PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR HAWKER BEECHCRAFT MODEL N35, P35

In Full View of Pilot (Airspeed values are CAS) SECTION III EMERGENCY PROCEDURES If for any reason it is necessary to land with more than 1/2 tank difference in tip tank quantities, the landing should be made with wing flaps in the “up” position. NORMAL CATEGORY AIRPLANE (WHEN OPERATED IN EXCESS OF 3125 LB. MAX. GROSS WEIGHT, OR WITH FUEL IN TIP TANKS) AIRSPEED LIMITATION (NORMAL CAT. OPERATIONS) MAXIMUM DESIGN MANEUVERING SPEED 142 MPH (123 KNOTS) OPERATE IN ACCORDANCE WITH FAA APPROVED FLIGHT MANUAL / PILOT’S OPERATING HANDBOOK. INTENTIONAL SPINS ARE PROHIBITED. NO ACROBATIC MANEUVERS APPROVED. SAMPLE D’Shannon Products, LTD Document No: FMS-DP-NP35 TT 1309 County Road 134 Hawker Beechcraft N35, P35 Buffalo, MN 55313 Revision B Date: __________________ Page 6 of 9 SECTION IV NORMAL PROCEDURES AIRSPEEDS FOR SAFE OPERATION Maximum Turbulent Air Penetration ...................................................................... CAS 123 KTS CAS 142 MPH PREFLIGHT INSPECTION Fuel drains are located on the lower surface of each tip tank. Drain these points daily before the first flight to purge any water from the system. Check security of flush mounted tip tank filler caps during preflight inspection. Before flight, check the tip tanks for unsymmetrical fuel loading. If fuel tank capacities differ more than 1/4 tank, relocate fuel prior to take-off. See Section VII, Systems for additional information. SECTION V PERFORMANCE The performance of this airplane operated according to STC(S) SA153EA or SA02722CH is equal to or better than the performance listed in the original Airplane Flight Manual (AFM) except that take-off and landing distance and rate-of-climb charts originally presented for this model do not apply to this STC modification. Increase AFM/POH take-off and landing chart values and decrease rate-of-climb chart values as shown in the table below when operating at the new maximum gross weight. Model INCREASE take off distance INCREASE landing distance DECREASE rate of climb N35, P35 15% 15% 6% In addition, range and endurance information in the original Airplane Flight Manual (AFM) does not apply to this STC modification. When operating at maximum gross weight with no tip tank fuel, decrease AFM/POH range data and endurance information as shown in the table below. These percentages do not account for additional range and endurance allowed by tip tank fuel: Model DECREASE range data DECREASE endurance information N35, P35 6% 10% SAMPLE D’Shannon Products, LTD Document No: FMS-DP-NP35 TT 1309 County Road 134 Hawker Beechcraft N35, P35 Buffalo, MN 55313 Revision B Date: __________________ Page 7 of 9 SECTION VI WEIGHT AND BALANCE Weight Condition Forward CG Limit Aft CG Limit 3325 lb. 82.1 84.7 3125 lb Straight line variation 85.7 2800 lb. or less 77 85.7 CG Limitations (wheels down) 77 82.1 84.7 85.7 Inches Aft of Datum Note: CG of Tip Tank Fuel Is 87” Aft of Datum 3325 3125 Gross Weight 2800 SAMPLE D’Shannon Products, LTD Document No: FMS-DP-NP35 TT 1309 County Road 134 Hawker Beechcraft N35, P35 Buffalo, MN 55313 Revision B Date: __________________ Page 8 of 9 Weight and Balance Loading Form Model __________________________ Date: ___________________________ Serial No: D- _________________ Reg. No.: ___________________________ Item Weight Mom./100 1. Basic Empty Weight 2. Front Seat Occupants 3. 3rd and 4th Seat Occupants 4. 5th and 6th Seat Occupants 5. Baggage 6. Cargo 7. Sub Total Zero Fuel Condition 8. Basic Fuel Loading 9. Tip Tank Fuel Loading 10. Sub Total Ramp Condition 11. Less Fuel for Start, Taxi, and Take-off * 12. Sub Total Take-off Condition 13. Less Fuel to Destination 14. Landing Condition * Fuel for start, taxi, and take-off is normally 10 lb. Usable tip tank fuel is located at an average arm of 87 inches aft datum. SAMPLE D’Shannon Products, LTD Document No: FMS-DP-NP35 TT 1309 County Road 134 Hawker Beechcraft N35, P35 Buffalo, MN 55313 Revision B Date: __________________ Page 9 of 9 SECTION VII SYSTEMS DESCRIPTION FUEL In addition to the basic airplane fuel system, two auxiliary wing tip fuel transfer tanks are installed with a capacity of 20 gallons each, all of which is usable. Take-offs are prohibited with more than 1/4 difference in tip tank fuel quantity. During flight if tip tank fuel quantity gauges indicate more than 1/2 tank difference the landing should be made with flaps up. Tip tank fuel is transferred into its respective main tank by an electric pump at a rate of approximately 15 gallons per hour. The transfer pump and a solenoid valve are mounted inside the wheel well of each wing on the rib at wing station 66. At higher power settings, fuel consumption may exceed the fuel transfer rate to the main tank selected. Tip tank transfer pump switches are located either on the face of the instrument panel or between the front seats on the partition assembly forward of the main spar truss. The pump and solenoid valve circuit breaker is installed adjacent to the pump switches. A fuel drain is provided on the lower surface of each tip tank. Fuel quantity is measured by observing the fuel level on a sight gauge located on the inboard side of each tip tank. Normal tip tank fuel transfer should be accomplished simultaneously to maintain symmetrical wing tip tank fuel loading. Initiate transfer with the left main at 1/2 full and feeding the engine. During the transfer, monitor fuel gauges for both main tanks and stop transfer if gauge indicates full to prevent overflow of fuel through the main tank vent tubes. SECTION VIII HANDLING, SERVICING AND MAINTENANCE No Change. SECTION IX SUPPLEMENTS No Change. SECTION X SAFETY INFORMATION No Change.