Grumman Tiger AA-5B Handling Notes

Starboard Wing: Check fuel contents, cap seal and cap secured, tank drain, ailerons checked for freedom of movement, then as for Port Wing. Starboard Fuselage: Static source unobstructed, antennas secure and undamaged, fuselage undamaged. Tail Section: Elevators free movement, rudder free movement, trim tabs secure, tail cone and lights checked, tie down removed. Port Fuselage: As for starboard but check baggage door secured. (c) INTERNAL CHECK On entering the aircraft, check flaps up, turn off the fuel, then adjust the seats and seat belts and check that passengers do likewise. Turn the master switch on and check all electrical instruments and required lighting is operational. Check the instrument panel from left to right making sure the radios are off, the controls are free, trim operative and set neutral. Check circuit breakers in. 3.0 Start-Up Brakes On Mixture Full Rich Carburettor Heat Off Fuel Select fullest tank Prime As required Master/Alternator Switch On Flaps Up Auxiliary Fuel Pump On check pressure then off Propeller Clear Ignition On left Throttle Open _ travel approximately Starter Button Press, release when engine starts Ignition On both Oil Pressure Check (if no pressure within 30 seconds, shut down engine) Engine Warm up at 100 RPM to 1200 RPM *Avoid prolonged idling while on the ground*  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 9 4.0 Pre Take-off Checks On reaching the holding point or holding bay, turn the aircraft as much as possible into wind, or at least 45 degrees across the taxiway. B Brakes On U Undercarriage Locked down T Trims Set for take-off Throttle Set 1000 RPM M Mixture Rich Master On P Pitch Fine F Fuel On fullest tank Fuel pump On check for pressure change then off Flaps Check then set up I Instruments Check and set flight instruments C Controls Free, full movement Carb Heat Cold H Harness Secure Hatches Locked E Engine Run up to 1800 RPM Check engine instruments and gauges Magnetos (175 max, 50 between) Carb Heat Return engine to 1000 RPM Check all switches on Obtain take-off clearance – transponder on if required. 5.0 Take Off (a) Normal take-off Auxiliary fuel pump On Power Full (b) Crosswind take-off As above but before commencing take-off check the wind direction and start initial take-off run with aileron into wind.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 10 6.0 After Take-off Checks After the aircraft is in a positive climb with an airspeed of not less than 65 kts. Engine instruments Check Auxiliary fuel pump Off Power Full Attitude 90 kts Trim for climb Check temperatures and pressures regularly 7.0 Cruising Normal maximum power 75% Trim as required Power setting 2200 to 2700 RPM Mixture leaned as required See Cruise Performance Charts at the end of these notes. 8.0 Let Down Procedures and Circuit Procedures For normal let down, maintain cruising speed and regulate power to achieve desired rate of descent. The mixture should be fully rich. No smoking rule in force. Avoid continuous operation at engine speeds between 1850 and 2250 RPM. B Brakes Off, heels on the floor U Undercarriage Down and locked M Mixture Rich, carb heat check for ice F Fuel Cock, contents, pump on and pressure H Harness Secure, seats upright 9.0. Approach and Landing Flaps down (unless flapless landing) below 103 kts Carb heat on if required Power reduced to 1500 RPM Speed 72 kts – trim to maintain Speed on final approach 70 kts: reducing to 69 kts Carb heat cold at 300 ft  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 11 Crosswind Landing Approach as for normal landing, tracing down the center line. On roundout close the throttle and line the aircraft with the runway before touchdown with rudder. Use aileron as required to maintain wings level. After touchdown apply aileron into wind. In strong crosswind nil flap may be desireable. Flapless Landing In extreme strong or gusty winds a flapless approach may be preferred. In this case the approach speed should be 72 kts . CAUTION: The nose wheel on the Grumman Tiger should be held off as long as possible to prevent prop damage or porpoising. If this situation does occur do not continue landing, go around. 10.0 After Landing Drill Leave the runway and move well clear of the holding point and stop. Flap Up Auxiliary fuel pump Off Carb heat Check off Trim Neutral 11.0 Shut Down Procedures Brakes On Radios Off Engine 1000 RPM Magnetos Check left and right for dead cut Mixture Idle cut back Throttle Fully back Ignition Off and keys out (after prop stopped) Master Off Fuel Off Chocks/Tiedowns Installed and brakes released If the aircraft has to be pushed back use the towbar – under no circumstances push on the spinner.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 12 12.0 Starting Engine when Flooded If the engine fails to start on the first try the second try should be made without Priming. If this also fails it is possible the engine is overprimed. Pull the mixture control to full lean, throttle full open, and turn the engine with the starter. When the engine starts, push the mixture control to full rich and reduce throttle.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 13 . Part 5 – Emergencies 1.0 Engine Failure after Take-off Lower nose for glide. Change fuel tanks, if engine does not respond then glide for landing straight ahead or 30 degrees either side of the flight path and try to avoid obstacles. *Do not try to turn back to the field * 2.0 Engine Failure at Altitude (Forced Landing) Engine fails T Close throttle, trim for glide – 72 kts F Fuel, switch tanks pump on, check pressure and contents M Mixture rich, carb heat hot I Ignition (left, right mags) Pick suitable landing area, formulate an approach plan. Check height – temps, pressure - throttle for available power. If engine failure not located: MAYDAY CALL Safety checks – fuel off- switches off- brakes off Harness tight and hatches unlocked Master off on final Warn passengers of the possibility of a heavy landing and to brace themselves suitably.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 14 3.0 Fire On ground – cranking Continue to get a start which would suck the flames and accumulated fuel through the carburettor and into the engine. If engine starts – Power 1800 RPM for few minutes. Engine shutdown for inspection of damage. (a) Fuel selector off (b) Master switch off (c) Ignition switch off If engine fails to start – evacuate passengers Secure engine with mixture idle cutoff, master off, ignition off, fuel selector off. Extinguish using extinguisher, seat cushion, wool blanket or dirt. In flight – engine fire Mixture idle cut off Fuel selector valve Off Master switch Off Cabin heat and air Off Airspeed 115 kts if fire is not extinguished, increase glide speed to attempt to blow the fire out. . Forced landing Execute as described.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 15 ELECTRICAL FIRE If fire is in engine compartment: Master switch Off Vents, cabin air and cabin heat Off Land aeroplane as soon as possible. If fire is in cockpit: Master switch Off All other switches Off except for ignition switch Vents, cabin air and cabin heat Off Fire extinguisher If activated open the canopy to ventilate cabin area. If fire appears to be out and electrical power is necessary to continue flight: Master switch On Circuits Check for faulty circuit. Do not reset Radio/electric switches On one at a time with delay after each until short circuit is located. Vents, cabin air and heat Open when fire is out. Cabin Fire: Master switch Off Vents, cabin air and heat Closed Fire extinguisher If activated open canopy for ventilation. Land as soon as possible. 4.0 Loss of Oil Pressure If no temperature change is detected, the failure is most likely in the indicating system. If oil temperature is high reduce power and proceed to the nearest suitable landing area. Be prepared for a forced landing.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 16 5.0 Alternator Failure Failure of the alternator is easily detected since the ammeter will show discharging to the extent of the loads being applied. If the alternator field circuit breaker opens (pops out) wait 15 seconds then attempt to reset by pushing the circuit breaker back into position. If it will not reset, turn off the alternator switch and land for electricl system inspection . Reduce electrical load as much as possible. 6.0 Engine Roughness Carburettor heat on, if the roughness continues after 1 minute: Carburettor heat off, mixture adjusted for maximum smoothness, electrical fuel pump on, switch fuel tanks, check engine gauges and then check magnetos. Use both position of magnetos unless roughness is such as to dictate use of single ignition position. If roughness cannot be rectified proceed to nearest aerodrome. Prepare for possible forced landing.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 17 Part 6 – Documention Required: Aircrafts flight manual and handling notes.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 18 Part 7 – Aircraft Systems 1.0 Fuel Systems This consists of two tanks with a total capacity of 199.1 litres of which 193 litres are useable, two sump tanks (one in each wing root fairing), independent fuel gauges and a fuel selector valve. Flush mounted fuel tank vents are located in the bottom of the outboard wing panels, just forward and inboard from the wing tie downs. A mechanical fuel pump, mounted on the engine, transfers fuel from the tanks to the carburettor. This is backed up by an auxiliary electrical fuel pump. This is used when the engine driven pump fails to deliver adequate pressure as shown by the fuel pressure gauge and at low altitudes such as at take-off or landing. There are four fuel drains located one beneath each fuel tank and of the wing root on each side of the aircraft. A drain cup is provided in the glove compartment. Flight with an unserviceable auxiliary fuel pump is prohibited. 2.0 Landing Gear The main landing gear struts are of tough, laminated fiberglass to achieve outstanding shock absorption and good ground stability. The nose gear is free-castering to approximately 90 degrees on either side of the centerline, which gives good manuoeverability on the ground. 3.0 Control Systems The control surfaces are operated by a combination of torque tubes and conventional cable systems. The elevator anti-servo trim tabs are located on the elevator trailing edges and are actuated manually by the trim wheel located on the center console. Ground adjustable tabs on the rudder and ailerons provide a simple method of adjusting directions and lateral trim. Flaps are electrically operated and provide a full range of settings by means of a spring loaded, three flap position switch. The flap actuator switch is held down until the flap position indicator shows the desired flap angle, when released it returns to neutral, and flap travel stops. CAUTION: Abruptly releasing the switch may cause it to snap through the neutral detent, into the retract position.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 19 4.0 Electrical System This system uses a 14 volt, 60 amp alternator with internal power diodes which delivers DC power directly to the main bus through a 60 amp circuit breaker. An external voltage regulator controls the alternator output voltage and automatically adjusts the battery charging rate to maintain proper charge. The electrical system ammeter is located in the engine instrument cluster and indicates current charge (+) and discharge (-) of the battery. The dual magneto ignition system is completely independent of the aircraft’s electrical system, and will continue to operate in the event of an electrical system failure. The master switch is the split rocker type which serves two functions. Side one (master) energises the battery circuit which produces the electrical field in the alternator. This then supplies all the required current for the system loads through the bus bar. Fuses and circuit breakers for the electrical systems are located on the lower right hand side of the instrument panel and spare fuses are located on the right side of the glove compartment. 5.0 Vacuum System An engine driven vacuum system is available and provides the suction necessary to operate the attitude indicator and the directional gyro indicator. The system consists of a vacuum pump mounted on the engine, a regulator and vacuum system air filter on the aft side of the firewall below the instrument panel, and instruments (including a suction gauge) on the instrument panel. The suction gauge is located at the upper edge of the instrument panel. The desired suction range is 4.6" to 5.4" Hg. A suction reading above or below this range may indicate a system malfunction or improper adjustment, and in this case, the indicators should not be considered reliable. 6.0 Canopy Entry into and exit from the aeroplane is accomplished by releasing the canopy latch and sliding the canopy aft. The canopy latch is actuated by an external handle on the front center of the canopy and an internal handle located inside the canopy at its front center. The external latch works by counterclockwise rotational and the internal handle opens the latch by rearwards motion. A lock on the left of the external handle provides a means of externally locking the canopy. It is designed to open a longitudinal distance of 86.4 cm and is limited by stops. The canopy can be partially opened in flight to provide ventilation or better visibility. However, it must be completely closed and locked when flying at airspeeds in excess of 113 kts. The cabin windows aft of the canopy are fixed and cannot be opened.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 20 7.0 Heating and Ventilation Systems Cabin heating and defrosting temperature is controlled by the Cabin Heat Control, located on the instrument panel above the throttle. When this control is pushed in, cabin heating is decreased and when pulled out, heating is increased. The cabin heat is directed into the cabin through vents near the firewall, under the instrument panel. To apply defrost open the sliding doors below the windshield. Ventilation is provided by vent controls located at the bottom left and right corners of the instrument panel. The air is directed through louvred vents. The rear cabin area vents are operated by a twisting motion. When cool and a high humidity do not use partial defrost as the windshield may fog rapidly on take-off. Always check defrost position before flight. The heater and fresh air systems can be operated simultaneously to provide a comfortable cabin temperature.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 21 Part 8 – Pilot Maintenance 1.0 Tyre Inflation For maximum service from tyres, keep inflated to proper pressure as per Part 1 of these notes. 2.0 Battery Service The battery is accessible by opening the top cowl. The battery is equipped with an overboard vent and drain. It should be inspected periodically for proper fluid level and if the fluid is found to be low, fill as recommended by the battery manufacturer. DO NOT fill above visible battery plates. 3.0 Care of Windows and Canopy It is recommended that you keep the plexiglass in the canopy, windshield and cabin windows clean and unscratched. The following is recommended: (a) If large deposits of mud and/or dirt have accumulated flush with clean water. Hand rubbing is recommended for stubborn patches to prevent scratching. (b) Wash with soap and water, using a sponge or soft cloth. DO NOT scrub or rub hard as abrasive action of the dirt will create fine scratches. (c) Grease and oil spots may be removed with a soft cloth soaked in kerosene. (d) After cleaning wax with a thin coat of hard polish-wax. Permatex `D` a suitable windscreen polish. Apply with a soft cloth pad using an up and down motion, allow to dry, then polish off with a soft cloth. Permatex `D` is available from the Flight School Office. (e) If severe scratch or marring occurs, jeweller’s rouge is recommended. Follow directions to rub out scratch then polish. (f) Never use gasoline, benzine, alcohol, acetone, carbon tetrachloride, fire extinguisher fluid, anti-ice fluid, lacquer thinner or glass cleaner as these items may cause severe crazing.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 22 PART 9 – Weight and Balance 1.0 Weight Maximum take-off weight (normal category) 1089 kg Maximum take-off weight (utility category) 930 kg Maximum landing weight 1089 kg Empty weight (VH-IGG only) 656.8 kg 2.0 Centre of Gravity NORMAL CATEGORY Forward Limit 2260.6 mm aft of the datum at 1089 kg and 2057.4mm aft of the datum at 871 kg or less, with linear variation between 871 kg and 1089 kg. Rear Limit 2349.5 mm aft of the datum at all weights UTILITY CATEGORY Forward limit 2112.5 mm aft of the datum at 930 kg and 2057.4 mm aft of the datum at 871 kg or less with linear variation between 871 kg and 930 kg. Rear Limit 2167.1 mm aft of the datum at all weights. 3.0 Datum 1270 mm forward of the front face of the firewall. 4.0 Baggage Compartment Loading (a) Maximum permissible baggage compartment load = 54 kg (normal category only). (b) Where rear passenger seats are folded to permit the carriage of cargo, the maximum load on the seat backs shall not exceed 154 kg.  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 23  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 24  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 25  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 26 Cruise Performance Charts Conditions: Recommended lean mixture, weight 2400 pounds (1089kg) PRESSURE ALTITUDE 2000 FEET 20°C Below Std. Temp -9°C (16°F) Standard Temp 11°C (52°F) 20°C Above Std. Temp 31°C (88°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 96 142 163 14.4 89 141 162 13.3 88 140 161 13.1 2600 85 136 156 12.6 79 135 155 11.2 75 134 154 10.7 2500 76 130 149 10.9 71 129 148 10.4 67 128 147 10.0 2400 68 124 142 10.0 63 122 141 9.5 60 121 140 9.2 2300 60 117 135 9.2 57 115 132 8.7 54 113 131 8.4 2200 54 110 126 8.4 51 108 124 8.1 49 107 123 7.9 PRESSURE ALTITUDE 3000 FEET -11°C (12°F) 9°C (48°F) 29°C (84°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 93 141 163 13.9 86 141 162 12.8 81 140 161 12.0 2600 83 135 156 12.3 77 134 155 11.0 73 134 154 10.6 2500 74 129 148 10.6 70 128 148 10.2 66 127 146 9.7 2400 67 123 142 9.9 62 122 140 9.4 59 120 138 9.0 2300 59 117 134 9.0 56 115 132 8.6 53 113 130 8.3 2200 53 109 125 8.3 50 107 123 8.0 48 105 121 7.8 PRESSURE ALTITUDE 4000 FEET -13°C (9°F) 7°C (45°F) 27°C (81°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 90 141 162 13.4 84 140 161 12.5 78 139 160 11.1 2600 81 135 156 12.0 75 134 154 10.8 72 134 154 10.4 2500 72 129 148 10.5 68 129 148 10.0 64 127 146 9.6 2400 65 123 142 9.6 61 121 140 9.2 58 120 138 8.8 2300 58 116 134 8.9 54 114 131 8.5 52 112 129 8.2 2200 51 108 125 8.1 49 107 123 7.9 47 103 119 7.6 PRESSURE ALTITUDE 5000 FEET -15°C (5°F) 5°C (41°F) 25°C (77°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 87 141 162 13.0 81 140 161 12.0 77 139 160 10.9 2600 78 134 155 11.1 74 134 154 10.6 69 132 152 10.1 2500 71 129 148 10.3 66 127 146 9.7 62 125 144 9.3 2400 63 122 141 9.5 59 120 138 9.0 56 119 137 8.7 2300 56 115 132 8.7 53 113 130 8.3 51 112 129 8.1 2200 50 108 124 8.0 48 106 121 7.8 46 104 119 7.6  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 27 Cruise Performance Charts (cont.) Conditions: Recommended lean mixture, weight 2400 pounds (1089kg) Note: Shaded area represents operation with full throttle. (F.T.) PRESSURE ALTITUDE 6000 FEET 20°C Below Std. Temp -9°C (16°F) Standard Temp 11°C (52°F) 20°C Above Std. Temp 31°C (88°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 85 141 162 12.6 79 139 160 11.2 75 139 160 10.8 2600 76 134 154 10.9 72 134 154 10.4 67 132 152 9.9 2500 69 129 148 10.1 64 127 146 9.6 61 125 144 9.2 2400 61 122 140 9.3 58 120 138 8.9 55 117 135 8.5 2300 55 114 131 8.5 52 112 129 8.2 50 110 127 8.0 2200 49 107 123 7.9 47 104 119 7.6 45 102 118 7.5 PRESSURE ALTITUDE 7000 FEET -11°C (12°F) 9°C (48°F) 29°C (84°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 83 140 161 12.3 77 139 160 11.0 73 138 159 10.5 2600 74 134 154 10.7 70 133 153 10.2 66 131 151 9.7 2500 67 128 147 9.9 63 126 145 9.4 59 124 143 9.0 2400 60 121 139 9.1 56 119 137 8.7 54 117 135 8.4 2300 53 113 130 8.4 51 112 129 8.1 48 108 124 7.8 2200 49 107 123 7.8 46 103 119 7.6 45 102 117 7.4 PRESSURE ALTITUDE 8000 FEET -13°C (9°F) 7°C (45°F) 27°C (81°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 80 139 160 11.2 75 139 160 10.8 71 137 158 10.3 2600 72 134 154 10.5 68 132 152 10.0 64 130 150 9.5 2500 65 127 146 9.7 61 125 144 9.2 58 123 142 8.9 2400 58 120 138 8.9 55 118 136 8.6 53 117 134 8.3 2300 53 113 129 8.3 50 111 128 8.0 48 109 125 7.8 2200 48 105 121 7.8 46 103 118 7.5 45 102 117 7.4 PRESSURE ALTITUDE 9000 FEET -15°C (5°F) 5°C (41°F) 25°C (77°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 76 138 158 10.9 72 138 158 10.5 69 137 157 10.1 2600 71 134 154 10.4 66 131 151 9.8 63 130 149 9.4 2500 63 126 145 9.5 60 124 143 9.1 57 123 141 8.7 2400 57 119 137 8.8 54 117 135 8.4 52 115 132 8.2 2300 52 112 129 8.2 49 108 125 7.8 47 107 123 7.7 2200 46 103 119 7.6 45 102 117 7.4 45 101 117 7.4  University Flying Club (Inc). Pilots must refer to the flight manual for actual data. These notes are a guide only. 28 Cruise Performance Charts (cont.) Conditions: Recommended lean mixture, weight 2400 pounds (1089kg) Note: Shaded area represents operation with full throttle. (F.T.) PRESSURE ALTITUDE 10 000 FEET 20°C Below Std. Temp -9°C (16°F) Standard Temp 11°C (52°F) 20°C Above Std. Temp 31°C (88°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH 2700 72 136 156 10.5 69 136 156 10.2 67 135 155 9.9 2600 68 132 152 10.0 64 130 150 9.6 61 129 148 9.2 2500 62 125 144 9.3 58 123 142 8.9 56 123 141 8.6 2400 56 118 136 8.6 53 117 135 8.3 50 113 130 8.0 2300 51 112 129 8.1 48 108 125 7.8 47 106 122 7.7 2200 46 104 120 7.6 45 102 117 7.4 45 101 116 7.4 PRESSURE ALTITUDE 11 000 FEET -11°C (12°F) 9°C (48°F) 29°C (84°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH F.T. 70 134 154 10.2 67 134 154 9.9 65 134 154 9.7 2600 67 132 152 9.9 63 130 150 9.5 60 129 148 9.1 2500 61 125 144 9.2 57 123 141 8.8 54 120 139 8.5 2400 55 117 135 8.5 52 115 133 8.2 50 114 131 8.0 2300 50 110 126 8.0 47 107 123 7.7 47 106 122 7.6 2200 45 102 117 7.5 45 101 117 7.4 45 101 116 7.4 PRESSURE ALTITUDE 12 000 FEET -13°C (9°F) 7°C (45°F) 27°C (81°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH F.T. 67 132 152 9.8 64 132 152 9.6 62 132 152 9.4 2600 65 131 151 9.7 61 129 148 9.3 58 128 147 8.9 2500 59 124 142 9.0 56 123 141 8.7 53 118 136 8.3 2400 54 117 135 8.4 50 113 130 8.0 49 111 128 7.9 2300 48 108 124 7.8 47 106 122 7.7 47 106 122 7.6 2200 45 102 117 7.4 45 101 116 7.4 45 101 116 7.4 PRESSURE ALTITUDE 13 000 FEET -15°C (5°F) 5°C (41°F) 25°C (77°F) RPM % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH % BHP TAS KTS TAS MPH Fuel GPH F.T. 64 130 150 9.5 62 130 150 9.3 60 130 150 9.1 2600 64 130 150 9.5 60 128 147 9.1 57 127 146 8.8 2500 58 123 142 8.9 55 121 139 8.5 52 118 136 8.2 2400 52 116 133 8.3 50 114 131 8.0 49 111 127 7.8 2300 48 109 125 7.8 47 106 122 7.6 47 106 122 7.6 2200 45 101 117 7.4 45 101 116 7.4 45 100 115 7.4