Performance
1. Normal Climb
TEST OBJECTIVE - Demonstration of normal climb performance.
INITIAL FLIGHT CONDITIONS
POWER - FULL THROTTLE or __________RPM_________MP
Flaps - UP
Trimmed for 72 or _______________KIAS climb.
TEST METHOD - Maintain Climb A/S 72 or _________________ KIAS
FTD DATA - VSI reads: ___________ FPM
TOLERANCE: +/- 3 KIAS and +/- 100 FPM
2. Stall Warning (actuation of stall warning device)
TEST OBJECTIVE - To determine that the FTD stall warning capabilities are adequate.
TEST METHOD - Case 1
Flaps - UP
POWER - PFLF@ 85 or ___________KIAS and trimmed for level flight.
Reduce power to idle.
Raise nose to decrease airspeed at a rate of approximately one knot/sec decelerating towards Vs.
FTD DATA - Stall warning: _____ KIAS
TOLERANCE +/- 3KIAS
Case 2
Flaps - LDG (Full)
POWER - PFLF @ 60 or __________ KIAS and trimmed for level flight
Raise nose to decrease airspeed at a rate of approximately one knot/sec decelerating towards Vso.
FTD DATA - Stall warning: _____ KIAS
TOLERANCE +/- 3KIAS
3. Engine Acceleration
TEST OBJECTIVE - Demonstrate engine acceleration response time.
INITIAL FLIGHT CONDITIONS
PRES ALT - On ground
POWER - Idle
Parking brake - ON
TEST METHOD - Slam power to MAX.
FTD DATA - Time required to indicate full power: _____ sec
TOLERANCE +/- 10% of time or 1 sec
4. Engine Deceleration
TEST OBJECTIVE - Demonstrate engine deceleration response time.
INITIAL FLIGHT CONDITIONS
PRES ALT - On Ground
Power - MAX T/O
Brakes - ON
TEST METHOD
Rapidly retard throttle to IDLE STOP.
Time engine response from MAX T/O power down through 1000 RPM (or as appropriate for your FTD).
FTD DATA
Time required to slow through 1000 RPM: ______ sec
TOLERANCE +/- 10% of time or 1 sec
Handling Qualities - Static Control Checks:
5. Column Position Versus Force
TEST OBJECTIVE - Demonstrate column position versus control force.
INITIAL CONDITIONS
On the ground, engine at IDLE, Parking Brake ON, trim centered, control column resting at neutral.
TOLERANCE
Breakout force +/- 2 lb.
Force to hold +/- 5 lb.
TEST METHOD - Case 1
Use the spring scale to measure the breakout force required to initiate aft column movement from neutral (use some appropriate method to attach the spring scale, suggest you may describe this in section 2, para 2.1.6 or in Annex 2).
Deflect column from neutral to full aft and measure the force with a spring scale (use some appropriate method to attach the spring scale, suggest you may describe this in section 2, para 2.1.6 or in Annex 2).
NOTE: For full column deflection, back off from stop (1/4 in. or less) to acquire free-floating reading.
FTD DATA
Breakout force: ________ lb.
Force to hold full aft: ________ lb.
Case 2
Measure the forward column break out and full deflection forces as above.
FTD DATA
Breakout force: ______ lb.
Force to hold full forward: ______ lb.
6. Control Wheel Position Versus Force
TEST OBJECTIVE - Demonstrate control wheel deflection versus control force.
INITIAL CONDITIONS
On the ground, engine at IDLE, Parking Brake ON, trim centered, control wheel resting at neutral.
TOLERANCE
Breakout force +/- 2 lb.
Force to hold +/- 3 lb.
TEST METHOD - Case 1
Use the spring scale to measure the breakout force required to initiate left control wheel movement from neutral (use some appropriate method to attach the spring scale, suggest you may describe this in section 2, para 2.1.6 or in Annex 2).
Deflect the control wheel from neutral to full left and measure force with the spring scale (use some appropriate method to attach the spring scale, suggest you may describe this in section 2, para 2.1.6 or in Annex 2).
NOTE: For full deflection, back off from stop (1/4 in. or less) to acquire a free-floating reading.
FTD DATA
Breakout force: ____ lb.
Force to hold full left aileron: ____ lb.
Case 2
Measure the right control wheel breakout and full deflection forces as above.
FTD DATA
Breakout force: ____ lb.
Force to hold full right aileron: ____ lb.
7. Rudder Pedal Position Versus Force
TEST OBJECTIVE - Demonstrate rudder pedal deflection versus control force
INITIAL CONDITIONS
On the ground, engine at IDLE, Parking Brake ON, trim centered, rudder pedals neutral.
TOLERANCE
Breakout force +/- 5 lb.
Force to hold full rudder deflection +/- 5 lb.
TEST METHOD - Case 1
Use the spring scale to measure the breakout force required to initiate left rudder (left pedal forward) movement from neutral (use some appropriate method to attach the spring scale, suggest you may describe this in section 2, para 2.1.6 or Annex 2).
Use the spring scale to measure the force to hold the left rudder left pedal deflected fully forward (use some appropriate method to attach the spring scale, suggest you may describe this in section 2, para 2.1.6 or in Annex 2).
NOTE: For full rudder pedal deflection, back off from stop (1/4 in. or less) to acquire a free floating reading.
FTD DATA
Breakout force: ____ lb.
Force to hold full left rudder pedal: ____ lb.
Case 2
Measure the right rudder pedal breakout and full deflection forces as above.
FTD DATA
Breakout force: ___ lb.
Force to hold full right rudder: ___ lb.
8. Longitudinal Power Change Force
TEST OBJECTIVE - Demonstrate longitudinal power change force.
INITIAL FLIGHT CONDITIONS
POWER - 2300 or _____RPM, and ____ MP.@ 100 or ____KIAS
Flaps - UP
Trimmed for level flight.
TEST METHOD
Reduce power to idle.
Maintain backpressure on control column to maintain 100 KIAS and measure force with the spring scale.
TOLERANCE: +/- 5 lb. or 20% of the force whichever is the lesser
FTD DATA
Back pressure on control column to maintain desired A/S: ____ lb.
9. Longitudinal Flap Change Force
TEST OBJECTIVE - Demonstrate longitudinal flap change force.
INITIAL FLIGHT CONDITIONS
Flaps - UP
TOLERANCE: +/- 5 lb. or +/- 20% of the force
TEST METHOD - Case 1
POWER - PFLF @ 100 or __________KIAS, trimmed for level flight
Select APPR flap; maintain level flight. Once the airspeed stabilizes, measure control column force.
FTD DATA
Pressure on control column to maintain level flight: ____ lb. FWD/AFT
Case 2
POWER - PFLF @ 60 or _______ KIAS, trimmed for level flight
Select LDG flap; maintain level flight. Once the airspeed stabilizes, measure control column pressure as above.
FTD DATA
Pressure on control column to maintain level flight: ____ lb. FWD/AFT
10. Flap Operating Time
TEST OBJECTIVE - Demonstrate flap operating times.
TOLERANCE +/- 3 sec or 10% of time
TEST METHOD - Case 1
POWER - PFLF @ 95 or ________ KIAS
Flap - Up, trimmed for level flight
Select APPR Flap and record the time for the flaps to cycle from UP to APPR.
FTD DATA - Length of time for flap to cycle to APPR: ____ sec
Case 2
POWER - reduce to PFLF @ 60 or ________KIAS with flap at APPR.
Maintain level flight.
Select LDG Flap and record the time for the flaps to cycle from APPR to LDG.
FTD DATA - Length of time for flap to cycle to LDG: ____ sec
Case 3
Select APPR Flap and record the time for the flaps to cycle from LDG to APPR.
FTD DATA - Length of time for flap to cycle up to APPR: ____ sec
Case 4
Select UP Flap and record the time for the flaps to cycle from APPR to UP.
FTD DATA - Length of time for flap to cycle to UP: ____ sec
NOTE: With the exception of the power and airspeed reduction when lowering flap, the test is meant to run from one step to the other. Airspeed is not critical other than in preventing a stall or an overspeed condition.
11. Longitudinal Trim
TEST OBJECTIVE - Measure pitch attitude and trim indicator position required to maintain level flight.
TOLERANCE +/- 1 deg Pitch angle, +/- ½ unit of trim
TEST METHOD - Case 1
POWER - PFLF @ 100 or ___________ KIAS
Flap - UP, trimmed for level flight
FTD DATA
The attitude indicator reads: ____ deg pitch
The trim indicator reads: ____ units
Case 2
Flap - Select APPR
POWER - PFLF @ 90 or __________ KIAS
Trim to maintain level flight.
FTD DATA
The attitude indicator reads: _____ deg pitch down
The trim indicator reads: _____ unit nose down trim
Case 3
Flap - Select LDG
POWER - PFLF @ 65 or ___________KIAS
Trim to maintain level flight.
FTD DATA
The attitude indicator reads: ____ deg pitch down
The trim indicator reads: ____ units
12. Longitudinal Static Stability
TEST OBJECTIVE - Determine the tendency of the aircraft to return to a trimmed condition.
INITIAL CONDITIONS
POWER - PFLF @ 90 or _________ KIAS
Flap - UP, trimmed for level flight
TOLERANCE +/- 5 lb. or 10% of control column force
TEST METHOD
NOTE: DO NOT RETRIM or CHANGE THE POWER SETTING.
Case 1
Apply backpressure on yoke to raise nose and stabilize the A/S at 70 or _______KIAS and measure the force with the spring scale.
FTD DATA - Control column pressure: _____ lb. aft
Case 2
NOTE: DO NOT RETRIM or CHANGE THE POWER SETTING.
Apply forward pressure on yoke to lower nose and stabilize A/S at 100 or _______KIAS and measure the force as above.
FTD DATA - Control column pressure: _____ lb. fwd
13. Longitudinal DynamicC Stability (Phugoid Dynamics)
TEST OBJECTIVE - Test longitudinal dynamic stability.
INITIAL FLIGHT CONDITIONS
POWER - PFLF @ 100 or __________ KIAS
Flap - UP, trimmed for level flight
TEST METHOD
Pitch nose UP to 10 degrees. Wait for VSI to stabilize.
Start timing and release controls. Allow the nose to pitch DOWN and then UP.
Record the time for the first two times the VSI stabilizes upwards.
Allow pitching to continue and record the total number of pitches until stabilized in level flight (or VSI change is less than + or - 50 FPM).
FTD DATA
Time for pitch cycles: (1) _____ sec, and (2) ______sec
Pitching totally dampened: _____th Oscillation
TOLERANCE 10% of period with representative damping
14. Roll Response (Rate)
TEST OBJECTIVE - Demonstrate lateral roll response at various airspeeds.
TOLERANCE +/- 10% or +/- 2deg/sec roll rate
TEST METHOD - Case 1
POWER - PFLF @ 100 or ___________ KIAS
Flap - UP, trimmed for level flight
Establish 30 deg left bank. Roll to 30 deg right bank with full aileron deflection.
Record the time from initiation of control wheel movement to 30 deg right bank.
NOTE 1: DO NOT ATTEMPT TO STOP ROLL AT 30 deg RIGHT BANK
NOTE 2: Roll rate = 60 ÷ time to roll from 30 deg on one side to 30 deg on the opposite side.
FTD DATA Roll rate: _____ deg/sec (rate per Case 1). Left to right.
FTD DATA Roll rate: ____ deg/sec (rate per Case 1). Right to left.
Case 2
POWER - PFLF @ 65 or ___________KIAS
Flap - LDG, trimmed for level flight
COMPLETE AS PER CASE 1
FTD DATA Roll rate: _____ deg/sec (rate per Case 1). Left to right.
FTD DATA Roll rate: _____ deg/sec (rate per Case 1). Right to left.
15. Spiral Stability
TEST OBJECTIVE - Demonstrate correct spiral stability representative of the type.
INITIAL FLIGHT CONDITIONS
POWER - PFLF @ 100 or __________ KIAS
Flap - UP, trimmed for level flight
TEST METHOD
Roll to 45 deg of bank to the left.
Pitch the nose DOWN to 10 deg.
Release the controls.
FTD DATA
Maximum Airspeed: ________________
Maximum Angle of Bank: ________________
TOLERANCE Correct trend
16. Rudder Response
TEST OBJECTIVE - To demonstrate roll response to a rudder input.
INITIAL FLIGHT CONDITIONS
POWER - PFLF @ 100 or ___________KIAS
Flap - UP, trimmed for level flight
TEST METHOD
Wings level.
Apply full left rudder.
Record the time to 10 deg of bank.
FTD DATA - Time to 10 deg of bank: ______ sec
TOLERANCE
Roll rate - +/- 2 deg/sec
Bank angle - +/- 3 deg
17. Steady State Sideslip or Constant Heading Cross-Controlled Bank Angle
TEST OBJECTIVE - To determine rudder/aileron effectiveness.
INITIAL FLIGHT CONDITIONS
POWER - PFLF @ 80 or __________ KIAS
Flap - APPR, trimmed for level flight
TEST METHOD
While maintaining a constant A/S;
(1) Apply full left rudder, and
(2) Apply sufficient right bank to stop the turn.
FTD DATA - Bank: ______ deg
TOLERANCE +/- 2 deg of bank
18. Transport Delay
Time from control input to recognizable system response (transport delay) must be 300 milliseconds or less. The standard must be certified by the manufacturer in the qualification guide submitted for qualification. Users will not be required to verify this standard when requesting approval of a FTD. Normally, Transport Canada inspectors will not be expected to measure or verify this maximum delay time as a part of the FTD approval process.
TEST OBJECTIVE - Demonstrate Transport Delay between control input and processor reaction.
TEST METHOD
The response time from control input to the instrument response shall be quick enough to simulate normal aircraft responses.
TOLERANCE 300 milliseconds or less