N106QS

Part: MECHANISM — STIFF (THRUST REVERSER) · airframe 2,730 hrs · 2,551 cycles

INVESTIGATED REPORTED RT ENGINE THRUST REVERSER NOT FULLY DEPLOYING AFTER LANDING. FOUND REVERSER ASSY. STICKING AND UNABLE TO UNLOCK INBD ACTUATOR. UNLOCKED ACTUATOR AFTER ISOLATING AND ACTUATING WITH HAND PUMP. FOUND REVERSER ASSY. UPPER AND LOWER DOOR ACTUATING MECHANISMS VERY STIFF AND DIFFICULT TO MOVE. LUBRICATED THE DOOR ACTUATING MECHANISMS GUIDE RODS AS REQUIRED IAW THE MM 12-20-00 AND 78-30-00 UNTIL FREE MOVEMENT OBTAINED. REASSEMBLED THRUST REVERSER, FOUND TO FUNCTION NORMALLY THROUGH REPEATED CYCLES. TRANSIENT ACFT, MX HISTORY UNKNOWN. IAW MM 12-20-00, THE GUIDE RODS SHOULD BE LUBRICATED EVERY "A" INSP (200 HRS).

Part: WARNING LIGHT — ILLUMINATED · airframe 2,386 hrs · 2,201 cycles

HORIZ STAB FAIL ANNUNCIATOR CAME ON.

Part: CIRCUIT BREAKER — TRIPPED (HORIZONTAL STAB) · airframe 2,386 hrs · 2,201 cycles

IN FLIGHT DURING ICING CONDITIONS, H STAB FAIL ANNUNCIATOR CAME ON. CHECKED BOTH AMMETERS AND VERIFIED H STAB WAS FAILED. INSPECTED THE STAB HEAT SYS AND FOUND "H STAB CONTROL" BREAKER OUT. RESET BREAKER AND PERFORMED A GOOD OPS CHECK IAW MM 30-12-00 AND ALLOW HEAT TO CYCLE FOR SEVERAL MINUTES WITH NO FAILURE.

Part: WIRE — BROKEN (STAB FAIL IND) · airframe 2,059 hrs · 1,878 cycles

(H) STAB FAIL) LIGHT ILLUMINATED IN FLIGHT. INSPECTED AND FOUND BROKEN WIRE AT P540 CONNECTOR PLUG. REPAIRED WIRE IAW MM 20-20-04. PERFORMED PITOT TEST, SYSTEM PASSED. PERFORMED GROUND CHECK, OPS CHECK GOOD. DONE IAW AMM 30-12-00.

Part: FUEL CONTROL — MALFUNCTIONED (ENGINE) · airframe 929 hrs · 835 cycles

RT ENGINE EFC CAME OFF LINE WHEN POWER WAS SET, SLOW SPEED ABOUT. THEY CLEARED RUNWAY AND RESET EFC. DISPATCH GAVE VERBAL RELEASE AND ENGINE POWER WAS MADE FOR TAKEOFF.

Part: HMU — OUT OF ADJUST (RT ENGINE) · airframe 684 hrs · 616 cycles

A RIGHT ENGINE WOULD NOT REACH SCHEDULED TAKEOFF POWER OF 98.2 PERCENT. FULL THROTTLE REACHED 96 PERCENT ONLY (N1). ADJUSTED HMU PRESSURE REGULATING VALVE. OPS CHECKED GOOD. PERFORMED EEC AUTHORITY CHECK.

Part: FILTER — BYPASSING (FUEL SYSTEM) · airframe 661 hrs · 590 cycles

ABORTED TAKEOFF AT 50 KTS DUE TO RIGHT FUEL BYPASS LIGHT ILLUMINATED AND STAYED ON UNTIL THROTTLES WERE BACK AT IDLE. REMOVED AND REPLACED BOTH FUSELAGE FUEL BOWL FILTERS, LEAK CHECK GOOD REF 400XP MM 28-20-00.

Part: PROBE — MALFUNCTIONED (FUEL TANK)

AFTER INSTALLATION IN TKS TANK, WITH TANK FULL, GAUGE READ ZERO. INSTALLATION OF ANOTHER NEW GAUGE SHOWED SYSTEM WORKED CORRECTLY.

Part: BOLT — LOOSE (CONTROL COLUMN)

BOTH PILOT'S AND COPILOT'S CONTROL COLUMN ASSY HAD EXCESSIVE PLAY. WHEN PRESSURE WAS APPLIED TO OPPOSITE COLUMN, FORWARD AND AFT OR INBOARD AND OUTBOARD, FOUND BOLTS HAD EXCESSIVE PLAY AND CLICKING NOISE WAS HEARD. (NO PUTTY WAS ON ANY BOLTS). TOTAL AIRCRAFT HOURS, 9,615.4.

Part: SEAL — LEAKAGE (DOOR)

AIRCRAFT FLYING AT 37,000 FEET. LOST PRESSURIZATION. MASK DROPPED AND AIRCRAFT DESCENDED. PASSENGERS WERE ON BOARD. AIRCRAFT INSPECTED BY MAINTENANCE PERSONNEL FROM A CESSNA SERVICE CENTER AND NO PROBLEM COULD BE FOUND. AIRCRAFT WAS FERRIED TO SERVICE CENTER. FOUND SEVERAL SMALL LEAKS AND A SMALL HOLE IN THE DOOR SEAL. SEALED THE LEAKS, REPLACED THE DOOR SEAL, AND BUILT THE DOOR FRAME UP TO GIVE THE SEAL A MORE POSITIVE SEAT.

Part: BEARING — CORRODED (RUD LT/RT TAB)

DURING INSPECTION FOUND RUDDER, LEFT AND RIGHT TRIM TAB BEARINGS, CORRODED AND WORN. TKS ANTI-ICE FLUID MOST LIKELY CAUSE OF CORROSION. SUBMITTER STATES THIS IS A COMMON PROBLEM. THE BEARINGS SHOULD BE MORE TKS/CORROSION RESISTANT.

Part: ACTUATOR — HOSE MISCONNECT (RT MLG)

DURING INSPECTION, FOUND RIGHT MAIN GEAR ACTUATOR GEAR EXTEND AND AUXILIARY AIR HOSES CONNECTED TO WRONG PORTS. THERE ARE TWO BRANDS OF ACTUATORS USED AND THEIR PORTS ARE OPPOSITE. THE PORTS SHOULD BE IN THE SAME POSITION ON EACH BRAND OF ACTUATOR. MORE ATTENTION SHOULD BE PAID TO ACTUATOR PLACARDS AND MAINTENANCE.