Pt. 60, App. C

14 CFR Ch. I (1-1-19 Edition)

TABLE OF CONTENTS - Continued
Paragraph
No.

Title

9. ..............

Engineering Simulator - Validation Data.

10. ............

[Reserved]

11. ............

Validation Test Tolerances.

12. ............

Validation Data Roadmap.

13. ............

Acceptance Guidelines for Alternative Engines
Data.

14. ............

Acceptance Guidelines for Alternative Avionics
(Flight-Related Computers and Controllers).

15. ............

Transport Delay Testing.

16. ............

Continuing Qualification Evaluations - Validation
Test Data Presentation.

17. ............

Alternative Data Sources, Procedures, and Instrumentation: Level A and Level B Simulators Only.

1. INTRODUCTION
a. If relevant winds are present in the objective data, the wind vector (magnitude and
direction) should be clearly noted as part of
the data presentation, expressed in conventional terminology, and related to the runway being used for the test.
b. The NSPM will not evaluate any simulator unless the required SOC indicates that
the motion system is designed and manufactured to safely operate within the simulator-s maximum excursion, acceleration, and
velocity capabilities (see Motion System in
the following table).
c. Table C2A addresses helicopter simulators at Levels B, C, and D because there are
no Level A Helicopter simulators.
END INFORMATION
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BEGIN QPS REQUIREMENTS

kpayne on VMOFRWIN702 with $$_JOB

2. TEST REQUIREMENTS
a. The ground and flight tests required for
qualification are listed in Table of C2A, FFS
Objective Tests. Computer-generated simulator test results must be provided for each
test except where an alternative test is specifically authorized by the NSPM. If a flight
condition or operating condition is required
for the test but does not apply to the helicopter being simulated or to the qualification level sought, it may be disregarded (e.g.,
an engine out missed approach for a singleengine helicopter, or a hover test for a Level
B simulator). Each test result is compared
against the validation data described in
Section 60.13 and in this appendix. Although use of
a driver program designed to automatically
accomplish the tests is encouraged for all

simulators and required for Level C and
Level D simulators, each test must be able
to be accomplished manually while recording
all appropriate parameters. The results must
be produced on an appropriate recording device acceptable to the NSPM and must include simulator number, date, time, conditions, tolerances, and appropriate dependent
variables portrayed in comparison to the validation data. Time histories are required unless otherwise indicated in Table C2A. All results must be labeled using the tolerances
and units given.
b. Table C2A sets out the test results required, including the parameters, tolerances,
and flight conditions for simulator validation. Tolerances are provided for the listed
tests because mathematical modeling and
acquisition/development of reference data
are often inexact. All tolerances listed in the
following tables are applied to simulator performance. When two tolerance values are
given for a parameter, the less restrictive
value may be used unless otherwise indicated. In those cases where a tolerance is expressed only as a percentage, the tolerance
percentage applies to the maximum value of
that parameter within its normal operating
range as measured from the neutral or zero
position unless otherwise indicated.
c. Certain tests included in this attachment must be supported with an SOC. In
Table C2A, requirements for SOCs are indicated in the  - Test Details -  column.
d. When operational or engineering judgment is used in making assessments for
flight test data applications for simulator
validity, such judgment may not be limited
to a single parameter. For example, data
that exhibit rapid variations of the measured
parameters may require interpolations or a
 - best fit -  data selection. 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 simulator to helicopter data
throughout a time history, differences must
be justified by providing a comparison of
other related variables for the condition
being assessed.
e. The FFS may not be programmed so
that the mathematical modeling is correct
only at the validation test points. Unless
noted otherwise, simulator tests must represent helicopter performance and handling
qualities at operating weights and centers of
gravity (CG) typical of normal operation. If
a test is supported by helicopter data at one
extreme weight or CG, another test supported by helicopter data at mid-conditions
or as close as possible to the other extreme
must be included. Certain tests that are relevant only at one extreme CG or weight condition need not be repeated at the other extreme. Tests of handling qualities must include validation of augmentation devices.

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