FAA REGISTRY
N-Number Inquiry Results
| Serial Number | 208B1049 | Status | Valid |
| Manufacturer Name | CESSNA | Certificate Issue Date | 12/04/2021 |
| Model | 208B | Expiration Date | 12/31/2028 |
| Type Aircraft | Fixed Wing Single-Engine | Type Engine | Turbo-prop |
| Pending Number Change | None | Dealer | No |
| Date Change Authorized | None | Mode S Code (base 8 / Oct) | 52755420 |
| MFR Year | 2004 | Mode S Code (Base 16 / Hex) | ABDB10 |
| Type Registration | Corporation | Fractional Owner | NO |
| Name | AIRPAC AIRLINES INC | ||
| Street | 1402 FAIRCHILD AIRPORT RD | ||
| City | PORT ANGELES | State | WASHINGTON |
| County | CLALLAM | Zip Code | 98363-9502 |
| Country | UNITED STATES | ||
| Type Certificate Data Sheet | None | Type Certificate Holder | None |
| Engine Manufacturer | P&W | Classification | Standard |
| Engine Model | PT6A SER | Category | Normal |
| A/W Date | 03/24/2004 | 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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| Mod Code | 28 | Mod Date | 20131021 |
| INSTALLED TEMPORARY FUEL SYSTEM CONSISTING OF FOUR ALUMINUM FUEL TANKSFUEL VALVE MANIFOLD, TWO 24 VOLT ELECTRIC FUEL TRANSFER PUMPS, AND ASSOCIATED FUEL LINES AW ATTACHED FUEL SYSTEM DRAWING LABELED "CARAVAN FUEL SYSTEM DRAWING #1". TANKS ARE INSTALLED IN THE CABIN AREA ON A RACK CONSISTING OF 2X4 AND 1/2" PLYWOOD BASE FOR EVEN LOAS DISTRIBUTION. TANKS ARE GROUNDED TO AIRFRAME FOR STATIC DISCHARGE. TANKS ARE RECTANGULAR, INTERNALLY BAFFLED, CONSTRUCTED FROM WELDED 5052 ALUMINUM .100" THICK AND PRESSURE TESTED IAW FAR 23.966A(1). THE TANKS ARE SECURED FORE AND AFT AND VERTICALLY TO THE PASSENGERS IN BOARD, MIDDLE AND OUTBOARD SEAT TRACKS USING AIRCRAFT TIE-DOWN RINGS AND FOUR 3000# RATING CARGO STRAPS MEETING OR EXCEEDING FAA TSO C22. THE TANKS ARE SUPPORTED LATERALLY BY CONTACT WITH THE AIRCRAFT SIDE STRUCTURE AND PROTECTED BY INTERIOR UPHOLSTERY AND VINYL PADDING. THE FUEL SYSTEM T'S INTO THE AIRCRAFT FUEL SYSTEM BY INSTALLATION OF A T IN THE AIRCRAFT FUEL TANK BALANCE VENT LINE. THIS INSTALLATION DOES NOTINTERFERE WITH VENTING OF THE AIRCRAFT FUEL TANKS. ALL FITTINGS ARE #8 OR LARGER AND FUEL AND OIL TOLERANT HOSE IS USED THROUGHOUT THE INSTALLATION. FERRY FUEL SELECTOR MANIFOLD AND TWO TSO'ED AIRBORNE FUEL PUMPS ARE MOUNTED BESIDE THE PILOTS SEAT. EACH PUMP IS CABABLE OFDELIVERINGENOUGH FUEL FOR CONTINUED FLIGHT. POWER OFR THE FUEL PUMPS IS TAKEN FROM THE MAIN BATTERY BUSS AND PROTECTED THROUGH A TEMPORARY 30 AMP FUSE AND SEPARATED 5 AMP FUEL PUMP CIRCUIT BREAKERS, ALL ACCESSIBLE TO THE PILOT IN FLIGHT. FERRY FUEL SYSTEM IS VENTED TO THE EXTERIOR OF THE AIRCRAFT THROUGH A TEMPORARY VENT PROTRUDING BENEATH THE RIGHT WING AND SUPPLYING RAM AIR TO THE FOUR FERRY FUEL TANKS. | |||
| Mod Code | 28 | Mod Date | 20071115 |
| 1. INSTALLED TEMPORARY FERRY FUEL SYSTEM CONSISTING OF 'XX' ALUMINUM FERRY FUEL TANKS, FUEL VALVE MANIFOLD, PUMPS AND ASSOCIATED LINES IAW LEAHY AVIATION CESSNA 208 SERIES DATA. 2. TANKS ARE INSTALLED IN THE CABIN AREA ON A 2X4" & 3/8" PLYWOOD BASE FOR EVEN LOAD DISTRIBUTION. TANKS ARE GROUNDED TO AIRFRAME FOR STATIC DISCHARGE. TANKS ARE REC- TANGULAR, INTERNALLY BAFFLED, CONSTRUCTED FROM 5052 ALUMINUM 0.100" THICK AND PRESSURE TESTED IAW FAR 23.965A(1). FORWARD THE TANKS ARE SECURED TO PASSENGER'S INBOARD, MIDDLE & OUTBOARD SEAT TRACKS VIA TIE DOWN RINGS & 10,000 LB. CARGO STRAPS. AFT THE TANKS ARE SECURED TO AIRCRAFT SEAT TRACKS CROSSWAYS & AFT. TANKS ARE SECURED USING 10,000 LB CARGO STRAPS MEETING OR EXCEEDING THE MATERIAL REQUIREMENTS OF FAA TSO C22. FLOOR LOADING LIMITS ARE NOT EXCEEDED. 3. FERRY FUEL SYSTEM TEES INTO AIRCRAFT FUEL SYSTEM BETWEEN AIRCRAFT FUEL TANK BALANCE LINE. ALL FITTINGS ARE NO.8 OR LARGER AND PARKER FUEL HOSE USED THROUGHOUT THE FERRY FUEL SYSTEM. FERRY FUEL MANIFOLD AND TSO'D WELDON FUEL PUMPS ARE MOUNTED BEHIND PILOT'S AND CO-PILOT'S SEATS. FUEL PUMP POWER IS TAKEN FROM AIRCRAFT BUSS 2 WITH INDIVIDUAL 5 AMP CIRCUIT PROTECTION. FERRY FUEL SYSTEM USES A RAM AIR VENT TO PROVIDE EXTERNAL VENTING AS WELL AS PROVIDE A POSITIVE PRESSURE TO AID THE FLOW OF FERRY FUEL. FERRY FUEL SYSTEM GROUND CHECKED. FERRY FUEL SYSTEM TO BE FLIGHT TESTED AND RESULTS ENTERED IN AIRCRAFT RECORDS. 4. TEMPORARY HF RADIO CONSISTING OF AN ICOM IC-718 TRANSCEIVER & ICOMAH-4 AUTOMATIC TUNER INSTALLED IAW ICOM INSTALLATION MANUAL P/N A-5649D-1EX5. POWER PROVIDED FROM AVIONICS BUS WITH DUAL 20A CIRCUIT PROTECTION THROUGH ASTRON 2412-20 24-12V VOLTAGE CONVERTER. ANTENNA | |||
