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Beechcraft Beech 95 2017, Pilot'S Information Manual

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Beechcraft Beech 95 2017 Pilot'S Information Manual Download Page 65

Selkirk College IATPL Program Manual

 

Beech 95 POH

   

Effective September 1, 2005

 

Appendix 14 - 65 

 
With the landing gear in the up position the wheels are completely enclosed by fairing 
doors that are operated mechanically by the retraction and extension of the gear. After the 
gear is lowered the main gear inboard fairing doors automatically close, producing extra 
lift and reduced drag for takeoff and landing. Individual down-locks actuated by the 
retraction system lock when the gear is fully extended. The linkage is also spring loaded 
to the over-center position. 
 
Two landing gear position lights, one red and one green, are located above the landing 
gear switch. Two switches on the gear actuator (gearbox) activate the lights. The red light 
indicates the gearbox has rotated to the full up position and the green light indicates the 
gearbox is in the down position. In addition a mechanical indicator beneath the control 
console, connected directly to the nose gear linkage, shows the position of the nose gear 
at all times. 
 
To prevent accidental gear retraction on the ground a safety switch on the left main strut 
breaks the control circuit whenever the strut is compressed by the weight of the airplane 
and completes the circuit so the gear may be retracted, when the strut extends. 

Never rely 

on the safety switch to keep the gear down while taxiing or on takeoff or landing 
roll. Always check the position of the gear handle.

 

 
With the gear retracted, if either or both throttles are retarded below an engine setting 
sufficient to sustain flight, a warning horn will sound an intermittent note. During single-
engine operation, advancing the throttle of the inoperative engine enough to open the 
horn switch will silence the horn. 
 
The nose wheel assembly is made steerable through a spring-loaded linkage connected to 
the rudder pedals. Retraction of the gear relieves the rudder pedals of their nose steering 
load and centers the wheel, by a roller and slot arrangement, to ensure proper retraction in 
the wheel well. A hydraulic dampener on the nose wheel strut compensates for the 
inherent shimmy tendency of a pivoted nose wheel. 
 
Wheels are carried by heat-treated tubular steel trusses and use Beech air-oil type shock 
struts. Since the shock struts are inflated with both compressed nitrogen and hydraulic 
fluid their correct inflation should be checked prior to each flight. Even brief taxiing with 
a deflated strut can cause severe damage. 
 
For manual operation of the landing gear (lowering only) a hand crank is located behind 
the front seats. The crank, when engaged, drives the normal gear actuation system. 
 
Main wheels are equipped with hydraulic disc brakes actuated by individual master 
cylinders on the pilot and co-pilot rudder pedals. The hydraulic brake reservoir is 
accessible from the nose baggage compartment and should be checked occasionally for 
specified fluid level. The parking brake is set by a push-pull control below the pilot sub-
panel just left of the center console. Setting the control does not pressurize the brake 
system, but simply closes a valve in the lines so that pressure built up by pumping the toe 

Summary of Contents for Beech 95 2017

Page 1: ...PL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 1 Beech 95 Pilot Information Manual For the exclusive use of students in the Selkirk College Professional Aviation Program Copyright 2005 revised 2010 ...

Page 2: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 2 ...

Page 3: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 3 ...

Page 4: ... Owner s Manual 3 Beechcraft Travelair Shop Manual Copies of the above manuals are available in the Selair Resource Center This manual is also based on actual experience operating the airplanes for 25 years at Selkirk College This Information Manual is for use with both GSAK and FXFG GSAK is a 1965 D95A FXFG is a 1968 E95 The procedures and performance of the two airplanes is identical except wher...

Page 5: ... 5 Contents General Section 1 Limitations Section 2 Emergency Procedures Section 3 Normal Procedures Section 4 Performance Section 5 Weight and Balance Section 6 Airplane Systems Description and Operation Section 7 Aircraft Handling Servicing and Maintenance Section 8 Supplements Section 9 ...

Page 6: ... of Gravity Limits 19 Maneuver Limits 20 Flight Load Factor Limits 20 Kinds of Operation Limits 20 Fuel Limitations 20 Other Limitations 22 Flap Limitations 22 Gear Limitations 22 Cowl Flap Limitations 22 Placards 22 Section 3 Emergency Procedures 23 Introduction to Section 3 23 Airspeeds for Emergency Operation 23 Emergency Checklists 23 Amplified Engine Failure Procedures 23 Simulated Zero Thrus...

Page 7: ... 46 Time Fuel and Distance to Climb 3500 lb 47 Beech 95 Cruise Performance Chart 48 B95 Cruise 70 2400 rpm 49 Single Engine Cruise Performance 50 Section 6 Weight and Balance 52 Introduction to Section 6 52 Weight and Balance Procedure 53 Weight Limits 55 Center of Gravity Limits 55 Section 7 Airplane Systems Description Operation 57 Introduction to Section 7 57 Airframe 57 Cabin Doors and Windows...

Page 8: ...ionics 71 HSI PN101 71 RMI 71 Gyro Slaving System 71 Heater and Ventilation System 72 Electric System 76 Alternators Voltage Regulators and Ammeters 76 Busses 77 Batteries 77 Circuit breakers and Fused Switches 77 Over Voltage Warning 78 Alternator Out Lights 78 Vacuum System 82 Brake System 83 Cabin Ventilation 84 Section 8 Aircraft Handling Servicing and Maintenance 86 Towing 86 CAUTION 86 Exter...

Page 9: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 9 Section 1 General Three View ...

Page 10: ... Engine Model IO 360 B1B Engine Type Normally aspirated direct drive Air cooled horizontally opposed Horsepower rating 180 hp 2700 rpm 29 MP Propellers GSAK Propeller Manufacturer Hartzel Propeller Model HC 92WK 2 Propeller Type 2 blade constant speed full feathering Propeller diameter 71 72 inches FXFG modified under STC SA00722CH Propeller Manufacturer Hartzel Propeller Model HC C2YK 2CUF FC7666...

Page 11: ...05 Appendix 14 11 Auxiliary tanks 62 US gallons useable Nacelle tanks INOPERATIVE DO NOT USE Note takeoff is prohibited with less than 10 gallons in each main tank A yellow band on the fuel gauges applicable only when main tanks are selected marks the minimum fuel for takeoff ...

Page 12: ...e viscosity oils multi viscosity oils meeting MIL L 22851 are approved OIL Capacity Sump each engine 7 quarts Total each engine 8 quarts Recommended minimum for takeoff 5 5 quarts Minimum for safe operation 2 quarts Maximum Certified Weights Ramp 4200 lbs Takeoff 4200 lbs Landing 4200 lbs Weight in nose baggage compartment 270 lb Weight in aft baggage compartment 400 lbs Cabin and Entry Dimensions...

Page 13: ...tion VNE Never Exceed Speed is the speed limit that may not be exceeded at any time Vs Stalling Speed or the minimum steady flight speed at which the airplane is controllable in cruise configuration Vso Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration at the most forward center of gravity Vx Best Angle of Climb Speed is the speed ...

Page 14: ...el pressure altitude and decreases 1 98 degrees per thousand feet Pressure Altitude Pressure altitude is the altitude read from an altimeter when the altimeter barometric scale has been set to 29 92 inches of mercury Density Altitude Density Altitude is pressure altitude corrected for non standard air temperature Engine Power Terminology BHP Brake Horsepower is the power developed by the engine RP...

Page 15: ...vity Arm is the arm obtained by adding the airplanes individual moments and dividing the sum by the total weight C G Limits Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight Empty Weight Empty weight is the weight of the standard airframe plus any optional equipment installed plus full oil Useful Load Useful load is th...

Page 16: ...is data has been gleaned from various sources within Beechcraft documentation but may not be totally accurate Design Limitations The following design speeds apply Speed KIAS KCAS Vfe Maximum flap extended 113 113 Vle Maximum landing gear extended 143 143 Vmc Minimum control speed 71 69 Vsse Single engine safety speed 78 75 Vno Maximum structural cruising speed top of green arc 161 161 Vne Never ex...

Page 17: ...5 1 19 78 73 Maneuvering speed Va This airplane is designed for normal operating limits of 4 4g and 3 0g pilot induced loads in the clean configuration It is limited to 2 0g and 0 0g pilot induced loads with any flaps extended Maneuvering speed clean is defined as Va 3 8 x Vs Weight Va KIAS Va KCAS 4200 139 139 4000 136 136 3800 132 132 3600 129 129 Turbulence Speed This airplane is designed to wi...

Page 18: ...llow Arc 161 208 Operations must be conducted with caution and only in smooth air Red Line 208 Maximum speed for all operations Blue Line 94 Vyse at maximum weight and sea level Power Plant Limitations Engine Manufacturer Avco Lycoming Engine Model IO 360 B1B Maximum rated Power 180 BHP 2700 rpm for all operations Engine Operating Limits for Takeoff and Continuous Operations Maximum engine speed 2...

Page 19: ...Maximum 2700 rpm Manifold Pressure 14 5 29 29 Fuel Flow 0 17 8 10 psi Oil temperature 140 245 245 Oil Pressure 25 65 85 85 Cylinder Head Temperature 200 500 500 Exhaust Gas Temperature Fuel Quantity Main E 3 gal Aux E 0 gal Main 10 Aux N A Suction Pressure 3 75 3 75 5 25 5 25 Weight Limits Maximum weight 4200 lbs Aft baggage limit 400 lbs Nose baggage limit 270 lbs Center of Gravity Limits Center ...

Page 20: ...ositive 2 0g negative 0 0g flaps down Gust limits positive 4 32g negative 2 32g flaps up Kinds of Operation Limits These airplanes are equipped for day and night VFR and IFR operations CAR 605 18 specifies the equipment that must be installed and serviceable for IFR operation Flight into known icing conditions is prohibited Fuel Limitations Each airplane has four fuel tanks two main tanks and two ...

Page 21: ...FF position to prevent any contamination from entering the main fuel tanks The left fuel selector provides fuel to the left engine and the right fuel selector provides fuel to the right engine Total Capacity 112 US gallons Total useable fuel 106 US gallons Main tanks 50 US gallons total Main tanks 44 US gallons useable Auxiliary tanks 62 US gallons total Auxiliary tanks 62 US gallons useable Nacel...

Page 22: ...ix 14 22 Other Limitations Flap Limitations Approved takeoff Range 0 to 20 Approved landing Range 0 to 29 Gear Limitations Maximum gear operating speed 143 KCAS Maximum gear extension speed 143 KCAS Cowl Flap Limitations Cowl flaps may be operated at any operational airspeed Placards ...

Page 23: ...sion speed 89 KIAS Vyse sea level 94 KIAS Yyse 5 800 density altitude 91 KIAS Vxse sea level 85 KIAS Vxse 10 000 density altitude 91 KIAS Maneuvering speed 4200 lb 139 KCAS 3600 lb 129 KCAS Maximum glide 4200 lb zero flap zero wind 103 KIAS Emergency Checklists All emergency checklists are provided in the aircraft operational checklist in each airplane Copies can be found in Appendix 1 of your Pro...

Page 24: ... choose to operate under these weight and altitude conditions Simulated Zero Thrust A manifold pressure of approximately 12 inches provides a level of thrust approximately equal to a feathered propeller During pilot training this value should be used rather than actually feathering the engine for safety and wear and tear reasons ...

Page 25: ...9 KIAS Enroute Climb flaps up 105 120 KIAS Best rate of climb sea level 95 KIAS Best rate of climb 20 000 82 KIAS Best angle of climb sea level 73 KIAS Best angle of climb 20 000 82 KIAS Landing approach Normal approach full flap 80 KIAS at 50 ft agl Normal approach flaps up 90 KIAS at 50 ft agl Short field approach full flap 74 KIAS until flare Balked Landing Maximum power flaps 20 80 KIAS Maximu...

Page 26: ...or several hours and feel cool to the touch use the Cold Engine Start checklist Prime the engine using the electric fuel pump prior to engaging the starter In temperatures above 10 C approximately three seconds of fuel flow with the mixture set to rich and the throttle set to inch will be sufficient Increase priming progressively up to six seconds for temperature at 15 C Guard against possible eng...

Page 27: ...its flight may be continued A mag drop of more than 125 accompanied by rough engine operation may mean that a spark plug has become fouled To clear the fouled plug increase rpm to 2200 then lean the mixture until rpm drops 25 to 50 rpm Allow the engine to run in the leaned condition for one minute then return the mixture to rich and reset rpm to 2000 Repeat the magneto check If the mag drop is now...

Page 28: ...such conditions while not prohibited is not recommended Soft or Rough Field Takeoff Takeoff on a soft or rough field may require liftoff below Vmc This procedure is therefore not recommended For takeoff on a soft field it is recommended to use 20 flaps and liftoff at 71 to 74 KIAS if possible If liftoff must be made below 71 KIAS accelerate in ground effect to 71 KIAS or above as quickly as possib...

Page 29: ... confusion GSAK is operated the same way The cruise performance charts in section 5 reflect the limitation Mixture should be set using the fuel flow gauge to the value from the B95 Cruise Performance Chart section 5 after manifold pressure and rpm are set Once engine temperatures stabilize mixture may be adjusted with the EGT to obtain maximum exhaust gas temperature On short flights less than 15 ...

Page 30: ...retracted until the stall has been eliminated and the airspeed is above 80 KIAS Descent Normally manifold pressure is reduced in descents in order to maintain a constant indicated airspeed It is acceptable to allow speed to increase during the descent provided that airspeed limitations are not exceeded The mixture level should be advanced progressively as the descent continues to prevent over lean...

Page 31: ... Landing Short field landings are conducted with full flaps Final descent should be initiated with the gear then full flaps should be applied The speed at 50 ft agl should be 74 KIAS plus half the wind gust factor Maintain this speed until the flare It is recommended that when the pilot is not familiar with the short field landing characteristics that 74 KIAS plus half the gust factor be establish...

Page 32: ... weights Based on years of operational experience at Selkirk College we feel that a competent and experienced Travelair pilot can safely achieve a crosswind limit of 15 knots Balked Landing IFR Missed Approach In a balked landing go around apply full power and establish a climb Immediately reduce flaps to 20 degrees and retract gear once positive rate of climb is established if obstacles must be c...

Page 33: ...5 Appendix 14 33 strike the ground Pilots should maintain situational awareness and realize that single engine balked landing is not possible when above or even near the single engine service ceiling See single engine climb performance chart in section 5 for climb performance ...

Page 34: ...ers Manual are identical The Normal takeoff chart is constructed based on the Beech charts pages 6 2 and 6 3 of the POH You will notice if you examine those charts that the chart for 20 MPH wind is defective as it shows the takeoff distance to be less than the chart for 30 MPH wind therefore it was ignored in creating the graph shown here Beech does not provide a chart to allow for less than gross...

Page 35: ...er switching from a planned Vgo speed to a planned go altitude or some other suitable method of deciding when to continue or reject a takeoff following an engine failure Note that the same situation exists when practicing short field takeoffs on a runway that is long and unobstructed The Accelerate go chart is based on the normal takeoff distance to 35 feet agl charts on pages 6 2 and 6 3 The airp...

Page 36: ...und in the official Beechcraft documentation IAS 73 5 94 139 CAS 71 5 99 139 The above data was used to develop the following two tables These are estimates only Estimated calibration table for flaps up IAS 70 80 90 100 110 120 130 140 150 CAS 68 77 86 95 105 117 129 140 150 Estimated calibration table for flaps extended IAS 60 70 80 90 100 110 CAS 56 66 77 88 99 110 ...

Page 37: ...etract gear at positive rate of climb Cowl flaps open Example Density altitude 5000 ft Weight 3500 lb Headwind 20 Knots Results Ground roll 1700 Distance to 50 feet 2110 NOTES Produced by Selkirk College based on approved POH For use by Selkirk College Professional Aviation students and instructors only Distances calculated with this chart are based on pages 6 2 and 6 3 of the Beechcraft Travelair...

Page 38: ...ore 50 feet agl Example Density altitude 5000 ft Weight 3500 lb Headwind 20 Knots Results Ground roll 1700 Distance to 50 feet 2110 NOTES Produced by Selkirk College based on approved POH For use by Selkirk College Professional Aviation students and instructors only Distances are based on Beechcraft Travelair D95A Owners Manual charts on pages 6 20 and 6 21 see notes on page 34 of this appendix ...

Page 39: ... students and instructors only Distances calculated with this chart are an estimate based on the normal takeoff distance chart such that the airplane is at 35 agl at 89KIAS a 20 second time period is allowed to complete the engine failure drill during which the assumed performance is gear down propeller windmilling A climb to 50 feet is then assumed based on gear up and propeller feathered The rel...

Page 40: ... Selkirk College Professional Aviation students and instructors only Distances calculated with this chart are an estimate based on the assumption that the airplane is at 35 agl at 89KIAS a 3 second reaction time is assumed with no change in altitude The stopping distance is then based on the normal landing distance chart from 35 feet Data was taken from pages 6 2 6 3 6 20 and 6 21 of the Beechcraf...

Page 41: ...k toward operating engine Note This chart is based on page 6 9 of the Beechcraft Travelair D95A Owners Manual All IFR departure procedures require a minimum of 200 ft Nm climb gradient Some procedures require more than 200 ft Nm Transport Canada regulations do NOT require single engine climb gradients for legal IFR departures but the lack of such climb gradients should cause pilots to prepare alte...

Page 42: ...rk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 42 Single Engine Ceiling Conditions All altitudes are ISA Density Altitudes Altitude for 200 ft Nm climb is with zero wind ...

Page 43: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 43 ...

Page 44: ... College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 44 Time to Climb at Vy Maximum Continuous Power Conditions Weight 4200 lb Airspeed Vy see chart below Maximum continuous power ...

Page 45: ...anual Beech 95 POH Effective September 1 2005 Appendix 14 45 Maximum Rate of Climb Conditions Weight 4200 lb Maximum continuous power Airspeed Best rate as shown in upper part of graph gives rate of climb shown in lower part of graph ...

Page 46: ...rd temperature Distances shown are based on zero wind Weight Lb Pressure Altitude Ft Temp C Climb Speed KIAS Rate of Climb Fpm From Sea Level Time Min Fuel Used Gallons Distance NM 4200 S L 1000 2000 3000 4000 5000 6000 7000 8000 9000 10 000 11 000 12 000 13 000 14 000 15 000 16 000 17 000 18 000 15 13 11 9 7 5 3 1 1 3 5 7 9 11 13 15 17 19 21 105 105 105 105 105 101 97 93 90 89 89 88 87 87 86 85 8...

Page 47: ... are based on zero wind Interpolate between 3500 and 4200 pound charts as required Weight Lb Pressure Altitude Ft Temp C Climb Speed KIAS Rate of Climb Fpm From Sea Level Time Min Fuel Used Gallons Distance NM 3500 Or less S L 1000 2000 3000 4000 5000 6000 7000 8000 9000 10 000 11 000 12 000 13 000 14 000 15 000 16 000 17 000 18 000 15 13 11 9 7 5 3 1 1 3 5 7 9 11 13 15 17 19 21 105 105 105 105 10...

Page 48: ...21 3 GPH MP rpm TAS IAS Full Throttle MP Sea Level 17 5 2400 120 120 20 0 2400 134 134 22 1 2400 145 145 23 4 2400 149 149 24 5 2450 154 154 29 0 2 000 17 1 2400 121 118 20 8 2400 137 133 21 7 2400 146 142 22 8 2400 152 148 24 0 2450 157 152 27 0 4 000 16 7 2400 122 115 19 3 2400 138 130 21 2 2400 149 140 22 4 2400 155 146 23 5 2450 160 151 25 1 6 000 16 3 2400 123 112 18 8 2400 140 128 20 7 2400 ...

Page 49: ...instrument panel of the piston simulators and is also on your quick reference sheet B95 Cruise 70 2400 rpm Density Alt 19 5 GPH 9 75 per eng MP TAS IAS Sea Level 23 4 149 149 2 000 22 8 152 148 3 000 22 9 153 147 4 000 22 4 155 146 5 000 22 2 156 145 6 000 21 9 157 144 7 000 21 7 158 143 8 000 21 5 160 142 9 000 Use 65 power 10 000 Use 65 power ...

Page 50: ...icated airspeed varies from 100 to 105 depending on weight altitude and temperature Because single engine cruise uses climb power and speed it is safe to set the mixture as you would normally in a climb We recommend using the climb performance fuel flow chart on page 6 10 copied on next page of this manual For example at 5000 fuel flow would be 15 5 gph In summary we recommend assuming 100 KIAS si...

Page 51: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 51 ...

Page 52: ... each airplane can be found in the Pilot Operating Handbook in the airplane The weight and balance report contains the actual weight moment and arm for the empty airplane This data must be used when computing takeoff landing and zero fuel weight moment and arm for the airplane Pilots must ensure that the airplane is loaded within the specified weight arm and moment limits throughout all flights It...

Page 53: ...raft reg GSAK 2939 234020 Fuel main tanks 200 75 15000 Fuel aux tanks 300 93 27900 Pilots 400 85 34000 Passengers 140 136 5040 Cargo area 1 50 31 1550 Cargo area 2 50 150 7500 Ramp Weight 4079 325 010 Taxi fuel allowance 15 84 1260 Takeoff Weight 4064 79 7 323750 Fuel Consumed mains 100 75 7500 Fuel consumed aux 75 93 6975 Landing Weight 3889 79 5 309275 The moment for fuel pilots passengers and c...

Page 54: ...ment to give the value 323750 The takeoff cg position is then determined by dividing the moment by the takeoff weight in the example this is 323750 divided by 4064 79 7 To allow for fuel used during the flight the weight of fuel used is subtracted and the moment for the fuel is calculated and subtracted also In the example 100 pounds of fuel is used from the main tanks with a moment of 7500 The mo...

Page 55: ...ition 136 Fuel main tanks 75 Fuel Aux tanks 93 Aft baggage area 150 Nose baggage compartment 31 If passenger seats are removed for baggage use Baggage ahead of spar 108 Baggage aft of spar 145 Weight Limits Maximum weight 4200 lbs Aft baggage limit 400 lbs Nose baggage limit 270 lbs Center of Gravity Limits Center of gravity limits gear extended Forward limit 75 inches aft of datum to gross weight...

Page 56: ...the Travelair weight and balance is quite easy to calculate Note that the Main tanks are at 75 inches which is the forward limit Therefore when you burn fuel from the main tanks cg always moves aft Note also that the auxiliary tanks are at 93 inches which is behind the aft limit Therefore when you burn fuel from the aux tanks cg always moves forward Be sure to check both takeoff and landing cg to ...

Page 57: ...tand flight loads in excess of the FAA requirements for normal category under which the Model D95 and E95 are certified Cabin Doors and Windows Access to the main cabin is through the single entry door on the right side of the fuselage Access to the door is via a step at the trailing edge of the right wing and a walkway on the top of the right wing and wing flap It is safe to step on the marked wa...

Page 58: ...s hatch on the right side of the fuselage just behind the wing trailing edge A small hat rack above and behind the main baggage compartment can be used to store light items The passenger seats can be removed to provide additional cargo carrying capacity All cargo in all baggage areas must be securely prevented from moving in flight Weight limitations for each baggage area are found in section 6 Vi...

Page 59: ... reversible electric motor located under the front seat On the D95A two position lights on the left side of the control consol indicate flap position A red light illuminates when the flaps are fully extended and a green light illuminates when the flaps are fully retracted On the E95 a flap position gauge on the control console displays the incremental flap positions from 0 to 28 On all airplanes 1...

Page 60: ...s on the face of the center console Full dual ignition systems are used with an ignition vibrator supplying starting voltage Each engine has an electric starter A 28 volt alternator mounted at the lower right side of each engine is driven by a belt and pulley system An engine accessory box on the aft of each engine supports a propeller governor vacuum pump and mechanical fuel pump Oil System The e...

Page 61: ...it of travel Un feathering and restarting in flight is achieved by moving the propeller control well into the governing range and following the engine restart in the air checklist Momentary use of the starter to initiate rotation is necessary only at low airspeeds Immediately after the engine starts the throttle and propeller controls should be adjusted to prevent an engine over speed condition FX...

Page 62: ...with 22 gallons useable The Main tanks must be used for all takeoffs and landings Main tanks should normally also be selected when performing special flight maneuvers such as stalls The Auxiliary tanks hold 31 US gallons with all 31 useable The auxiliary tanks may be used in normal climbs cruise and descents Auxiliary tanks should not be used when performing steep turn slips stalls or other unusua...

Page 63: ... The auxiliary tank drain is located near the wing trailing edge just behind the main gear It drains water and other contaminants from the Auxiliary tanks The fuel strainer drain is just ahead of the wheel well It drains contaminants trapped in the fuel strainer which is a cup type strainer in the main fuel line where contaminants heavier than water will settle out The fuel selector drain removes ...

Page 64: ...s Gear The gear is electrically operated tricycle landing gear The gear is operated through push pull tubes by a reversible electric motor and actuator gearbox under the front seat A two position landing gear switch located on the right hand side of the center console controls the motor Limit switches and a dynamic braking system automatically stop the retract mechanism when the gear reaches its f...

Page 65: ...both throttles are retarded below an engine setting sufficient to sustain flight a warning horn will sound an intermittent note During single engine operation advancing the throttle of the inoperative engine enough to open the horn switch will silence the horn The nose wheel assembly is made steerable through a spring loaded linkage connected to the rudder pedals Retraction of the gear relieves th...

Page 66: ... opens the valve and releases the brakes Instrument Panel Ignition Panel The ignition sub panel is on the left sidewall just below the pilot s storm window This panel contains a key operated battery switch two combination magneto starter knobs and two alternator control switches In addition the E95 FXFG has the outside air temperature gauge mounted here also ...

Page 67: ...nted on the main panel are DME control GPS Annunciator and on FXFG the amber Cowl Flap position light Pilot Sub panel The pilot sub panel contains the RMI and second VOR ILS indicator The RMI is equipped with a three position switch labeled Nav1 GPS Nav2 This is explained below under avionics The above picture shows the switches and circuit breakers on the Pilot sub panel The pilot side sub panel ...

Page 68: ...At its top are the engine power controls propellers throttles and mixtures The control yoke is mounted below the engine power controls The elevator and rudder trim actuator wheels are mounted below the yoke The aileron trim actuator is in the center of the control yoke Panel lighting knobs are adjacent to the elevator trim wheel Alternate air knobs are on the front of the lower section of the cons...

Page 69: ... floodlight This not an effective lighting system so can usually be left off In addition to adjusting the panel lighting with the rheostat certain lights are individually dimmable The landing gear and flap position lights as well as the cowl flap light and the over voltage light each have a built in iris that can be adjusted to vary the light intensity from full to almost zero Rotating the housing...

Page 70: ...ght side of the instrument panel and consist of Oil Temperature Gauge Cylinder Head Temperature Gauge Exhaust Gas Temperature Gauge Suction Gauge GSAK Pressure Gauge FXFG In addition to the above engine gauges this panel also contains Fixed Card ADF Vacuum Heading Indicator not slaved Altimeter Avionics Circuit Breaker Panel The avionics circuit breaker panel is just below the avionics stack descr...

Page 71: ...DF KT76A Transponder In addition to the stacked radios listed above a KM64 DME and a GPS annunciator panel are mounted on the left side of the Main instrument panel Navigation information is displayed on the following instruments PN101 HSI located on Main panel A standard VOR ILS indicator on the Pilot s sub panel An RMI on the Pilots sub panel HSI PN101 The PN101 is an electric horizontal situati...

Page 72: ...iter unit two fuel pumps a fuel filter a shut off valve an electric ventilation air blower and temperature limiting thermostats Above picture shows heater as viewed with fiberglass nose cowl removed Iris valve shown below is also removed The pilot activates the heater by turning the three position switch on the pilot sub panel to Heater up position and pushing the cabin air T handle all the way in...

Page 73: ...l seconds for warm air to be delivered after turning the heater on If no warm air arrives within one minute adjust the cabin heat knob explained below and the adjustment of the cabin outlets explained below Picture shows controls below pilot sub panel T handle labeled cabin air can be seen on the left Cabin heat knob controls thermostat Note that defroster is pull for off but pilot air is pull to ...

Page 74: ...re than half way Pulling the cabin air handle out all the way stops all airflow through the system preventing drafts in the cabin when the heater is not in use With the iris valve open ram air forces air through the heating system in flight for ground operation the ventilation air blower maintains airflow A switch connected to the nose landing gear actuation linkage ensures that the blower operate...

Page 75: ...heat in this situation by pulling the cabin air knob part way out partially closing the iris valve For safety a normally open fuse in the heater discharge plenum will close making the system inoperative if the temperature in the plenum exceeds 150 C This fuse is located on the upper bulkhead behind the instrument panel where it cannot be reached in flight If this fuse activates in flight have an A...

Page 76: ... equipped with two voltage regulators and the pilot can choose which one is activated with a switch on the pilot sub panel Normal practice is to alternate use of the regulators to ensure that both remain serviceable Flight with only one serviceable voltage regulator is not prohibited but eliminates the safety factor inherent in a redundant electric system The voltage regulators draw current from t...

Page 77: ...ed switches The avionics bus is behind the avionics circuit breaker panel and supports all avionics circuit breakers The two alternators send current directly to the main bus through the two 50 amp circuit breakers labeled left alternator and right alternator The avionics bus is fed through a switch that takes power directly from the main bus Two switches are provided to ensure redundancy explaine...

Page 78: ...he light see diagram on following page The over voltage relay activates when system voltage exceeds approximately 32 volts The relay blocks the field current from reaching the alternators Once the relay is open the over voltage light illuminates The E95 FXFG is equipped with voltage regulators that have built in over voltage protection When the over voltage circuit senses a system voltage above 32...

Page 79: ...ppendix 14 79 Above picture shows alternator out lights on FXFG The push to test button is between the two lights A push to test button for the lights is provided Note that the lights will only illuminate if the alternator switch is in the on position and the battery switch is on ...

Page 80: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 80 ...

Page 81: ...Selkirk College IATPL Program Manual Beech 95 POH Effective September 1 2005 Appendix 14 81 ...

Page 82: ...l Operationally the suction and pressure systems work the same In both systems one pump is adequate to power the instruments should the other pump fail Check valves prevent loss of pressure if one pump fails The diagram above shows the vacuum system in TD638 GSAK Note that the vacuum gauge shows the amount of suction inside the case of the attitude indicator The standby heading indicator has its o...

Page 83: ...is not connected to the gauge Each pump has a filter in the engine nacelle through which the pump draws air A plugged filter will render the pump inoperative In this system the outflow air is collected into a common manifold and then dumped in the nose baggage compartment Brake System The Travelair is equipped with hydraulic disc brakes on each main landing gear The brakes are individually control...

Page 84: ...s pedal This also ensures that the brake system will continue to function should any master cylinder develop a leak Cabin Ventilation Fresh air can be brought into the cabin in several different ways When operating on the ground the most effective method is to open the door storm window and lift the two emergency exits to the partially open position In flight the above mentioned portals should be ...

Page 85: ...d eyeball vents to the open position Extra airflow is obtained if the outflow valve rotary knob in photograph above is opened The outflow allows air in the cabin to escape which is necessary if new air is to enter through the eyeball vents Note that an always open outflow vent below the pilots seat allows some air circulation even if the above mentioned outflow vent is closed ...

Page 86: ...nd the auxiliary power unit disconnected the electrical system switches may be turned on the and normal procedures resumed Landing Gear The shock struts are filled with dry compressed air and hydraulic fluid When the struts are properly inflated 3 inches of the piston will be exposed on the main strut and 3 1 2 inches of the piston will be visible on the nose strut The inflation check should be ma...

Page 87: ...n dome light 303 Compass light 327 Cowl flap position light 313 Flap position light TD638 313 Pilot sub panel lights Center Console light 1819 Glare shield instrument lights TD638 1864 Glare shield instrument lights TD711 1820 Ignition panel light 327 Post lights 327 Landing gear position lights 4553 4596 Landing light 356 327 Taxi light 4522 Nose gear position indicator light 303 O A T light 303 ...

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