Elite Air, Inc.

Operated by Elite Air Inc (per NTSB report)

The first officer's failure to maintain a safe distance from a large turbine-powered airplane while escorting passengers, resulting in a passenger encounter with jet blast.

Sanction: $2,500 · case closed 2012-08-06

Sanction: $8,000 · case closed 2010-10-15

Sanction: $5,000 · case closed 2008-06-18

Sanction: $8,000 · case closed 2007-03-02

Part: ENGINE — FAILED (LEFT) · airframe 5,261 hrs · 2,546 cycles

ON SHORT FINAL APPROACH INTO AGS FELT A VIBRATION FROM THE LEFT ENGINE. SHUT ENGINE DOWN AND LANDED WITHOUT INCIDENT. UPON PRELIMINARY INSPECTION COULD NOT ROTATE TURBINE AND METAL DEBRIS FOUND IN TAIL.

Part: CONTROLLER — ODOR (ZONE 100) · airframe 6,772 hrs · 2,853 cycles

L WINDSHIELD HEAT FAIL CAS MESSAGE FOLLOWED BY BURNING SMELL.

Part: COWLING — UNKNOWN (ZONE 400) · airframe 3,549 hrs · 1,896 cycles

UPPER LEFT COWLING DEPARTED AIRCRAFT ON TAKEOFF. NO INDICATIONS

Part: INDICATION SYS — ERRATIC (ENGINE OIL) · airframe 9,228 hrs · 6,327 cycles

OIL PRESSURE INDICATION ERATIC. SHUTDOWN ENGINE AS PRECAUTIONARY.

Part: ENGINE — FAILED (NR 1) · airframe 5,405 hrs · 4,317 cycles

NUMBER 1 ENGINE FAILURE AT FL150. CREW HEARD A BANG, AIRCRAFT YAWED, ENGINE ROLLBACK, NO THRUST AVAILABLE, ITT STARTED TO RISE AND CREW SHUTDOWN. DIVERTED AND LANDED WITHOUT FURTHER ISSUE.

Part: NONE — FAILED (PILOTS CONTROL) · airframe 955 hrs · 696 cycles

SUSPECT PITCH TRIM JAM ON DEPARTURE. STABILIZER WOULD NOT MOVE FROM 7.7 DEGREES POSITION CAUSING THE CREW TO SIGNIFICANTLY USE FORCE ON ELEVATOR CONTROL AND DECREASE ENGINE THRUST TO LEVEL OFF. RETURNED TO DEPARTURE AIRPORT KIAD WITHOUT FURTHER INCIDENT

Part: PUMP — LEAKING (ZONE 500) · airframe 7,320 hrs · 7,178 cycles

CRUISE AT FL390 AND GOT A LOW HYD QTY LIGHT, FOLLOWED BY R ENG HYD PRESS, THEN L ENG HYD PRESS. CREW FOLLOWED CHECKLIST AND BLEW DOWN GEAR USING NITROGEN.

Part: TRANSDUCER — ERRATIC (ZONE 200) · airframe 7,294 hrs · 7,157 cycles

HYDRAULIC PRESSURE ABOVE NORMAL OPERATING RANGE. CHECKLIST CALLS FOR SELECTING HYDRAULIC PRESSURE RELIEF SWITCH, THEN BLOW DOWN GEAR USING PNEUMATIC BOTTLE, AND LAND WITHOUT BRAKES.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 7,280 hrs · 7,142 cycles

STARTED DESCENDING INTO KPHL WE NOTICED THE HYDRAULIC GAUGE WENT UP PAST RED LINE (HIGH HYDRAULIC PRESSURE). PULLED OUT THE CHECKLIST AND AS PER THE CHECKS PERFORMED A HYDRAULIC SYSTEM RELIEF WHICH HAD US DO AN EMERGENCY GEAR EXTENSION, NO FLAP LANDING AND POWER BRAKE FAILURE LANDING. WENT TO A HOLD AT BUNTS INTERSECTION TO FINISH OUR EMERGENCY GEAR EXTENSION CHECKLIST AND THEN CONTINUED TO KPHL FOR A NO FLAP ILS Z TO 9R AND LANDED WITHOUT INCIDENT.

Part: UNKNOWN — ODOR (COCKPIT) · airframe 4,329 hrs · 2,836 cycles

CLIMBING AT FL300 AND HEARD A LOUD BANG, FOLLOWED BY A BURNING SMELL AND VIBRATION. DIVERTED TO NEAREST AIRPORT

Part: BOTTLE — EMPTY (LG EMER EXTEND) · airframe 7,984 hrs · 5,039 cycles

DURING SERVICE CHECKS, TECHNICIAN NOTICED LANDING GEAR EMERGENCY EXTENSION BOTTLE GAUGE READING ZERO. UPON SERVICING, NOTICED THE NITROGEN WAS NOT FILLING AND IMMEDIATELY LEAKING OUT. FURTHER TROUBLESHOOTING REVEALED THE UNION THAT SCREWS INTO THE BOTTLE HAD SHEARED OFF. NO AIRCRAFT DAMAGE FROM THE HIGH PRESSURE UNION SHEARING, BUT HAD THERE BEEN A GEAR ISSUE ON THE PREVIOUS FLIGHT, THE EMERGENCY SYSTEM WOULD NOT HAVE WORKED. UNIT WAS HYDROSTATIC TESTED 10/2020.

Part: AUTOPILOT SYS — FAILED · airframe 4,091 hrs · 2,673 cycles

AUTO PILOT FAILURE DURING CLIMB. CREW DEVIATED FLIGHT PLAN.

Part: WARNING LIGHT — ILLUMINATED (AIR CON SYS) · airframe 6,544 hrs · 5,519 cycles

SHORTLY AFTER TAKEOFF "AIR COND FAIL" LIGHT ILLUMINATED. CREW RETURNED TO AIRPORT.

Part: DRAIN VALVE — CRACKED (NR 1) · airframe 246 hrs · 202 cycles

FL450 MACH TRIM FAIL, YD FAIL, NR 1 ADC ALT/IASA/VS FAIL. FOLLOWED BY R/L ENGINE TRUST FAULT, RUDDER LIMITER FAULT, STAB TRIM FAULT. FOUND CRACKED PITOT DRAIN ASSEMBLY P/N 50033-001 THAT CAUSED THIS EVENT.

Part: PITOT HEAD — OBSTRUCTED (LEFT) · airframe 3,973 hrs · 2,601 cycles

AIRSPEED INDICATION MISCOMPARE FROM LT TO RT. DEBRIS FOUND IN LT PITOT, REMOVED, AND LEAKED CHECKED.

Part: AHRS — FAILED (ZONE 200) · airframe 6,455 hrs · 5,457 cycles

DURING TAKEOFF ROLL. PILOT AHRS FAILED.

Part: PITOT HEAD — BLOCKED (PILOTS) · airframe 7,535 hrs · 6,048 cycles

ABORTED TAKE OFF DUE TO AIRSPEED INDICATION MISMATCH. "ESTIMATED" PILOT INDICATION WAS AT 80KTS AND CO-PILOT INDICATION WAS AT 120KTS. AFTER INSPECTION, PITOT TUBE WAS BLOCKED WITH DEBRIS. CURRENTLY, OUR OPERATIONS MANUAL REQUIRES TO SUBMIT SDR FOR ABORTED TAKE OFF.

Part: VALVE — LEAKING (FUEL VENT) · airframe 30 hrs · 20 cycles

AIRCRAFT DEPARTED AND MADE A LEFT BANK TURN. TOWER NOTIFIED OF FUEL COMING FROM LEFT WING DURING MANUERVER. CIRCLE BACK TO LAND AND ACCESS FUEL LEAK.

Part: STARTER GEN — FAILED (NR 2 ENGINE)

DURING CRUISE THE NR 2 ENGINE STARTER/GENERATOR FAILED AND CAUSED VIBRATION.

Part: PRESSURE SWITCH — FAILED (HYD SYSTEM)

DURING FLIGHT, THE CREW NOTICED THE HYDRAULIC QUANTITY LOW MESSAGE ILLUMINATE. SHORTLY THEREAFTER THE HYDRAULIC PRESSURE FROM THE MAIN ENGINE HYDRAULIC PUMPS STARTED TO DROP FOLLOWED BY THE LT MAIN PRESSURE LOW WARNING LIGHT ILLUMINATE. THE MAIN PRESSURE DROPPED TO 300 PSI AND THE CREW HAD TO USE THE EMERGENCY EXTENSION FOR THE LANDING GEAR. THE ACFT THEN LANDED WITHOUT INCIDENT. UPON INVESTIGATION, THE LT MAIN PRESSURE LOW SWITCH WAS FOUND TO BE SPLIT OPEN ALLOWING THE HYDRAULIC FLUID TO BE DRAINED. THE PRESSURE SWITCH WAS REPLACED AS WELL AS BOTH ENGINE HYDRAULIC FLUID TO BE DRAINED. THE PRESSURE SWITCH WAS REPLACED AS WELL AS BOTH ENGINE HYDRAULIC PUMPS AND THE SYSTEM WAS FLUSHED AND CLEANED. ACFT RETURNED TO SERVICE 5/29/2015. FURTHER INVESTIGATION HAS REVEALED THAT MFG HAS ISSUED A SB 40-29-05 TO ADDRESS THESE FAULTY SWITCHES HOWEVER THEY LIST IT AS A RECOMMENDED BULLETIN.

Part: EXHAUST STACK — BROKEN (ZONE 400) · airframe 8,408 hrs

PILOT NOTED RT ENGINE EGT INDICATOR INOPERATIVE IN CRUISE FLIGHT. MX FOUND EXHAUST STACK BROKEN IN 2 JUST FORWARD OF EGT PROBE. NO DAMAGE TO COWLING NOTED.

Part: SKIN — DENTED (BS 101) · airframe 1,065 hrs · 514 cycles

DURING LANDING APPROACH, AIRCRAFT STRUCK SECURITY FENCE, RESULTING IN DAMAGE TO FUSELAGE SKIN PANEL ON THE LT SIDE OF THE FUSELAGE. THE LOCATION OF THE DAMAGE IS AT FUSELAGE STATION 101.18, WATER LINE 73.50. DAMAGE SUSTAINED TO SKIN PANEL IS A DENT WITH GOUGES APPROX 2 INCHES LONG.

Part: LEVER — OBSTRUCTED (LEFT)

DURING SCHEDULED MAINTENANCE, AN INSPECTION THROUGH THE ACCESS PANEL IN THE LT WHEEL WELL REVEALED THAT LT THRUST LEVER TELEFORCE IS FULLY IN CONTACT WITH THE LT RUDDER CABLE WHICH MIGHT CAUSE CHAFFING. FURTHER INSP SHOWED THAT THE TELEFORCE WAS NOT ROUTED PROPERLY AND NOT IN THE TEFLON HOLDER AS WELL. TELEFORCE CABLE WAS ALSO FOUND TO BE WRAPPED AROUND THE RUDDER CONTROL CABLE ALL ALONG. WHILE PERFORMING ELEVATOR CABLE INSPECTION, IT WAS FOUND THAT THE PRIMARY ELEVATOR CONTROL WAS NOT POSITIONED IN ITS DEDICATED GROOVE WHERE IT WAS FOUND MOUNTED OVER THE PITCH SERVO CABLE ADJACENT TO THE ELEVATOR PRIMARY CABLE GROOVE. THE ELEVATOR PRIMARY CABLE WAS FOUND WITH 3 BROKEN STRANDS. DURING INSPECTION OF ELEVATOR CONTROL SYS, A COTTER PIN WAS FOUND TO BE MISSING ON THE JOINT POINT OF RT ELEVATOR UPPER PUSHROD AND RT ELEVATOR HORN ASSY. THIS IS TO INFORM YOU FURTHER OF THE CRITICAL FINDINGS ON THIS AC, UNDERGOING MAINTENANCE. LT THRUST LEVER TELEFLEX IN UNDER FLOOR AREA ADJACENT TO LT WHEEL WELL NOT (ROUTED) THRU TEFLON GUIDE AND FOUND (TWISTED) AROUND LT RUDDER CABLE. RT ELEVATOR CONTROL (PUSH/PULL) ROD CONNECTED TO ELEVATOR CONTROL HORN NOT SAFETIED. COTTER PIN NOT INSTALLED. IN TAIL CONE AREA- ELEVATOR CONTROL CABLE (TWISTED) AND OUT OF CABLE TRACK AND TENSIONED ON TOP OF THE ADJACENT ELEVATOR SERVO CABLE TRACK AND CABLE. DUE TO THE (TWIST) AND DIRECT CONTACT OF THE EDGE OF THE PULLEY TRACK- PRIMARY ELEVATOR CABLE WAS FOUND TO HAVE (3) BROKEN STRANDS. (K)