N814QS

Part: CONTROL COLUMN — NOISE (ZONE 200) · airframe 4,315 hrs · 2,889 cycles

WHEN MOVING CONTROL COLUMNS FORWARD AND AFT, THERE IS A VERY NOTICABLE SQUEAKING AND SUBTLE STIFFNESS/BINDING FEELING IN THE CONTROLS. ARRIVED AT A/C AND VERIFIED THE DISCREPANCY. FOUND THAT THE NOISE WAS COMING FROM THE FWR CENTER PEDESTAL NEAR THE AVDTS. CONTACT CLEANED THE AREA AND THE HUMMING NOISE WAS NOT LONGER THERE. THE OTHER NOISE WAS A HIGH PITCH SQUEAKING NOISE. WE FOUND THAT THE SQUEAKING WAS COMING FROM THE AFT CENTER PEDESTAL. FURTHER ACCESS SHOWED THAT THE AFT SIDE OF THE ELEVATOR CONTROL PUSH ROD BOTH LH AND RH WERE CAUSING THE NOISE DUE TO LACK OF CLEANLINESS AND LUBRICATION .. CLEANED AND LUBRICATED IT AS NEEDED, CYCLED THE CONTROL COLUMNS FWA AND AFT AND THE DISCREPANCY NO LONGER PERSIST. INSPECTED THE PUSH RODS AND NO ISSUES NOTED. WORK PERFORMED IRW AMM 27-30·20

Part: LIGHT — MALFUNCTIONED (ZONE 200) · airframe 3,675 hrs · 2,184 cycles

STARBOARD OVERWING EMERGENCY LIGHT IS INOP. POWERED UP AIRCRAFT AND TURNED ON EMERGENCY LIGHTS. ALL EMER LIGHTS ILLUMINATED. UNABLE TO DUPLICATE DISCREPANCY. TAPPED ON AROUND LIGHT TY TRY AND DUPLICATE DISCREPANCY, UNABLE TO DUPLICATE. MCC IS OKAY TO SIGN OFF AND RELEASE. OPS CHECKS GOOD.

Part: LIGHT — INOPERATIVE (ZONE 200)

STARBOARD OVERWING EMERGENCY LIGHT IS INOP. POWER UP AIRCRAFT AND TURNED EMERGENCY LIGHTS ON . ALL EMERGENCY LIGHTS ILLUMINATED . UNABLE TO DUPLICATE DISCREPANCY . TAPPED ON AROUND LIGHT TO TRY AND DUPLICATE DISCREPANCY . UNABLE TO DUPLICATE CONTACTED MCC AND SPOKE TO SARA . MCC IS OK TO SIGNOFF AND RELEASE . OPS CHECK GOOD.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 2,726 hrs · 1,616 cycles

AMBER BRAKE 50% DEGRADED ON TAXI OUT. NO PSI ON OUTBOARD SYSTEM NORMAL BRAKING.

Part: CIRCUIT BOARD — DEFECTIVE (ZONE 100) · airframe 2,633 hrs · 1,566 cycles

WHEN ATTEMPTING TO MOVE AIRCRAFT, FOUND MAIN CABIN DOOR WILL NOT CLOSE ELECTRICALLY. REMOVED FAULTY CED MONITOR PCB AND INSTALLED INSPECTED PCB IAW CE-700 AMM CHAPTER 24-60-25. OPS CHECKS GOOD NO DEFECTS NOTED.

Part: SCREEN — DEBONDED (ZONE 400) · airframe 2,417 hrs · 1,428 cycles

PROTRUDING WIRE MESH AND PARTIAL DAMAGE TO THE FWD AND AFT EDGES OF THE ACOUSTING MESH ON INNER BARREL OF RH INLET ASSEMBLY. REPAIR WAS ACCOMPLISHED WITH GKN TECHNICAL VARIANCE TV00122895 REV H, ISSUE 2 DATED 07/12/2021.

Part: THRUST REVERSER — CORRODED (ZONE 400) · airframe 2,417 hrs · 1,428 cycles

ACCOMPLISHED SAFRAN REPAIR SCHEME NO. RS907-622 REVISION A, PROCEDURE TO REPAIR CORROSION DAMAGE AND RESTORING SURFACE PROTECTION ON THE BEAM INNER SKIN DATED 28JUL2023.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 2,309 hrs · 1,358 cycles

CAPTAIN COCKPIT WINDOW: COCKPIT LEFT SIDE WINDOW CRACKED DURING APPOACH PASSING 12,000 FT. /REMOVED FAILED/CRACKED LH COCKPIT SIDE WINDOW 9914809-1 S/N 20024H0921 AND REPLACED IT WITH NEW CUSTOMER SUPPLIED SIDE WINDOW P/N 9914-1 S/N 22318H9439. VISUAL, LEAK AND OPERATIONAL TESTS SATISFACTORY. ALL WORK IAW MM:56-10-10,

Part: WINGLET — DAMAGED (ZONE 500) · airframe 1,399 hrs · 813 cycles

LEFT WING WING TIP: DURING PRE-FLIGHT INSPECTION, FOUND BURN MARK AND DAMAGE THAT LOOKS LIKE POSSIBLE LIGHTNING STRIKE DAMAGE ON UPPER LEFT WINGLET

Part: ACTUATOR — UNSERVICEABLE (RT MLG) · airframe 6,067 hrs · 4,875 cycles

RIGHT MAIN GEAR INDICATOR DID NOT ACTUATE NORMALLY. RIGHT MAIN GEAR DOWN LIGHT WAS NOT ON. LANDING GEAR WILL NOT EXTEND CHECKLIST COMPLETED AND RIGHT MAIN GEAR EXTENDED LIGHT CAME ON. R & R THE RT SIDE BRACE ACTUATOR. OPS CHECKS GOOD, REF MM 32-31-04. R & R GEAR MONITOR PCB NZ044. OPS CHECKS GOOD, REF MM 24-51-02. PARTS REPLACED: MLG ACTUATOR ASSY, PN: 1556600-4A, SN: 453A, PCB, PN: 6518394-1, SN: 0328.

Part: SEAL — LEAKING (BLEED AIR SYS) · airframe 5,820 hrs · 4,687 cycles

RT ENG FIRE LIGHT ILLUMINATED IN FLT. DISCHARGED LT FIRE BOTTLE. FIRE LIGHT EXTINGUISHED. NO SIGN OF FIRE ON PREFLIGHT. CRASH & FIRE CREWS REPORTED NO HOT SPOTS. INSP ENG FOR EVIDENCE OF FIRE WITH NO FINDINGS. PERFORMED RESISTANCE CHECK OF RT FIRE DETECT SYS WITH NO DEFECTS. OPERATED ENG & NOTED ENG BLEED LEAKS ON RT ENG BLEED AIR TUBING COUPLINGS. REPLACED RT ENG BLEED AIR COUPLINGS SEALS. COMPLETED REPLACEMENT OF FWD FIRE BOTTLE & CARTRIDGES. PERFORMED LEAK CHECKS OF RT ENG BLEED SYS WITH NO DEFECTS NOTED. PERFORMED ENG RUNS THROUGHOUT TLA RANGE FOR EXTENDED PERIOD WITH NO FIRE DETECT ILLUMINATION. OPERATIONS CHECKED SATISFACTORY, ACCOMPLISHED IAW AMM 26-11-00, 26-21-01 & 36-12-01.

Part: SKIN — DAMAGED (BS 205) · airframe 5,133 hrs · 4,112 cycles

ANOMALY FOUND AT BS 205 AND WL 94-96 SKIN JOINT DURING PHASE 49 INSPECTION WHICH APPEARS TO BE A SCRATCH APPROXIMATELY 2" IN LENGTH. COMPLIED WITH MFG ENGINEERING MEMO: M150403DK DATED 04/02/2015 AND COMPLIED WITH ALL OF THE REQUIRED STEPS. THE SEAM WAS FILLED WITH "B" SEALANT, 2 COATS OF 10P8-11 EPOXY PRIMER AND PAINT HAS BEEN APPLIED.

Part: UNKNOWN — MALFUNCTIONED (BRAKE SYSTEM) · airframe 4,224 hrs · 3,387 cycles

ON LANDING ROLL BELOW 60 KNOTS, PILOTS RT BRAKE PEDAL WENT TO THE FLOOR. RIGHT PILOT GOT THE AIRPLANE SLOWED TO TAXI SPEED, THEN HIS RT PEDAL WAS INTERMITTENTLY SPONGY. AFTER CLEARING THE RUNWAY, TRIED THE BRAKES AGAIN & THE PILOT RIGHT WENT ALMOST TO THE FLOOR AGAIN. WE HAD THE AIRPLANE TOWED IN. NO EMERGENCY BRAKE USED. POST FLIGHT HAD NO FLUID LEAKS OR FLAT SPOTS ON BOTH MAINS.

Part: SEAL — DAMAGED (BLEED AIR SYS) · airframe 4,078 hrs · 3,280 cycles

RIGHT ENG FIRE LIGHT ON IN FLIGHT. PERFORMED ENG FIRE LIGHT ON MEMORY ITEMS LIGHT EXTINGUISHED AFTER APPROXIMATELY 3 SECONDS AFTER EFFECTED ENG THROTTLE WAS REDUCED TO IDLE. REMOVED UPPER & LOWER COWLS ON RT ENG FOR FURTHER INSPECTION STARTED INSPECTING RT ENG. NOTED SIGNS OF OVERHEAT ON AFT INLET BULKHEAD. RAN RT ENG FOUND AIR LEAKING FROM BLEED AIR LINES AT SEALS, R & R SEALS IAW MM 36-12-011/30/14. LEAK CHECK DUE, PERFORMED CONTINUITY & RESISTANCE CHECK ON FIRE DETECT SENSOR. CHECKED GOOD IAW 560 MM CH 26-11-00. 1/30/14 RAN ENG LEAK CHECKED GOOD. MX CONTROL REQUESTS SWAPPING THE FIRE DETECTION CONTROL UNITS. REMOVED RT INLET OUTER SKIN. INSPECTED BLEED AIR PLUMBING TO INLET ANTI-ICE, NO DEFECTS NOTED, INSTALLED RT ENG INLET OVER SKIN, ACCESS PANEL, IAW MM SECTION 71-11-00. R & R RT FIRE DETECTION BOX PN 377-02838, SN 1243-323 WITH NEW PN 377-02838, SN 1344-379 IAW MM 26-11-02. PERFORMED SELF-TEST ON FIRE DETECTION SYSTEMS, OPERATIONS CHECKED GOOD.

Part: FIRE LOOP — MISROUTED (RT NACELLE) · airframe 3,900 hrs · 3,137 cycles

DURING CLIMB THRU FL230, RT ENGINE FIRE LIGHT AND WARNING BELL CAME ON. RETARDED RT THROTTLE TO IDLE IAW THE CHECKLIST AND BELL AND LIGHT EXTINGUISHED. FOUND LEFT ENGINE FIRE LOOP ROUTED INCORRECTLY. ROUTED FIRE LOOP PER DRAWING 6555660. DWG.0003. OPS CHECKED GOOD.

Part: SEAL — LEAKING (ENGINE) · airframe 3,852 hrs · 3,100 cycles

IN FLIGHT, RT ENGINE FIRE LIGHT AND WARNING BELL ACTIVATED. RETARDED THROTTLE TO IDLE AND BELL AND LIGHT EXTINGUISHED. LANDED WITH ENGINE IN IDLE, NO OTHER ABNORMAL INDICATIONS. PERFORMED HIGH POWER RUN UP AND VERIFIED NO BLEED AIR LEAKS. PERFORMED HIGH POWER RUN WITH COWLINGS INSTALLED TO VERIFY NO FALSE FIRE INDICATION POSSIBLE. ALL ENGINE RUNS NORMAL. REF MM 20-10-13, PARTS USED: 2EA MS9204-038 GASKETS. 8EA W932-24E SEALS.

Part: SEAL — LEAKING (BLEED AIR) · airframe 3,852 hrs · 3,100 cycles

AT 25,000 FT, RT ENGINE FIRE BELL AND LIGHT SOUNDED AND ILLUMINTED. PERFORMED ENGINE FIRE CHECK LIST DECLARED EMERGENCY AND LANDED WITHOUT FURTHER EVENT. INSPECTED RT ENGINE FOR SIGNS OF FIRE, NO DAMAGE FOUND. PERFORMED RUN UP AND FOUND FOUR BLEED AIR COUPLINGS LEAKING. REMOVED AND REPLACED BLEED AIR SEALS. PERFORMED HIGH POWER RUN UP AND VERIFIED NO BLEED AIR LEAKS. PERFORMED HIGH POWER RUN WITH COWLINGS INSTALLED TO VERIFY NO FALSE FIRE INDICATION POSSIBLE. ALL ENGINE RUNS NORMAL IAW MM 20-10-13.

Part: GPS — FAILED (COCKPIT) · airframe 1,641 hrs · 1,377 cycles

RT CIRCUIT BREAKER PANEL "WARN" CIRCUIT BREAKER POPPED IN FLIGHT. FOUND GPS TO BE CAUSE OF PROBLEM. R & R GPS. OPS CHECKED GOOD AT THIS TIME. ALL WORK DONE IAW MM 34-50-05, 53-50-02 .

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 454 hrs · 406 cycles

RIGHT ENG FIRE LIGHT ILLUMINATED IN FLIGHT DISCHARGED FIRST BOTTLE, LIGHT EXTINGUISHED. LIGHT RE-ILLUMINATED AND WOULD NOT EXTINGUISH AFTER SECOND BOTTLE DISCHARGED.

Part: FIRE DETECTOR — FALSE INDICATION (RT NACELLE) · airframe 454 hrs · 406 cycles

RT ENG FIRE LIGHT ILLUMINATED IN FLT, DISCHARGED FIRST BOTTLE, LIGHT EXTINGUISHED. LIGHT RE-ILLUMINATED & WOULD NOT EXTINGUISH AFTER SECOND BOTTLE DISCHARGED. ACCOMPLISHED ALL MEMORY ITEMS & PROCEDURES FOR ENG FIRE LIGHT ILLUMINATED. REMOVED RT ENGINE TOP AND BOTTOM COWLS. FOUND AIR LEAK EVIDENCE AT FIRST FLANGE FWD OF THRUST REVERSER FLANGE AT 6 O'CLOCK POSITION. FWD & AFT FWD BOTTLES REMOVED. RT SENSOR CHECKS SATISFACTORY AT THIS TIME. COMPLIED WITH BOROSCOPE INSPECTION OF THE HPT, COMBUSTION LINEN, LPT AND THE FRONT OF THE IMPELLER IAW MM 72-00-00. NO DEFECTS NOTED. REMOVED FIRE TRAY FOR BENCH CHECK. FIRE TRAY BENCH CHECKED GOOD AND PCB NZ007 ALSO CHECKED GOOD. RE-INSTALLED FIRE TRAY ASSY. INSTALLED FWD AND AFT OVERHAULED ENGINE FIRE BOTTLES. IAW MM 26-21-01. PERFORMED ENGINE GROUND RUNS, INSPECTED FOR LEAKS DURING RUNS, NO LEAKS NOTED. COULD NOT DUPLICATE DISCREPANCY. CONTACTED MX CONTROL AND UPDATE FIRE ISSUE TO ( CHUCK MAINT CONTROL) AND IAW CUSTOMERS REQUEST TO REPLACE ENGINE FIRE LOOP SENSOR AND FIRE DETECTION CONTROL BOX. REMOVED RT FIRE DETECTION CONTROL BOX AND INSTALLED NEW FIRE DETECTION CONTROL BOX, IAW MM 26-11-02. REMOVED RT ENGINE FIRE LOOP SENSOR AND INSTALLED NEW FIRE LOOP SENSOR IAW MM 26-11-01. PERFORMED OPS CHECK ON ROTARY TEST ALL CHECKED GOOD. PERFORMED ENGINE GROUND RUN, CHECKED GOOD.

Part: AUTOPILOT SYS — MALFUNCTIONED (COCKPIT)

AUTO PILOT KICKS OFF WHEN IN CLIMB OR TURN.

Part: TRIM SYSTEM — OUT OF LIMITS (ELEVATORS) · airframe 429 hrs · 384 cycles

AUTO PILOT KICKS OFF WHEN IN CLIMB OR TURN. ACFT CONTROLS APPEAR TO BE LOADED WHEN AUTOPILOT KICKS OFF. PERFORMED OPS CHECK OF AUTOPILOT DISENGAGEMENT SYS TO ENSURE PROPER OPERATION. ALL CHECK GOOD. PERFORMED AHRS FUNCTIONAL TEST. ALL AHRS OPS CHECK GOOD. GAINED ACCESS IN AFT CABIN AREA TO AUTO PILOT SERVO FOR AILERON. CHECKED CABLE TENSIONS FOUND CABLE TENSIONS TO BE AT 21 LBS. REQUIRED TENSION IS 20LBS + 30LBS. GAINED ACCESS TO ELEVATOR SERVO IN AFT BAGGAGE COMPARTMENT. FOUND ELEVATOR AUTOPILOT SERVO CABLE TENSIONS TO BE AT 29 LBS. LIMIT IS 20 + 30LBS. ADJUSTED CABLE TENSIONS. TO 20 LBS AS REQUIRED. PERFORMED TRAVEL CHECK AT ELEVATOR & ELEVATOR TRIM. ELEVATOR TRAVELS CHECK GOOD. ELEVATOR TRIM IN NOSE UP POSITION FOUND TRAVELS TO BE OUT OF LIMITS. GAINED ACCESS TO ELEVATOR TRIM STOP BLOCKS AND ADJUSTED STOP BLOCK TO BRING TRAVELS WITHIN LIMITS AT 4.5.+1-0 DEGREES NOSE DOWN AND 11' +.5'-0' NOSE DOWN. OPERATED AUTO PILOT SYS AFTER ALL TENSIONS CHECKED AND ADJUSTMENTS MADE. NO FAULTS NOTED AT THIS TIME. CLOSED ALL ACCESS IN CABIN AREA AND AFT BAGGAGE. ALL WORK DONE IAW MM 22-11-03, 34-21-16-27-11-00 AND 27-31-00.

Part: PRESSURE SWITCH — INOPERATIVE (ANTI SKID SYS) · airframe 306 hrs · 270 cycles

WHILE TAKING THE RUNWAY FOR DEPARTURE THE LOW BRAKE PRESSURE - ANTI-SKID ANNUNCIATOR LIGHT ILLUMINATED. REMOVED DEFECTIVE PUMP MOTOR PRESSURE SWITCH AND INSTALLED REPAIRED SWITCH. SYSTEM CHECKS GOOD REF MM 32-20-00. TAXI CHECKED GOOD IAW PILOTS HANDBOOK.

Part: PCB — INOPERATIVE · airframe 191 hrs · 175 cycles

LANDING GEAR DID NOT EXTEND WHEN GEAR HANDLE WAS PUT DOWN. REPLACED PCB NZ014 PER CE560 ENCORE & MM 24-51-01, REPLACED LANDING GEAR CONTROL HANDLE ASSY. PER CE560 ENCORE & MM 32-31-01. FUNCTIONAL CHECKED GOOD PER 560 ENCORE & MM 32-01-00.

Part: INDICATOR — LOOSE (ELEVATOR TRIM) · airframe 157 hrs · 145 cycles

ELEVATOR TRIM POSITION INDICATOR INOP. INDICATES INCORRECT TRIM POSITION. FOUND TRIM LOOSE. SHIMMED & RESECURED INDICATOR IAW MM 27-31-00. OPERATIONAL AND TRAVEL CHECK NORMAL.

Part: ANTI-SKID SYS — MALFUNCTIONED (MLG) · airframe 140 hrs · 130 cycles

ON TAXI OUT LOW BRAKE PRESS AND ANTI-SKID INOP LIGHT ILLUMINATED. NORMAL BRAKING WAS INEFFECTIVE. EMERGENCY BRAKE WAS USED TO STOP THE AC. GAINED ACCESS TO ANTI-SKID CONTROLLER AND FOUND NO FAULTS. EMERGENCY PNEUMATIC BOTTLE IS SERVICED TO TOP OF GREEN ARC. BLED ANTI-SKID BRAKE SYS IAW CHECKLIST AND MM CHAPTER 32-42-01. SERVICED BRAKE RESERVOIR IAW MM CHAPTER 12-12-02. ANTI-SKID SYSTEM OPS CHECK GOOD. TAXI CHECK GOOD. AFTER RESETTING CIRCUIT BREAKER IT NEVER TRIPPED DURING SERVICING OR OPS CHECKS.

Part: WARNING LIGHT — UNKNOWN (MLG) · airframe 36 hrs · 32 cycles

WHEN THE GEAR WAS CYCLED DOWN NORMALLY (GEAR HANDLE TO DOWN POSITION) THERE WAS NONE OF THE 3 GREEN DOWN INDICATORS. JACKED ACFT, CONNECTED HYDRAULIC MULE. EXTEND & RETRACTED GEAR 13 TIMES. ALL GEAR OPS NORMAL. DISCONNECTED MULE. ALL WORK DONE IAW AMM 32-01-00 AND 7-10-01. SERVICED HYD FLUID TO PROPER LEVEL IAW AMM 12-12-01. DOWNJACKED A/C IAW AMM 07-10-01