Flight Options LLC

Operated by Flight Options LLC (per NTSB report)

The airplane’s hydroplaning during the landing roll, which resulted in a runway excursion. Contributing to the accident was the pilot’s continuation of an unstabilized approach, his decision to land in heavy rain conditions, and his improper use of the main and emergency brake systems. Also contributing was the air traffic controller’s failure to disseminate current airport weather conditions to the flight crew in a timely manner.

Operated by FLIGHT OPTIONS LLC (per NTSB report)

The pilots’ failure to use available sources of wind information before landing and recognize cues indicating the presence of the tailwind and conduct a go-around, which resulted in their landing with a significant tailwind and a subsequent runway overrun.

Operated by FLIGHT OPTIONS LLC (per NTSB report)

The flight crew's failure to execute a go-around during a non-stabilized approach, which resulted in a runway overrun.

Operated by Flight Options LLC (per NTSB report)

The dual-engine flameout due to high-altitude ice crystals that had accreted onto the JT15D-5 engines' compressor vanes and were ingested into the engine when the pilots retarded the power levers, resulting in compressor surges and rapid reduction in fuel flow due to temporary ice blockage of the combustion pressure return line, and additionally preventing an in-flight restart. Contributing to the cause of the dual-engine flameout was the lack of training on the hazards of high-altitude ice crystals to gas turbine engines and guidance to the pilots to activate the engine anti-ice system in conditions where high-altitude ice crystals may exist.

Operated by FLIGHT OPTIONS LLC (per NTSB report)

The pilot-in-command's improper use of the flight controls during climb which resulted in the flight attendant injury. A factor was the flight crew failure to follow written procedures during transfer of flight controls.

Operated by Flight Options, LLC (per NTSB report)

The loss of directional control by the operator of a ground service vehicle.

Operated by Flight Options LLC (per NTSB report)

The pilot in command's improper decision to continue taxi without a ground marshaller, and her misjudged clearance from a parked airplane, which resulted in a ground collision during taxi. Factors which contributed to the accident were fatigue, night conditions, and a lack of ramp markings.

Operated by Flight Options (per NTSB report)

High-altitude ice crystals that had accreted on the compressor vanes and were ingested into the high pressure compressor when the pilots retarded the power levers causing compressor surges and flameouts of both engines. Contributing factors were the lack of training on the hazards of high-altitude ice crystals to gas turbine engines and guidance to the pilots to activate the engine anti-ice system in conditions where high-altitude ice crystals may exist.

Operated by Flight Options, Inc. (per NTSB report)

The captain's failure to go around. Factors included the captain's preoccupation with the flight management system, the crew's failure to adhere to company standard operating procedures, and the lack of proper crew coordination.

Sanction: $50,000 · case closed 2010-05-21

Part: WIRE — BURNED (PDU) · airframe 6,026 hrs · 4,140 cycles

ELECTRICAL BURN SMELL. FOUND BURNT WIRE HARNESS (W311) AT LH PDU CONNECTING TO THE GPU POWER RECEPTACLE. REMOVED AND REPLACED THE LPDU EXTERNAL POWER RECEPTACLE, AND HARNESS W311 REF PHENOM 300 AMM 24-65-01 AND 24-41-00 PERFORMED OPS CHECKS OPS CHECKED GOOD. AMM 24-61-00

Part: TUBE — BROKEN (FUEL VENT) · airframe 5,828 hrs · 3,972 cycles

AIR TURN BACK DUE TO FUEL 1 FEED FAULT. MOTIVE FLOW PUMP 1 RED X DISPLAY. AIRCRAFT LANDED WITHOUT INCIDENT.REPLACED LH WING ENGINE FEED CHECK VALVE. REPLACED LH FUEL TANK VENT TUBE DRAIN VALVE FOUND BROKEN OFF IN FUEL TANK. PERFORMED HIGH POWER ENGINE RUN AND MOTIVE FLOW NO LONGER DISPLAYS RED X . OPS CHECK AND LEAK CHECK GOOD.

Part: STARTER GEN — VIBRATION (NR 2) · airframe 5,575 hrs · 3,889 cycles

DIVERTED DUE TO VIBRATION. THROUGH CLIMB FELT VIBRATION THAT WENT AWAY AT FL330 WHEN RIGHT GEN WENT OFF LINE. AFTER ATTEMPTING TO RESET GENERATOR VIBRATION CAME BACK. FOLLOWED CHECKLIST AND SHUT DOWN RIGHT ENGINE. AIRCRAFT LANDED WITHOUT INCIDENT. R&R # 2 ENGINE STARTER GENERATOR AND COMPLETED ALL ASSOCIATED TASKS FOR UNSCHEDULED STARTER GEN REMOVAL.

Part: STARTER GEN — INOPERATIVE (NR 2 ENGINE) · airframe 4,928 hrs · 3,460 cycles

RIGHT (#2) STARTER / GENERATOR INOP. REMOVED FAILED STARTER GENERATOR INSTALLED AN OVERHAULED STARTER GENERATOR REF AMM 24-31-01. PERFORMED STARTER GENERATOR UNSCHEDULED REMOVAL INSPECTION REF EMM 05-50-00. OPSAND LEAK CHECK GOOD WITH NO DEFECTS NOTED P/N 400SG180Q S/N S00083XL.

Part: FCU — MALFUNCTIONED (FLIGHT CONTROL) · airframe 4,997 hrs · 3,467 cycles

DURING DESCENT RECEIVED FLAP FAIL, PTRIM BKP FAIL, SWPS FAULT, AND SPOILER FAULT CAS MESSAGES. REMOVED AND REPLACED FCE NR 1 IAW MM 27-03-01. COMPLIED WITH RIGGING OF THE FLAP SYSTEM AND FLAP SYSTEM OPERATIONAL CHECK IAW MM 27-50-00. COMPLIED WITH PITCH TRIM OPERATIONAL CHECK IAW MM 27-40-00. COMPLIED WITH PRESSURIZATION OPERATIONAL CHECKS IAW 21-31-00 ALL OPERATIONAL CHECKS GOOD. NO FURTHER DEFECTS NOTED AT THIS TIME. PN 462900-1017 S/N 0662.

Part: SENSOR — FAULTY (LT SPOILER) · airframe 4,656 hrs · 3,225 cycles

TROUBLESHOOT SPOILER FAULT & GRND SPOILER FAIL CAS MESSAGE. ACCOMPLISHED CMC DOWNLOAD AND DONWLOADED CMC INTERFACE FILES TO ACCESS TO MED OEM PAGE AND SENT SCREENSHOTS OF SPOILER SYSTEM SENSORS TO CONTACT CENTER FOR ANALYSIS. DURING TROUBLESHOOTING PER SL505-27-0002 FOUND SPOILERS ARE FAILED TO DEPLOY WITH "SPBRK SW DISAS" WHTE CAS MESSAGE ILLUMINATED. CONTACT CENTER REQUESTED TO SWAP FCE 1 AND FCE 2 FOR FURTHER TROUBLESHOOTING. SWAPPED FCE 1 AND FCE 2 FOR FURTHER TS. FOUND DISCREPANCY REMAINED ON SPOILERS, PERFORMED SPOILER RIGGING. SPOILER REMAIN FAILED TO DEPLOY AND "SPBRK SW DISAG" WHITE CAS ILLUMINATED REPLACED LT SPOILER LVDT PER CONTACT CENTER.

Part: SPOILER — MALFUNCTIONED (WING) · airframe 874 hrs · 634 cycles

AT FL450 ACTIVATED THE SPOILERS THEY CAME OUT THEN RETRACTED RIGHT AWAY.  RECEIVED GRND SPLR FAIL CAS MESSAGE AND SPOILER FAULT CAS PERFORMED FIM TASK 27-66-00. PERFORMED MULTIPLE F/T OF SPOILER SYSTEM WITH NO DEFECTS NOTED. PER CUSTOMER REQUEST REPOSITIONED LT AND RT FCE. LT FCE NOW P/N 462900-1017 S/N 1199. RT FCE NOW 462900-1017 S/N 1200. PERFORMED FLAP SYSTEM RIGGING WITH REF TO MM 27-50-00. PERFORMED SPOILER SYSTEM RIGGING WITH REF TO MM 27-60-00. ALL SUBSEQUENT OPS CHECKS SATISFACTORY.

Part: UNKNOWN — MALFUNCTIONED (TE FLAP) · airframe 5,513 hrs · 3,741 cycles

FLAP FAIL, SPWS FAULT, SPOILER FAULT. PERFORMED CMC DOWNLOAD FINDING FAULT CODE27522041 AND 27020141. COMPLIED WITH FIM TASK 27-53-00-810-808 FINDING CONDITION TO BE TRANSITORY. PER CUSTOMER REQUEST SWAPPED FCE 1 AND FCE 2 IAW AMM 27-03-01. PERFORMED FLAP SYSTEM RIGGING AND MULTIFUNCTION SPOILER SYSTEM RIGGING IAW AMM 27-50-00 AND 27-62-00. PERFORMED OPS CHECK OF FLAP SPOILER AND HS PITCH TRIM SYSTEM IAW AMM 27-50-00, 27-60-00 AND 27-40-00 WITH NO DEFECTS. SYSTEM OPS CHECK GOOD AT THIS TIME P/N 4629.

Part: CONTROL UNIT — DEFECTIVE (SPOILERS) · airframe 2,236 hrs · 1,657 cycles

AT CRUISE ALTITUDE (FL450) HAD YELLOW X FOR BOTH SPOILER AND PITCH TRIM INDICATIONS.  ALSO THE PRIMARY PITCH TRIM WAS INOPERATIVE.  WE HAD NO CAS MESSAGES UNTIL AFTER LANDING (SPWS FAULT). TROUBLESHOT SYSTEM. FOUND # 2 FCE TO BE DEFECTIVE. REMOVED AND REPLACED # 2 FCE WITH A TESTED UNIT. PERFORMED OPERATIONAL CHECKS WITH NO DEFECTS NOTED AT THIS TIME. ALL WORK PERFORMED WITH REF TO EMB 505 MM 27-03-01 AND 27-60-00 P/N 462900-1017 S/N 0870

Part: CONTROL UNIT — FAILED (PITCH TRIM) · airframe 5,506 hrs · 3,736 cycles

BACKUP PITCH TRIM FAIL CAS MESSAGE ON PDFS. POWERED AIRCRAFT DOWN AND BACKUP, MESSAGE STILL THERE ON PDFS. REMOVED AND REPLACED #1 FCE AND ACCOMPLISHED ELECTRONIC RIGGING PROCEDURE. ACCOMPLISHED IAW PHENOM 300 AMM 27-03-00. OPS CHECKS GOOD IAW PHENOM 300 AMM 27-03-00. PN OFF AND ON: 462900-1017 SN OFF: 0779 SN ON: 0414   TSN: 467.3 CSN: 308

Part: VALVE — BROKEN (AC BAY) · airframe 6,657 hrs · 4,505 cycles

WHILE IN CLIMB FLT LVL 400-430 HAD CAS MESSAGES DUCT 1 OVER TEMP COME ON AND WITHIN ONE MINUTE HAD CAS MESSAGE DUCT 2 OVERTEMP COME ON AS WELL. ACCOMPLISHED THE QRH PROCEDURE WITH RESULTING PAX O2 MASKS DEPLOYMENT. FOUND RAM AIR VALVE FLAPPER BROKEN. REMOVED AND REPLACED RAM AIR VALVE ASSEMBLY AND OPS / LEAK CHECKED WITH NO DEFECTS FOUND IAW AMM 21-23-00 P/N 550-17170-401 S/N 0001016409

Part: WARNING MESSAGE — FALSE ACTIVATION · airframe 13,410 hrs · 8,250 cycles

IN CLIMB AT ABOUT FL270 THE R BATT R GEN APU GEN AND EXT PWR PBA'S ON THE ECP FLASHED A FEW TIMES. DISPLAYED THE ELEC SYNOPTIC PAGE AND THE EXT PWR APPEARED FOLLOWED BY THE LINES BETWEEN THE MAIN BUSES CHANGING FROM GREEN TO MAGENTA. NO CAS MESSAGES AND NO LOSS OF ELECTRICAL POWER. REMOVED PCB1 & PCB3 OF L/H DCPC AND CLEANED AREA OF ALL FUSE RESIDUES. RERACKED EACH CARD MULTIPLE TIMES TO MANUALLY CLEAN MOTHER BOARD CONNECTORS. WORK DONE IAW AMM 24-61-73. PERFORMED SAME PROCEDURE FOR PCB 2 & PCB 4 OF THE R/H DCPC IAW 24-61-75. PER REQUEST OF F.T.M REPLACED LH DC POWER CENTER WITH MODIFIED UNIT IN REFERENCE WITH AMM 24-61-01. COMPLETED ALL FUNCTIONAL TESTS AS REQUIRED PER TASK # 24-61-01-720-801 SUCCESSFULLY.

Part: CONTROL UNIT — MALFUNCTIONED · airframe 2,197 hrs · 1,630 cycles

AT CRUISE ALTITUDE (FL430) HAD YELLOW X FOR BOTH SPOILER AND PITCH INDICATIONS.  ALSO SPWS FAULT CAS MESSAGE, AND MAIN TRIM WAS NOT WORKING. TROUBLESHOT, COMPLIED WITH CMC DOWNLOAD, IASP AND ADS OPS - CHECK OK REMOVED AND REPLACED FCE 2 PER MCC IAW AMM 27-03-01  PERFORMED MULTIFUNCTION SPOILER SYSTEM RIGGING IAW 27-60-00.  NO DEFECTS NOTED.  P/N 462900-1017 S/N 0889

Part: CONTROL UNIT — FAILED (SPOILERS) · airframe 5,520 hrs · 3,746 cycles

GND SPLR FAIL CAS MESSAGE IN FLIGHT. REMOVED AND REPLACED FCE 2 UNIT AND PERFORMED SATISFACTORY RIGGING/OPERATIONAL TEST OF THE SPOILER SYSTEM PER EMB 505 AMM 27-03-01 P/N 462900-1017 S/N 0938

Part: CONTROL UNIT — MALFUNCTIONED (NR 2) · airframe 1,882 hrs · 1,310 cycles

DIVERTED DUE TO YELLOW X IN THE BOX UNDER SPOILER AND 2 MORE YELLOW X'S OVER PITCH TRIM INDICATOR RANGE AND NUMNERICAL VALUE AT FL430. DURING DECENT AP PITCH MISTRIM CAS MESSAGE APPEARED AND APPROPRIATE CHECK LIST FOLLOWED. AIRCRAFT LANDED WITHOUT INCIDENT. REPLACED FCE #2 AND PERFORMED RIGGING AND OPS CHECKS.

Part: UPLOCK — MALFUNCTIONED (NLG) · airframe 6,630 hrs · 4,484 cycles

MISSED APPROACH AND DECLARED AN EMERGENCY DUE "LG LEVER DISAGREE" MSG AFTER SELECTING GEARDOWN. WITH A RED NOSE GEAR INDICATION. THE NOSE GEAR EXTENDED WITH A SAFE INDICATION AFTER PULLING THE FREE-FALL HANDLE. (ALL LANDING GEARS HAVE BEEN PINNED DUE TO EMERGENCY) AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT. REMOVED AND REPLACED NLG UPLOCK BOX ASSY. ALL OPS/FUNCTIONAL CHECKS GOOD NO DEFECTS NOTED AT THIS TIME. GOOD TO CONTINUE. (ALL LANDING GEAR PIN HAVE BEEN REMOVED PRIOR TO FLIGHT).

Part: TRIM SYSTEM — MALFUNCTIONED (TE FLAP)

IN FLIGHT WE HAD SWPS FAULT CAS AND SPOILER FAULT CAS ONLY. ON THE MFD IN YELLOW "X" FLAP POSITION, FLAP INDICATION AND PITCH TRIM FLAPS STAYED AT ZERO AND WOULD NOT EXTEND. PITCH TRIM WORKED/ BACKUP PITCH TRIM DIDN'T WORK. AIRCRAFT LANDED WITHOUT INCIDENT. COMPLIED WITH FLAP SYSTEM OPERATIONAL CHECK REF AMM 27-50-00-710-801-A OPS CHECK GOOD. PERFORMED HORIZONTAL STAB PITCH TRIM SYSTEM OPS CHECK IAW AMM CH 27-40-00-710-801-A. OPS CHECK GOOD. PERFORMED PUSHER CUTOUT SWITCH OPERATIONAL CHECK IAW AMM CH 27-36-03-710-801-A. OPS CHECK GOOD.

Part: VALVE — FAILED (RAM AIR) · airframe 1,443 hrs · 1,019 cycles

DIVERTED DUE TO DUCT 1 OVER TEMP CAS MESSAGE ILLUMINATED AT FL410. WHILE CONDUCTING QRH PROCEDURES, DUCT 1 OVER TEMP AND DUCT 2 OVERTEMP CAS MESSAGES ILLUMINATED CONDUCTED QRH PROCEDURE DESCENDED TO 10,000 FT PER PROCEDURE. AIRCRAFT LANDED WITHOUT INCIDENT. REMOVED AND REPLACED RAM AIR VALVE. OPS CHECK GOOD.

Part: STARTER GEN — MALFUNCTIONED (NR 2 ENGINE) · airframe 2,195 hrs · 1,543 cycles

WHILE INFLIGHT WE FELT A VIBRATION IN THE AIRCRAFT AFTER 10-15 MINUTES RIGHT GENERATOR OFF LINE CAS MESSAGE, FOLLOWING CHECKLIST AND LANDED EYW. MX ASK US TO DO A RESET AND START ENGINES. UNSUCCESSFUL. WHILE INFLIGHT WE FELT A VIBRATION IN THE AIRCRAFT AFTER 10-15 MINUTES RIGHT GENERATOR OFF LINE CAS MESSAGE, FOLLOWING CHECKLIST AND LANDED EYW. MX ASK US TO DO A RESET AND START ENGINES. UNSUCCESSFUL. WHILE INFLIGHT CREW FELT A VIBRATION IN THE AIRCRAFT AFTER 10-15 MINUTES RIGHT GENERATOR OFF LINE CAS MESSAGE, FOLLOW CHECKLIST AND LANDED WITHOUT INCIDENT. R&R NR 2 ENGINE STARTER/GENERATOR AND C/W UNSCHEDULED REMOVAL INSPECTION/PROCEDURE.

Part: NOT REPORTED — MALFUNCTIONED · airframe 2,131 hrs · 1,552 cycles

DIVERTED DUE TO AT FL450 THE "SHED BUSS OFF" CAS MESSAGE FOLLOWED BY " GEN 1 OFF BUSS" CAS MESSAGE. THERE WAS BOTH UNUSUAL NOISE AND VIBRATION SO WE SHUT THE NR 1 ENGINE DOWN IAW THE CHECKLIST. AIRCRAFT LANDED WITHOUT INCIDENT.

Part: STARTER GEN — FAILED (NR 2 ENGINE) · airframe 5,870 hrs · 4,028 cycles

DIVERTED DUE TO ENGINE VIBRATION FOLLOWED BY GEN FAIL. SHUT DOWN NR 2 ENGINE PER THE CHECKLIST. DECLARED AN EMERGENCY. AIRCRAFT LANDED SAFELY. R&R NR 2 STARTER/GENERAL AND C/W UNSCHEDULED STARTER/GENERATOR SPECIAL INSPECTION. ALL CHECKS NORMAL.

Part: STARTER GEN — MALFUNCTIONED (NR 1 ENGINE) · airframe 2,218 hrs · 1,585 cycles

DIVERTED DUE TO VIBRATION NOTICED FOLLOWED BY A "GEN 1 OFF BUS" CAS. NR 1 ENGINE WAS THEN SHUT DOWN IAW CHECKLIST. AIRCRAFT LANDED WITHOUT INCIDENT. R&R STARTER/GEN AND COMPLIED WITH 05-50-02 UNSCHEDULED STARTER/GEN REMOVAL INSP WITH NO DEFECTS NOTED.

Part: STARTER GEN — MALFUNCTIONED (LT ENGINE) · airframe 2,034 hrs · 1,509 cycles

LEFT ENGINE HAS A RUMBLING VIBRATION WHEN RUNNING. STARTER GENERATOR LUGS AND SURGES DURING START CYCLE. REMOVED AND REPLACED STARTER GENERATOR. WORK WAS DONE IRT 24-81-01. OPS AND LEAK CHECK GOOD. COMPLIED WITH CMM TASK 05-50-00 FOR UNSCHEDULED GENERATOR CHANGE. NO DEFECTS NOTED. RAN A/C MULTIPLE TIMES WITH NO VIBRATION.

Part: POSITION UNIT — FAILED (SPOILERS)

AUTO PILOT AND YAW DAMPER DISENGAGED ON THEIR OWN IN FLIGHT ON APPROACH. YELLOW AP FAIL AND YD FAIL CAS MESSAGES ON BOTH PFDS. THIS WAS DUE TO SPEED BRAKES RETRACTING ON THEIR OWN. REMOVED AND REPLACED SPOILER SURFACE POSITON UNIT. CHECKS GOOD ON GROUND AT THIS TIME.

Part: STARTER GEN — MALFUNCTIONED (NR 1 ENGINE) · airframe 5,722 hrs · 3,951 cycles

DIVERTED DUE TO LOSS OF NR 1 GENERATOR. CREW ATTEMPTED RESET WITH NO SUCCESS. NO VIBRATIONS NOTED, JUST A HUM. LANDED WITHOUT INCIDENT. R&R STARTER/GEN AND COMPLIED WITH 05-50-02 UNSCHEDULED STARTER/GEN REMOVAL INSP WITH NO DEFECTS NOTED.

Part: DCU — MALFUNCTIONED (NR 1) · airframe 4,305 hrs · 3,014 cycles

"PRESN AUTO FAIL" CAS MESSAGE ILLUMINATED IN FLIGHT ALONG WITH "AP FAIL" AND "YD FAIL". R&R GSD41 1 (DCU1). OPS CHECK GOOD. MESSAGE CLEARED.

Part: STARTER GEN — FAILED (NR 1 ENGINE) · airframe 5,219 hrs · 3,545 cycles

DIVERTED DUE TO VIBRATION GEN NR 1 FAIL CAS MSG APPEARED SHORTLY AFTER. CREW RAN CHECKLIST. VIBRATION WENT AWAY WITH REDUCED POWER BUT GEN WOULD NOT RESET. AIRCRAFT LANDED WITHOUT INCIDENT. R&R NR 1 GEN, STARTER PAD SEAL MAGNETIC SEAL, ACCESSORY DRIVE GEARSHIFT SEAL, AND INLET FUEL PRESSURE TUBE. OPS AND LEAK CHECK GOOD.

Part: STARTER GEN — FAILED (RT ENGINE) · airframe 4,068 hrs · 2,886 cycles

DIVERTED DUE TO STRONG VIBRATION FROM RT ENGINE FOLLOWED BY RT GEN FAIL. AIRCRAFT LANDED WITHOUT INCIDENT. R&R STARTER/GEN AND HIGH PRESSURE FUEL LINE. OPS AND LEAK CHECKS GOOD.

Part: TRIM SYSTEM — OUT OF RIG · airframe 6,297 hrs · 4,323 cycles

DIVERTED DUE TO PTRIM NML FAIL CAS AT FL450. RAN THE CHECKLIST THEN FLEW MANUALLY ON THE BACKUP TRIM. AIRCRAFT LANDED WITHOUT INCIDENT. R&R #2 FCE. COMPLIED WITH RIGGING PROCEDURES AND OPS CHECK. OPS AND RIGGING CHECK GOOD.

Part: LANDING GEAR — MALFUNCTIONED (NOSE) · airframe 4,729 hrs · 3,292 cycles

AFTER SELECTING GEAR DOWN ONLY NOSE GEAR SHOWED DOWN AND LOCKED. FOLLOWED CHECKLIST AND USED ALTERNATE GEAR EXTENSION AND GOT THREE DOWN AND LOCKED INDICATION. TROUBLE SHOT. GAINED ACCESS TO HYDRAULIC SELECTOR VALVE AND REPAIRED CHAFED WIRES. PERFORMED MULTIPLE SATISFACTORY OPERATIONAL CHECKS OF THE LANDING GEAR EXTERIOR RETRACTION. NO DEFECTS NOTED.

Part: ENGINE — VIBRATION (RIGHT) · airframe 2,234 hrs · 1,622 cycles

DIVERTED DUE TO RIGHT ENGINE VIBE AT FL450. ENGINE ITT TEMP EXCEEDED RED LINE. RECEIVED AN E2 CAS AND NO DISPATCH. RAN CHECKLIST, PULLED RIGHT THROTTLE TO IDLE AND ENGINE STABILIZED. AIRCRAFT LANDED WITHOUT INCIDENT. TACCOMPLISHED FADEC DOWNLOAD AND DATA INDICATED ON ITT. EXCEEDANCE HAD OCCURED FOR AN EXTENED PERIOD THAT WAS IN EXCESS OF ALLOWABLE PARAMETERS. RECEIVED DIRECTION FROM PRATT + WHITNEY TO REMOVE # 2 ENGINE FROM SERVICE.

Part: CONTROLLER — MALFUNCTIONED (TE FLAPS) · airframe 4,439 hrs · 3,111 cycles

DIVERTED DUE TO SWPS FAULT, PITRIM BKP FAIL, FLAP FAIL, SPOILER FAULT, RED XS IN FLAP INDICATOR BOX AND RED XS IN PITCH INDICATOR BOX AT ALTITUDE. R & R #1 FCE. PERFORMED RIGGING AND OPS CHECKS WITH NO DEFECTS NOTED AT THIS TIME.

Part: CONTROLLER — MALFUNCTIONED (SPOILERS) · airframe 4,149 hrs · 2,885 cycles

DIVERTED DUE TO NO PITCH TRIM NO SPOILERS AUTOPILOT DISCONNECT COM LINK FAIL DURING CLIMB OUT AT 28,000. AIRCRAFT LANDED WITHOUT INCIDENT. TS TO AND REPLACED #2 FCE. OPS CHECK SATISFACTORY NO DEFECTS NOTED.

Part: CONTROLLER — FAULTED (TE FLAPS) · airframe 6,222 hrs · 4,261 cycles

DIVERTED DUE TO SWPS FAULT, PTRIM BKP FAIL, FLAP FAIL, SPOILTER FAULT CAS MESSAGES DURING FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. R&R #1 FCE. PERFORMED RIGGING. OPS CHECK GOOD.

Part: WARNING MESSAGE — FALSE ACTIVATION (SPOILERS) · airframe 1,120 hrs · 791 cycles

DIVERTED DUE TO SWPS FAULT AND SPOILER FAULT. WITH THE AUTO PILOT/FLIGHT DIRECTOR ENGAGED THE AUTO PILOT WOULD ONLY HOLD ALTITUDE AND NAV IT WOULD NOT CLIMB OR DESCEND. USING VNAV PROMPTED MAX SPEED WARNING AT ALL SPEEDS. AIRCRAFT LANDED WITHOUT INCIDENT. PERFORMED OPS CHECK OF FLAPS, CMC DOWNLOADS, AND FIM. NO DEFECTS NOTED.

Part: STARTER GEN — FAILED (LT ENGINE) · airframe 4,690 hrs · 3,261 cycles

DURING FLIGHT WE HAD A "GEN1 FAIL". WE TRIED TO RESET GEN 1 ACCORDING TO CHECK LIST. WE WERE NOT ABLE TO RESET IT. REMOVED AND REPLACED LT STARTER GENERATOR AND OPS TESTED WITH NO FURTHER DEFECTS FOUND IAW AMM 24-31-00. ACCOMPLISHED PWC EMM TASK 05-50-00-210-821. STARTER / GEN UNSCHEDULED REMOVAL. REPLACED STARTER MAGNETIC FACE SEAL PN 3059820-01 ACCESSING GEAR BOX BREATHER SEAL PN 307981801 AND FMU INPUT FUEL TUBE PN 3126971-01. REPLACED OIL FILTER PN 3052590-01. OPS AND LEAK CHECKS GOOD.

Part: STARTER GEN — FAILED (NR 2 ENGINE) · airframe 1,751 hrs · 1,229 cycles

SIGNIFICANT VIBRATION ASSOCIATED WITH ALL TLA SETTINGS ON NR 2 ENGINE. LOTS OF BLACK SOOT UNDER SIDE OF NACELLE SINCE PREFLIGHT. (48 MIN FLIGHT). REMOVED FAILED STARTER GENERATOR. INSTALLED A REPAIRED STARTER GENERATOR REF AMM 24-31-01. PERFORMED STARTER GENERATOR UNSHEDULED REMOVAL. INSPECTOR REF EMM 05-50-00 OPS AND LEAK CHECK GOOD WITH NO DEFECTS NOTED. MAGNETIC SEAL P/N OFF/ON 3059820-01 NSN BREATHER SEAL P/N OFF/ON 3079823-01 NSN GENERATOR P/N 400SG180Q S/N S00088XL.

Part: STARTER GEN — MALFUNCTIONED (LT ENGINE) · airframe 1,897 hrs · 1,342 cycles

DURING MVF - VIBRATION COMING FROM LEFT ENGINE. HEARD LOW RUMBLE DURING TAKEOFF ROLL. AFTER ROTATION, WE COULD HEAR AND FEEL VIBRATION. WITH CONSTANT AIRSPEED DURING CLIMBOUT / CRUISE FLIGHT, WE MANIPULATED EACH POWER LEVER INDIVIDUALLY - LEFT ENGINE THROTTLE POWER UP / DOWN GREATLY CHANGED VIBRATION. RIGHT THROTTLE - NO CHANGE. REMOVED AND REPLACED NR 1 ENGINE STARTER/GEN AND OPS CHECKED GOOD. IAW AMM 24-31-01. NO DEFECTS NOTED AT THIS TIME.P/N 00SG180Q S/N S00297XL.

Part: CONTROL UNIT — FAULTY (BRAKE SYSTEM) · airframe 4,550 hrs · 3,153 cycles

RECEIVED A BRAKE FAIL CAS, AFTER GEAR RETRACTION. CYCLED THE GEAR ONE TIME. IT DID NOT RESET. ON LANDING WITH THE MESSAGE, USED THE EMERGENCY BRAKE IAW CHECKLIST. LEFT TIRE FAILED AND THERIGHT TIRE PRODUCED A FLAT SPOT. APPEARED FROM THE SKID MARKS THAT THE LT TIRE HAD DRAGED MUCH MORE THAT THE RT. REMOVED THE MAIN WHEELS, PERFORMED A VISUAL INSPECTION OF THE MLG AND ADJACENT AREAS WITH NO DEFECTS NOTED. INSTALLED NEW MLG WHEEL ASSEMBLIES. TROUBLESHOT THE BRAKE FAIL CAS IAW FIM 32-41-00-810-810-A. PERFORMED SATISFACTORY ELECTRICAL CHECKS OF BELL AIRFRAME SYSTEM, CONCLUDED THE BRAKE CONTROL UNIT (BCU) TO BE FAULTY. REMOVED AND REPLACED THE BCU AND PERFORMED A SATISFACTORY FUNCTIONAL TEST OF THE BRAKE SYSTEM. COMPETED WITH 5 MLG SWINGS WITH NO BRAKE FAIL CAS POSTING. TAXIED AIRCRAFT AND VERIFIED BRAKING SYSTEM TO BE OPERATING NORMAL WITH NO DEFECTS NOTED.

Part: GENERATOR — MALFUNCTIONED (NR 2) · airframe 36 hrs · 30 cycles

NR 2 GENERATOR SPIKED TO 990 AMPS, SHED AIR CONDITIONER, AMPS WENT TO 100, AFTER 3 MINUTES THE GENERATOR SPIKED TO 990 AMPS, SHED THE RT WINDSCREEN, AMPS WENT TO 90 AMPS. AFTER 30 MINS CLOSE TO LANDING, AMPS SPIKED TO 800 AMPS, SHED THE RT GENERATOR, AMPS STAYED AT ABOUT 700 AMPS. AFTER 2 - 3 MINUTES, SHUT DOWN RIGHT ENGINE. WITH RIGHT ENGINE OFF AMPS SHOWED 675 AMPS. TROUBLESHOT TO AND REPLACED GEA 2 WITH AN OVERHAULED GEA IAW MM 31-41-03. LEADED SOFTWARE AND CONFIGURATION TO GEA 2 IAW MM 31-41-03. OPS CHECKED GOOD. VERIFIED CORRECT AMP DATA ON BOTH ENGINES WHILE RUNNING AND AFTER SHUT DOWN IAW MM 24-31-00.

Part: MODULATING VALVE — DEFECTIVE (BLEED AIR SYS) · airframe 5,644 hrs · 3,857 cycles

ON DESCENT PASSING 1200 (H STAB AND ENGINE HEATS ON) IMC, "DUCT 2 OVERTEMP" CAS MESSAGE ILLUMINATED. AIR CONDITION TO MANUAL - NO EFFECT, ECS KNOB - 1 NO EFFECT, ECS KNOB OFF - VENT CAS MESSAGE WENT OUT. LANDING UNEVENTFUL AFTER SHUT DOWN STRONG BURNING SMELL WAS NOTICEABLE. REMOVED AND REPLACED TEMP MODULATING VALVE NR 2 AND DUCT TEMP SENSOR NR 2 PERFORMED OPS CHKS. OPS CHKS GOOD.

Part: ACTUATOR — FAILED (PITCH TRIM) · airframe 3,976 hrs · 2,737 cycles

PITCH TRIM ACTUATOR LEAKING OIL. REMOVED AND REPLACED THE PITCH TRIM ACTUATOR IAW AMM 27-41-01.

Part: STARTER GEN — FAILED (NR 1 ENGINE) · airframe 3,742 hrs · 2,580 cycles

AIR TURN BACK DUE TO A VIBRATION SHORTLY AFTER TAKEOFF FOLLOWED BY GEN1 FAIL APPROX 90 SEC LATER. AIRCRAFT LANDED WITHOUT INCIDENT. R&R STARTER/GEN. OPS CHECK GOOD. NO OTHER DEFECTS NOTED.

Part: ACTUATOR — FAILED (PITCH TRIM) · airframe 6,094 hrs · 4,070 cycles

DURING FLIGHT AT FL450 THE PTRIM NML FAIL CAS CAME ON. SWAPPED FCE. REMOVED AND REPLACED PITCH TRIM ACTUATOR. OPS CHECKED GOOD.

Part: STARTER GEN — MALFUNCTIONED (RT ENGINE) · airframe 4,872 hrs · 3,260 cycles

NR 2 GEN TRIPPED OFFLINE AND WOULD NOT RESET. VIBRATION WAS FELT IN NR 2 ENGINE. REMOVED AND REPLACED NR 2 STARTER GEN WITH OVERHAULED PER AMM 24-31-01 COMPLIED WITH STATER GENERATOR UNSCHEDULED REMOVAL TASK 05-50-00-810-821. OPERATIONAL CHECK SATISFACTORY. LEAK CHECK SATISFACTORY COMPLIED WITH FCD 0179 WITH NO DEFECTS NOTED. ALL WORK DONE IAW EMM 05-50-00 AND AMM 24-31-01-400-801-A. REPLACED RT ENGINE OIL FILTER AS REQUIRED PER AMM 79-21-00

Part: ACTUATOR — FAILED (PITCH TRIM) · airframe 4,682 hrs · 3,141 cycles

PITCH TRIM NORMAL FAIL CAS MESSAGE AT HIGH ALTITUDE. WHEN BACKUP TRIM ENGAGED PTRM BKP FAIL CAS MESSAGE. TRIM FULL DOWN AT 14.1. REPLACED THE PITCH TRIM ACTUATOR. OPS CHECKED GOOD. R & R TELESCOPING DUCT O-RING SEALS. LEAK CHECKED GOOD.

Part: WARNING MESSAGE — FALSE ACTIVATION (PITCH TRM) · airframe 4,672 hrs · 3,134 cycles

PASSING FLIGHT LEVEL 390, PTRIM NML FAIL, CAS MESSAGE ILLUMINATED AND REMAINED ON FOR REMAINDER OF FLIGHT. OPS CHECK GOOD AT THIS TIME.

Part: ACTUATOR — MALFUNCTIONED (PITCH TRIM) · airframe 4,673 hrs · 3,135 cycles

PITCH TRIM NORMAL FAIL, CAS MESSAGE ILLUMINATED ON CLIMB PASSING 16,000FT. REPLACED THE STAB TRIM ACTUATOR WITH REPAIRED UNIT. REPLACED FCE NR 2 WITH MODIFIED UNIT. OPS CHECKED GOOD AND NO DEFECTS NOTED.

Part: CONTROL UNIT — FAILED (BRAKES) · airframe 5,294 hrs · 3,572 cycles

BRAKES FAILED CAS MESSAGE ON LANDING. MAIN BRAKES DID NOT WORK. BOTH MAIN TIRES HAD FLAT SPOTTED. R & R THE BRAKE CONTROL UNIT AND BOTH MAIN WHEEL AND TIRE ASSYS. OPS CHECKED GOOD.

Part: WARNING MESSAGE — FALSE ACTIVATION

DUCT NR 2 OVERTEMP CAS MESSAGE DURING CLIMB OUT. DECLARED EMERGENCY AND DIVERTED. LANDED WITHOUT INCIDENT. RESET THE CIRCUIT BREAKER AND COMPLIED WITH AN ELECTRICAL CHECK. NO FAULTS FOUND..