~ FLIGHT TRAINING DEVICE VALIDATION TESTS (Cont'd) Appendix 2 AC 120-45A
2. TEST REQUIREMENTS. The ground and flight tests verify the correct flight condition. For example, required for qualification are listed in the Table to show that control force is within +5 1b of Validation Tests. Results of these tests should (2.224 daN) in a static stability test, data to show be available in a form which can be compared to the correct airspeed, power, thrust or torque, validation reference data. For those devices listed airplane configuration, altitude, and other in the following table requiring "generic" appropriate datum identification parameters should aerodyamic modeling, the FAA-approved data supplied also be given. If comparing short period dynamics, by the manufacturer or the operator sponsoring the normal acceleration may be used to establish a match device will be used as the comparison basis for objective testing.
Flight test data which exhibit rapid variations of the measured parameters may require engineering judgment when making assessments of flight training device validity. Such judgment must not be limited to a single parameter. All relevant parameters related to a given maneuver or flight condition must be provided to allow overall interpretation. When it is difficult or impossible to match data throughout a time history, differences must be justified by providing a comparison of other related variables for the condition being assessed.
to the airplane, but airspeed, altitude, control input, airplane configuration, and other appropriate data must also be given. All airspeed values should be clearly annotated as to indicated, calibrated, etc., and like values used for comparison.
a. Parameters, Tolerances, and Flight Conditions. The Table of Validation Tests in this appendix describes the parameters, tolerances, and flight conditions for training device validation.
If a flight condition or operating condition is shown which does not apply to the qualification level sought, it should be disregarded. Results 2/5/92 must be labeled using the tolerances and units given.
b. Plight Conditions Verification. When comparing the parameters listed to those of the airplane, sufficient data must also be provided to
7861 Tolerance TABLE DE VALIPATION TESTE Flight Condition Qualification Requirement Commente 2/5/92 LEVEL 6 Laval 7 devices will require distance
(1) Ground Acceleration 9 second of Ground/Takeoff measuroments also.
+1 Second Tolerances will be +5% tina and distance or +5% time and +200 foot (60 matars) of distance.
Accoleration time (and distanca for Laval 7) should be recorded for minimum of 80% of total at (brako release to ·z>.
(2) Minimum Unstick Spsed or equivalent as +3 Rte Airspoed +1.5 Pitch Ground/Takeoff You is defined as that speed at which the last provided by the sain landing gear leaves aircraft manufacturer the ground.
(3) Horzal Takeöff +1.5 +3 Rts Airspeed Pitch, 21.5° and First Segment Ground/Takeoff Angle of Attack CLIND +20 Feet (6 Meters) Altitude
(4) Critical Engine +3 Rts Airspoed Pitch Or 11.3° Ground/Takeoff Failure on Takeoff +1.5 and First Segment Angle of Attack +20 Feet (6 Meters) Altitude + 2 Bank and Sideslip Angle Appendix 2 AC 120-45A
TABLE OF VALIDATION TESTS (Cont'd) Appendix 2 AC 120-45A Jest Tolerance Flight Condition Qualification Requirement Commenta LEVEL
1. FERRORMANCE 6
(5) Crosewind fakooff 11.5 Bitch, 31 Pitch, $1.5° Ground/Takeoff and First Segment Angle of Attack +20 Feat (6 Matars) Altitude ÷2 Banx and Sideslip Angle
b. CLIMB
(2) Normal Climb +3 Kts Airspeed Clinb With all May be a snapshot tast.
All ingines Operating 158 OF 2100 FPH Engines Operating
(0.5 Hoters/Soc) Clish Rate
(2) One Engine Inoperative 13 Kte Airspeed Second Segment Second Segment Climb +58 or 1100 FPM Climb With One
(0.5 Hoters/50с) Engine Climb Rate but not Inoperativa Lass than the pi Approved fLight Marual Rate of Clinb
(3) One Engine Inoperative +3 Kts Airspeed Approach Climb Approach Climb for +5% or +100 FPH With One Engine Airplanes With Icing (0.5 heters/80c) Accountability par climb fate but not Approved Airplane lose than the FAA Flight Marial (AFH) Approved Flight Marmal Rate of Clino 2/5/92 ~
~ TAPLE OF VALIDATION TESTS (Cont'd) 2/5/92 Isat Tolerance Flight Condition Qualification Requirement Comments LEVEL
1. PERFORIANCE 5
c. In Plight
(1) Stall Warning, 12° Its Airspeed Seconi Segment Stall Speeds Bank Climb and Approach.
or Landing
(2) Stall Warning Second Segsent (actuation of stall Bank Climb and Approach earning device) or Landing
d. STOPPING Lavel 7 devices will require distance measuraments also.
(2) Stopping Time, Landing Tolerances will be +5% tima Wheel Brakes and the waaller of +10% of DIy Runway distanco or 200 feet (60 matars).
Time (and Distance for Leve]
7) should be recorded for at least 80% of total segment.
(Initiation of Rajected Take Off [RIO] to full stop).
(2) Stopping Time, {38 T1D0 OX Landing Loval 7 devices will require Rovares Thrust +1 Second distanco measurements also.
Dry Hurray Tolerances wil1 be +5% time and the smaller of +10% of distance or 200 feet (60
•etere).
Time (and Distance for Level
7) should be racorded for at least 80% of total sagrant.
(Initiation of RIO to full stop.) Appendix 2 AC 120-45A
TABLE DE VALIDATION TESTS (Cont'A) Appendix 2 AC 120-45A Test Tolerance Flight Condition Dualification Res Ca LEVEL
1. FERFORHANCE (STOPPING cont'd) 5 7
(3) Stopping Time and Representative Landing Tise and Distance should Distance, Stopping Time and be recordad for at least Wheel Brakes Only Distance 80% of total sagment.
Wat Runway (Initiation of RIO to full stop.) TAA approved AFH data ja accaptable.
(4) Stopping Time and Representative Landing Time and Distance should Distance, Stopping Time and be rocorded for at least Wheel Brakes Only Distance 80% of total sagent.
Icy Runway (Initiation of RIO to full stop.) FAA approved AFH date is accaptable.
e. ENGINES Tast from flight idle to go-around povar.
Tolerances of 11 second
(1) Accaleration +10% TiNo Approach or authorized for levels 2, 3, Landing and 5.
(2) Deceleration +10% Time Grourd/Takeoff fast from maxinum takeoff powsr to 10% of maximus takeoff power (90% decay in pover available above idle).
Tolerance of ti second sauthorized for Levels 2, 3, and 5.
2/5/02
Tost Tolerance TABLE OF VALIDATION TESTS (Cont'd) Flight Condition Qualification Requirement Comente 2/5/92 LEVEL
2. HANDLING OUALITIES
a. STATIC CONTROL CHECKS**
(1) Coluen Position vs. 12 1b (0.89 daN) Ground Uninterrupted control sweep.
Force and Surfaco Breakout Position Calibration 15 1b (2.224 dat) or +10% Porce ‡2 Elovator Column Position va. +2 16 (0.89 daM) Force Breakout $5 16 (2.224 dat) or +10% Force
(2) Wheel Position vs. +2 1b. (.89 daM) Ground & Uninterrupted control sueep.
Force and Burface Breakout Position Calibration +3 16 (1.334 daM) or +10% Force #1 Sposter Wheel Position ve. +2 1b (.89 daM) Force Breakout +3 1b. (2.336 da.)
OI +10% Force
(3) Pedal Position ve. +5 2b (2-224 dall) Ground Uninterrupted control sucep.
Force and Surface Bruakout Position Calibration +5 1b (2.224 daM) Rudder **Colum, wheel, and padal position vs. force shall be seasured at the control. An alternative method acceptable to the ASPH in lieu of the test fixture at the controls would be to instrumant the training device in an equivalent manner to the flight test airplane. The force and position data from this instrumentation can be directly recorded and satched to the airplane data. such a permanent installation could be used repeatedly without any time for installation of axternal davices.
Appendix 2 AC 120-45A
Appendix 2 Consente If appropriate to the airplane or set of airplanas being simulated. If appropriate to the airplane or set of airplanes being simulated Qualification Raguiresent LEVEL TABLE DE VALIDATION TEETE (COnt 'd) Flight Condition Ground Ground Ground Ground Tolerance 2. HANDLING QUALITIES (STATIC CONTROL CHECKS cont'&) +5 Ib (2.224 daN) Breakout (2.224 daN) +5 10 or +10% Force +2 1b. (.89 daM) Breakout (1.336 2AN) ·3 1b or $10% Force Angle $0.5' of Computed Trim Anglo +5" of Poster Lever Angle or Cross Shaft Angle or Equivalent Test Podal PoBition ve. Force (4) Nosewheel Steering Force Rudder Pedal Steering Calibration Pitch Trie Calibration Indicator va, Computed Alignment of Power Laver (or Cross Shaft Angle) ve. Belected Engine Paramotor (i.o., Manito ta Pressure, otc.)
(5) (6) (7)
~ TEEt Tolerance TABLE OF VALIDATION TESTE (Cont'd) Flight Condition Qualification Requirement Commente 2/5/92 LEVEL
2. HANDLING QUALITIES (STATIC SATROL CHECKE CONt'A) 1617
(8) Brake Pedal Ground Computer output results may Position ve. Forco be usad to show compliance.
Or 10% Levels 3 and 6 only need data points at zero and maximum braking application.
D. DYKAMIC CONTROL CHECKS**
(1) Pitch Control +10% Time for Bach Takooft, Cruise, I Data should be normal control Zero Crossing displacement in both +10% Amplitude of directions. Approximately 25% and and Subsequent to 50% of full throw.
Overshoots Greater Then 58 of Initial Refer to par. 3 of this Displacemant. Appendix 11 overahoot.
Refer to Paragraph 3 this Appendix.
(2) Roll Control Sam as (1) above. Takeoff, Cruise, Landing
(3) You Control Sara as (1) abova. Takeoff, Cruise, Landing **Colun, wheel, and pedal position vs. force or time shall be measured at the control. An alternative nethod acceptable to the NSPH in lieu of the test fixture at the controls would be to instrument the training device in an equivalent manner to the flight test airplane.
The force and position data from this instrumentation can be directly recordad and natched to the airplane data. Such a permanent installation could be used repeatedly without any time for installation of external devices.
Appendix 2 AC 120-45A
Appendix 2 Pover change dynazice will be accepted. rap change dynes de opte be Snapshots will be acceptable. Gear change dynamics wil1 be Son menta Snapehots will be accepted.
nt Qualification Requir LEVEL TABLE OF VALIDATION TESTS (Cont 'd) 1 2 Flight Condition Cruise or Approach Cruise or Approach Takeoff to Second +100 Feet (30 Meters) Seguent Climb, Approach to Landing Takeoff to Sacond Segment Climb, Approach to Landing Cruise and +100 Feet (30 Muters) Approach Takeoff to Second #100 Poet (30 Meters) Sagent to Be. Approach to Landing Takeoff to Second Segment Climb, Approach to Landing Tolerance +3 Rts Airspeed +100 Feet (30 Motars) Altitude +20% or t1.5° Pitch +S 1b or 120% +3 Xts Airspeed #let or 11.5° Pitch +5 lb or +20% +3 Kts Airspood Altitude +20% or +1.5° Pitch Altitudo +20% or t1.5" Pitch +5 1b 0r 1208 Test HANDLING QUALITIES c. LONGITUDINAL (1) Pover Change Dynemica Pover Change Force Flap Change Dynamics Flap Change Force Spoiler/Spendbrake Change Dynamics (4) Gear Change Dynarics Gear Change Force
(2) (3)
2.
Par 2
Appendix 2 Commente May be a snapshot. Levels 2, 3, and 5 may use equivalent stick and trie controllers in lieu of stabilizer and elevator. Hay be a series of snapshot Force or surface deflection must be in the correct direction. Hay be snapshot taste. Lovels 2, 3, and 5 must exhtbit positive static stability, but need not comply with the ramerical tolerance. Test should include 6 cycles or that sufficient to deteraine time to 1/2 amplitude, whichever is less.
tusts.
LEVEL TABLE OF VALIDATION TESTS (Cort 'd) Flight Condition Takeoff, Approach Cruise, Approach, Landing Cruise, Approach Landing Approach Cruise Cruise Tolerance HANDLING QUALITIES (LONGITUDINAL Cont'A) +3 Seconde or 10% of Time • І* Pitch Control (Stab and Elev) Pitch Angle +1 128 Hat Ihrust or equivalent in Стиіве +58 Net Thrust, or equivalant in Approach and Landing +5 1b (+2.224 dak) or +10% Column Force or Equivalent Surface Force or Equivalent Surface +10% of Period +10% of Timo to 1/2 or Double Amplitude or +.07 of Damping Ratio +10% of Period With Representative Damping Test Gear and Flap Operating Times Longitudinal Trie (7) Longitudinal Haneuver- ing Stability (Stick Force (a) Longitudinal Static Stability (9) Phugoid Dynamics
(5) (6) (8)
2.
Appendix 2 Commente Patte in the Are rection may be used Lavel 1 requires test in both directions.
Qualification Require LEVEL TABLE OF VALIDATION TESTS (Cont'd) Flight Condition Cruise Takeoff or Landing (whichever is most critical in airplano) Cruise and Landing or Approuch Approach or Landing Cruise cruise Cruise Tolerance HANDLING QUALITIRS (LATERAL DIRECTIONAL Cont'd) +1.5" Pitch or 2 /sec Pitch Rate ‡.10g Normal Acceleration (1) Hir ye control Speed, 43 Rts Airpeed +107 0I +2"/801 Roll Date +2° or t10% of Bank +10% or +2°/sec Ro1l Ratr Correct Trend Correct Trend 13° of Bank Angle or +10% in 30 восв. Correct Trend +2° of Bank Angle or +10% in 20 60cs.
Tost (10) Short Pariod Dynamics d. LATERAL DIRECTIONAL device's has Standard, of hom Speed Engine Inoperative Handling Characteristics in Air (2) Roll Response (Rate) Roll Overshoot or Respanse to Roll Controller Step Inaust (4) Spiral Stability
(3) Par 2
2/5/92 AC 120-45A Appendix 2 Consents May be snapshot test. Test may be deleted if ruddar input and response is shown in dutch roll test. Test ray be roll response to a given rudder deflection. For Level 7, additior 1 sec. requiremant of time difference between peaks of bank and sideslip. I May be a series of snapshot testa.
Qualification Requirement LEVEL TABLE OF VALIDATION TESTE (Cont'd) Elight Condition Second Seg Approach or Landing Approach or Landing Approach or Landing Cruise and Approach or Landing Cruise and Approach or Tolerance HANDLING COALITIES (LATERAL DIRECTIO cont 'd) +1 Rudder Angle Tab Angle or 11 or Equivalent Pedal Sideslip Angle 12 /sec Or +10% You Rate or Heading Change Roll Rate Bank Angle +10% of Pariod. +10% of Time to 1/2 or Double AmpLitude or 1.02 of Damping Ratio +10% of Period With Correct Trend and Number of Bank, Sideslip, Aileron, 110% or 45- pourer or Equivalent Wheel Position or Force Tast Engine Inoperative Trim Rudder Response Dutch mpet OFF (8) Steady State Sideslip or Heading Angle
(5) (6) 87)
2.
Par