FAA REGISTRY
N-Number Inquiry Results
| Serial Number | 108-818 | Status | Valid |
| Manufacturer Name | STINSON | Certificate Issue Date | 03/11/2023 |
| Model | 108-1 | Expiration Date | 03/31/2030 |
| Type Aircraft | Fixed Wing Single-Engine | Type Engine | Reciprocating |
| Pending Number Change | None | Dealer | No |
| Date Change Authorized | None | Mode S Code (base 8 / Oct) | 53321771 |
| MFR Year | 1946 | Mode S Code (Base 16 / Hex) | ADA3F9 |
| Type Registration | Partnership | Fractional Owner | NO |
| Name | JEFFERS JASON W | ||
| Street | PO BOX 338 | ||
| City | GIRDWOOD | State | ALASKA |
| County | ANCHORAGE DIV | Zip Code | 99587-0338 |
| Country | UNITED STATES | ||
| Type Certificate Data Sheet | None | Type Certificate Holder | None |
| Engine Manufacturer | LYCOMING | Classification | Standard |
| Engine Model | O-360-A1A | Category | Normal |
| A/W Date | 06/15/2009 | Exception Code | No |
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The information contained in this record should be the most current Airworthiness information available in the historical aircraft record. However, this data alone does not provide the basis
for a determination regarding the airworthiness of an aircraft or the current aircraft configuration. For specific information, you may request a copy of the aircraft record at https://aircraft.faa.gov/e.gov/ND/ |
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| JEFFERS MARILYN E |
| None |
| Mod Code | 28 | Mod Date | 20070310 |
| INSTALLATION AUXILIARY FUEL TANK PER SPECIFICATION A-767 AND ITEM #607FOR INSTALLATION APPROVAL MET-CO-AIR DRAWING #5108 AND 4108 TANK AND FUEL SYSTEM PRIOR APPROVED ON STINSON 108-N769C. SYSTEM OPERATION: RIGHT FUEL TANK MUST BE SELECTED TO ALLOW FUEL FROM AUXILIARY TO FLOW INTO LEFT WING TANK. POWER FROM BREAKER 10AMP FLOWS THROUGH SWITCH ANDROUTED 2 DIRECTIONS: ONE WIRE ENERGIZES PUMP OTHER WIRE POWERS ANNUNCIATOR AND THEN TO PRESSURE SWITCH. FUEL PRESSURE BUILDS PAST 2 PSI PRESSURE SWITCH ISOLATES ANNUNCIATOR FROM GROUND AND ANNUNCIATOR EXTINGUISHES DURING FUEL TRANSFER. WHEN FUEL IN AUXILIARY TANK HAS BEEN TRANSFERRED PRESSURE IN TRANSFER HOSE DROPS. PRESSURE SWITCH CLOSES GROUND CIRCUIT FROM ANNUNCIATOR AND LIGHT COMES ON ALERTING PILOT TRANSFER IS COMPLETE. SWITCH IS TURNED OFF. FUEL GUAGES FOR LEFTWING TANK AND AUXILIARY TANK WILL ALSO CONFIRM FUEL TRANSFER, AUXILIARY SWITCH AND ANNUNCIATOR IS PLACARD WITH INSTRUCTIONS FOR OP- ERATION, FUEL FLOW .225 GALS/MIN 13.5 GPH, OPERATIONPLACARDS INSTALL- ED COPY OF 337 TO REMAIN IN AIRCRAFT WITH EQUIPMENT LIST. REVERSE FUELFLOW IS PREVENTED BY: CHECK VALVE INSTALLED LEFT MAIN FUEL TANK, PRESSURE SWITCH AND SOLENOID PREVENTS REVERS FLOW, FUEL PUMP HAS BOTH INTERNAL CHECK AND ANTI-SIPHON VALVES. MANUALLY OPERATED SHUTOFF VALVEINSTALLED BETWEEN AUXILIARY TANK AND PUMP TO ALLOW SERVICE FOR FUEL FILTER AND IN-LINE FILTER. VALVE WOULD NORMALLY BE LOCK-WIRED OPEN. ANOTHER MANUAL VALVE LOCATED AT LOW POINT IN SYSTEM ALLOWS CON- TAMINATION WATER REMOVAL. VALVE IS SPRING LOADED CLOSED AND LOCATED OUTSIDE THE AIRCRAFT. TANK VENT IS ROUTED OUTSIDE BOTTOM OF AIRCRAFT VIA 1/4 TUBE WITH A FORWARD SCARF CUT TO HELP PRESSURIZE AUXILIARY | |||
