Appendix 3-B - Rotorcraft Simulator Validation Tests


Test Tolerance Flt Condition Requirement Comments
      A B C D  
3. Control Response
(a) Longitudinal Pitch Rate - ±10% or ±2°/sec
Pitch Attitude Change - ±10% or ±1.5°
Hover
Augmentation On/Off
    x x Step control input. Off axis response must show correct trend for non-augmented cases.
(b) Lateral Roll Rate - ±10% or ±3°/sec
Roll Attitude Change - ±10% or ±3°
Hover
Augmentation On/Off
    x x Step control input. Off axis response must show correct trend for non-augmented cases.
(c) Directional Yaw Rate - ±10% or ±2°/sec
Heading Change - ±10% or ±2°
Hover
Augmentation On/Off
    x x Step control input. Off axis response must show correct trend for non-augmented cases.
(d) Vertical Normal Acceleration - ±0.1g Hover     x x Step control input. Off axis response must show correct trend for non-augmented cases.
C. Longitudinal Handling Qualities Two cruise airspeeds to include minimum power required speed.
1. Control Response Pitch Rate - ±10% or ±2°/sec
Pitch Attitude Change - ±10% or ±1.5°
Cruise
Augmentation On/Off
  x x x Step control input. Off axis response must show correct trend for non-augmented cases.
2. Static Stability Longitudinal Control Position - ±10% of change from trim or ±0.25 in (6.3 mm) or
Longitudinal Control Force - ±0.5lb (0.223 daN) or ±10%
Cruise or Climb
Autorotation
Augmentation On/Off
  x x x Minimum of two speeds on each side of the trim speed. May be a snapshot test.
3. Dynamic Stability
(a) Long Term Response ±10% of Calculated Period
±10% of Time to ½ or Double Amplitude or ±.02 of Damping Ratio
Cruise
Augmentation On/Off
  x x x Test should include three full cycles (6overshoots after input completed) or that sufficient to determine time to ½ or double amplitude, whichever is less. For non-periodic response the time history should be matched.
(b) Short Term Response ±1.5° Pitch or
±2°/sec Pitch Rate
±0.1g
Normal Acceleration Cruise or Climb
Augmentation On/Off
  x x x Two airspeeds.
4. Manoeuvring Stability Longitudinal Control Position - ±10% of change from trim or ±0.25 in (6.3 mm) or Longitudinal Control Force - ±0.5lb (0.223 daN) or ±10% Cruise or Climb
Augmentation On/Off
  x x x Force may be a cross plot for irreversible systems. Two airspeeds. May be a snapshot test. Approximately 30° and 45° bank attitude data should be presented.
5. Landing Gear Operating Time ±1 sec Take-off (retraction)
Approach (extension)
  x x x  
D. Lateral and Directional Handling Qualities Two airspeeds to include at or near the minimum power required speed.
1. Control Response
(a) Lateral Roll Rate - ±10% or ±3°/sec
Roll Attitude Change - ±10% or ±3°
Cruise
Augmentation On/Off
  x x x Step control input. Off axis response must show correct trend for non-augmented cases.
(b) Directional Yaw Rate - ±10% or ±2°/sec Yaw Attitude Change - ±10% or ±2° Cruise
Augmentation On/Off
  x x x Two airspeeds to include at or near the minimum wer required speed. Step control input. Off axis response must show correct trend for non-augmented cases.
2. Directional Static Stability Lateral Control Position - ±10% of change from trim or ±0.25 in (6.3 mm) or Lateral Control Force - ±0.5lb (0.223 daN) or 10%
Roll Attitude - ±5°
Directional Control Position - ±10% of change from trim or ±0.25in (6.3 mm) or Directional Control Force - ±1 lb (0.448daN) or 10% Longitudinal Control Position - ±10% of change from trim or ±0.25 in (6.3 mm)
Vertical Velocity - ±100fpm (0.50 m/sec) or 10%
Cruise or Climb/Descent
Augmentation On/Off
  x x x Steady heading sideslip. Minimum of two sideslip angles on either side of the trim point. Force may be a cross plot for irreversible control systems. May be a snapshot test.
3. Dynamic Lateral and Directional Stability
(a) Lateral-Directional Oscillations ±0.5 sec or ±10% of Period
±10% of Time to 1/2 or Double Amplitude or ±.02 of Damping Ratio ±20% or ±1 sec of Time Difference Between Peaks of Bank and Sideslip
Cruise or Climb
Augmentation On/Off
  x x x Two Airspeeds. Excite with cyclic or pedal doublet. Test should include six full cycles (12 overshoots after input completed) or that sufficient to determine time to ½ or double amplitude, whichever is less. For non-periodic response, time history should be matched.
(b) Spiral Stability Correct Trend, ±2° Bank or ±10% in 20sec Cruise or Climb
Augmentation On/Off
  x x x Time history of release from pedal only or cyclic only turns in both directions.
(c) Adverse/Proverse Yaw Correct Trend, ±2° transient sideslip angle Cruise or Climb
Augmentation On/Off
  x x x Time history of initial entry into cyclic only turns in both directions. Use moderate cyclic input rate.
3. MOTION SYSTEM**
A. Motion Envelope
1. Pitch   N/A          
(a) Displacement
±TBD° ±25°
      x x x  
(b) Velocity
±TBD°/sec ±20°/sec
      x x x  
(c) Acceleration ±TBD°/sec2 ±100°/sec2       x x x  
2. Roll
(a) Displacement
±TBD° ±25°
      x x x  
(b) Velocity
±TBD°/sec ±20°/sec
      x x x  
(c) Acceleration ±TBD°/sec2 ±100°/sec2       x x x  
3. Yaw N/A
(a) Displacement ±25°         x x  
(b) Velocity ±20°/sec         x x  
(c) Acceleration ±100°/sec2         x x  
4. Vertical
(a) Displacement ±TBD in ±34in       x x x  
(b) Velocity ±TBD in ±24 in/sec       x x x  
(c) Acceleration ±TBD g ±0.8g       x x x  
5. Lateral   N/A          
(a) Displacement ±45in         x x  
(b) Velocity ±28in/sec         x x  
(c) Acceleration ±0.6g         x x  
6. Longitudinal
(a) Displacement ±34in         x x  
(b) Velocity ±28in/sec         x x  
(c) Acceleration ±0.6g         x x  
7. Initial Rotational Acceleration Ratio, All Axes TBD°/sec
2/sec 300°/sec
2/sec
      x x x  
8. Initial Linear Acceleration Rate
(a) Vertical ±TBD g/sec ±6g/sec       x x x  
(b) Lateral ±3 g/sec         x x  
(c) Longitudinal ±3 g/sec         x x  
B. Frequency Response Amplitude N/A          
Band, Hz
0.1 to 0.50.51 to 1.01.1 to 2.02.1 to 5.0
Phase, deg
-15 to -20-15 to -20-20 to -40-40 to -100
Ratio, dB
±2
±2
±4
±4
    x x x  
C. Leg Balance 1.5°     x x x The phase shift between a datum jack and any other jack shall be measured using a heave (vertical) signal of 0.5Hz at ±0.25g
D. Turn Around 0.05g N/A   x x x The motion base shall be driven sinusoidally in heave through a displacement of 6in (150 mm) peak to peak at a frequency of 0.5Hz. Deviation from the desired sinusoidal acceleration shall be measured.
E. Motion Cue Repeatability       x x x See Section4 of this Appendix.
4. VISUAL SYSTEM

Note: Refer to Appendix3-C for additional visual tests.

A. Visual Ground Segment (VGS) ±20% of calculated VGS. Threshold lights must be visible if they are in the visual segment (see example under "Comments"). Static at 100ft (30.5 m) wheel height above touchdown zone on glideslope
RVR = 1200ft (350 m)
  x x x The QTG should indicate the source of data, i.e. ILS G/S antenna location, pilot eye reference point, cockpit cut-off angle, etc., used to make visual scene ground segment content calculations. Tolerance Example: If the calculated VGS for the rotorcraft is 840ft, the 20% tolerance of 168ft may be applied at the near or far end of the simulator VGS or may be split between both as long as the total of 168ft is not exceeded.
B. Visual System Colour Demonstration Model       x x  
C. Visual RVR Calibration Demonstration Model       x x  
D. Visual Display Focus and Intensity Demonstration Model       x x  
E. Visual Attitude vs. Simulator Attitude Indicator (Pitch and Roll of Horizon) Demonstration Model       x x  
F. Demonstrate 10 Levels of Occulting Through Each Channel of System Demonstration Model       x x  
5. SIMULATOR SYSTEMS
A. Visual, Motion and Cockpit Instrument Systems Response
1. Visual, Motion and Instrument System Response to an abrupt pilot controller input, compared to rotorcraft response for a similar input 100 milliseconds or less after rotorcraft response Climb, Cruise, Descent, Hover     x x One test is required in each axis (Pitch, Roll and Yaw) for each of the 4conditions (3 conditions, LevelB) compared to rotorcraft data for a similar input. (Total 12 tests) (Total 9tests, LevelB)
150 milliseconds or less after rotorcraft response Take-off, Climb, Descent   x    
OR              
2. Transport Delay 100 milliseconds or less after control movement Pitch, Roll, Yaw     x x One test is required in each axis (total 3 tests). See Appendix3-A, Section3, paragrapht.
150 milliseconds or less after control movement Pitch, Roll, Yaw   x    
B. Sound
1. Realistic amplitude and frequency of cockpit noises and sounds, including transmission, rotor and airframe sounds           x Test results must show a comparison of the amplitude and frequency content of the sounds that originate from the rotorcraft or rotorcraft systems. Sound data should be presented in one-third octave band or continuous frequency spectrum.
C. Diagnostic Testing
1. A means for quickly and effectively testing simulator programming and hardware. This could include an automated system which could be used for conducting at least a portion of the tests in the QTG         x x  
2. Self testing of simulator hardware and programming.           x  
3. Diagnostic analysis printout of simulator malfunctions sufficient to determine compliance with the SCIG           x  
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