N521FX

Part: COLLECTOR — FULL (PITOT STATIC)

WHILE IN CRUISE AT FL 430 THE CA ALTIMETER SHOWED A DESCENT / VSI ABOUT -110 FPM / AIRSPEED DECREASING. STANDBY AND FO INSTRUMENTS SHOWED LEVEL FLIGHT. SEVERAL CAS MESSAGES POSTED. RED "CABIN DELTA P" CAS ILLUMINATED. INITIATED A DESCENT FOR CAUTIONARY PURPOSES. SWITCHED ADC 2 RESUMED NORMAL FLIGHT. AUTOPILOT WOULD ENGAGE BUT WAS FOLLOWED BY AMBER "AP STAB TRIM FAIL". CONDUCTED REMAINDER OF FLIGHT W/O AUTOPILOT. GAINED ACCESS TO L/H # 1 PITOT STATIC VISUAL DRAIN COLLECTORS AND DISCOVERED THE PRESENCE OF WATER IN 3 OF THE 4 COLLECTORS DISCOVERED FRACTURED SIGHT GLASS AND INSTALLED SERVICEABLE SIGHT GLASS AND PERFOMRED SYSTEM PURGING PROCEDURE. RECONNECTED SYSTEM FITTINGS AND COUPLINGS AND PERFORMED SATISFACTORY PITOT STATIC SYSTEM INDICATION AND LEAK CHECK WITH NO FURTHER DISCREPANICES NOTED

Part: SENSOR — MALFUNCTIONED (APU BAY) · airframe 12,728 hrs · 7,866 cycles

DIVERTED DUE TRIPLE CHIME WITH APU FIRE WARNING IN FLIGHT. FIRED NR 2 FIRE BOTTLE AND CAS CLEARED. AIRCRAFT LANDED WITHOUT INCIDENT. R&R NR 2 FIRE BOTTLE. OPS CHECK OF FIRE DETECT AND EXTINGUISHING SYSTEM GOOD. INSPECTED APU FOR SIGNS OF FIRE. NO DEFECTS NOTED. INSTALLED 3 DISCARGE CARTRIDGES. R&R APU EDUCTOR SENSING ELEMENTS.

Part: BEARING — FAILED (RT ENGINE) · airframe 12,354 hrs · 7,616 cycles

VIBRATION FELT FOLLOWED BY R ENGINE VIBRATION CAS MESSAGE WHILE IN DESCENT.  EXCESSIVE VIBRATION CONTINUED.  PRECAUTIONARY SHUTDOWN OF RIGHT ENGINE IN FLIGHT.  EMERGENCY DECLARED, LANDED WITHOUT INCIDENT. COMPLETED REPLACEMENT OF NR 2 ENGINE WITH A SERVICEABLE RENTAL ENGINE DUE TO HIGH VIBRATION/INTERNAL DAMAGE CAUSED BY NR 4 BEARING FAILURE. COMPLETED LEAK AND OOPS CHECKS SATISFACTORY.

Part: STUD — CORRODED (GENERATOR) · airframe 12,182 hrs · 7,507 cycles

DUAL GENERATOR FAILURE IN FLIGHT WHEN STARTING APU AT 5000 FEET. AIRCRAFT LANDED WITHOUT INCIDENT. CLEANED CORROSION FROM BOTH LT AND RT GEN STUDS. CORRECTED TORQUE ON THE LT AND RT DCPC NR 1 AND 2 STUDS.

Part: BRACKET — CRACKED (APU FIREWALL) · airframe 12,710 hrs · 7,500 cycles

APU FIREWALL LOWER BRACKET CRACKED AROUND RIVETS. R & R THE LOWER BRACKET.

Part: CONTROL PANEL — FAILED (SEAT)

SPARKS AND SMOKE OBSERVED COMING FROM SEAT CONTROL PANEL LOCATED AT THE LT FRONT REAR FACING SEAT, WHILE ON THE GROUND AND NOT IN USE. REPLACED THR NR 1 AFT FACING SEAT SWITCH CONTROL PANEL. OPS CHECKED GOOD.

Part: MANIFOLD — LEAKING (HYD SYSTEM) · airframe 11,400 hrs · 7,027 cycles

DIVERTED DUE TO BOTH MAIN LANDING GEAR NOT LOWERING ON APPROACH AND WAS FOLLOWED BY LOW HYDRAULIC PRESSURE. THE LT SIDE HAD A QUANITY OF ZERO ON THE SYNOPTIC DISPLAY. PILOTS FOLLOWED QRH TO EXTEND THE GEAR USING AN ALTERNATE METHOD. GEAR EXTEND. CREW DECLARED AN EMERGENCY AND SAID THEY NEEDED A MINIMUM OF 10,000 FT RUNWAY. UPON LANDING 3 MLG TIRES BLEW, 2 RT AND LT OUTBOARD. REPLACED ALL 4 MAIN WHELL ASSEMBLIES. INSPECTED AIRCRAFT FOR DAMAGE DUE TO BURST TIRES. FOUND LH PRESSURE MANIFOLD LEAKING. REPLACED THE LT PRESSURE MANIFOLD. PERFORMED MULTIPLE GEARS SWINGS, OPS CHECK GOOD. MVF COMPLETED AND SATISFACTORY.

Part: PRESSURE VALVE — FAILED (RT ENGINE) · airframe 7,389 hrs · 4,516 cycles

RED RIGHT BLEED AIR LEAK POSTED IN FLIGHT. REPLACED INTERMEDIATE PRESSURE VALVE AND SEALS.

Part: PUMP — FAILED (RT HYD SYS) · airframe 7,214 hrs · 4,415 cycles

ENROUTE, AN AMBER RT HYD PRESSURE LOW CAS POSTED IN FLIGHT. PERFORMED AN AIR RETURN. REPLACED RT EDP.

Part: SAFETY VALVE — ILLUMINATED (CABIN PRESSURE)

RED CABIN ALTITUDE CAS MESSAGE POSTED AT 43000 FT AND CABIN ALT READ 10,300 FT CAS MESSAGE WENT OUT AFTER 1 MIN, PASSING 19,800 FT RED CABIN CAS MESSAGE POSTED AGAIN FOR 30 SECONDS. REPLACED CABIN SAFETY VALVES.

Part: FITTING — LOOSE (HYD PUMP) · airframe 4,406 hrs · 2,677 cycles

CREW OBSERVED HYD QTY DEPLETING ALONG WITH PRESSURE. IFE DECLARED AND FLIGHT DIVERTED FOR MX WITH UNEVENTFUL LANDING AND TAXI. MX FOUND A LOOSE FITTING AT RT DC ELECTRIC PUMP. FITTING TIGHTENED APPROX 1/2 TURN AND ALL OTHER FITTING CHECKED NORMAL. SERVICED SYS WITH FLUID AND OPS CHECKED NORMAL. INVESTIGATION FOUND THIS PUMP WAS CHANGED APPROX 3 DAYS PREVIOUS. MX THAT PERFORMED CHANGE STATED ALL WORK DONE IAW MX MANUAL. FACILITY WILL CHANGE LEAK CHK PROCEDURE TO INCLUDE ENGINE RUN TO FULLY PRESSURAIZE SYS AND LOADING OF SYS BY MOVEMENT OF FLIGHT CONTROLS. MUST BE NOTED THE AFT FLEW TRIPS BETWEEN THE PUMP CHG AND THIS EVENT.

Part: DISPLAY — BURNED OUT (COCKPIT) · airframe 4,402 hrs · 2,673 cycles

COPILOT'S MFD WENT BLANK & RELEASED SMOKE. SHOWS UP AS WHITE ON FIRE FIGHTER'S THERMAL IMAGING CAMERA. OCCURRED ON DESCENT. FLIGHT COMPLETED AS FILED. IFE DECLARED ON APPROACH TO KAPC. LANDING UNEVENTFUL. UPON FURTHER T/S, FOUND COPILOT'S PFD TO BE MALFUNCTIONING. REMOVED COPILOT'S PFD & INSPECTED AREA FOR HEAT DAMAGE, NONE FOUND. INSPECTED OTHER THREE SCREENS FOR HEAT DAMAGE, NONE FOUND. REPLACED COPILOT'S SIDE PFD WITH O/H UNIT. PERFORMED OPS CHECK, OPS CHECK GOOD, NO DEFECTS NOTED.

Part: TRANSDUCER — MALFUNCTIONED (RT ENGINE) · airframe 3,885 hrs · 2,329 cycles

RT OIL PRESSURE DROPPED TO 20 PSI WITH A RED INDICATION DURING DESCENT THROUGH FL280. THE RT THRUST LEVER WAS REDUCED AND THE INDICATION DROPPED TO 10 PSI. SHUT THE ENGINE DOWN PER THE QRH AND LANDED SINGLE ENGINE. IFE DECLARED WITH NO DIVERSION REQUIRED. PERFORMED ENGINE DOWNLOAD. REMOVED AND REPLACED OIL PRESSURE TRANSDUCER. TEST RAN RT ENGINE FOR LEAK CHECKS. PERFORMED POST RUN DOWNLOAD, FOUND NO FAULTS ON OIL PRESSURE TRANSDUCER. OPS CHECKS GOOD.