N587QS

Part: WIRE HARNESS — FAULTED (ANTI-SKID SYS) · airframe 14,330 hrs · 10,963 cycles

DURING FLIGHT ANTISKID LIGHT WOULD ILLUMINATE AND EXTINGUISH BEFORE COMPLETION OF AMBER C1 ANTISKID INOP CHECKLIST. DURING TAXI, ANTISKID INOP LIGHT ILLUMINATED (TAXIWAY WAS CLEAR OF ICE CONTAMINATION), LT BRAKE WOULD FAIL CAUSING ACFT TO AGGRESSIVELY TURN RT. AFTERWARDS, THE LT BRAKE WOULD AGGRESSIVELY ACTIVATE & CAUSE ACFT TO MANEUVER MOMENTARILY WITH UNCOMMANDED CONTROL. OCCURED TWICE. 11-29-25 T/S THE BRAKE ANTI SKID FAULT TO A LT MLG WBA HARNESS. COMPLETED WIRING CKS & PLACED PARTS ON ORDER RT & LT MLG-WBA HANESS REMOVED & INSTALLED A NEW LT MLG WBA HARNESS, ACCOMPLISHED SQUAT SWITCH RIGGING, LANDING GEAR SYS CHECKS & BRAKE ANTI SKID CKS. ALL CHECKS, INDICATIONS ARE NORMAL & NO DEFECTS . RESTORED ALL ACCESS. WORK DONE WITH AMM 32-61-00, 32-10-00 & 32-44-00. PERFORMED TAXI CHECK WITH NO DEFECTS NOTED.

Part: WIRE SPLICE — DAMAGED (ZONE 200) · airframe 14,232 hrs · 10,887 cycles

THE LEFT FLOOR EMERGENCY LIGHTS ARE EXTREMELY DIM. ALL OTHER LIGHTS ARE BRIGHT. WHEN THE FLOOR LIGHTS ARE TAPPED, THEY GET BRIGHT FOR A SECOND THEN RETURNS TO BEING DIM. NSPECTED THE LIGH CONNECTION AND FOUND SPLICE END TO BE DAMAGED. RE-SPLICED THE DAMAGED END OF THE T WIRE IAW CE-560XL AMM 20-00-00. OPS CHECK GOOD.

Part: HANDLE — BINDING (ZONE 800) · airframe 14,061 hrs · 10,741 cycles

MAIN CABIN DOOR HANDLE REQUIRES EXCESSIVE FORCE TO OPEN OR CLOSE DOOR FROM INSIDE CABIN. INSPECTED AND NOTED TWO DOOR PINS ADJUSTED TO TIGHT AND BINDING IN THE ECCENTRIC HOLES CLOSE DOOR FROM INSIDE CABIN. ON DOOR FRAME. PERFORMED LATCH PLATE ADJUSTMENT TO THE MAIN CABIN DOOR IA W CE560XL AMM S2-10-00. OPS CHECKS GOOD.

Part: STRAKE — CORRODED (ZONE 300) · airframe 13,756 hrs · 10,504 cycles

LH AND RH STRAKES HAVE SEVERAL AREAS OF CORROSION ON UPPER AND LOWER SURFACES. PERFORMED 4 EACH DOUBLER REPAIRS TO LH STRAKE AND PERFORMED 6 EACH DOUBLER REPAIRS TO RH STRAKE. ALL WORK WAS ACCOMPLISHED IN ACCORDANCE WITH EO NO: C56-53-0001 TITLED: MINOR REPAIR SPECIFICATION FOR MODEL 560XL AND 560XLS VENTRAL STRAKES REV 0, DATED 25JAN2016.

Part: STRAKE — CORRODED (ZONE 300) · airframe 13,756 hrs · 10,504 cycles

LH STRAKE TRAILING EDGE WEDGE FITTING

Part: DOOR — OUT OF ADJUST (MAIN)

MAIN CABIN DOOR NEEDS ADJUSTED. AFTER LANDING WITH COLD SOAKED AIRCRAFT, MAIN CABIN DOOR WILL NOT STAY IN DOWN LOCKED POSITION USING CABIN DOOR HANDLE. CORRECTIVE ACTION: ADJUSTED SUPPORT STRUT ASSY AS NEEDED. NO DEFECTS FOUND AT THIS TIME OPS CHECKS GOOD. PERFORMED WORK IAW MM 52-10-01

Part: LIGHT — INOPERATIVE (CABIN) · airframe 13,215 hrs · 10,109 cycles

AISLE EMERGENCY LIGHTING ON LEFT, FRONT HALF OF THE AISLE ONLY LIGHTS FROM THE GALLEY TO JUST FORWARD OF SEAT 3 (AFT FACING SEAT ON LEFT SIDE). IT IS INOP FROM THAT POINT BACK TO MID -FUSELAGE. UPON INITIAL INVESTIGATION FOUND AISLE LIGHTING WAS COVERED BY FLOOR CARPET. PERFORMED FUNCTION TEST OF THE EMERGENCY LIGHTS IAW AMM 33-50-00-7100. FUNCTION TEST PASSED.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 12,958 hrs · 9,915 cycles

EMERGENCY LIGHTS BATTERY INOP ON PRE-FLIGHT. REMOVED FAULTY FWD BATTERY PACK & INSTALLED OVERHAULED BATTERY PACK IAW MM 33-50-01. REMOVED FAULTY AFT BATTERY PACK & INSTALLED OVERHAULED BATTERY PACK IAW MM 33-50-01. CONNECTED EXTERNAL POWER & CHARGED FOR 1.75 HOURS IAW MM 33-50-01. REMOVED EXTERNAL PWR & BATTERY POWER. PERFORMED E LIGHTING BATTERY PACK OPS CHECK IAW MM 33-50-01, NO DEFECTS NOTED. ALL E LIGHTS ILLUMINATED

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 12,722 hrs · 9,753 cycles

MAIN DOOR WILL NOT LOCK IN DOWN PISITION FROM INSIDE CABIN. IT WILL LATCH DOWN FRIM OUTSIDE HANDLE. OP'S CHECKED DOOR COMFRIMED THAT IT WASNT LOCKING. ADJUSTED THE MAIN DOOR PUSH PULL ROD AND OP'S CHECKED IT MULTIPLE TIMES UNTIL I ADJUSTED IT ONE TURN FWD FROM ORIGINAL POS AND OP'S CHECK GOOD WITH NO DEFECTS NOTED. CALLED MCC AND THEY ELECT TO SIGN IT OFF ALL WORK DONE IN REF WITH CE 560 AMM 52-10-00

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 12,542 hrs · 9,619 cycles

THE MAIN DOOR IS HEAVILY WEIGHTED TOWARDS THE CLOSED POSITION. WHEN INSIDE & CLOSING THE DOOR IT SLAMS SHUT. WHEN ON THE OUTSIDE WITH A CLOSED DOOR, VERY DIFFICULT TO OPEN. PERFORMED A GVI IAW AMM 52-10-00. A COMPLETE DOOR INTERNAL STRUCTURE DETAILED INSP PER AMM 52-10-00 REVEALED FOREIGN OBJECT FOUND INSIDE DOOR LOCKING MECHANISM. AFTER THOROUGH INTERNAL INSPECTION OF ALL BELLCRANKS & ROD ENDS FOUND NO DAMAGE TO ANY INTERNAL PARTS. LUBED DOOR INTERNAL LOCKING MECHANISMS & PERFORMED DOOR OPS AND FUNCTIONAL CHECKS WITH DOOR CLOSEOUT REMOVED & INSTALLED. DOOR OPS CHECKS ARE GOOD, DOOR SHUTS NORMALLY. CHECKED CABLE TENSIONS FOUND TO BE 142 LBS WITHIN TECH DATA LIMITS PER AMM 52-10-03.

Part: BATTERY PACK — DISCHARGED (UNKNOWN) · airframe 12,123 hrs · 9,304 cycles

EXTERIOR EMERGENCY LIGHTS AND AFT LEFT BULKHEAD EXIT SIGN ARE INOP WHEN THE MAIN BATTERY IS OFF. CHARGED FOR 1.5 HOURS AND HAD THE SAME RESULT.

Part: SWITCH — OUT OF ADJUST (NLG) · airframe 11,820 hrs · 9,086 cycles

ON TAKE OFF, RECEIVED A FLASHING HYD PRESS WITH A MASTER CAUTION AFTER FLAP RETRACTION. GEAR & FLAPS RETRACTED ON SCHEDULE. HYD PRESS, NLG UNLOCK LIGHT, & STAB MISCOMP. RAN HYD PRESS QRH. PULLED & RESET HYD CONTROL CB IAW QRH. MAINTAINED 200KTS & FL 310 IAW QRH. HYD PRESS REMAINED ILLUMINATED FOR 30 MIN JUST PRIOR TO LANDING, WHEN LIGHT EXTINGUISHED. STAB MISCOMP STAYED ON & NLG UNLOCK LIGHT. PRIOR TO APPROACH, PUT DOWN MLG & FLAPS. NORMAL INDICATIONS. 3 GREEN FOR MLG & STAB MISCOMP EXTINGUISHED. PERFORMED STRUT REPACK & OPS CHECKED GOOD, PERFORMED ENGINE RUNS & SERVICED HYD SYS, OPS & LEAK CHECKED GOOD, WORK DONE IAW AMM 32-30-00. PERFORMED CHECKS OF FLAPS & STAB, CHECKED GOOD. OPS CHECKED GEAR SWINGS, GETTING A GEAR WARNING & AN UNLOCKED ANNUNCIATOR. ADJUSTED NLG UPLOCK SWITCH, UNLOCKED LIGHT WENT AWAY BUT HORN IS STILL ON. PERFORMED STRUT REPACK & OPS CHECKED GOOD,

Part: BATTERY — DEFECTIVE (ZONE 100) · airframe 11,738 hrs · 11,738 cycles

MAIN EXIT SIGN/LIGHT: FORWARD EMERGENCY POWER BATT PACK WILL NOT TAKE CHARGE - LIGHTS ARE OUT. // SIGNOFF // REMOVED AND REPLACED THE FWD EMERGENCY BATTERY PACK IAW CB60XLS MM 33-51-01, OPERATIONAL CHECK IS GO0D AT THIS TIME

Part: SEAL — DEFECTIVE (PAX DOOR) · airframe 10,451 hrs · 8,057 cycles

MAIN DOOR: MAIN CABIN DOOR OPEN WITH EXTREME DIFFICULTY AFTER BEING AT ALTITUDE FOR ANYTHING OVER ONE HOUR. I.E. ONCE OPEN ON THE GROUND IT OPERATES FINE. REPEAT WRITE UP///SIGN-OFF///REPLACED SHEARED OFF BOLT AND ALL 3 ACCOUSTIC LINER SEALS IAW CE-560XLS AMM 52-10-04.OPS CHECK OK.

Part: CONTROL VALVE — DEFECTIVE (ACM FLOW) · airframe 10,324 hrs · 7,962 cycles

ACM OVERHEAT ON TAKEOFF. THERE WAS A HOT/BURN SMELL IN THE AIRCRAFT. COMPLETED CHECKLIST AND LANDED. DID NOT DECLARE AN EMERGENCY. DID NOT LAND OVER WEIGHT. COMPLIED WITH OPERATIONAL PROCEDURE. REMOVED AND REPLACED RH FLOW CONTROL VALVE. IAW 560XL MM 21-61-00. OPS CHECK GOOD.

Part: DOOR — FROZEN (MAIN CABIN) · airframe 10,108 hrs · 7,800 cycles

MAIN CABIN DOOR FROZEN SHUT. OPENED EMERGENCY EXIT DOOR TO EGRESS AIRCRAFT. EMERGENCY EXIT DOOR REQUIRES REINSTALLATION. COMPLIED WITH TASK T2PL6D007YVC5. INSPECTED THE CABIN EMERGENCY EXIT DOOR AND SURROUNDING AREAS FOR DEFECTS. NO DEFECTS NOTED. INSTALLED THE CABIN EMERGENCY EXIT DOOR ASSEMBLY. OPERATIONAL CHECK WAS GOOD. ALL WORK COMPLIED WITH, IAW THE MAINTENANCE MANUAL CHAPTER 52-20-00.

Part: RELIEF VALVE — ABNORMAL (BRAKES) · airframe 10,015 hrs · 7,734 cycles

WHILE TAXIING IN, THE "LOW BRAKE PRESSURE" AND "ANTI SKID INOP" AMBER MESSAGES ILLUMINATED. A FEW SECONDS LATER, THE BRAKE PEDALS WENT TO THE FLOOR AND WE HAD ALMOST NO BRAKES. NO BREAKERS WERE TRIPPED. SIGN OFF. REMOVED POWER BRAKE RELIEF VALVE CAUSING LOW PRESSURE P/N 1785-2 S/N 1371 AND INSTALLED OVH BRAKE RELIEF VALVE, IAW 560XLS AMM CH 32-44-20. OPERATIONS CHECK GOOD.

Part: COUNTERBALANCE — OUT OF ADJUST (PAX DOOR) · airframe 9,820 hrs · 7,578 cycles

THE MAIN CABIN DOOR IS OUT OF ADJUSTMENT. IT IS HARD TO OPEN FROM THE INSIDE AND IT SLAMS SHUT WHEN CLOSING.ADJUSTED CABIN ENTRY DOOR COUNTERBALANCE ASSEMBLY IAW CE-560XLS AMM.

Part: SKIN — CRACKED (NLG DOOR) · airframe 8,137 hrs · 6,306 cycles

RIGHT NOSE LG DOOR SKIN CRACKED AT THE LATCH.

Part: WINDSHIELD — DAMAGED (COCKPIT) · airframe 7,295 hrs · 5,672 cycles

DURING CRUISE FLIGHT AT FL400 AFTER 25 MINUTES AT FL400 A STRONG SMELL OF BURNING WIRES. THAT SMELL CONTINUED ON THE FLIGHT DECK THEN AFTER 15 MINUTES OF THE BURNING SMELL THE RIGHT WINDSHIELD HEAT FAULT LIGHT ANNUNCIATOR ILLUMINATED. WE THEN DECLARED AN EMERGENCY AND DIVERTED TO KAVL. TROUBLESHOOTING REVEALED P3 TERMINAL ON WINDSHIELD BURNED. REMOVED DAMAGED WINDSHIELD (RIGHT) AND INSTALLED NEW WINDSHIELD IAW AMM 56-11-00. CUT OFF DAMAGED END OF P3 WIRE AND REPLACED TERMINAL END IAW WDM 20-10-06. INSTALLED NEW WINDSHIELD COATING PLACARD P/N: 6200181-164, WITH REFERENCE TO AMM 11-00-00. OPERATIONAL AND LEAK CHECKS GOOD.

Part: SKIN — DENTED (RT WING) · airframe 6,975 hrs · 5,447 cycles

RIGHT LOWER WING SKIN AT RWS 143.07 DENTED, REPAIRED IAW ERO-877762.

Part: STRUCTURE — CORRODED (TAILCONE) · airframe 6,975 hrs · 5,447 cycles

CORROSION FOUND UNDER THE DATA PLATE ON THE TAILCONE. REPAIRED CORROSION IAW DQ6626.

Part: STRUCTURE — CORRODED (WINGS) · airframe 6,975 hrs · 5,447 cycles

CORROSION FOUND IN MULTIPLE LOCATIONS ON THE UPPER SIDE OF THE LT AND RT WINGS. REPAIRED IAW REPAIR S-560XL-5805/06RD.

Part: STRUCTURE — CORRODED (WING) · airframe 6,975 hrs · 5,447 cycles

CORROSION FOUND IN MULTIPLE LOCATIONS ON THE UPPER SIDE OF THE LT AND RT WINGS. REPAIRED IAW REPAIR S-560XL-5805/06RD.

Part: SPAR — GOUGED (ZONE 300) · airframe 5,780 hrs · 4,528 cycles

GOUGES ON LT AND RT FWD SIDE OF THE VERTICAL SPAR. GOUGE DAMAGE WAS FOUND ON THE FWD SURFACE OF THE LOWER AFT VERTICAL STABILIZER SPAR WEB. REPAIRED IAW SR 5805/05RD.

Part: BULKHEAD — GOUGED (FUSELAGE) · airframe 5,780 hrs · 4,528 cycles

A GOUGE & A SCRATCH WERE FOUND ON THE AFT SIDE OF THE 6611371-1 AFT PRESS BULKHEAD BOND ASSEMBLY AT FS 373.75, RBL 29.63, WL 114.27, NEAR STRINGER 11R. THE GOUGE WAS APPROX 0.173 INCHES IN DIAMETER & 0.013 INCHES DEEP. THE SCRATCH WAS 0.75 INCHES LONG & NEGLIGIBLE DEPTH. THE DAMAGE AFFECTED THE 6211085-35 RADIAL STRAP. THE DAMAGE WAS DUE TO CONTACT WITH AN AN3 BOLT FOR CLAMPS ON FUEL LINES. THE TOTAL BONDED THICKNESS IN THIS AREA IS 0.089 INCHES. REPAIRED IAW S-560XL-5805 04.

Part: BULB — INOPERATIVE (MLG INDICATOR) · airframe 5,442 hrs · 4,248 cycles

WHEN LANDING, LEFT MAIN GEAR DIDN'T HAVE GREEN LIGHT. PERFORMED EMERGENCY GEAR EXTENSION. FOUND THE LT GEAR DOWN & LOCK LIGHT BULBS INOPERATIVE. REMOVED THE FAILED INDICATOR BULBS & INSTALLED NEW BULBS. JACKED ACFT & CYCLED THE GEAR SEVERAL TIMES WITH NO FAILURES. DOWN JACKED ACFT. OPERATIONAL TESTS CHECKED GOOD IAW MM 32-30. BULB REMOVED & INSTALLED . VERIFIED THAT THE LANDING GEAR SHUTTLE VALVES WERE RESET AFTER THE GEAR BLOW DOWN.

Part: BOLT — WORN (ELEVATOR)

TWO PUSH/PULL TUBES THAT ATTACH TO THE AFT ELEVATOR BELLCRANK, WHEN TORQUING ATTACHING HARDWARE, THE NUT SHANKS OUT ON THE BOLT, ALLOWING THE BOLT TO BE ROTATED BY AND AND CAUSING WEAR IN THE BELLCRANK ATTAHCH HOLE. THIS WEAR CAUSES EXCESSIVE PLAY AT THE ATTACH POINT, IN TURN ALLOWING THE BOLT TO BEGIN ROCKING BACK AND FORTH IN THE HOLE AND RESULTING IN CHAFING BETWEEN ATTACHED PARTS. WHEN INSTALLING HARDWARE ASSURE NUT DOES NOT SHANK OUT ON BOLT. REPLACE BOLT IF WORN AND ADD WASHERS AS REQUIRED TO PREVENT NUT FROM SHANKING OUT ON THE BOLT.

Part: SHAFT — WORN (RUDDER)

FOUND GROOVES WORN INTO SHAFT OF THE 2 SCREWS THAT ENTER INTO THE RUDDER ACTUATOR ASSEMBLY. ACFT IS SET FOR CRUISE CONFIGURATION: DURING FLIGHT, TAIL VIBRATES CAUSING GROOVES TO WEAR INTO SHAFT OF SCREWS AT POINT WHERE SCREWS ENTER INTO ACTUATOR.

Part: ACTUATOR — BINDING (ELEVATOR) · airframe 2,155 hrs · 1,648 cycles

ELEVATOR TRIM TAB JAMMED AND COULD NOT BE MOVED ELECTRICALLY OR MANUALLY. FLIGHT WAS AT 41000' AND THE PITCH TRIM ANNUNCIATOR ILLUMINATED DESCENDING THROUGH 34000'. THE TRIM TAB REMAINED LOCKED IN POSITION UNTIL 19000' WERE ABLE TO MANUALLY BREAK IT LOOSE. REMOVED LT ACTUATOR, PN 6660161-13, RT ACT PN 6660161-14. INSTALLED NEW ACTUATORS IAW MM 27-32-03. COMPLETED TRIM TAB RIGGING IAW MM 27-31-00 SYS, OPS CHECKED GOOD.

Part: AHRS — ILLUMINATED · airframe 1,945 hrs · 1,493 cycles

RED HEADING AND ATTITUDE FAIL MESSAGE ON THE NR 2 PFD. REMOVED FAULTY NR 2 AHRS & INSTALLED. OPS CHECKED REPAIRED UNIT IAW MM 34-21-01. OPS CHECKED GOOD.

Part: TRIM SYSTEM — MALFUNCTIONED (PITCH) · airframe 1,871 hrs · 1,439 cycles

DURING THE DESCENT FROM 39000' THE PITCH TRIM ANNUNCIATION ON THE PFDS CAME ON. WITH THE AUTOPILOT OFF THE TRIM WHEEL COULD NOT BE TRIMMED ANY FURTHER FWD. AT LOWER ALTITUDES THE TRIM WORKED FREELY. PURGED AND LUBRICATED THE ELEVATOR TRIM ACTUATORS, INSPECTED THE MANUAL TRIM CONTROL WHEEL. NO DEFECTS NOTED. INSPECTED THE TRIM INDICATOR THE TRIM TAB HARDWARE, AND THE TRIM ACTUATORS. NO FAULTS FOUND. INSPECTED THE MANUAL TRIM CONTROL WHEEL CHAIN. NO FAULTS FOUND. RAN THE TRIM SYS ELECTRICALLY AND MANUALLY SEVERAL TIMES. OPS TESTS GOOD. WORK DONE IAW MM CH 12-21-01.

Part: STRUT — LEAKING (LT MLG) · airframe 1,869 hrs · 1,437 cycles

ON FINAL APPROACH THE LT MLG FAILED TO FULLY EXTEND TO GIVE A GREEN DOWN AND LOCKED LIGHT INDICATION. THE LANDING GEAR WAS BLOWN DOWN IAW THE EMERGENCY CHECKLIST. WHEN PNEUMATIC PRESSURE WAS APPLIED, THE LT MAIN GEAR FULLY EXTENDED GIVING A GREEN LIGHT INDICATION. THERE IS EVIDENCE OF LIGHT HYD FLUID LEAKAGE ON THE LT MAIN GEAR STRUT. JACKED ACFT, COMPLETED LAST GEAR DOWN FUNCTIONAL, WITH NO FAULTS. FROZEN LT MAIN DOWN LOCK SWITCH, FAULT OCCURED, OHMED SWITCH FOUND SWITCH STUCK OPEN ON INDICATING SIDE, CONTROL SIDE IS NORMAL. R & R SWITCH WITH NEW SWITCH IAW MM 32-30-04. OPS CHECK NORMAL. RESET AND SERVICED GEAR BOTTLE IAW MM 12-13-01.

Part: TUBE — SHORT (ZONE 100) · airframe 1,184 hrs · 914 cycles

THE RUDDER CONTROL CABLES PASS THROUGH A PLASTIC GUIDE TUBE BETWEEN WING AND FUSELAGE. THIS GUIDE TUBE IS NOT SUPPORTED AT AFT END. IT IS TOO SHORT TO PASS THROUGH THE SUPPLIED SUPPORT CLAMP. SB560XL-27-20 ADDRESSES THIS CONDITION BUT IS NOT APPLICABLE TO THIS SN ACFT. ON THIS ACFT, THE INTENT OF THE SB WAS INCORPORATED DURING PRODUCTION. REPLACEMENT OF THE GUIDE TUBE WITH A LONGER TUBE WOULD CORRECT THE PROBLEM BUT DUE TO ACCESS DIFFICULTY, REPLACEMENT IS NOT REALLY FEASIBLE. MFG ENGINEERING SUPPLIED DWGS TO CORRECT THE SITUATION ON THIS ACFT.

Part: CONTROL COLUMN — VIBRATION · airframe 797 hrs · 620 cycles

EXCESSIVE VIBRATION IN CONTROL YOKE/COLUMN STARTING AT 230 KTS, APPROX 9-10K FT, CONTINUED AT ALL A/S AND ALTITUDES ABOVE THAT. REPEAT WRITE-UP. VIBRATES WITH AUTOPILOT ON OR OFF.

Part: CONTROL CABLE — OUT OF ADJUST (ELEVATORS) · airframe 797 hrs · 620 cycles

CHECKED ALL FLT. CONTROL CABLES (PRIMARY) IAW MM 27-10-00, 27-20-00 & 27-30-00. ADJUSTED & CHECKED AILERON WING, FUSELAGE & SERVO CABLE TENSION IAW MM 27-10-00. ADJUSTED & CHECKED ELEVATOR & RUDDER CABLES IAW MM 27-31-00 & 27-20-00.

Part: ACTUATOR — BYPASSING · airframe 604 hrs · 457 cycles

STAB MISCOMPARE ILLUMINATED AFTER TAKOFF, RAN CHECKLIST AND LIGHT WENT OUT AFTER THE HYD CONTROL C/B WAS CYCLED. FOUND HORIZ STAB ACTUATOR BYPASSING HYDRO FLUID. REMOVED AND REPLACED STAB ACTUATOR. LEAK AND OPS CHECK GOOD. IAW MM 27-40-00.