Pilot's Operating Handbook

Registration: N540VF
Manufacturer: Frazier
Designation of Aircraft: F-1H
Serial Number: 4339  
Certification Category: Experimental

Vince Frazier
3965 Caborn Road
Mount Vernon, IN 47620
812-464-1839 work
812-985-7309 home 

Section 1.0 - Aircraft General Data

 1.1          Engine

              Manufacturer:                    LYCOMING

              Type:                                IO-540-C4B5                      

 1.2          Propeller

              Manufacturer:                    Hartzell

              Type:                                Constant Speed

              Diameter:                          80”

              Pitch Setting:                    Adjustable

 1.3          Fuel

              Grade:                              91/100 minimum grade aviation gasoline

              Capacity:                          STBD tank:             21 US gal useable

                                                      PORT tank:             21 US gal useable 

1.4          Oil

               Specification:                     LYCOMING OIL       SPECIFICATION No. 301-E

                Capacity:                                                     3 US gallons

               Ambient Air Temperatures            Viscosity Grades 

              Above 60° F                                        SAE 50*

              30 to 90° F                                           SAE 40*

              0 to 70° F                                             SAE 30*

              Below 10° F                                        SAE 20*

              * or suitable multigrade oil

Section 2.0 - Operating Limitations

VFR Operations only.

2.1          Airspeeds (I.A.S.)

Never Exceed                                                                              240 knots / 275 MPH  

Normal Operating Limit (Maximum Structural Cruising)        160 knots / 184 MPH

Maneuvering                                                                                125 knots / 144 MPH

Maximum, wing flaps extended                                                  95 knots/109 mph 

Vx                                                                                                74 knots/85 mph

Vy                                                                                                91 knots/105 mph*

* up to 121 knots/140 mph works very well and allows better engine cooling.     

 2.2          Maneuvers Permitted

 2.2.1       Normal Operations

Normal operations at up to maximum take off weight (as stated in section 2.5), are limited to normal flying maneuvers, but may include straight and steady stalls, and turns in which the angle of bank does not exceed 60 degrees.  Spins are permitted. 

2.2.2       Aerobatic Maneuvers

Aerobatic maneuvers are permitted within the following limitations:

              Aircraft weight not to exceed 2000 lbs.

               G limits are +6/-3

              Aft C of G limit not to exceed 97.4” aft of datum (where datum is 80” fwd of wing leading  edge)

 2.2.2.1    Approved maneuvers-recommended entry speeds

 Note: The application of these entry speeds presupposes that control pressures applied limit acceleration to +6 G's or less.  The maneuvering speed of 125 knots/144MPH is the maximum speed at which full and abrupt control movement is permitted.

              Maneuver                                                  Entry Speed Range (I.A.S.) 

              Inside loops & horizontal eights               121-165 kts/       139-190 MPH

              Chandelles, wingovers (Immelmans)       130-165 kts/       150-190 MPH

              Aileron rolls, barrel rolls                          105-165 kts/       121-190 MPH

              Vertical rolls                                             156-165 kts/       179-190 MPH

              Split-S turns                                              86-95   kts/        99-109 MPH

 2.2.2.2    Prohibited maneuvers

               Tail slides

 2.2.2.3    Maneuvers not recommended

              Snap rolls (allowable at entry speed less than 90 knots/ 104 MPH, but not recommended.)

Negative G maneuvers (not recommend due to possible engine oil starvation and possible prop overspeed.)

 2.3          Crosswind Component

 The maximum demonstrated crosswind component for take-off and landing is 15 knots/17 MPH.

 2.4          Power Plant

 2.4.1       Power and Temperature

 Power             RPM      Manifold Pressure         Cylinder Head Temp.               Oil Temp.

Max.                2700          Full Throttle               500 ° F absolute max                 245 ° F max
Take off                                                           450 ° F recommended max
260 bhp

Max.                2575         Full Throttle               500 ° F absolute max                 245 ° F max
Continuous                                                     450 ° F recommended max                
250 bhp

 2.4.2       Oil Pressure

               Normal                                60-100 lbs psi
               Minimum safe in flight        60 lbs psi
               Minimum safe idling           15 lbs psi

 2.4.3       Oil Temperature

              Recommended for take-off power                       160 ° F 
Warm oil prior to takeoff as much as practical without allowing CHTs to exceed 400 ° F.
Using the sump heater while preflighting is one way to warm the oil.

2.4.4       Fuel Pressure 

              Normal                                 28 lbs psi
              Minimum safe in flight         20 lbs psi
              Max                                      45 lbs psi 

2.5          Weight and Balance 

2.5.1       Weight 

Empty weight: 1226 pounds with 10 quarts oil

Maximum take-off weight (normal category)             2000 lbs

Maximum landing weight                                        2000 lbs

 2.5.2       Center of Gravity 

Normal Category Data 

Forward limit:                       87.7” Aft of Datum at all weights

Rear limit:                            97.4” Aft of Datum at all weights 

Observe the limits as are calculated on the Aircraft CG Calculations page 

2.5.3       Datum 

Datum:                                80” fwd of Wing Root Leading Edge 

2.5.4       Baggage Compartment Loading 

(i)            Maximum permissible aft baggage compartment load:             

              Fwd section: 80 lbs                   Rear section: 30 lbs 

(ii)     Where passenger seat is removed to permit the carriage of cargo, the permitted maximum load in the seat area shall not exceed 250 pounds plus the weight of the removed seat. The rear pilot control stick should be removed during any cargo carrying operations.

 2.7          Fuel Management 

Either tank may be used for take-off and landing.

SEE LAST PAGE FOR FUEL FLOW CHART EXAMPLE

Section 3.0 - Handling 

This section contains essential information relating to the handling characteristics and operation of the aircraft and its systems. 

3.1          Stalling Speeds (I.A.S.)

 Flap Setting                    Stalling Speeds - Power Off
                                  Gross weight                Gross weight
                                        2000 lbs                      1800 lbs
0 deg                                                                 67 MPH                    
20 deg (1st notch)                                              65 MPH                   
40 deg (2nd notch)                                             63 MPH                     

3.2          Stall Warning 

N540VF is not equipped with an audible stall warning system.   An angle of attack device known as a “Lift Reserve Indicator” is installed. 

3.3          Flaps 

              First notch                                20 deg
              Second notch                           40 deg 

3.4          Electrical Power 

Do not turn off the alternator in flight except in an emergency. 

This aircraft is fitted with a generating system that relies on battery power for initial excitation, therefore there is a possibility that if the alternator is turned off in flight, the loss of the battery system, or the subsequent discharge of the battery will result in the loss of all electrical power. 

3.5          Fuel System 

Prolonged uncoordinated flight with low fuel quantities may uncover the fuel tank outlets, causing fuel starvation and engine failure. 

Section 4.0 - Performance 

Take-off Safety Speed                67 MPH I.A.S. 0 deg. Flap
Minimum Approach Speed         85 MPH I.A.S. 20 deg. Flap      (1st notch)   OR
Minimum Approach Speed         80 MPH I.A.S. 40 deg. Flap      (2nd notch)
 

* 45%        + 55%           # 65%            = 75% 

 Checklists:

PREFLIGHT

1.  COCKPIT- CHECK SWITCHES AND FUEL OFF
2.  CONTROL SURFACES – CHECK  HINGES AND BOLTS
3.  TRIM TABS – SECURE
4.  WING TIE DOWNS - REMOVE
5.  COWLING - CHECK FASTENERS
6.  TIRES – 35 to 40 PSI
7.  STATIC PORTS, FUEL VENTS, PITOT TUBE, AND  LRI ORIFICES - CLEAR
8.  INSPECT PROP AND SPINNER
9.  FUEL SUMPS - CHECK FOR WATER OR DEBRIS
10.  FUEL CAPS - CHECK LEVEL- SECURE CAPS
11.  INSPECT TAIL WHEEL AND CHAINS
12.  ENGINE OIL - 9 MINIMUM

 

BEFORE ENGINE START

1.   FUEL SELECT - FULLEST TANK
2.   ALL SWITCHES  - OFF
3.   CIRCUIT BREAKERS - IN
4.   LOOSE ITEMS - STOWED
5.   SEAT BELTS – TIGHT
6.   CANOPY- CLOSED OR LATCHED IN TAXI POSITION
7.   FLAPS – UP
8.   TRIM - SET

ENGINE START

1.  MASTER - ON
2.  PROP CONTROL FORWARD
3.  THROTTLE / MIXTURE LEVERS - SET FOR START
4.  ENGINE - PRIME AS REQUIRED WITH BOOST PUMP - (5 SECS COLD)
5.   PROP ARC - CLEAR
6.  STARTER - ENGAGE
7.  IDLE AT 1000 RPM
8.  OIL PRESSURE SHOULD BE AT LEAST 20 PSI 

BEFORE TAXI

1.  ENGINE INSTRUMENTS - CHECK EIS
2.  AVIONICS MASTER - ON
3.  ALTIMETER - SET IN EFIS
4.  RADIOS AND LIGHTS - SET AS REQUIRED

ENGINE RUN UP

1.  CANOPY- CLOSED OR LATCHED IN TAXI POSITION
2.  ENGINE INSTRUMENTS - CHECK
3.  RPM - 1500
4.  PROP - CYCLE 2-3 TIMES
5.  CHECK MAGS,  SWITCH TACH SELECT INPUT AS REQ’D
6.  POWER - IDLE/ AS REQUIRED
7.  BOOST PUMP - ON

BEFORE TAKE OFF

1.  FLIGHT CONTROLS - FREE AND CORRECT
2.  ENGINE AND FLIGHT INSTRUMENTS - CHECK
3.  SET FLIGHT TIMER
4.  TRANSPONDER - ON
5.  FUEL SELECT - VERIFY ON FULLEST TANK
6.  WARNING LIGHTS – OFF
7.  CANOPY - CLOSED AND LOCKED!

TAKEOFF

1.  MIXTURE AND PROP CONTROL FULL FORWARD
2.  SMOOTHLY APPLY THROTTLE TO FULL POWER
3.  ROTATE AT 65
4. CLIMB AT  85 OR CRUISE CLIMB AS REQUIRED
5. MONITOR TEMPS DURING CLIMB

LEVEL OFF CHECK

1.  ENGINE POWER - AS REQUIRED
2.  MIXTURE - LEAN AS REQUIRED
3.  LIGHTS - AS REQUIRED
4.  BOOST PUMP - OFF

DESCENT/ APPROACH CHECK

1.  MIXTURE - RICHEN AS REQUIRED
2.  LIGHTS - AS REQUIRED
3.  RPM - INCREASE
4.  BOOST PUMP - ON

AFTER LANDING

1.  FLAPS – UP
2.  TRANSPONDER - STBY

SHUT DOWN

1.  TURN OFF BOOST PUMP, RADIOS, GPS,  LIGHTS AND STROBES
2.  MASTER OFF
3.  CLOSE MIXTURE
4.  CLOSE THROTTLE
5.  KEY SWITCH TO OFF
6.  FUEL VALVE OFF

EMERGENCY CHECKLISTS

ENGINE - ROUGH OR FAILURE – FIRST PRIORITY IS TO FLY THE PLANE!

1.  FUEL - SWITCH TANKS, CHECK EIS AND EFIS
2.  MIXTURE RICHEN
3.  BOOST PUMP ON
4.  RESTART -  AS REQUIRED
4.  POWER -  AS REQUIRED
5.  PROP CONTROL  - PULL BACK  FOR BEST GLIDE IF ENGINE  IS STILL TURNING
6.  IF ENGINE NOT TURNING, FORWARD UNTIL ENGINE RESTART

LOW VOLT/ ALTERNATOR FAILURE

1.  CHECK  VOLTAGE
2.  SWITCH TO EMERGENCY BUSS IF ALTERNATOR HAS FAILED

ELECTRICAL FIRE / SMOKE

1.  TURN OFF SMOKING ITEM OR SHUT OFF MASTER AS REQUIRED
2.  IF EFIS IS TURNED OFF, USE LRI FOR AIRSPEED REFERENCE. 
3.  LRI RED LINE IS FULL FLAP STALL.
4.  SWITCH TO EMERGENCY BUSS IF SITUATION PERMITS