N337QS
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| NETJETS AVIATION, INC. (DXTA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
NO T/O CONFIG RED CAS APPEARED IMMEDIATELY UPON TAKEOFF (NORMAL AURAL TAKEOFF OK ON THE GROUND). FLAP FAIL YELLOW CAS, PTRIM BKP FAIL YELLOW CAS, SWPS FAULT YELLOW CAS, SPOILER FAULT WHITE CAS, & YELLOW X'S ON FLAP INDICATORS ALL UPON FLAP RETRACTION. REPAIRED BROKEN WIRE. OPS CHECK GOOD. IAW PHENOM 300 AMM 27-03-01.
APPROX. 5 MINUTES AFTER FINISHING ECS 2 VALVE FAIL QRH, A GRADUAL LOSS OF CABIN PRESSURIZATION STARTED. CABIN ALTITUDE WAS ROUGHLY 3000FT. ROUGHLY 2-3000FPM CLIMB IN THE LOSS OF PRESSURIZATION, RATE READING WAS IN THE RED. THIS OCCURED WHILE AT 280+KTS, ROUGHLY AROUND 29,000FT. WE WERE ABLE TO DESCEND RAPIDLY TO 10,000FT. ONCE LEVEL AT 10,000FT, CABIN ALTITUDE EQUALED 10,000FT, MASK DID NOT DEPLOY. CABIN DELTA P AT 10,000FT WAS 0.0, CAB ALTITUDE HI CAS CAME ON, WE CONTINUED A DECENT BELOW 10,000FT, ACCOMPLISHED QRH PROCEDURE. CORRECTIVE ACTION; REPLACED THE RH FCSOV AND COMPLIED WITH OPS AND LEAK CHECKS WITH NO FAULTS. WORK DONE WITH REFERENCE TO EMB505 AMM 21-21-01.
FUSELAGE STRUCTURE: WHILE ENROUTE AT 21,000 FT WE ENCOUNTERED SEVERE TURBULENCE THAT LASTED FOR APPROX. 15 SECONDS. THERE DOESN'T APPEAR TO BE ANY VISUAL DAMAGE TO THE AIRCRAFT. CORRECTIVE ACTION; COMPLETED UNSCHEDULED: SEVERE TURBULENCE INSPECTION/CHECK. PERFORMED CVDR DL AND SENT FOR REVIEW. FOUND AIRCRAFT WAS NOT OPERATED OUTSIDE THE THE NORMAL ACCELERATION LIMITATIONS AND NO FURTHER INSPECTIONS REQUIRED. ALL !AW PHENOM 300 AMM 05-50-20.
LEFT ENGINE FAILURE DEPARTING SFO AT 1000' MSL. 2-3 BANGS THEN ENGINE FAILURE. NOT ASSOCIATED WITH ANY CAS MESSAGES. SHUT LEFT ENGINE DOWN & BURNED OFF FUEL & RETURNED TO SFO. ACCOMPLISHED THE REMOVAL OF THE LT ENGINE AND INSTALLED A RENTAL INSPECTED ENGINE. PERFORMED THE TLD CLEARING PROCEDURE. ACCOMPLISHED OIL SERVICING AND INITIAL IDLE RUN WITH SATISFACTORY RESULTS, NO LEAKS NOTED. ACCOMPLSIHED POST ENGINE INSTALLTION OPERATIONAL CHECKS WITH ENGINE WITH IN EMM PARAMETERS, NO LEAKS NOTED. CLOSED ALL ACCESS AS REQUIRED. MAINTENANCE ACCOMPLISHED IAW AMM 71-00-00/400 AND EMM 71-00-00-760-804 AND 71-00-00-760-823.
EMERGENCY LIGHTS ON IN THE ARMED POSITION INFLIGHT. REPEAT WRITEUP. REMOVED AND REPLACED FORWARD AND AFT EMERGENCY LIGHT BATTERIES AND PERFORMED IOPERATIONAL CHECK OF THE EMERGENCY BATTERIES REF AMM 33-52-01. OPS CHECK GOOD AT THIS TIME.
CABIN EMERG LIGHTS STROBE WHEN SWITCH IS IN ARM POSITION. PERFORMED TOP CHARGE TC-505-33-200403. EMER BATTERY OPS TEST PERFORMED WITH NO DEFECTS NOTED AT THIS TIME. WORK PERFORMED WITH REF. TO THE PHENOM 300 AMM 33-52-01.
FLAP FAIL YELLOW CAS: AFTER SELECTING FLAPS FULL ON APPROACH, RECEIVED FLAP FAIL YELLOW CAS. WE EXECUTED A GO AROUND, RAN THE QRC (BUT DID NOT CYCLE THE FLAPS), AND RETURNED TO LAND. AFTER LANDING, WE SELECTED FLAPS 0, BUT THE FLAPS REMAIN EXTENDED. PERFORMED MULTIPLE FUCNTIONAL CHECKS OF FLAPS SYS. NO DEFECTS NOTED & CAS MESSAGE CLEARED. FLAPS WORKED PERFECTLY THROUGH MULTIPLE CYCLES OF FLAPS SYS & NO CAS MESSAGES WERE DISPLAYED. ALL WORK WAS ACCOMPLISHED IAW AMM 27-50-00. NO FURTHER DEFECTS NOTED.
ENTRANCE STAIRS: ENTRY DOOR FWD LOWER "LOCK" PIN INDICATOR IS PARTIALLY BLOCKED BY SOMETHING BEHIND THE WINDOW. LOCK PIN CAN BE CONFIRMED IN PLACE WITH A FLASHLIGHT. VIEW OF THE PIN IS PARTIALLY BLOCKED. // SIGNOFF// VERIFIED SQUAWK. GAINED ACCESS TO DISCREPANT AREA OF MCD ENTRANCE STAIRS & FOUND A STRAY PIECE OF SPEED TAPE PARTIALLY BLOCKING VIEW OF GREEN FLAG INDICATOR. REMOVED STRAY SPEED TAPE AS REQUIRED, THEN RESTORED MCD ENTRANCE STAIRS TO ORIGINAL CONDITION. GREEN INDICATORS ARE VISIBLE WITHIN MCD STAIR LOCK-PIN WINDOWS. MCD FUNCTIONS NORMALLY. REF. EMB PHENOM 300 AMM 52-11-21.
CABIN EMERG LIGHT: EMERGENCY FLASHING IN CRUISE FLIGHT. SWITCH IN ARM POSITION CABIN EMERGENCY LIGHTS BEGAN FLASHING DURING CRUISE. REMOVE AND REPLACED FWD EMER BATTERY PACK WITH CUSTOMER PROVIDED TESTED BATTERY PACK WORK DONE PER PHENOM 300 AMM 33-52-01 OPS CHECK GOOD AT THIS TIME.
EMERGENCY LIGHTS STARTED BLINKING ON/OFF DURING FLIGHT. REMOVED FORWARD AND AFT EMERGENCY UGHT BATTERIES FOR UGHT BUNKING ON/OFF, INSTALL.ED TWO EACH TESTED BATTERIES IAW EMRAER PHENOM 300 AMM PART II TASK 33-52-01-000-801-A/400-801-A OPERATIONAL CHECK GOOD. ORIG SUBMISSION DATE: 1/16/2023
WHILE PERFORMING EO WC E50-24-0002_2-JIC (EMBRAER PHENOM EXTERNAL POWER RECEPTACLE HARDWARE INSPECTION, TECH REPORTED THE BACK OF THE POSITIVE TERMINAL ON THE GPU CONNECTOR SHOWS SIGNS OF BURNING AND ARCING.//CORRECTIVE ACTION// REMOVED AND REPLACED ELECTRICAL CABLES (W311 & W310) AT GPU RECEPTACLE IAW EMB505 AMM 24-65-01 & 24-41-01. PERFORMED OPS CHECK OF ENERGIZATION OF THE AIRCRAFT WITH AN EXTERNAL DC POWER SUPPLY IAW EMB505 AMM 24-41-00 AND FOUND SYSTEM WORKING PROPERLY AT THIS TIME.
WHILE PERFORMING EO WC E50-24-0002_2-JIC (EMBRAER PHENOM EXTERNAL POWER RECEPTACLE HARDWARE INSPECTION, TECH REPORTED THE BACK OF THE POSITIVE TERMINAL ON THE GPU CONNECTOR SHOWS SIGNS OF BURNING AND ARCING.
FIRST OFFICER RUDDER PEDAL: ON LANDING ROLLOUT DISCOVERED CO-PILOTS LEFT BRAKE PEDAL IS BINDING. INSPECTED PILOT AND FIRST OFFICER RUDDER PEDAL TORQUE TUBES CONNECTING RODS LINKAGE AND HARDWARE WITH NO DEFECTS NOTED LUBRICATED ALL CONNECTING RODS BEARINGS AND VERIFIED RUDDER PEDALS ARE WORKING PROPERLY WITH NO BINDING OPS CHECK GOOD AT THIS TIME, REF AMM 27-21-00
CABIN EMERG LIGHT: WITH EMERGENCY LIGHTS IN ARM POSITION, DURING ENGINE START WE GOT A CAS MESSAGE THAT SAID EMER LIGHTS NOT ARMED. WHILE INFLIGHT, EMERGENCY LIGHTS WERE FLICKERING WITH THE SWITCH IN THE ARM POSITION COMPLIED WITH SL 505-33-0005 AND FIM 33-50-00-810-801-A ISOLATED THE EMERGENCY LIGHT ISSUE TO THE AFT BATTERY. WE DISCONNECTED THE AFT BATTERY AND THE EMERGENCY LIGHTS OPERATED NORMAL. REMOVED AFT EMERGENCY BATTERY PIN 6450LS-00 SIN 1609. ACCESSED FWD EMERGENCY BATTERY. REMOVED AND REPLACED THE FWD EMERGENCY BATTERIES. COMPLIED WITH SATISFACTORY OPERATIONAL CHECK. REFERENCE AMM 33-52-01-000/400-80-A.
COMPLYING WITH S.B.505-55-004R3 FOUND CORROSION ON 1 EACH R/H AND L/H ELEVATORS ADJUSTABLE MASS BALANCE WEIGHTS P/N PE915109-L33 REPLACED WITH NEW.
COMPLYING WITH S.B.505-55-004R3 FOUND CORROSION ON 1 EACH R/H AND L/H ELEVATORS ADJUSTABLE MASS BALANCE WEIGHTS P/N PE915109-L33 REPLACED WITH NEW.
STANDBY ALTIMETER SETTING IS FROZEN ON "29.91". ALTIMETER SETTING WILL NOT ADJUST UP OR DOWN WITH THE KNOB. REPLACED SECONDARY FLIGHT DISPLAY WITH AN O/H UNIT IAW AMM CHAP 34-21-14, OPS CK GOOD.
DURING DESCENT, THE PITCH TRIM, MISTRIM ANNUNCIATOR CAME ON. TRIED THE TRIM WHEEL AND IT WOULD NOT MOVE. DID THE JAMMED TRIM AND NO FLAP CHECKLIST. AFTER SHUTDOWN, TRIED THE TRIM WHEEL AGAIN AND IT MOVED FREELY. PERFORMED OPS CHECK OF THE AUTOPILOT SYS AND ELEVATOR TRIM SYS, SYS CHECKED GOOD. PERFORMED TRAVEL CHECK OF ELEVATOR TRIM TRAVELS CHECKED GOOD. INSPECTED ELEVATOR TRIM MECHANISM IN THE TAIL CONE AREA WHILE OPERATING THE ELEVATOR TRIM. NO DISCREPANCY NOTED. LOOKED AT THE IMT FOR FAULTS NO FAULTS NOTED. ACCESS THE IAC. REMOVED IAC AND REINSTALLED. CLOSED ALL ACCESS PANELS. PERFORMED OPS CHECK OF THE AVIONICS SYS. SYS CHECKS GOOD. ALL WORK DONE IAW MM 27-30-00 AND 22-00-00 .
RT SIDE BRAKES DID NOT FUNCTION, LT SIDE REQUIRED HEAVY PRESSURE. (K)
RT SIDE BRAKES DID NOT FUNCTION, LT SIDE REQUIRED HEAVY PRESSSURE, THEN GRABBED. ANTI SKID INOP LIGHT THEN CAME ON AND STAYED ON . LANDING SOLDERED BROKEN WIRE ON X-DUCER P108 RT MLG IAW WM 20-10-03. REMOVED AND REPLACED DAMAGED CONNECTOR PLUG AT X-DUCER P107 LT MLG IAW WM 20-10-04. OPS CK OF ANTI-SKID SYS GOOD IAW MM 32-40-01.
RT BRAKE PEDAL ON RT SEAT SIDE GOES TO THE FLOOR WHEN BRAKES ARE PRESSED. COMPLIED WITH BRAKE BLEED IAW MM 32-42-00.
CO-PILOTS RT BRAKE PEDAL IS VERY SPONGY. IT REQUIRES (2) TO (3) PUMPS TO PRESSURIZE THE BRAKE. [06-15-07] BLED LT & RT BRAKE SYSTEMS MULTIPLE TIMES, WITH AND WITHOUT ACCUMULATOR PUMP. SERVICED BRAKE RESERVOIR AS REQUIRED. TAXIED AIRCRAFT AND VERIFIED BRAKE SYSTEM WORKED PROPERLY IAW MODEL 560 MM 32-42-00. OPERATIONAL CHECK GOOD.
UPON TOUCHDOWN AND ROLLOUT, THE RUDDER PEDALS WERE BINDING. YAW DAMPER WAS OFF PRIOR TO LANDING. PEDALS BECAME FREE AFTER 3000' (FT) OF ROLLOUT TO FULL STOP, 70'(DEGREES) TURN, TAXI, 10'(DEGREE) TURN, FOLLOWED BY 200 YARDS OF VERY SLOW TAXI. AFFECTED BOTH SIDES. CHECKED NOSE WHEEL STEERING ASSY, LINKAGES IN WHEEL WELL, CHECKED RUDDER PEDAL THROWS IN COCKPIT AND FOUND PILOTS LEFT SIDE KICK PANEL COMING INTO CONTACT WITH LEFT RUDDER PEDAL. REPOSITIONED KICK PANEL TO ALLOW FREE MOVEMENT OF PEDALS. CONDUCTED TAXI CHECK OF STEERING. FOUND NO EVIDENCE OF RESTRICTION OR BINDING. STEERING CHECKS GOOD AT THIS TIME, MAINTENANCE IAW CE560 MM CH 32-50-00.
AFTER LANDING AND DEPLOYING BOTH T.R'S THE MASTER WARNING ANNUNCIATOR FLASHES. I MADE CERTAIN THAT WEIGHT WAS ON ALL 3 WHEELS BEFORE DEPLOYING T.R'S - PERFORMED SEVERAL OPS CHECKS OF BOTH LT AND RT TR'S WITH NO DEFECTS. REF AMM 78-31-00. OK FOR CONTINUED SERVICE.
DURING TAXI FOR TAKEOFF SIC HAD NO BRAKES. PIC CHECKED NO BRAKES. USED EMERGENCY BRAKES TO SLOW DOWN. TRIED BRAKES AGAIN AND APPEARED NORMAL. CAME TO A STOP, SAW ANTISKID LIGHT ON. RAN THE CHECKLIST, RESET CIRCUIT BREAKER AND LIGHT STAYED ON. TURNED ANTISKID OFF. ITEM IS UNDER INVESTIGATION.
DURING TAXI, CO-PILOT LEFT BRAKE PEDAL GOES TO THE FLOOR DURING BRAKE APPLICATION, PILOT BRAKES OPERATE NORMALLY. INSPECTED CO-PILOT'S MASTER CYLINDER, NO DEFECTS FOUND. APPLIED HYDRAULIC POWER AND CHECKED LEFT BRAKE PEDAL AND NOTICED IT WAS SPONGY. BLED BRAKE SYSTEM IAW CESSNA MM CHAPTER 32-42-00, SYSTEM OPS CHECKED GOOD.