N609QS
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
INTERIOR DOOR HANDLE WILL NOT EXTEND OR RETRACT BAYONET PINS. EXTERIOR DOOR HANDLE EXTENDS AND RETRACTS PINS NORMALLY. (PRE-FLIGHT) REMOVED DOOR STEPS TO GAIN ACCESS TO THE INTERIOR DOOR HANDLE UPON INSPECTION FOUND THE BOLTS ON INTERIOR DOOR HANDLE THAT CONNECT THE DOOR HANDLE AND INNER HANDLE BELLCRANK BROKEN INSPECTED INNER HANDLE HOUSING AND FOUND CENTERING SPRING ON DOOR HANDLE HOUSING OFF THE TRACK REPLACED BOLTS ON INNER HANDLE BELL CRANK IAW 52-10-01 REINSTALLED CENTRERING SPRING ON DOOR HANDLE IAW AMM 52-10-01 INSPECTED DOOR NO OTHER DISCREPANCY NOTED AT THIS TIME PERFORMMED A SATIFACTORY OPS CHECK OF THE MAIN CABIN DOOR IAW AMM 52-10-00 RESTORED AIRCRAFT TO ORGINAL CONFIGURATION.
JUST AFTER TAKEOFF AROUND 200 FEET AGL WE NOTICED A BURNING SMELL AND FOUND THAT THE ITT ON THE RIGHT ENGINE WAS UP NEAR 800 DEGREES. WHEN WE REDUCED POWER TO LEVEL OFF AND RETURN TO THE AIRPORT THE TEMPERATURE REDUCED INTO THE NORMAL RANGE AND THE SMELL SEEMED TO GO AWAY. REMOVED RH ENGINE DUE TO ITT LIMITED AT TAKE OFF POWER. IAW EMM 72-00-00 AND AMM 71-00-03. ORIGINAL SUBMISSION DATE: 4-5-2024
AIRCRAFT WILL NOT CROSSFEED AT ALTITUDE. AT FL320 WHEN SELECTING CROSSFEED LEFT TO RIGHT, LEFT BOOST PUMP ANNUNCIATOR ILLUMINATED FOLLOWED BY RIGHT BOOST PUMP ANNUNCIATOR AND MASTER CAUTION. MASTER CAUTION EXTINGUISHES SHORTLY AFTER THIS SEQUENCE OF EVENTS. FUEL CROSSFEED APPEARS TO OPERATE NORMALLY AT LOWER ALTITUDES. REMOVED LH SOLENOLD VALVE PN 4151 SN 1848A AND INSTALLED OVERHAULED PN 4151 SN 1115 IAW CESSNA 560XL AMM 28-21-05
AISLE EMERGENCY LIGHTS, A SECTION OF THE FLOOR AISLE EMERGENCY LIGHTS ARE INOPERATIVE, LEFT SIDE, AFT HALF. (AFT OF SEAT 3) //SIGNOFF//ADJUSTED CARPET FOR BETTER AISLE LIGHT VISABILITY IAW AND PERFORMED EMERGENCY UGHTING BATTERY OPS CHECK IAW 560XL MM 33-50-00. ALL OPS CHECK GOOD
WITH THE EMER LIGHT SWITCH IN ARM AND THE BATT SWITCH ON AND THE PASS SAFETY SWITCH OFF, THE FORWARD EMERGENCY LIGHTS REMAIN ON (FORWARD EXIT SIGNS, FORWARD DROPPED AISLE LIGHTS, READING LIGHTS SEATS 3 AND 10) DURING THE OPS CHECK I NOTICE THE PASS SAFETY SWITCH WAS ON SHICH WAS CAUSING THE EMERG LIGHT TO STAY ON WHEN EMERG LIGHT SWITCH IS ON THE ARM POSITION WHEN POWER WAS APPLIED. TURNED OFF PASS SWITCH AND PERFORM OPS CHECK OPS CHECK NORMAL IAW WITH AMM 33-50-00 (REV 47)
REPEAT WRITE-UP. POST FLIGHT, FOUND CIRCUIT BREAKER NUMBER HT043, CORRESPONDING TO EMER LIGHTS-FWD, TRIPPED. REMOVED PILOT SIDE EMERG UGHT P/N 9913-1 S/N 1994.INSTALLED OVERHAULED EMERG LIGHT P/N 9913â¢15/N 2650 IAW 660XLS AMM 33·60-0L{REV 47). PERFORMED OPS CHECK,OPS CHECK NORMAL IAW 560XLS AMM 33·50·00-(REV 7). NO DISCREPANCIES FOUND AT THIS TIME
DURING CROSSFEED AT FL300 FROM LEFT TANK TO RIGHT GOT XFEED FEED ANNUNCIATOR ALONG WITH STEADY LEFT BOOST PUMP AND FLASHING RIGHT BOOST PUMP AND CAUTION LIGHT. RAN CHECKLIST AND RESET BOOST PUMPS. ON GROUND TRIED XFEED AND WAS NORMAL. FUEL IMBALANCE REACHED APPROXIMATELY 300. TESTED CROSSFEED SYSTEM IAW AMM 28-20-00 WITH NO DEFECTS NOTED. REPLACED THE CROSSFEED ACTUATOR WITH NEW UNIT & LEFT FUEL CONTROL PCB WITH A REPAIRED UNIT OPS CHECK GOOD WITH NO LEAKS NOTED WORK DONE IAW AMM 28-21-06.
MAIN CABIN DOOR WOULD NOT OPEN FROM THE INSIDE. HAD A GROUND CREW OPEN IT WITH THE EXTERIOR HANDLE. MAIN CABIN DOOR FOUND TO BE DIFFICULT TO OPEN AND CLOSE FROM INSIDE THE AIRCRAFT BUT EASY TO OPEN AND CLOSE FROM OUTSIDE OF THE AIRCRAFT. PERFORMED GVI OF MAIN CABIN DOOR PINS AND HOUSINGS AND FOUND DOOR PINS TO BE DRY AND STICKY. PERFORMED CLEANING AND LUBRICATION OF ALL PINS AND HOUSINGS WITH NO CHANGE IN OPERATION. PERFORMED ADJUSTMENT OF AFT UPPER LATCH PLATE. PERFORMED MULTIPLE OPERATIONAL CHECKS OF OPENING AND CLOSING MAIN CABIN DOOR FROM INTERIOR AND EXTERIOR OF AIRCRAFT WITH NO DEFECTS NOTED. NO FURTHER ACTION REQUIRED. WORK PERFORMED IAW CESSNA 560XLS MM 52-10-00 AND 12-21-03.
FLOOR EMERG EXIT LIGHT: FLOOR EMERGENCY LIGHTING FROM BETWEEN SEATS 3 & 5 TO THE MAIN CABIN DOOR DO NOT ILLUMINATE (APPROXIMATEY 4'). LIGHTS DO NOT ILLUMINATE WHEN AISLE LIGHTS ARE SELECTED ON AS WELL. // SIGNOFF// REMOVED FAILED THRESHOLD LIGHT PN: CDAL-45-1 SN: N/A. INSTALLED THRESHOLD LIGHT BETWEEN SEAT 3 & 5 PN: 9919040-22 SN: 202200000007150 IAW MODEL 560XLS MM CH. 33-20-04. OPS CHECKS GOOD.
DURING CRUISE, OWNER PLUGGED IN AIRSHOW MONITOR AT SEAT 8. WHILE PUSHING POWER BUTTON ON MONITOR, SMOKE CAME OUT OF THE PLUG AREA. THE SMOKE STOPPED WHEN THE MONITOR WAS REMOVED. THERE WAS A NOTICABLE ELECTRICAL AMOKE SMELL IN THE ENTIRE CABIN. REMOVED DAMAGED AIRSHOW MONITOR DUE TO BEING INOP. INSTALLED CUSTOMER SUPPLIED SERVICABLE AIRHOW MONITOR. REMOVED RECEPTACLE FOR CUSTOMER CONVENIENCE. INSTALLED CUSTOMER SUPPLIED NEW RECETABLE IAW MODEL 560XL IMM 25-40-04. OPS CHECKS GOOD, NO DEFECTS NOTED.
MAIN CABIN DOOR EMERGENCY EXIT LIGHT INOP. APPLIED POWER TO AIRCRAFT TO CHARGE EMERGENCY BATTERY PACK FOR 30MIN. EXIT LIGHT STILL FAILS TO ILLUMINATE. REPLACED THE MAIN CABIN DOOR EXIT SIGN WITH A NEW ONE. IAW MM 33-50-02.
A) REPAIRED THREE CHAFED AREAS ON CABIN INTERIOR STRUCTURE, TWO ON THE RIGHT SIDE AT FS 280.45, FS 337.66 AND ON THE LEFT SIDE FS 280.15 IAW AQRD ERO-106971 REVISION IR APPROVED BY FAA FORM 8110-3 DATED SEPTEMBER 23, 2022. SEE FAA FORM 337 DATED 27 SEPTEMBER, 2022.
CABIN EMERG LIGHT: FORWARD CABIN EMERGENCY LIGHTING BATTERY IS INOPERATIVE. (LIGHTS TESTED WITH PASSENGER ADVISORY SYSTEM OK). *** CORRECTIVE ACTION *** TROUBLESHOT FWD EMERGENCY LIGHTING SYSTEM AND FOUND DIODE DI051 IS BAD. REMOVED AND REPLACED DIODE WITH CUSTOMER SUPPLIED NEW DIODE. DIODE PN: S3106-4 NSN. OPS CHECK OF EMER LIGHTS GOOD. WORK PERFORMED REF CES60XL AWM 33-50-01-01.
FUEL PRESSURE INDICATION: REPEAT WRITEUP. DURING CROSSFEED FROM LEFT TANK TO RIGHT ENGINE, CROSSFEED WORKED NORMALLY. AFTER MOVING CROSSFEED TO OFF POSITION, THE RIGHT LOW FUEL PRESSURE ANNUNCIATOR FLASHED MOMENTARILY FOLLOWED BY THE RIGHT FUEL BOOST ON ANNUNCIATOR. THE FUEL BOOST L/R QRH WAS PERFORMED AND THE ANNUNCIATOR EXTINGUISHED. // SIGNOFF// RAN AIRCRAFT ENGINES AND APU. ATTEMPTED TO DUPLICATE DISCREPANCY MULTIPLE TIMES, COULD NOT DUPLICATE. SPOKE TO NETJETS MAINTENANCE CONTROLLER KEVIN, HE REQUESTED THAT WE REPLACED THE FUEL CROSS FLOW VALVE AND INSPECT R/H FUEL TANK COMPONENTS. SPOKE WITH RUSS FROM CITATION TEAM XL HE RECOMMENDED TO INSPECT MOTIVE FLOW SUPPLY TUBING TO THE R/H MOTIVE FLOW PUMP. DEFUELED AND SUMP OUT THE FUEL FROM BOTH WINGS. GAINED ACCESS TO THE RH FUEL BOOST PUMP AND CROSSFLOW VALVE. REMOVED THE RH FUEL BOOST PUMP. WORK DONE IAW CESSNA MODEL 560XL MM CHAPTER 28-21-01. INSPECTED R/H TANK PRESSURE LINES FROM ELECTRIC BOOT PUMP AND MOTIVE PUMP EJECTOR, NO DISCREPANCIES NOTED. INSPECTED R/H MOTIVE FLOW SUPPLY LINES AND CHECKED MOTIVE FLOW SUPPLY LINES FITTINGS, NO DISCREPANCIES NOTED. ADVISED NJ MCC CONTROLLER KEVIN OF FINDINGS, HE REQUESTED FOR US TO CONTINUE BY REPLACING THE FUEL CROSS FLOW VALVE, WITH POSSIBLE MORE TO FOLLOW. REMOVED THE CROSSFLOW VALVE AND THE CROSSFLOW VALVE ACTUATOR. INSTALLED A NEW CROSS FLOW VALVE AND INSTALLED THE ORIGINAL CROSSFLOW VALVE ACTUATOR. CLOSED FUEL PANELS. WORK DONE IA W THE CESSNA 560XL MM CHAPTER 28-21-06 REMOVED VALVE PN 9914423-4 SN AA619263 INSTALLED VALVE PN 9914423-4 SN AA755083. VERIFIED. PERFORMED ENGINE RUNS. PERFORMED FUEL TRANSFER FROM L/H TANK TO R/H ENGINE, AND R/H TANK TO L/H ENGINE MULTIPLE TIMES. NO DISCREPANCIES NOTED. OPS CHECK OF CROSS-FEED BALL VALVE, ACTUATOR AND R/H FUEL BOOST PUMP GOOD. ALL LEAK CHECKS GOOD.VERIFIED WORK PERFORMED
CABIN WINDOW SHADE: CABIN WINDOW SHADE ON THE EMERGENCY EXIT DOOR AND OVER THE LAV IS INOP//CORRECTIVE ACTION//REMOVED WINDOW SHADE ASSY PN.6619325-27 SN.N/A AND INSTALLED NEW CUSTOMER SUPPLIED WINDOW PN.6619325-27 SN.N/A. REF CE-560XL AMM 25-60-00
CABIN EMERG LIGHT: ONE SECTION OF THE DROP ISLE EMERGENCY LIGHTING STRIP APPEARS INOP OR NOT IN CORRECT POSITION UNDER THE MAIN CABIN ENTRY DOOR // SIGNOFF// VERIFIED LEFT ENTRY DOOR LIGHT WAS NOT SECURE, AND IT IS NOT AN EMERGENCY LIGHT. ADHERED LIGHT BACK TO ITS ORIGINAL POSITION. OPS CHECKED GOOD. WORK PERFORMED IAW CE560XLS SPM 20-00-00. RETURNED AC BACK TO ORIGINAL CONDITION.
MLG BRAKE PRESSURE: TAXIING OUT TO RUNWAY, "ANTISKID" ANNUNCIATOR CAME ON AND SIMULTANEOUSLY THE "PWR BRKS" CIRCUIT BREAKER POPPED. TURNED AIRCRAFT AROUND AND HAD A BRAKE BURNING SMELL AND SHUTDOWN, AND THEN THE "LO BRK PRESS" ANNUCIATOR CAME ON FLASHING. TOWED AIRCRAFT TO RAMP. // SIGNOFF// REMOVED HYDRAULIC BRAKE POWER PACK PUMP, MOTOR, AND PRESSURE SWITCH AND INSTALLED AN OVERHAULED MOTOR ASSY, A NEW HYDRAULIC PUMP ASSY, AND A NEW PRESSURE SWITCH WITH NEW PACKINGS ANO RETAINERS. OPS AND LEAK CHECKS GOOD. DONE I.A.W. CESSNA CE-560XL AMM 32-44-20. NO DEFECTS NOTED. ALSO FLUSHED LEFT ANO RIGHT BRAKE EMERGENCY PNEUMATIC LINE TO CLEAR OF RESIDUAL HYDRAULIC FLUID.
REPEAT WRITE: THE WHITE EMER EXIT LIGHT OVER THE MAIN ENTRANCE DOOR AND THE TWO RED EXIT LIGHTS FWD AND AFT OF THE MAIN ENTRANCE DOOR ARE ALL INOP. ALSO, THE FWD FLOOR PATH LIGHTING IS INOP. THE EMER LIGHTS OVER SEATS 10 AND 3 WORK NORMALLY WITH THE READING LIGHT SWITCHES TURNED OFF. ALL THE AFT EMER LIGHTS AND THE EXTERIOR EMER LIGHTS ARE WORKING NORMALLY. CORRECTIVE ACTION PERFORMED OPERATIONAL TEST OF EMER LIGHT SYSTEM. WAS ABLE TO VERIFY FAULT. GAINED ACCESS TO EMER BATT IN COCKPIT AND EMER BATT IN AFT AREA OF CABIN. SWAPPED EMER BATTERIES AND PERFORMED OPERATIONAL TEST, FAULT FOLLOWED TO AFT SIDE OF EMER LIGHT SYSTEM. INSTALLED EMER BATTERIES BACK TO ORIGINAL CONFIGURATION. PERFORMED A RESET OF G SWITCH ON THE FORWARD EMER BATTERY. PERFORMED SATISFACTORY OPERATIONAL TEST OF THE EMER LIGHT SYSTEM. WORK PERFORMED IAW 560XL AMM 33-50-01.
MAIN CABIN DOOR ANNUNCIATIOR DID NOT EXTINGUISH AFTER CLOSING DOOR. OTHER INDICATION OF DOOR CLOSING WERE NORMAL. REMOVED SUSPECTED FAULTY CABIN DOOR MONITOR PCB CARD NZ007 AND INSTALLED A REPAIRED CABIN DOOR MONITOR PCB CARD IAW AMM 24-50-01, & 52-70-00 OPERATIONAL TEST IS SATISFACTORY AT THIS TIME.
FOUND CORROSION AROUND THE RH FORWARD NOSE DOOR (AVIONICS ACCESS DOOR) ON THE FUSELAGE SKIN, REPAIRED BY BLENDING, NDT AND INSTALLING REPAIR DOUBLERS.
DURING DESCENT FROM 35, 000 FT, RECEIVED A NOTICEABLE SHUDDER IN THE AIRFRAME. SUBSIDED ONCE BELOW 250KTS. GEAR AND FLAPS WERE UP AND SPEEDBRAKE WAS RETRACTED. INSPECTION FOUND LT GEAR DOOR HINGE HAS A CRACK ON THE L/E. REMOVED, FIT AND INSTALLED NEW HINGE HALF PN 6622024-19 ON LT MAIN GEAR DOOR IAW DWG 6622024. FOUND MLG DOOR LOWER ROD BEARING FROZEN. ACCOMPLISHED REPLACEMENT OF MLG DOOR LOWER ROD BEARING, PN M81835/1-5K AND ATTACH BOLT, PN NAS6305-19D. REPLACED NUT PN MS17826-5 FROM BULK STOCK. ACCOMPLISHED INSTALLATION OF MLG DOOR. ALL WORK DONE IAW MM 32-10-00. VERIFIED GEAR DOOR CLEARANCE CHECK.
DURING SCHEDULED MAINTENANCE, WE FOUND THIS RT AVIONICS ATTACH BRACKET CRACKED .7500", HALF OF THE BRACKETS LENGTH. REPLACED ATTACH BRACKET WITH NEW.
WHILE STARTING APU, CABIN IMMEDIATELY FILLED UP WITH THICK, ACRID SMOKE. REMOVED APU IAW MM 49-10-00. DRAINED REMOVED APU OF OIL. CLEANED APU CONTAINMENT BOX & FLUSHED DRAIN LINES. INSTALLED APU IAW MM 49-10-00. R&R CONDENSER SOCK, PN 83237-12, IAW MM 21-51-00. SERVICED APU OIL IAW MM 12-11-02. OPS CHECK & LEAK CHECK SATISFACTORY ON APU RUN. IAW MX CONTROL, COMPLETED ECS DUCT BURN OUT. R&R WATER SEPARATOR CONDENSER SOCK, POST ECS BURN OUT PROCEDURE IAW MM 21-51-00. PRESSURIZED ACFT TO 8 PSI FOR LEAK CHECKING WATER SEPARATOR ASSEMBLY. LEAK CHECK SATISFACTORY OF WATER SEPARATOR ASSEMBLY ON PRESSURIZATION RUN. INSTALLED APU ENCLOSURE BOTTOM ACCESS PANEL & APU OUTER COVER PANEL REMOVED FOR ACCESS.
MCD FORWARD, LOWER HINGE HALF ASSY CORRODED. R & R MCD LOWER HINGE IAW SRM 51-40-03 AND DWG 6611071, DWG 0003.2. CORROSION DAMAGED WAS CONTAINED TO LOWER HINGE ONLY; NO DAMAGE TO UPPER HINGE OR SURROUNDING FUSELAGE.
SMOKE WAS COMING INTO COCKPIT, WITH APU RUNNING, BLEED AIR ON OR OFF AND WITH ENGINE RUNNING. REMOVED AND REPLACED APU IAW MM 49-10-00. OPS AND LEAK CHECKED GOOD.
AFTER TAKEOFF, WHEN FLAPS WERE SELECTED TO 0, FLAPS STUCK AT 7 DEGREES. ON GROUND FLAP HANDLE SELECTED TO 35 DEGREES & STUCK AT 35 DEGREES. REPLACED THE LT FLAP ACTUATOR ASSEMBLY, LT FLAP OUTBOARD BELLCRANK ASSEMBLY AND LT FLAP OUTBOARD BELLCRANK BOLT. SYSTEM OPS AND LEAK CHECKED GOOD IAW MM 27-51-04.
WHEN MAKING A TIGHT TURN USING RUDDER AND BRAKES, THE BRAKE PEDALS GO TO THE FLOOR WITHOUT BRAKING. THIS OCCURS BOTH IN RT AND LT TURNS AND IS FELT FROM BOTH PILOT & CO-PILOT PEDALS. BRAKING FEELS NORMAL WHEN MAKING SHALLOW TURNS OFF AND ON THE RUNWAY, BUT THE PROBLEM IS WHEN THE ACFT NEEDS TO MAKE A 90 DEGREE TURN AND THE PEDAL IS FLOORED. FOUND RUDDER PEDALS COULD BE MOVED TO AREA OF FORWARD DETENT WHICH SHOULD NOT BE AVAILABLE ON THIS ACFT. FOUND SB 560XL-27-28 HAD NOT BEEN C/W. BRAKE PEDALS WILL CONTACT BULLHEAD IN THIS CONDITION IF IN HARD TURN. PEDALS WILL NOT CONTACT BULKHEAD. BRAKE SYS OPS CHECK GOOD IAW MM 32-44-10.
AFTER TAKEOFF, GEAR HANDLE WOULD NOT MOVE FROM THE EXTENDED POSITION. R & R LT MLG WIRING HARNESS IAW WM 20-10-01. ADJUSTED SQUAT SWITCH IAW MM 32-44-00. OPS CHECKED SATISFACTORY.
GEAR WOULD NOT RETRACT AFTER TAKEOFF, GEAR HANDLE WOULD NOT MOVE INTO THE UP POSITION. REPLACED THE LT MLG SQUAT SWITCH WITH A NEW SWITCH IAW MM 32-61-00, OPS CHECKED GOOD. PERFORMED MLG HYD SYS ADJUSTMENT TEST WHICH INCLUDES ASSOCIATED SQUAT SWITCH SYS, FLAP POSITION, T/R 32-01-00.
AFTER TAKEOFF AND CALLING A POSITIVE RATE AND GEAR UP, THE GEAR HANDLE COULD NOT BE MOVED. REPLACED LANDING GEAR CONTROL HANDLE ASSY IAW AMM CHP 32-30-00. PERFORMED GEAR SWING. OPS CK OF GEAR HANDLE GOOD.
UNSAFE NOSE GEAR INDICATION. 2 GREEN 1 RED INDICATION, NO AOA INDEXER. DURING THE VECTORS TO RUN THE CHECKLIST, THE GREEN NOSE INDICATION CAME ON WITH AOA INDEXER AFTER ABOUT 5 MINUTES. LANDING WAS UNEVENTFUL. FOUND INTERMITTENT PC BOARDS NZ004 AND NZ009. REMOVED AND REPLACED BOTH BOARDS WITH NEW. SYS OPS CHECKS GOOD REF MM 32-61-00, REMOVED PCB-LANDING GEAR CONT NZ009 PN 6618735-1, SN 0127 INOPERATIVE.
FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE.
ON LANDING THE ANTISKID LIGHT ILLUMINATED AND ON TAXI IN THE LOW BRAKE PRESSURE LIGHT ILLUMINATED AND THE PNEUMATIC BRAKES HAD TO BE USED TO STOP THE PLANE. C/W BRAKE SYSTEM BLEED, BIT TEST & AN ANTISKID FUNCTIONAL TEST. NO FAULTS FOUND AT THIS TIME, WORK DONE IAW CE-560XL MM CH 32-42-00 & 32-44-00.
FORWARD RT FUSELAGE STATIC DRAIN VALVE NOT FLUSH. NEW UNIT ORDERED AND INSTALLED, LEAK CHECKED. DURING REMOVAL OF SUSPECTED BAD PART, ENTIRE CORE POPPED OUT, CONDITION WOULD HAVE DIRECTLY OPENED STATIC SYSTEM. CORE OF UNIT APPEARS TO BE PRESSED AND GLUED INTO PLACE, VERY LITTLE GLUE RESIDUE APPEARED ON CORE OR BASE. THIS IS A RVSM A/C. ALSO, THE VERBIAGE IN THE IPC REFERS TO IT AS A FUEL DRAIN NOT A STATIC DRAIN.