N373QS
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
WHILE IN CRUISE WE NOTICED THE EMER LIGHTS WERE ILLUMINATED WITH THE SWITCH IN THE ARM POSITION. REMAINED ILLUMINATED FOR THE REST OF THE FLIGHT. REMOVED EMERGENCY LIGHT IN AFT LOCATION AND INSTALLED REPAIRED CONDITION EMERGENCY LIGHT IN SAME LOCATION. PERFORMED FUNCTIONAL CHECK OF THE EMERGENCY LIGHTS. ALL CHKD GOOD. ALL WORK PERFORMED IAW AMM 33-52-01.
DURING DESCENT FOR LANDING IN NORMAL CONFIGURATION; FLAPS & GEAR UP, SPEED BRAKES RETRACTED, 175KTS, BOTH PILOTS FELT A VIBRATION AND ASSOCIATION SOUND WHEN FLAPS 1 WAS SELECTED. THE VIBRATION AND SOUND CONTINUED UNTIL FLAP 2 WAS SELECTED. THE VIBRATION AND SOUND CONTINUED UNTIL FLAP 2 WAS SELECTED. CORRECTIVE ACTION: FOUND TAPE ATTACHED TO L/H LOWER FLAP TRACK THAT APPEARS TO HAVE PEELED BACK AND TORN APART DURING FLIGHT. DURING VIBRATION/NOISE INSPECTION, I COULD NOT FIND ANY OTHER CULPRITS OF REPORTED EVENT. REF AMM 05-50-27-200-801-A.
EMERGENCY LIGHT SWITCH IN ARM POSITION. ALL EMERGENCY LIGHTS WERE ON IN THE CABIN. TOWARDS THE END OF THE FLIGHT, THE EMERGENCY LIGHTS STARTED TO FLICKER. CORRECTIVE ACTION: REMOVED AND REPLACED FWD AND AFT EMERGENCY BATTERY PACKS IAW EMB300 MM 33-52-01. OPS CHECK GOOD.
COM 1 YELLOW X AS SOON AS WE KEYED THE MIC. SUSPECTED SHORT SMELLED IN COCKPIT ELECTRICAL BURNING SMELL. MM 31-41..05. AFTER ALL WORK COMPLETE, WE FULLY POWERED UP THE AIRCRAFT FOR A MINIMUM OF. 60 MINUTES, RAN ENGINES, PNEUMATICS, AND VCS AND VERIFIED NO SMELLS OF BURNING/OVERHEATING ELECTRONIC WERE PRESENT. NO FURTHER DISCREPANCIES OR DEFECTS NOTED AT THIS TIME. OPS CHECKS GOOD.
DOOR IS EXTREMELY DIFFICULT TO CLOSE. ACCOMPLISHED CHECK OF THE MAIN-DOOR INTERNAL HANDLE OPENING AND CLOSING FORCES (AMM TASK 52-11-23-720-801-A/500). INTERNAL HANDLE CLOSING FORCE FOUND AT 23.5KGF. MAX TOLERANCE IS 22.LKGF. PERFORMED MAIN DOOR ADJUSTMENT IAW AMM 52-10-00. INTERNAL HANDLE CLOSING FORCE CHANGED SLIGHTLY. PERFORMED NUMEROUS ADJUSTMENTS IN SMALL INCREMENTS TO DECREES THE FORCE DOWN TO 16.SKGF. INTERNAL HANDLE FORCE NOW WITHIN TOLERANCE FOR RELEASE. AIRCRAFT GOOD TO CONTINUE.
ATTEMPTING TO CLOSE THE MAIN CABIN DOOR REQUIRES EXCESSIVE FORCE. MY FO IS PHYSCIALLY UNABLE TO CLOSE THE AIRCRAFT DOOR. CORRECTIVE ACTION: THE ARRIVAL AT THE AIRCRAFT REVEALED THE MED CLOSED WITH THE VENT FLAP OPEN. AFTER OPENING THE DOOR, A VISUAL INSPECTION SHOWED THE DOOR SEAL LOOKED NEW BUT HAD EXCESSIVE RTV AROUND THE EDGES. THE DOOR STOPPED ABOUT 2 INCHES FROM CLOSING. IT WAS NOTED THAT THE WIRE BUNDLE FOR THE MED LIGHT AND SWITCHES WAS UNSECURED AND PINCHED BETWEEN THE DOOR AND AIRFRAME. UPON REMOVING THE TOP MOVABLE STEP, SEVERAL STRIPPED SCREW HEADS AND MISSING WASHERS WERE FOUND. THESE FINDINGS WERE REPORTED TO MCC, WHO REQUESTED THE REMOVAL OF THE EXCESS RTV. AFTER REMOVAL, THE DOOR CLOSED WITHOUT SLAMMING BUT STILL REQUIRED EXTRA FORCE. THE DOOR SEAL WAS REMOVED, ALLOWING THE DOOR TO CLOSE EASILY, AND A REPLACEMENT SEAL WAS ORDERED. THE SURFACE WAS CLEANED, AND NEW SEALANT P/N RTV157-2-80Z WAS APPLIED AROUND THE CONTOUR OF THE DOOR, WITH THE ORIGINAL SEAL REINSTALLED ACCORDING TO AMM GUIDELINES. THE WIRING HARNESS UNDER THE MOVABLE STEP WAS SECURED, ENSURING IT WASNÃâ¬â¢T PINCHED. THE TOP MOVABLE STEP WAS REINSTALLED, AND THE STRIPPED SCREWS AND MISSING WASHERS WERE REPLACED. A CABIN PRESSURIZATION CHECK WAS COMPLETED, AND THE MAIN DOOR WAS INSPECTED FOR LEAKS, WITH NO LEAKS FOUND. ORIGINAL SUBMISSION DATE: 7/3/2025
MAIN CABIN ENTRY DOOR, EXTERIOR HANDLE DOES NOT STOW WHEN DOOR IS CLOSED WHEN USING THE INTERIOR LOCK/LATCH HANDLE. PHOTO ATTACHED CORRECTIVE ACTION: INSPECTED DOOR AND VERFIED CREW WRITE UP, AND FOUND THE OUTER DOOR HANDLE STIFF TO LOCK AND UNLOCK. REMOVED DOOR STEP ASSY. TO FURTHER INSPECT THE DOOR LINKAGES FOUND THE OUTER DOOR HANDLE MAIN THROUGH ROD ASSY. TO BE OVERTIGHTED PER AMM AND THIS WAS CAUSING THE FRICTION AND ALSO NOT ALLOWING THE OUTER DOOR HANDLE TO STOW PROPERLY. RETORQUED OUTER DOOR HANDLE MAIN THROUGH ROD ASSY. NUT AS REQUIRED AND SAFTIED ALL CHECKS GOOD THE CABIN DOOR OPENS AND CLOSES SMOOTHLY ALSO CW OPS CHECK OF OUTER CABIN DOOR HANDLE WHICH NOW STOWS WHEN USING THE INTERIOR DOOR HANDLE TO CLOSE MAIN CABIN DOOR ALL CHECKS GOOD IAW EMB 505 AMM 52-10-00 TORQUE WRENCH USED: TL-106338
MAIN DOOR HANDLE DIFFICULT TO MOVE. ADJUSTED LOCKING TAB OF DOOR HANDLE AND LUBRICATED MED DOOR HANDLE, OPERATION IS NOW SMOOTH AND REQUIRES LESS EFFORT TO OPEN. \ \ WORK PREFORMED !AW EMB÷505 AMM 52-11-24.
MAIN DOOR: MAIN ENTRY DOOR HANDLE IS BROKEN OFF. UNABLE TO OPEN OR CLOSE DOOR CORRECTIVE ACTION: REPLACED DOOR HANDLE. OPS CHECK GOOD. EMBRAER PHENOM 300 AMM CH 52-11-24
REPEAT WRITE UP. IN-FLIGHT EMERGENCY, LIGHTS ILLUMINATED, THEN STARTED TO FLICKER. COMPLIED WITH FIM 32-50-00-810-802A INCORRECT FUNCTIONING OF THE EMERGENCY LIGHTS (FLICKERING OR BLINK). EMERGENCY LIGHTS FAILED TEST. REPLACED EMERGENCY LIGHT BATTERIES WITH CUSTOMER SUPPLIED UNITS REFERENCING PHENOM -AMM CH 33-52-01-400-801-A AND OPS CHECKED REFERENCING PHENOM AMM CH 33-52-00-05-1-710-801-A NOTING NORMAL OPERATION AT THIS TIME.
EMERGENCY LIGHTING: 30 MINUTES INTO FLIGHT UPON LOOKING AFT INTO CABIN WE DISCOVERED THE EMERGENCY LIGHTS ILLUMINATED WITH THE SWITCH IN THE ARM POSITION. WE COULD NOT TURN THEM OFF. NO BREAKERS WERE POPPED . AFTER LANDING AND DE-POWER , WE APPLIED BATTERIES AND GPU. THE EMER LIGHTS WOULD ILLUMINATE IN THE ARM CONDITION. //SIGNOFF// TROUBLE SHOT AND FOUND THAT BOTH FWD AND AFT ERNER BATT'S ARE DEPLETED OF MOST OF THERE CHARGE, REMOVED AND REPLACED BOTH FWD AND AFT EMER BATT'S IAW EMB-505 AMM CH 33-52-01/400 OP'S CK GOOD.
RIGHT MLG BRAKE: UPON LANDING WITH A LONG ROLLOUT AND MINIMAL BRAKING. THE RIGHT LANDING GEAR WAS SMOKING FOR OVER TEN MINUTES. NO ADVERSE PULLING OR SHUDDERING NOTED. ALSO FREE OF ANY OIL OR FLUID. FOUND R/H BRAKE ASSEMBLY TO HAVE GREASE ON IT CAUSING IT TO SMOKE. REMOVED R/H BRAKE ASSEMBLY AND INSTALLED NEW RT BRAKE ASSEMBLY, OPS AND LEAK CHECK GOOD IAW AMM 32-45-21.
IN FLIGHT THE CABIN EMERGENCY LIGHTS AS WELL AS THE ENTRY LIGHT IN THE CEILING WERE FLASHING. TURNING THE EMER LIGHT SWITCH TO OFF TURNED THEM OFF. REMOVED & REPLACED FWD & AFT EMERGENCY BATTERIES IAW MM 33-52-01. OPS CHK GOOD.
MAIN DOOR: THE MAIN ENTRY PASSENGER DOOR SLAMS DOWN WHEN OPENING FROM THE INSIDE. THE DOOR ACTUATORS ARE NOT ASSISTING THE MAIN ENTRY DOOR DURING THE OPEN FREE FALL OPERATION. *** CORRECTIVE ACTION *** DURING TROUBLESHOOTING FOUND THE RIG PIN HOLES TO NOT BE ALIGNED. WHICH ENDED UP BEING ASSOCIATED WITH THE TORISON BAR NEEDING TO BE REPLACED. WE DID TRY TO REMOVE DOOR CABLES TO SEE IF WE COULD REALIGN THE RIG PIN HOLES, BUT THERE WAS NO LUCK. INSTALLED CUSTOMER SUPPLIED NEW TORSION BAR P/N:500-09894-003 S/N:F040863555 CLOSED ALL INTERIOR ACCESS AS REQUIRED. ALL CHECKS GOOD. WORK DONE IN REF TO EMB-505S AMM 52-13-20.
DISCREPANCY: IN ZONE 122, COCKPIT EMERGENCY BATTERY FAILED FUNCTIONAL CHECKS AT 18:20 MINUTES. CORRECTIVE ACTION: PERFORMED REPLACEMENT NR 1 (FORWARD) EMERGENCY LIGHT BATTERY IN ACCORDANCE WITH PHENOM 300 AMM CHAPTER 33-52-01. PERFORMED OPERATIONAL TEST OF EMERGENCY LIGHT BATTERY IN ACCORDANCE WITH PHENOM 300 AMM CHAPTER 33-52-00. NO DEFECTS NOTED. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR'S GMM REQUIREMENTS.
DURING ACCOMPLISHMENT OF EMBRAER SB 505-55-0004 REV 01 PART I, II, III (DATED 06/24/2020), WE NOTED THE FOLLOWING MASS BALANCE WEIGHTS BELOW TOLERANCE AT LEFT ELEVATOR. ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (1 EACH BELOW MINIMUM OF 84G), HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G), ALSO LEFT HAND AILERON MASS WEIGHT PART NUMBER PE915109-L31 (1 EACH BELOW MINIMUM OF 2809G) ALL WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS, THE ELEVATOR AND AILERON BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11079-639 AND THE LEFT HAND AILERON TO PART NUMBER 505-14736-619, AS PER SB INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RIGHT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (7 EACH BELOW MINIMUM OF 84G); HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G); ALL WEIGHTS HAVE BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED. THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11079-640, AS PER SB INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATORâS GMM REQUIREMENTS.
MAIN CABIN DOOR WILL NOT OPEN. CORRECTIVE ACTION, VERIFIED DISCREPANCY, FOUND AFT MAIN CABIN DOOR TRIM LOOSE AND WEDGED BETWEEN DOOR FRAME AND MED CAUSING IT TO JAM. UPON FURTHER REVIEW FOUND DUAL LOCK FROM AFT DOOR TRIM UNADHERED CAUSING IT TO BECOME LOOSE AND AFT TELESCOPING ROD JOINT SHROUD BROKEN. RE-APPLIED DUAL LOCK (FROM FREE STOCK) TO AFT CABIN DOOR TRIM (LINING) AND RE-ATTACHED TO MAIN CABIN DOOR. INITIAL OPERATIONAL CHECKS GOOD, WAITING ON AFT TELESCOPING ROD SHROUD WORK DONE IN REF TO AMM 25-23-04, 25-00-26. INSTALLED REPLACEMENT AFT TELESCOPING ROD SHROUD, PERFORMED MED OPERATIONAL CHECKS GOOD. WORK DONE IN REF TO AMM 25-23-04.
GEN 2 OFF BUS YELLOW CAS ILLUMINATED - 45,000 FEET, -65 DEGREES GEN 2 OFF MESSAGE. RAN QRC AND IT WOULDN'T COME BACK ONLINE. DIVERTED TO KIWA. AT APPROXIMATELY 30,000 FEET STARTED TO HEAR ENGINE NOISE. CONFIRMED RIGHT ENGINE NOISE WAS GETTING LOUDER. SHUT DOWN ENGINE AND LANDED SINGLE ENGINE WITHOUT INCIDENT. REMOVED AND REPLACED #2 ENGINE STARTER/GEN WITH AN OVERHAULED UNIT IAW AMM 24-31-01-400-801.
BIRD STRIKE LT WING ROOT, DENT OVER 12" LONG & 3" DEEP. REMAINS IN & AROUND ENG NACELLE. CRACK ON LT OTBD ENG NACELLE. R&R LT WING INBD LE ASSY & PICCOLO TUBE. PERFORMED LEAK & OPERATIONS CHECK OF WING ANTI-ICE SYS WITH NO DEFECTS NOTED IAW AMM 57-40-00 400 & 30-12-03 400. REPORTED CRACK ON LT OTBD ENG NACELLE, INSPECTED & FOUND ONLY TO BE A SUPERFICIAL SCRATCH IN THE TOP LAYER OF POINT, REQUIRING NO FURTHER CORRECTIVE ACTION. COMPLETED FOREIGN OBJECT DAMAGE, BIRD STRIKE TASK CARD REQUIREMENTS & MX ITEMS ON NR 1 ENG WITH NO FURTHER DISCREPANCIES NOTED IAW EMM 05-50-00-210-805. PARTS REPLACED LE PANEL PN 505-12600-407, SN 901498849 00090, PICCOLO TUBE LT WING PN 505-17398-901 & SN T2PL6D004ED1F OLD.
AFTER SUCCESSFUL COMPLETION OF 1ST LEG AND 1 COMPLETE CYCLE OF THE GEAR, TOOK OFF ON SECOND LEG. WHEN GEAR HANDLE WAS RAISED GEAR DID NOT COME UP. GEAR CONTROL C/B HAD POPPED WHEN GEAR WAS RAISED. MATCHED CONDITION WITH GEAR HANDLE DOWN AND TRIED TO RESET C/B. THE C/B WOULD NOT RESET. RETURNED FOR LANDING. ALL OTHER HYD SYS WORKED. TURNED POWER ON AND ENGAGED CIRCUIT BREAKER. CIRCUIT BREAKER REMAINED ENGAGED. JACKED ACFT & PERFORMED 20 GEAR SWINGS WITH NO FAULTS NOTED. INSPECTED WIRING FOR SQUAT SWITCHES & GEAR CONTROL VALVE WITH NO FAULTS NOTED. LANDING GEAR OPS CHECK GOOD AT THIS TIME IAW MM 32-01-00.
PRESS LIGHT FOLLOWED BY AN ANTI SKID INOP LIGHT. WE LANDED AND USED THE EMERGENCY BRAKING SYSTEM. UNABLE TO DUPLICATE. SERVICED GEAR/ BRAKE ACCUMULATOR. BLED BRAKES. R & R ANIT-SKID CONTROL RELAY. INSPECTED GEAR HANDLE WIRES AND SWITCHES; CLEANED AS WELL. INSPECTED WIRES TO PRESSURE SWITCH. OPS CHECK GOOD. WORK DONE IAW MM 20-20-00, 32-31-09, 32-42-00 AND 32-42-09.
DURING AN OCF FOR THE RT ENG, THE ENG QUIT AFTER PULLING THE POWER LEVER BACK TO IDLE QUICKLY. ALSO, AFTER LANDING IT QUIT AGAIN AFTER A RAPID POWER LEVER REDUCTION. R & R RT AFT THROTTLE CABLE AND FUSELAGE CABLE IAW MM 76-12-03. OPS CHECK GOOD. AFT CABLE PN 580-291-852.
DURING SPEED BRAKE TEST, RT ENGINE SHUTDOWN. NORMAL FORCE USED DURING TEST. (REPEAT WRITE UP). REMOVED RT LWR COWLING ADJUSTED THROTTLE CABLE FRICTION BLOCKS. CHECKED FRICTION IN COCKPIT-FRICTION IS GOOD ON RT THROTTLE LEVER- RAN ACFT AND CHECKED FOR ENGINE SHUTDOWN WHILE RUNNING SPEED BRAKE SYS-CHECK GOOD. CLOSED LWR COWLING IAW MM 71-01-03.
DURING SPEED BRAKE TEST (USING NORMAL FORCE) THE RT ENGINE SHUTDOWN. RAN BOTH ENGINES AND PERFORMED SPEED BRAKE SYS OPS CHECK SEVERAL TIMES WHILE GRADUALLY INCREASING FORCE. NO DISCREPANCIES NOTED. DONE IAW MM 27-61-00.
AFTER TAKE OFF SMOKE SMELL - (NO SIGN OF VISUAL SMOKE) APPEARED.
BUFFETING/GRINDING NOISE INTERMITTENT AT ALL ALTITUDES AND SPEEDS. FOUND STARTER/GENERATOR ON LT ENGINE VIBRATING EXCESSIVELY. REMOVED AND REPLACED GENERATOR IAW ULTRA MM 80-11-01. GROUND RUN OPERATIONAL CHECKS SATISFACTORY. EXTERIOR INSPECTION OF AC REVEALED NO FAULTS.
CABIN DOOR LIGHT ILLUMINATED IN FLIGHT. REMOVED CABIN DOOR SWITCH P/N P18M30 S/N 1020. INSTALLED NEW PART P/N P18M30 S/N 4317. OPERATIONAL AND LEAK CHECK GOOD. WORK DONE IAW CESSNA MAINTENANCE MANUAL 560 36-11-02.
ALL 4 BRAKE PEDALS TRAVEL ABOUT 2 TO 3 INCHES BEFORE BRAKE PRESSURE CAN BE FELT. PRESSURE AT THAT POINT IS ABOUT 70 PERCENT OF NORMAL. TROUBLESHOT LT AND RT PILOTS AND COPILOTS BRAKES, BLED LT AND RT BRAKE SYSTEMS IAW MM CH 32-42-00, OPS CK AND LEAK CHECK GOOD. SERVICED BRAKE RESERVOIR IAW MM CH 12-12-02.
COPILOTS BRAKES SPONGY. LEFT PEDAL REQUIRES SIGNIFICANTLY MORE TRAVEL TO ENGAGE BRAKE (ABOUT 2 INCHES). TROUBLESHOT BRAKE SYSTEM A FAULTY CO-PILOT LT BRAKE MASTER CYLINDER. REMOVED AND REPLACED COPILOT'S LT BRAKE MASTER CYLINDER. BLED BRAKES LEAK & OPS CK WAS GOOD IAW CE560 MM CH 32-42-02.
DURING TAXIING THE F/O'S BRAKES FELT SOFT, CAPTAIN'S SIDE WAS GOOD. AFTER TAKEOFF CONTINUED TO OBSERVE BRAKE PRESSURE, ALL NORMAL. AT CRUISE NOTICED A VIBRATION AND HUMMING SOUND, DIVERTED AIRCRAFT INTO MEM AND DECLARED EMERGENCY FOR LANDING. BRAKES OPS CHECK GOOD ON GROUND, JACKED AIRCRAFT FOUND BRAKE PUMP CYCLED PROPERLY. SWUNG GEAR AND PUMP STOPPED, PRESSURE BLEEDS OFF, WHILE BRAKE WAS BEING BLEED LOUD BANG FROM POWER BRAKE VALVE. REPLACED BRAKE VALVE, LEAK CHECKED AND OPS CHECKED GOOD, ALL WORK DONE IAW CESSNA 560 MM CHAPTER 32-42-05.
CLIMBING THROUGH 12,000 FT AT 280 KNOTS, NOTICED A "THUMPING NOISE" FOLLOWED BY AN INTERMITTENT GEAR UNSAFE LIGHT. SLOWED DOWN BELOW 250 KNOTS THEN THE PROBLEM STOPPED, RE-ACCELERATED IT HAPPENED AGAIN. LOWERED THE GEAR NORMALLY AND DIVERTED TO ACY. - ITEM IS UNDER INVESTIGATION.
CLIMBING THROUGH 12,000 FEET AT 280 KNOTS, NOTICED A "THUMPING NOISE" FOLLOWED BY AN INTERMITTENT GEAR UNSAFE LIGHT. SLOWED DOWN BELOW 250 KNOTS THEN THE PROBLEM STOPPED, RE-ACCELERATED IT HAPPENED AGAIN. LOWERED THE GEAR NORMALLY AND DIVERTED TO ACY. FOUND NOSE GEAR UP-LOCK ROLLER NOT SEATED IN HOOK WHEN GEAR WAS RETRACTED. ADJUSTED UP-LOCK ASSEMBLY PER CESSNA 560 MM CHAPTER 32-31-05, PERFORMED NUMEROUS LANDING GEAR SWINGS WITH NO PROBLEMS.
DURING ROUTINE INSPECTION LOOKED INTO DORSAL NACA SCOOP AND SAW THE LOWER AIR VANE WITH A 1.5 INCH CRACK STARTING FROM THE CENTER OF THE (V) CUT TOWARD THE OB EDGE. GAINED ACCESS FROM THE TAILCONE BAGGAGE AREA AND REMOVED CRACKED VANE. UPON REMOVAL NOTICED THAT THERE WAS NO RELIEF HOLE WAS INSTALLED AT INTERSECTION OF (V) NOTCH WHICH ALSO APPEARS TO HAVE BEEN CUT WITH HAND SNIPS. RECEIVED NEW PART AND INSTALLED WITH A RELIEF HOLE AT (V) INTERSECTION. REINSTALLED ITEMS REMOVED FOR ACCESS AND CLOSED UP BAGGAGE AREA.
DURING TEST OF BOTH STATIC SYSTEMS ON AIRCRAFT, FOUND EXCESSIVE STATIC LEAK IN BOTH NR1 AND NR2 SYSTEMS. FOUND STATIC HOSE IN BOTH SIDES LEAKING IN EXCESS OF FACTORY SPECS. REMOVED DEFECTIVE HOSES AND REPLACED WITH NEW, STATIC SYSTEM TESTED SATISFACTORY.