECKED WIRING FOR DAMAGE/SHORTS. FOUND JY056 PIN 1 SHORTED TO GROUND. REMOVED RH FWD EXTERIOR EMER LIGHT AND CHECKED WIRING FOR DAMAGE/SHORTS. FOUND JY056 PIN 1 SHORTED TO GROUND. REMOVED RH OVERWING ACCESS PANEL TO FOM. REMOVED RH WING ROOT FAIRING TO FOM. DISCONNECTED GROUND GY107 AND RECHECKED JY056, NOTED SHORT CIRCUIT NOW GONE. RECONNECTED GY107 AND DISCONNECTED PY002, SHORT CIRCUIT STILL PRESENT. REMOVED RH WING LANDING LIGHT ACCESS PANEL TO FOM. DISCONNECTED PR006, SHORT CIRCUIT GONE. PERFORMED RESISTANCE CHECK OF JR006, NOTED O.RN, TOO LOW FOR INCANDESCENT LIGHT BULB. REMOVED SHARK LIGHT BULB TO FOM, MEASURED RESISTANCE ACROSS BULB, NOTED SQ. REMOVED SHARK LIGHT SOCKET AND PERFORMED GVI OF INTERNALS, NOTED CAP AND SPRING WERE NO LONGER CONNECTED AND FREELY FLOATING, OUT BATTERY PACK #3. RECONNECTED ALL DISCONNECTED CONNECTORS AND RECHECKED FOR SHORTS, WHILE HOLDING CENTER CONDUCTOR OF SHARK LIGHT OFF OUTER CONDUCTOR, NO SHORTS NOTED. PLACED SOCKET ON ORDER, REINSTALLED ALL REMOVED ACCESS PANELS, RECONNECTED ALL REMOVED CONNECTORS. REF WDM 33-50-01.

Part: DOOR SEAL — DEFECTIVE (ZONE 800) · airframe 12,514 hrs · 8,408 cycles

EMERG EXIT DOOR SEAL: DURING FLIGHT AT 23,000FT PAX NOTIFIED US THAT THERE WAS A LOUD NOISE COMING FROM THE LAV. I WENT BACK TO LAV AND THERE WAS A LOUD HIGH PITCH NOISE COMING FROM THE UPPER RIGHT PORTION OF THE EMERGENCY EXIT DOOR WHEN FACING THE IT. WHEN IN THE FRONT PORTION OF THE CABIN AREA YOU COULD NOT HEAR IT BUT IN LAST 2 SEATS THE NOISE WAS VERY PROMINENT. // SIGNOFF// REMOVED AND REPLACED EMERGENCY EXIT DOOR SEAL IAW CE-680 MM 52-20-00. OFF P/N: 9914713-1 S/N:N/A ON P/N: 9914713-1 S/N:43486 REINSTALELD ORGINAL EMERGENCY DOOR IAW CE-680 MM 52-20-00 AND ACCOMPLISHED EMERGENCY DOOR PRESSURIZATION AND LEACK CHECK PASS. NO LEAK DETECTED AT THIS TIME. WORK DONE IAW CE-680 MM 21-30-00.

Part: NONE — NONE · airframe 12,490 hrs · 8,391 cycles

MAIN DOOR PRECATCH LEVER: MAIN CABIN DOOR PRECATCH WILL NOT RETRACT. MOVES WITH DOOR OPENING BUT SEEMS LIKE IT SKPPED A NOTCH ON THE GEAR. DOOR SECURES CORRECTLY PRECATCH STICKS STRAIGHT OUT. MEL DOES NOT APPLY AS CANT SECURE PRECATCH. // SIGNOFF // CONFIRMED ISSUE, GAINED ACCESS TO MECHANISM, AND ADJUSTED AS NEEDED, INSTALLED NEW HARDWARE AND SPRING, OPS CHECKS OK, ALL WORK IA W CE-680 AMM 52-10-40.

Part: ACM — INOPERATIVE · airframe 12,431 hrs · 8,351 cycles

ACM O'TEMP AMBER CAS: ACM O'TEMP MSG ILLUMINATED AT 45,000'. CHECKLIST ACCOMPLISHED.

Part: BATTERY PACK — DEFECTIVE (EMERGENCY LIGHTS) · airframe 12,250 hrs · 8,222 cycles

CABIN EMERG LIGHT: MULTIPLE EMERGENCY LIGHTS IN BACK HALF OF CABIN DO NOT ILLUMINATE. // SIGNOFF// REMOVED AND REPLACED #4 EMERGENCY BATTERY DUE TO AFT LIGHT NOT ILLUMINATING OPS CHECKS GOOD CHARGED BATTERY, ALL WORK DONE I.AW. CE-680 AMM CH 33-50-00. REMOVED PIN: CBS28-1 SIN: 007028 INSTALLED PIN: CBS28-1 SIN: 008782

Part: LAMP — DEFECTIVE · airframe 12,073 hrs · 8,108 cycles

WITH BATTERIES OFF, EXTERIOR SHARK LIGHT WILL NOT ILLUMINATE WITH THE EMER LTS SWITCH IN EITHER THE ON OR ARM POSITION.//CORRECTIVE ACTION// REMOVED AND INSTALLED NEW LAMP PN 1495X

Part: BATTERY — DEFECTIVE · airframe 11,982 hrs · 8,062 cycles

UNABLE TO ACTIVATED THE CABIN EMERGENCY LIGHTS WITH THE EMERGENCY LIGHT SWITCH SELECTED IN THE ON POSITION AND BATTERIES OFF. WITH THE EMERGENCY SWITCH POSITIONED TO ARM WE ONLY GET THE EXIT SIGN OVER THE CABIN DOOR THE EXIT SIGNS LEFT AND RIGHT OF MAIN CABIN DOOR, THE THREE CEILING LIGHTS AND THE FORWARD AISLE LIGHTS. WE ARE MISSING THE THREE EMERGENCY EXIT SIGNS AROUND THE EMERGENCY WINDOW AND THE REAR FLOOR LIGHTS, THE CEILING LIGHT OVER THE LAV. EXTERIOR WE ARE ONLY GETTING THE LEFT EGRESS LIGHT AND THE FORWARD OVER WING LIGHT. EXTERIOR WE ARE MISSING R WING INSPECTION LIGHT, SHARK LIGHT, AND AFT WING EMERGENCY LIGHT. ALL LIGHTS AND SIGNS ILLUMINATE NORMALLY WITH BATTERIES ON.///REMOVED AND REPLACED FAILED EMERGENCY BATTERY PACKS #3 & #4. IAW CE-680 AMM 33-50-10. OPS CHECK GOOD.

Part: SKIN — DAMAGED (RT WING LE) · airframe 10,532 hrs · 7,084 cycles

RIGHT WING INBOARD LEADING EDGE PANELS DAMAGED (OVERSIZED ATTACH FASTENER HOLES). ACCOMPLISHED TEXTRON AVIATION ENGINEERING LETTER DQ27059M1 DATED SEPT. 18, 2020; 680-0235 (N361QS). RIGHT WING INBOARD LEADING EDGE PANELS DAMAGED (OVERSIZED ATTACH FASTENER HOLES).

Part: STRINGER — CORRODED (BS 164-209) · airframe 10,532 hrs · 7,084 cycles

CORROSION, FUSELAGE, DROP AISLE, FS 164 TO FS 209. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR FR-680-0235-8359 REV-, DATED SEP 9, 2020 AND FAA FORM 8100-9 DATED 9/11/2020. FIELD REPAIR-CORROSION, FUSELAGE, DROP AISLE, FS 164 TO FS 209.

Part: DOUBLER — GOUGED (ESCAPE HATCH) · airframe 10,532 hrs · 7,084 cycles

SCREW GOUGES, AFT CABIN, ESCAPE HATCH INTERIOR SURROUND, FS 400-FS 430. ACCOMPLISHED TEXTRON AVIATION FIELD REPAIR FR-680-0235-8382 REV-, DATED SEP 17, 2020 AND FAA FORM 8100-9 DATED 9/18/2020. FIELD REPAIR-SCREW GOUGES, AFT CABIN, ESCAPE HATCH INTERIOR SURROUND, FS 400-FS 430.

Part: FRAME — CRACKED (NLG AREA) · airframe 10,532 hrs · 7,084 cycles

NLG MID FRAME CRACK. ACCOMPLISHED NETJETS RFTS-104151 REV 0 DATED 03SEP20; N361QS (S/N 680-0235) NLG MID FRAME CRACK PERMANENT REPAIR.

Part: COOLING FAN — CONTAMINATED (COCKPIT) · airframe 10,362 hrs · 6,969 cycles

APU START - INFLIGHT APU START AT 1500 FEET PRIOR TO LANDING. FMS 1 WENT BLANK DURING APU START. SMELLED SOMETHING AFTER FMS 1 WAS BACK ONLINE. WE SHUT DOWN THE APU. //SIGNOFF// WE GAINED ACCESS TO THE BACK SIDE OF APU CONTROL PANEL AND COPILOTS CIRCUIT BREAKER PANEL AND INSPECTED FOR DAMAGE, SECURITY OF WIRES AND COMPONENT AND SNIFF TEST, NO DAMAGE OR SMELL NOTED AND ALL IS SECURE. INSPECTED BOTH FMS UNITS, MFDS AND PFDS FOR CLEANLINESS AND SNIFF TEST. NO SMELL NOTED, REMOVED CARPET FIBERS THAT ACCUMULATED ON EXTERIOR ESPECIALLY IN COOLING FAN AREA. CLEANED ACCUMULATED CARPET FIBERS AND DUST FROM TOP FWD GLARE SHIELD AVIONICS COOLING FANS. RAN APU NUMEROUS TIMES (APPROX 12) IN NUMEROUS CONFIGURATIONS IN AN ATTEMPT TO DUPLICATE CREW DISCREPANCY, NO DEFECTS, NO SMELLS NOTED. CHECKED OPERATION OF WINDSHIELD RAIN REMOVAL FAN, RECIRC FAN, OPS CHECKS GOOD, NO ABNORMAL SMELLS NOTED. VERIFIED APU OIL LEVEL IS GOOD. COMPLETED ECU SYSTEM DUCT BURN OUT. ALL OPS CHECKED GOOD AT THIS TIME. REF CE-680 M/M 24-60-02, 34-23-00, 49-00-00 AND TC680-21-120905M

Part: SPAR — CORRODED (RT WING) · airframe 10,265 hrs · 6,891 cycles

CORROSION ALONG FWD SIDE OF THE RH WING AFT SPAR, LOWER CLIP AS VISIBLE FROM INSIDE THE GEAR WELL.

Part: SPAR — CORRODED (LT WING) · airframe 10,265 hrs · 6,891 cycles

CORROSION ALONG FWD SIDE OF THE LH WING AFT SPAR, LOWER CLIP AS VISIBLE FROM INSIDE THE GEAR WELL

Part: SKIN — CORRODED (LT WING) · airframe 9,927 hrs · 6,654 cycles

REPAIRED CORRODED AREAS OF THE LT & RT WINGS UPPER SKINS LOCATED UNDER AND ADJACENT TO THE LT FORWARD, MIDDLE, AND AFT, AND RT FORWARD AND AFT FUSELAGE/WING DRAG ANGLES (WING/FUSELAGE FAIRING) BY R&R THE DRAG ANGLES FOR ACCESS, BLENDING, PERFORMING NDT, TREATING, PRIMING, AND REPLACING FASTENERS AS REQUIRED IN ACCORDANCE WITH FIELD REPAIR.

Part: SKIN — CORRODED (FUSELAGE) · airframe 9,927 hrs · 6,654 cycles

REPAIRED CORRODED AREAS OF THE LT AND RT FORWARD FUSELAGE SKINS, LOCATED UNDER AND ADJACENT TO THE FORWARD CHIN FAIRINGS, BY R&R THE FORWARD CHIN FAIRINGS FOR ACCESS, BLENDING, PERFORMING NDT, FABRICATING AND INSTALLING DOUBLERS AND FILLERS AS REQUIRED IN ACCORDANCE WITH ENGINEERING REPAIR ORDER.

Part: SKIN — CORRODED (TAILCONE) · airframe 9,927 hrs · 6,654 cycles

REPAIRED CORRODED AREAS OF THE TAILCONE SKINS LOCATED UNDER THE AFT CHIN FAIRINGS BY R&R CHIN FAIRING FOR ACCESS, BLENDING, PERFORMING NDT AND INSTALLING REPAIR DOUBLERS PER REPAIR DRAWING.

Part: COWLING — ERODED (ZONE 400) · airframe 9,133 hrs · 6,137 cycles

LEFT ENGINE LOWER COWLING DAMAGE (EROSION) ENGINEERING LETTER # DQ14437M1

Part: SPAR — CORRODED (LT WING) · airframe 7,664 hrs · 5,129 cycles

LT WING SPAR CORRODED.

Part: SKIN — CORRODED (PAX DOOR) · airframe 7,287 hrs · 4,902 cycles

CORROSION ON LOWER CABIN DOOR SKIN.

Part: SKIN — GOUGED (APU BAY) · airframe 7,287 hrs · 4,902 cycles

APU BAY RIGHT INSIDE SKIN GOUGED. REPAIRED IAW EO DQ5840M1.

Part: SKIN — CORRODED (PAX DOOR) · airframe 7,287 hrs · 4,902 cycles

CORROSION ON LOWER CABIN DOOR SKIN.

Part: BRAKE ASSY — WORN (MLG) · airframe 5,404 hrs · 3,617 cycles

DURING LANDING, BRAKES GRAB & GRIND WITH LOUD METAL TO METAL NOISE. VERY PRONOUNCED EVEN WHEN PARKING. BRAKE WEAR PINS ON LT MAIN INBD HAS MINIMAL INDICATION. FOUND NR 1 & 2 BRAKES GRABBING & MAKING NOISE. R & R NR 1 & 2 BRAKE ASSEMBLIES. BLED SYS, OPS & LEAK CHECKED GOOD. HIGH SPEED TAXI CHECKED GOOD IAW MM 32-42-10.

Part: SEAL — TORN (NR 3) · airframe 5,256 hrs · 3,518 cycles

WHEN STOPPING THE ACFT ON THE RAMP THE RT BRAKE GROWLS & AS THE ACFT STOPS THE BRAKE GRABS. REMOVED NR 3 & NR 4 MAIN WHEEL ASSEMBLIES IAW AMM 32-41-20. FOUND NR 3 INNER GREASE SEAL DAMAGED, RUBBER HAS A TEAR. VISUALLY INSPECTED NR 3 & NR 4 BRAKE ASSEMBLIES, NO DEFECTS NOTED. BRAKES SET & RELEASED NORMALLY ON JACKS. BLEW OUT BRAKE ASSEMBLIES WITH SHOP AIR. INSTALLED NEW INNER GREASE SEAL & INSTALLED SAME NR 3 & NR 4 MAIN WHEEL ASSEMBLIES IAW AMM 32-41-20. TAXI CHECK PERFORMED, CHECKED GOOD, NO DEFECTS NOTED.

Part: HEAT EXCHANGER — CRACKED (ZONE 400) · airframe 3,867 hrs

HEAT EXCHANGER SIDE PLATE HAD TWO CRACKS ABOUT .35 INCH LONG. THE OPPOSITE SIDE OF THE HEAT EXCHANGER WAS CRACKED IN TWO OF THE FOUR CORNERS. A NEW HEAT EXCHANGER WAS INSTALLED. PREFORMED A LEAK CHECK ON THE DEFECTIVE UNIT AND FOUND THE CRACKS EXTENDED INTO THE COOLING FIN AREA, WHERE THEY CAN NOT BE SEEN.

Part: HEAT EXCHANGER — CRACKED (ZONE 400) · airframe 3,867 hrs

HEAT EXCHANGER SIDE PLATE HAD FOUR CRACKS ABOUT .35 INCH LONG. THE OPPOSITE SIDE OF THE HEAT EXCHANGER WAS CRACKED IN FOUR OF THE FOUR CORNERS. A NEW HEAT EXCHANGER WAS INSTALLED. PREFORMED A LEAK CHECK ON THE DEFECTIVE UNIT AND FOUND THE CRACKS EXTENDED INTO THE COOLING FIN AREA, WHERE THEY CAN NOT BE SEEN.

Part: STEERING UNIT — MALFUNCTIONED (NLG) · airframe 923 hrs · 633 cycles

AFTER LIFING UP LANDING GEAR HANDLE DURING TAKEOFF, RED GEAR UNLOCK LIGHT ILLUMINATED STEADY WITH A NOSE GEAR DOWN LIGHT INDICATION. LATER EXTENDED LANDING GEAR HANDLE WITH NORMAL GEAR EXTENDED INDICATION. REPLACED NLG STEERING UNIT IAW MM 32-50-00.

Part: SCHRADER VALVE — MALFUNCTIONED (NLG STRUT) · airframe 435 hrs · 314 cycles

NOSE WHEEL WOULD NOT RETRACT AFTER TAKEOFF. RESERVICED NOSE STRUT AFTER CHANGING SCHRADER VALVE. OP/LEAK CHECKS GOOD.

Part: STRUT — DISCHARGED (NLG) · airframe 163 hrs · 122 cycles

FOUND NOSE STRUT LWR NITROGEN SERVICE AT 0 PSI. SERVICED NOSE STRUT WITH 5606 HYD FLUID AND NITROGEN. JACKED ACFT AND PERFORMED LANDING GEAR OPS CHECK. OPS AND LEAK CHECK GOOD. DOWNJACKED ACFT. WORK PERFORMED REF MM 32-20-00 AND 32-00-00.

Part: LANDING GEAR — UNKNOWN (NLG) · airframe 163 hrs · 122 cycles

NOSE GEAR DID NOT RETRACT ON TAKE-OFF.

Part: CONTROL VALVE — OUT OF ADJUST (ANTI SKID SYSTEM)

BRAKES VERY INEFFECTIVE ON LANDING ROLL-OUT. REPLACED ANTI-SKID POWER CONTROL VALVE IAW MM 32-42-05 OP'S CHECK GOOD.

Part: FUEL CONTROL — MALFUNCTIONED (LT ENGINE)

LT ENGINE SHUT DOWN IN FLIGHT WHEN THROTTLE WAS BROUGHT BACK TO IDLE FIRMLY. ADJUSTED FCU, IAW MM 71-00-00 CHECK GOOD. C/W ENGINE RUN CHECKS IAW MM 71-00-00. OP'S CHECK GOOD.

Part: PRESSURE SWITCH — MALFUNCTIONED (MLG BRAKES) · airframe 10,789 hrs · 8,667 cycles

ON FINAL APPROACH THE BRAKE LOW PRESSURE AND ANTI SKID INOP LIGHT ANNUNCIATORS ILLUMINATED FOR ABOUT 10 SECONDS AND THEN EXTINGUISHED. DURING TAXI THE LIGHTS ILLUMINATED AGAIN AND BOTH THE CAPTAIN AND F/O BRAKES BECOME EXTREMELY MUSHY. AFTER ABOUT 10 SECONDS THE BRAKE PUMP CYCLED AND BRAKE PRESSURE WAS RESTORED. REMOVE & REPLACE BRAKE SYSTEM HIGH/LOW PRESSURE SWITCH. OPS & LEAK CHECKS GOOD IAW CE560MM 32-42-00.

Part: MASTER CYLINDER — LEAKING (BRAKES) · airframe 10,605 hrs · 8,526 cycles

CO-PILOTS BRAKES ARE SPONGY WITH EXCESSIVE TRAVEL BEFORE BECOMING EFFECTIVE. INSPECTED LT AND RT CO-PILOT BRAKE MASTER CYLINDERS FOUND LEAKING. REMOVED AND REPLACED LT AND RT BRAKE MASTER CYLINDERS WITH A OVERHAULED UNITS AND SECURED; BLED BRAKE SYST. AS REQUIRED. OPS CHECKED SATISFACTORY IAW MM CHAPTER 32-42-02.

Part: BRAKE ASSY — WEAK (MLG) · airframe 10,599 hrs · 8,519 cycles

BOTH CO-PILOTS BRAKES ARE SPONGY, THE PEDALS TRAVEL ABOUT 1/4 WAY DOWN BEFORE THE BRAKES APPLY. PERFORMED BRAKE BLEEDING PROCEDURE. OPS CHECK NORMAL AT THIS TIME, WORK PERFORMED IAW CE-560 MM CHAP 32-42-00.

Part: ENGINE — SHUTDOWN (LEFT) · airframe 10,336 hrs · 8,313 cycles

ON THE GROUND, DURING THE SPEED BRAKE CHECK, POWER LEVER WAS RETARDED TO IDLE ON THE LT ENGINE AND ENGINE SHUTDOWN. ADJUSTED GROUND IDLE IAW CE 560 MM CH 71-01-03. GROUND CHECKS GOOD.

Part: HANDLE — LOCKED (COCKPIT) · airframe 10,098 hrs · 8,123 cycles

ONCE AIRBORNE GEAR HANDLE REMAINED LOCKED IN THE DOWN POSITION. CREW UNABLE TO RETRACT LANDING GEAR. JACKED AIRCRAFT CONNECT MULTIMETER TO P65 CHECK INFLIGHT STATES FOUND SWITCH OPEN. AFTER FURTHER TROUBLESHOOTING FOUND SW (S83) 180 DEGREES OUT. REMOVED ARM AND ADJUST SWITCH TO CORRECT SETTING. PERFORMED RIG ADJUSTMENT AND OPS CHECKS SYSTEM OPS CHECKED GOOD IAW CESSNA 560 MM 32-61-00.DOWN JACK AIRCRAFT.

Part: SWITCH — DIRTY (MLG) · airframe 10,060 hrs · 8,088 cycles

UPON LIFT OFF, LANDING GEAR HANDLE WOULD NOT RELEASE FROM DOWNLOCK POSITION, FLIGHT TIME CLOCKS AND TRANSPONDER DID NOT WORK AS WELL. PERFORMED LANDING GEAR RETRACTION 10 TIMES. CHECKED CONDITION OF SQUAT SWITCHES AND ASSOCIATED WIRING AND CONNECTORS. CHECK OK. TRANSPONDER REPLIES WHEN SQUAT SWITCH IS IN AIR MODE, DOES NOT REPLY IN GROUND MODE. CLEANED SWITCHES OFF. COULD NOT DUPLICATE ON GROUND. WORK DONE IAW CE560 MM 32-01-00-710.

Part: FCU — OUT OF ADJUST (ENGINE) · airframe 9,956 hrs · 8,005 cycles

DURING SPEED BRAKE CHECK, AFTER RIGHT THROTTLE WAS BROUGHT BACK TO IDLE, THE ENGINE SPOOLED DOWN AND FLAMED OUT. FOUND FUEL CONTROL TO FLOW DIVIDER INTERCONNECTING ROD TO BE OUT OF ADJUSTMENT. ADJUSTED ROD. CW GROUND RUN FUNCTION CHECK. FUNCTION CHECK OK. REPAIRED IN ACCORDANCE WITH P AND W JT15D MM 71 00 00.

Part: BOLT — LOOSE (FUEL SYSTEM) · airframe 9,952 hrs · 8,001 cycles

DURING SPEED BRAKE RETRACTION CHECK, THE LEFT THROTTLE WAS ADVANCED FORWARD AND THEN BROUGHT BACK TO IDLE. THE LEFT ENGINE THEN SPOOLED DOWN. FUEL FLOW WAS STILL PRESENT ON GAUGES DURING SPOOL DOWN. TIGHTENED LOOSE AFT BOLT ON FFDU+FCU INTERCONNECT ROD AND RESET TENSION ON FLOW DIVIDER VALVE DETENT BALL ON LT ENGINE. RIGGED AND OPERATION CHECKS GOOD PER P AND WC JT15D-5A MM 73-10-04 AND 71-00-00.

Part: BRAKE — WEAK (MLG) · airframe 9,006 hrs · 7,193 cycles

BRAKES SOFT ON RIGHT SIDE, NEED TO GO ALMOST TO THE FLOOR BEFORE ANY HINT OF PRESSURE IS FELT. CHECKED BRAKE PEDAL FEEL ON PILOT AND COPILOT SIDE STATICALLY AND WITH POWER, FEELS NORMAL. CHECKED SYSTEM FOR SERVCIE, ALL CHECKS GOOD. INSPECTED THOSE VISUAL BRAKE COMPONENTS FOR LEAKS- NONE FOUND. SERVICED AND BLED BRAKES IAW 560 MM 32-42-00. PRESSURIZED BRAKE SYSTEM FOR 5 MINUTES- NO LEAKS NOTED

Part: BRAKE — WEAK (MLG) · airframe 9,006 hrs · 7,193 cycles

BRAKES SOFT, ESPECIALLY ON RIGHT SIDE. CO-PILOTS BRAKES GO ALL THE WAY TO THE FLOOR, MUST PUMP UP PRESSURE. THEN PRESSURE LOST WITHIN SECONDS. PERFORMED BRAKE BLEED PROCEDURE AS REQUIRED. NO OTHER DEFECTS NOTED. WORK PERFORMED IAW CE-560 MM CHAP 32-42-00.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 8,882 hrs · 7,105 cycles

BRAKES FELT SPONGY, EXCESSIVE PEDAL TRAVEL BEFORE BRAKES ENGAGED. T/S SYSTEM, BLEED BRAKES. TAXI ACFT, OPS & LEAK CHECKS GOOD IAW 560 M/M CH 32-42-00.

Part: LINE — CHAFED (BRAKES) · airframe 8,804 hrs · 7,039 cycles

UPON LANDING COPILOT LEFT BRAKE PEDAL WENT TO FULL DOWN W/O BRAKING AIRCRAFT, HARD RIGHT TURN UNTIL RIGHT BRAKE LEASED. FOUND LT BRAKE CROSSOVER LINE RUBBING ON RUDDER CABLE TO RUDDER PEDAL TORQUE TUBE ATTACH ARM (LT), RUBBING CAUSED HOLE IN LINE. REMOVED AND REPLACED BRAKE LINE WITH NEW, BLED BRAKES, OPS CHECK GOOD IAW CIT 560 ULTRA M/M CH 20-10-06 & 32-42-00.

Part: RELAY — FAILED (BRAKE ASSY) · airframe 8,595 hrs · 6,887 cycles

NORMAL BRAKE SYSTEM FAILED ON LANDING, INITIATED EMERGENCY PNEUMATIC STOP. FOUND SKID CONTROL MOTOR RELAY CONTACTOR WELDED CLOSED & PUMP OPERATES CONTINUOUSLY. REPLACED RELAY WITH A NEW RELAY PER CE 560 MM 32-42-08. REPLACED SKID CONTROL MOTOR / PUMP ASSY WITH A REPAIRED UNIT DUE TO CONTINUOUS OPERATION IN FLIGHT PER CE560 MM 32-42-06. SERVICED EMERGENCY BRAKE / GEAR BOTTLE PER CE560 MM 12-13-01. BLED BRAKE SYSTEM PER CE560 MM 32-42-00. OPS CHECK BRAKE SYSTEM NORMAL.

Part: PEDAL — STIFF (COCKPIT) · airframe 8,490 hrs · 6,804 cycles

BRAKES ARE VERY HARD TO PUSH, THE TOPS OF BRAKE PEDALS SEEM TO BE TOO FAR FORWARD IN THE FRAME. TESTED LT AND RT BRAKES ON PILOT & CO-PILOT SIDES, OPS CHECKS GOOD AT THIS TIME. ALL WORK DONE IAW CESSNA 560 MM CHAPTER 32-42-00.

Part: ACTUATOR — BROKEN (FLAP)

DURING PHASE 2 INSPECTION, FOUND HEAD OF BOLT SHEARED CLEAN. THIS IS ONE OF FOUR BOLTS HOLDING BARREL TO BASE OF THE FLAP ACTUATOR. BOLT HEAD WAS HELD CAPTIVE BY SAFETY WIRE IN CONJUNCTION WITH THREE REMAINING BOLTS. DID NOT APPEAR TO BE OVERTORQUED. POSSIBLE BAD BATCH OF BOLTS.