N324QS

Part: CHECK VALVE — FAULTED (ZONE 700)

AFTER DEPARTURE AND AFTER LIFTING THE GEAR RETRACTION HANDLE, THE RIGHT MAIN GEAR LIGHT REMAINED ILLUMINATED. THE TOWER ALSO CONFIRMED THAT THE RIGHT MAIN GEAR WAS STILL EXTENDED IN THE DOWN POSITION. WE RAN THE QRH AND EXTENDED THE LANDING GEAR AND ALL THREE GREEN LIGHTS ILLUMINATED AND WE LANDED WITHOUT INCIDENT. REMOVED LANDING GEAR CONTROL TEE CHECK VALVE AND REPLACED WITH A NEW IAW AMM 32-30-20. PERFORMED LANDING GEAR CYCLE TEST AND OPERATIONAL TEST, AND AIRCRAFT SYSTEM BLEEED IAW AMM 32-00.00 WITH NO DEFECTS NOTED.

Part: PUMP — LEAKING (HYD SYSTEM) · airframe 14,667 hrs · 9,833 cycles

WHEN LEVEL IN FLIGHT, SELECTED CROSSFEED LEFT, AFTER APPROX 2 MIN SELECTED OFF AND RECEIVED AMBER FUEL BOOST PUMP ON RT, CONDUCTED QRH CHECKLIST AND COULD NOT CLEAR. CHECKLIST SAID TO LAND AS SOON AS PRACTICAL. THIS OCCURRED ON THE PREVIOUS FLIGHT/LEG. THE CAS MSG CLEARED ON THE GROUND. REMOVED R/H ENGINE HYDRAULIC PUMP P/N 51171-02 S/N K1567B DUE TO LEAK NOTED DURING ENGINE RUNS. REPLACED WITH CUSTOMER SUPPLIED OVERHAULED HYDRAULIC PUMP P/N 51171-02 S/N K0660. REMOVED AND REPLACED HYDRAULIC PUMP GEARSHAFT OIL SEAL, CHECK GOOD. COMPLIED WITH ENGINE DRIVEN HYDRAULIC PUMP POST-MAINTENANCE CHECKS. NO FURTHER DEFECTS TO BE NOTED. ALL WORK DONE I/A/W CE-680 AMM29-10-05, PW306C MM 72-60-01.

Part: BRAKE ASSY — VIBRATION (ZONE 700) · airframe 14,662 hrs · 9,830 cycles

THE MLG BRAKE ASSY GENERATING FRICTION & DRAGGING WHEN BRAKES RELEASED & ACFT IN MOTION. ACFT GROUND BEHAVIOR IS SLIGHTLY PULL TO RT WITHOUT BRAKING APPLIED. CANNOT DETERMINE WHICH BRAKE SYS ON RT MLG MALFUNCTIONING. CARBON SMOKE EMANATING FROM RT MLG. VIBRATION PRESENT THROUGHOUT AIRFRAME WHEN ACFT IS SLOWED BELOW 10 KTS WITH BRAKES. VIBRATION ALSO FELT WHEN BRAKE PRESSURE RELEASED & ACFT IN MOTION. INSPECTED BRAKES FOR LEAKS OR DEFECTS; NONE FOUND. TIRES SPIN FREELY, NO DRAGGING, APPLIED HYDS & ACTUATED BRAKES, BRAKES RELEASE WITH NO DRAG. SAME TO LT SIDE. NO ISSUES ON LT SIDE. CHECKED BRAKE WEAR OF ALL BRAKES, FOUND ALL BRAKES WORN EVENLY WITH ONLY 1/32 DIFFERENCE BETWEEN BRAKES. ACCESSED BRAKE INTERCONNECT SLIDE ASSY, CLEANED & LUBED SLIDE ASSYS & VERIFIED SMOOTH OPS OF SLIDES, NO BINDING. NO FURTHER ACTION. RT BRAKES OPS CHECK GOOD, NO BINDING OR DRAGGING. WORK PERFORMED IAW AMM 32-42-20 AND 32-42-00.

Part: FLAP SYSTEM — FAULTED · airframe 14,193 hrs · 9,513 cycles

FLAPS FAIL AMBER CAS: UPON FLAP SELECTION DURING APPROACH CAUSING A FLAPS FAIL CAS MESSAGE (ALSO TRIGGERED GRD PROX FAIL AND WINDSHEAR FAIL CAS MESSAGE). SYSTEM DID NOT RESET BY FOLLOWING QRC AND FLAPS FAIL STAYED ILLUMINATED. UPON POST FLIGHT NOTED FLAPS WERE EXTENDED FOR APPROXIMATELY 1 INCH. SEE PICTURES. CORRECTIVE ACTION: AT POWER UP, NO FLAP FAIL CAS, WINDSHEAR FAIL CAS, GROUND PROXIMITY FAIL CAS NOTED. FOUND 3 BITE FAULTS ON FLAP CONTROLLER. BITE (2)= POWER DRIVE UNIT (POU) FAULT. BITE(3)= COMMAND ERROR. BITE(6)= NO COMMAND FAULT. PERFORMED RESET (CLEAR) THE BITE FAULT CODES, QUICKLY PUSH THE FLAP RESET ANNUNCIATOR SWITCH IN THE COCKPIT THREE TIMES IN TWO SECONDS TO RESET THE FAULT CODES. USE THE FLAP HANDLE TO OPERATE THE FLAPS THROUGH 7 CYCLES. ON THE BITE ANNUNCIATORS ON THE FLAP CONTROLLER AND RECORDED NO BITE FAULT CODES. PERFORMED VISUAL INSPECTION OF THE FLAP SYSTEM WITH FLAPS DOWN. INSPECTED FLAP PANELS, FLAP ISLAND TRACKS, AND FLAP ROLLERS FOR INDICATIONS OF WEAR AND DAMAGE, NO FAULTS NOTED. CHECKED FLAP ACTUATORS FOR CORRECT OIL LEVEL AND ADDED FLAP ACTUATOR OIL - MIL-L-7808 IF NEEDED. NO OIL LEAKS NOTED. ALL WORK PERFORMED IAW CE680 AMM 27-50-00-FLAP SYSTEM - TROUBLESHOOTING AND IAW AMM 12-20-27-FUGHT CONTROLS LUBRICATION - SERVICING. NO FAULTS NOTED AT THIS TIME.

Part: SPAR — CORRODED (LT WING) · airframe 14,095 hrs · 9,453 cycles

MECHANICALLY REMOVED 3 AREAS OF CORROSION WITH 1 ADDITIONAL AREA LOCATED ON THE LH AFT WING SPAR, AFT FACE AROUND THE CARRY THROUGH FITTINGS INSIDE FLAP WELL BAY 523AB. MECHANICALLY REMOVED 1 AREA OF CORROSION LOCATED AROUND SPOILER HYDRAULIC PRESSURE LINE CARRY THRU FITTING ON RH WING IN INBD FLAP WELL BAY 623AB. MECHANICALLY REMOVED INTERGRANULAR CORROSION WHICH WAS FOUND DURING UT PROCESS AROUND HYD LINE CARRY THRU FITTING AND RH AFT SPAR, AFT FACE, INBD OF JACKING POINT. MECHANICALLY REMOVED INTERGRANULAR CORROSION WHICH WAS FOUND DURING UT PROCESS AROUND ALL 4 HYD LINE CARRY THRU FITTING AND LH AFT SPAR, AFT FACE, INBD OF JACKING POINT. REPAIRED CORROSION ON LH AND RH AFT SPARS AT HYDRAULIC FEED-THROUGHS PER AQRD ERO-982519 REV IR TITLED "N324QS LH AND RH WING AFT SPAR CORROSION REPAIR" DATE JAN 29, 2025. SUPPORTED BY FORM 8110-3 DATED 01/29/2025. FAA FORM 337 DATED 31 JAN 2025 HAS BEEN COMPLETED.

Part: RIB — CORRODED (ZONE 500) · airframe 14,095 hrs · 9,453 cycles

LH MLG WING RIB LWS 52 INBD SIDE HAS 14 HI-LOK COLLARS WITH CORROSION AROUND THEM. MECHANICALLY REMOVED CORROSION LOCATED IN LH GEARWELL ON INBD/UPPER SIDE OF LWS 52.00 CROSSOVER RIB WHERE 14 HI-LOK'S PLUS 1 ADDITIONAL HI-LOK WERE REMOVED IAW C680 SRM 51-70-02. FOUND CORROSION BLENDS TO BE BEYOND LIMITS IAW C680 SRM 51-70-02 EXCEEDING .002" OF MATERIAL REMOVED FROM NOMINAL THICKNESS. REPAIRED CORROSION BLENDS IAW TEXTRON ENGINEERING FIELD REPAIR FR-680-0242-14380 REV- TITLE: FIELD REPAIR-CORROSION, LH WING, AFT RIB FITTING, WS52.00 DATED 06-NOV-2024.

Part: DOOR FRAME — CORRODED (ZONE 200) · airframe 14,095 hrs · 9,453 cycles

BLENDED TWO AREAS OF CORROSION FOUND ALONG THE EMERGENCY EXIT DOOR CONTOUR RINGS. REMOVED THE CONTOUR RINGS AND BLENDED ADDITIONAL CORROSION FOUND. PERFORMED NDT AND REPORTED RESULTS OR REPAIR DISPOSITION. EMERGENCY EXIT DOOR P/N 6911251-6 WAS SENT OUT FOR REPAIR.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 13,085 hrs · 8,728 cycles

ON ENTRY TO THE AIRCRAFT NOTICED THAT IN THE FULL DOWN POSITION WITH THE ENTRY HANDLE IN THE OVER CENTER LOCKED POSITION. THE DOOR IS NOT LOCKED DOWN IT STILL TRYS TO GO BACK UP ABOUT 2-3 INCHES. THE DOOR IS LOOSE AND NOT SECURED. WHEN WEIGHT IS PUT BACK ON IT THE DOOR GOES BACK DOWN. //SIGNOFF// GAINED ACCESS TO AIRCRAFT AND OPENED MED NOTING WHEN THE DOOR WAS FULLY OPENED, THE STAIRS WOULD SLIGHTLY MOVE UP AND DOWN. ADJUSTED MED REF CE680 MM 52-10-30. VERIFIED DOOR OPERATION WAS GOOD WITH NO DEFECTS NOTED. ALSO NOTED THE STAIRS NO LONGER MOVED WHEN IN THE OPEN AND LATCHED POSITION.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 12,949 hrs · 8,632 cycles

AFTER ENGINES ARE SHUTDOWN WITH APU RUNNING AND BLEED AIR ON APU, THE CABIN FILLS WITH A VERY HEAVY JET FUEL SMELL. THIS WAS POINTED OUT BY PASSENGERS AS WELL. WHEN AIRCRAFT WAS SHUTDOWN WINDS WERE CALM. REMOVED TEMP CONTROLLER AND INSTALLED OVERHAULED CONDITION TEMP CONTROLLER JAW CE680 AMM 21-61-00. TECHS PERFORMED ECU DUCT BUMOUT/OEAN PROCEDURE IAW TC-C68-21-1001. TECHS PERFORMED ECU OPS AND FUNCTIONAL CHECKS JAW AMM 21-61-00, OPS AND FUNCTIONAL CHECKS GOOD WITH NO DEFECTS NOTED. NO FURTHER OII/EXHAUST SMELL COMING FROM CABIN/COCKPIT GASPER DUCTS.

Part: LIGHT — FAILED · airframe 12,465 hrs · 8,327 cycles

CABIN EMERG LIGHT: TEST OF EMERGENCY LIGHTS FAILED. IN ARM POSITION, NO INTERIOR OR EXTERIOR LIGHTS ARE FUNCTIONING. IN ON POSITION, EXTERIOR LIGHTS FUNCTION BUT THE FORWARD SECTION OF INTERIOR LIGHTS ARE DEAD. THE BACK SECTION OF CABIN THE LIGHTS ARE DIM.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · corrosion level 2 · airframe 12,108 hrs · 8,100 cycles

CORROSION WAS FOUND ON THE LH & RH AFT FUSELAGE SKIN ALONG THE AFT FUSELAGE CLOSEOUT FAIRING ATTACHMENT LINE. REPAIRED PER AQRD ERO 972834. THIS IS A MAJOR/PERMANENT REPAIR.

Part: CONTROL PANEL — DEFECTIVE (CABIN PRESSURE) · airframe 11,376 hrs · 7,591 cycles

CABIN ODOR: PRESSURIZATION CONTROLLER FAULT LIGHT ILLUMINATED IN FLIGHT, ACCOMPANIED BY LIGHT OILY SMELL IN COCKPIT AND CABIN AIR CONDITIONING SYSTEM. APU WAS RUNNING ON GROUND AND UP TO 10,000 FT AGL (T2PL6D008M0Y4). R & R PRESSURIZATION CONTROL IAW MM 21·31-00 WITH TESTED PARTS. YELLOW FAULT LIGHT WAS STILL PRESENT ON CABIN ALTITUDE CONTROLLER. ALL OTHER CHECKS WERE OK: CABIN PRESSURIZED/DEPRESSURJZED NORMALLY IN MANUAL MODE. CONTACTED MCC AND INSTALLED NEW PRESSURIZATION CONTROL PANEL IAW MM 21·31·00. OPS CHECKS GOOD. COMPLEDTED NJA ECS DUCT BURN OUT TASK CARD TC-680-21-120905M & CE-680 MM 21-21-03. RAN APU BLEED AIR AFTERWARDS WITH NO SMELL NOTED. WATER SEPERATOR LEAK CHECKS GOOD.

Part: SPAR WEB — CORRODED (RT WING) · airframe 10,758 hrs · 7,193 cycles

REPAIRED CORROSION ON THE RT WING FWD SPAR WEB, IAW AEROSPACE QRD ERO-104487 REV: A TITLED "N324QS - RT WING MID SPAR WEB CORROSION REPAIR" DATE: JANUARY 26, 2021 AND SUPPORTED BY FAA FORM 8110-3 DATED JANUARY 26, 2021.

Part: AUTOPILOT SYS — FAILED · airframe 10,611 hrs · 7,115 cycles

WHILE LEVELING AT FL260, FO FLYING FROM RIGHT SEAT, WE NOTED THE LEFT SIDE ALTIMETER WAS READING APPROXIMATELY 300' LOW AND VSI SHOWED A DESCENT. FD MODE OFF CAS MESSAGE CAME ON AND AUTOPILOT FAILED. WE VERIFIED THAT THE RIGHT SIDE SYSTEM WAS CORRECT AND DIVERTED. AIRCRAFT SAT IN RAIN OVERNIGHT AND ENTIRE FLIGHT WAS IN LIGHT TO MODERATE PRECIP. OAT AT FL260 WAS AROUND -20 TO -30 C. PERFORMED AIR DATA TEST, PER CE-680 AMM 34-11-00 AND FOUND NO LEAKS AND THAT THE PITOT STATIC SYSTEM IS WORKING PROPERLY. NO FURTHER DEFECTS NOTED AT THIS TIME.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 10,600 hrs · 7,106 cycles

BLENDED 85 AREAS OF CORROSION ON THE UPPER SURFACE OF THE LOWER FUSELAGE SKIN AND STRINGERS, COMMON TO THE DROPPED AISLE FLOOR. PERFORMED NDT AND REPORTED FOR REPAIR DISPOSITION. CLEANED, TREATED, AND PRIMED AREAS FOUND ACCEPTABLE. FABRICATED AND INSTALLED REPAIR DOUBLERS ON REMAINING AREAS, PER ENGINEERING ORDER.

Part: HINGE BRACKET — CORRODED (VERTICAL STAB) · airframe 8,900 hrs · 5,930 cycles

MECHANICALLY BLENDED CORROSION ON THE MIDDLE RUDDER HINGE BRACKET UPPER HINGE HALF ON VERTICAL STABILIZER NEAR THE BONDING STRAP HOLE, PERFORMED EDDY CURRENT AND ULTRASONIC THICKNESS INSPECTIONS AND SUBMITTED FINDINGS TO MANUFACTURER ENGINEERING. TREATED METAL AND PRIMED IAW ENGINEERING REPAIR MEMO.

Part: TRANSMITTER — MALFUNCTIONED (LT WING TE FLAP) · airframe 7,909 hrs · 5,255 cycles

AT FL410 IN CRUISE FLAPS WENT TO 7 DEGREE AMBER INDICATION WITH ASSOCIATED FLAPS FAIL, GROUND PROX AND WINDSHEAR WARNINGS WITH ASSOCIATED AURAL WARNING. FLAPS DID NOT EXTEND, NO LIMITATION EXCEEDED. ON APPROACH, MATCHED 7 DEGREE INDICATION WITH FLAP HANDLE AND WORKED NORMALLY. LANDED FLAP 7. TESTED SYSTEM AND FOUND LEFT FLAP POSITION TRANSMITTER DEFECTIVE. REMOVED LEFT FLAP POSITION TRANSMITTER AND INSTALLED MODIFIED POSITION TRANSMITTER. PERFORMED FLAP SYSTEM ELECTRICAL RIGGING. WORK PERFORMED IAW CE680 MM 27-51-00, OPS CHECKED GOOD. NO BITE FAULTS AFTER OPS CHECKS.

Part: LINK — SHEARED (FLIGHT CONTROL) · airframe 6,367 hrs · 4,272 cycles

DURING TAKEOFF ROTATION, A DISTINCT BUMP & REARWARD FORCE OCCURRED IN THE CONTROL YOKE. AS THE ACFT ACCELERATED, EXCESSIVE NOSE DOWN TRIM WAS REQUIRED. AT MAXIMUM NOSE DOWN SETTING -1.2, ANY SPEED ABOVE 156 KNOTS WAS OUT OF TRIM & REQUIRED FWD CONTROL YOKE FORCE. INSPECTED THE LINEAR ACTUATOR, AND FOUND INSTALLED PROPERLY. FURTHER INSPECTION FOUND THE LINK ASSEMBLY SHEARED. THE INBD LINK WAS REMOVED & THE REPLACEMENT LINK WAS INSTALLED. THE ACTUATOR ASSEMBLY WAS INSTALLED & RECONNECTED IAW MM 27-40-00 & ASL680-27-02. PERFORMED RIGGING OF MACH TRIM SYS IAW MM 27-40-00. RIGGING & TRAVEL CHECKED GOOD. PERFORMED THE OPS CHECK, CHECKED GOOD. VERIFIED INSTALLATION & OPS CHECKED GOOD.

Part: TRANSISTOR — FAILED (LIGHT) · airframe 6,185 hrs · 4,130 cycles

WITH BATTERY POWER ON, THERE IS A STRONG ELECTRICAL ODOR, NO SMOKE. WHILE REPAIRING THE FLOOD LIGHTS, FOUND RESISTOR & TRANSISTOR BURNED OUT IN THE FLOOD LIGHT CIRCUIT. ODOR WENT AWAY AFTER REPLACING THESE COMPONENTS. FLOOD LIGHTS OPS CHECKED GOOD. IAW AMM 33-10-00.

Part: MONITOR — FAILED (ENGINE VIBRATION) · airframe 5,127 hrs · 3,434 cycles

RIGHT ENGINE VIBRATION MASTER WARNING, CLIMBING THROUGH 11,000 FT FOR 12,000 FT IN CLIMB DETENT. NO VIBRATION WAS PHYSICALLY FELT. REMOVED AND REPLACED ENGINE VIBRATION MONITOR IAW MM 77-20-00. REMOVED AND REPLACED RIGHT ENGINE VIBRATION ACCELEROMETER IAW MM 77-20-00. COMPLIED WITH POST RUN VIBRATION SURVEY IAW MM 71-00-00. OPS CHECKED GOOD.

Part: PUMP — DAMAGED

EXTENSIVE FRETTING DAMAGE ON PRIMARY JET PUMPS WHERE CLAMP W991-18DE ATTACHES TO. DAMAGE ALSO OCCURS TO ADJACENT PLUMBING. DAMAGE IS NOT SEEN UNLESS CLAMPS ARE REMOVED.

Part: ADC — INOPERATIVE · airframe 1,711 hrs · 1,104 cycles

AT FL410, STDBY HORIZON HAD RED X'S OVER AIRSPEED, AND ALTITUDE. ON DECENT THRU FL200 THE DATA DISPLAYED. INSTALLED A REPAIRED STBY ADC. OPS CHECKED GOOD. WORK DONE IAW MM 34-22-00 AND CH 34-11-00 AND FAR 91.411, PART 43, APPENDIX E.

Part: PRESSURE SWITCH — FAULTY (FUEL SYSTEM) · airframe 854 hrs · 567 cycles

RT ENG FUEL FILTER BYPASS AMBER CAS MESSAGE FL 410 REPEAT WRITE UP. R & R RT ENG FUEL FILTER AND PRESSURE SWITCH. OPS AND LEAK CHECKS GOOD AT THIS TIME. THERE ARE NO FURTHER CAS MESSAGES. ALL WORK DONE IAW MM, CHAPTER 73-10-03.

Part: OXYGEN MASK — MALFUNCTIONED (COCKPIT) · airframe 9,346 hrs · 7,649 cycles

BOTH PILOT AND COPILOT OXYGEN MASK HAVE REDUCED OXYGEN FLOW, AS IF AN OBSTRUCTION OF VALVE FAILURE OCCURED. RESEATED OXYGEN MASKS OPS CHECKED SATISFACTORY IAW MM 35-00-00.

Part: SQUAT SWITCH — WORN (MLG) · airframe 9,242 hrs · 7,564 cycles

LANDING GEAR WILL NOT RETRACT. GEAR INDICATES DOWN AND 3 GREEN . GEAR HANDLE WILL NOT RAISE AS IF LOCKED DOWN. JACKED AIRCRAFT AND FOUND LH SQUAT SWITCH TO BE IN GROUND MODE. WITH SLIGHT SIDE LOAD TO THE SCISSOR LINK MOVES SWITCH SHAFT LATERALLY BACK INTO FLIGHT. SWITCH SHAFT SHOULD NOT HAVE A LATERAL WIGGLE TRIGGERING GROUNF FROM FLIGHT AND VISE VERSA. WAS ABLE TO NUDGE SHAFT TO TRIGGER GROUND AND FLIGHT MODE. SWITCH FAULTY FROM STOCK. REMOVED LH SQUAT SWITCH AND INSTALLED NEW. RIGGED AND TESTED THROUGHLY. PERFORMED GEAR SWINGS. GEAR SWINGS OPS CHECKED GOOD. RAN ENGINES AND PRESSURIZED AIRCRAFT ON GROUND AND IN FLIGHT MODE. LH SQUAT SWITCH OPERATES NORMALLY AT THIS TIME IAW CE560 MM 32-61-00 AND 21-31-00.

Part: BRAKE ASSY — WEAK (MLG) · airframe 9,241 hrs · 7,563 cycles

COPILOT RT BRAKE IS MUSHY. BLED RT BRAKE SYSTEM IAW CE-560 M/M 32-42-00. PERFORMED TAXI CHECK. R/H BRAKE SYSTEM OPS CHECK GOOD AT THIS TIME.

Part: NONE — NONE (NONE) · airframe 7,648 hrs · 6,292 cycles

CLEAR AIR TURBULENCE, NO WARNING, 16000 FT LEVEL FLIGHT, ABOUT 260 KTS, AUTOPILOT DISENGAGED, ATTITUDE REMAINED LEVEL, ALTITUDE +/- ABOUT 100, FORCED VIOLENTLY AGAINST SEAT BELTS, CREW HIT CEILING, TOILET SEAT FLIPPED INTO AISLE, EVENT LASTED LESS THAN 5 SECONDS. DISASSEMBLED AIRCRAFT AND INSPECTED PER CE560 M/M CH 5-50-00 PARA 5, FOUND TO BE SATISFACTORY AT THIS TIME, RE-ASSEMBLED WING & TAIL PANELS. DISASSEMBLED AIRCRAFT AND INSPECTED PER CE560 M/M FOUND TO BE SATISFACTORY, REASSEMBLED TAIL & WING PANELS.

Part: BRAKE — MALFUNCTIONED (MLG)

BRAKES VERY SPONGY, ACCUMULATOR GAUGE READS IN YELLOW. BLED BRAKES IAW CE560 M/M 32-42-00 SERVICE ACCUMULATOR.

Part: RELAY — MALFUNCTIONED (ANTI-SKID SYS) · airframe 7,151 hrs · 5,884 cycles

WHEN GEAR SELECTED DOWN, BRAKE PRESS LOW AND ANTI SKID INOP ANNUNCIATORS LIT. DIVERTED TO CMH, UPON 2ND GEAR EXTENSION NO ANNUNCIATORS ILLUMINATED. INSTALLED NEW SKID CONTROL RELAY (K74) AND NEW HI-PRESSURE SWITCH (S168) IAW CE-560 WDM 32-40-01. OPS CHECK GOOD.

Part: CHECK VALVE — FAILED (BRAKES) · airframe 6,864 hrs · 5,666 cycles

RIGHT BRAKE PEDAL ON CO-PILOT SIDE WAS MUSHY AND THEN WENT COMPLETELY TO THE FLOOR DURING TAXI. REMOVED AND REPLACED CHECK VALVE. BLED BRAKES IN ACCORDANCE WITH CE560 MM 32-42-00. OPERATIONAL CHECK GOOD.

Part: O-RING — LEAKING (MASTER CYLINDER) · airframe 6,864 hrs · 5,666 cycles

CO-PILOT RIGHT BRAKE PEDAL LOST PRESSURE DURING TAXI. BLEED OFF CAUSED A SOFT PEDAL. INSPECTED SYSTEM FOUND, CO-PILOTS RT MASTER CYLINDER LEAKING FLUID. REMOVED AND REPLACED O-RINGS. BLED BRAKE SYSTEM. OPERATIONAL CHECKS AND LEAK CHECKS GOOD. MAINT PERFORMED IAW CC560 MM CHAPTER 32-42-00.

Part: O-RING — LEAKING (LT BLEED PORT) · airframe 6,860 hrs · 5,664 cycles

CREW REPORTED RIGHT BRAKE PEDAL LOSES PRESSURE DURING TAXI. PRESSURE BLEEDS OFF CREATING A SOFT PEDAL. REPLACED O-RINGS ON LEFT BRAKE BLEEDER PORT, BLEED BRAKES, CHECKED BRAKE RESERVOIR AND LINES FOR LEAKS. CHECKED GOOD. PERFORMED CO-PILOTS SPONGY BRAKE CHECKLIST. EVERYTHING CHECKED GOOD IAW CESSNA MM 32-42-00.

Part: WARNING LIGHT — ILLUMINATED (THRUST REVERSER) · airframe 6,222 hrs · 5,099 cycles

ON TAKEOFF ROLL AT 50 KNOTS, THE LEFT ENGINE THRUST REVERSER ARMED LIGHT CAME ON. REJECTED TAKEOFF. ITEM IS UNDER INVESTIGATION.