kpayne on VMOFRWIN702 with $$_JOB Pt. 60, App. A 14 CFR Ch. I (1-1-19 Edition) (3) This test is only required to be run once for the initial qualification of the FSTD and will not be required for continuing qualification purposes. The FAA will accept test results provided by the FSTD manufacturer as part of a Statement of Compliance confirming that the objective motion cueing tests were used to assist in the tuning of the FSTD-s motion cueing algorithms. e. Motion Vibrations. (1) Presentation of results. The characteristic motion vibrations may be used to verify that the flight simulator can reproduce the frequency content of the airplane when flown in specific conditions. The test results should be presented as a Power Spectral Density (PSD) plot with frequencies on the horizontal axis and amplitude on the vertical axis. The airplane data and flight simulator data should be presented in the same format with the same scaling. The algorithms used for generating the flight simulator data should be the same as those used for the airplane data. If they are not the same then the algorithms used for the flight simulator data should be proven to be sufficiently comparable. As a minimum, the results along the dominant axes should be presented and a rationale for not presenting the other axes should be provided. (2) Interpretation of results. The overall trend of the PSD plot should be considered while focusing on the dominant frequencies. Less emphasis should be placed on the differences at the high frequency and low amplitude portions of the PSD plot. During the analysis, certain structural components of the flight simulator have resonant frequencies that are filtered and may not appear in the PSD plot. If filtering is required, the notch filter bandwidth should be limited to 1 Hz to ensure that the buffet feel is not adversely affected. In addition, a rationale should be provided to explain that the characteristic motion vibration is not being adversely affected by the filtering. The amplitude should match airplane data as described below. However, if the PSD plot was altered for subjective reasons, a rationale should be provided to justify the change. If the plot is on a logarithmic scale, it may be difficult to interpret the amplitude of the buffet in terms of acceleration. For example, a 1 10Section3 g-rms2/Hz would describe a heavy buffet and may be seen in the deep stall regime. Alternatively, a 1 10Section6 g-rms2/Hz buffet is almost not perceivable; but may represent a flap buffet at low speed. The previous two examples differ in magnitude by 1000. On a PSD plot this represents three decades (one decade is a change in order of magnitude of 10; and two decades is a change in order of magnitude of 100). NOTE: In the example, - g-rms2 is the mathematical expression for - g-s root mean squared. - 7. SOUND SYSTEM a. General. The total sound environment in the airplane is very complex, and changes with atmospheric conditions, airplane configuration, airspeed, altitude, and power settings. Flight deck sounds are an important component of the flight deck operational environment and provide valuable information to the flight crew. These aural cues can either assist the crew (as an indication of an abnormal situation), or hinder the crew (as a distraction or nuisance). For effective training, the flight simulator should provide flight deck sounds that are perceptible to the pilot during normal and abnormal operations, and comparable to those of the airplane. The flight simulator operator should carefully evaluate background noises in the location where the device will be installed. To demonstrate compliance with the sound requirements, the objective or validation tests in this attachment were selected to provide a representative sample of normal static conditions typically experienced by a pilot. b. Alternate propulsion. For FFS with multiple propulsion configurations, any condition listed in Table A2A of this attachment should be presented for evaluation as part of the QTG if identified by the airplane manufacturer or other data supplier as significantly different due to a change in propulsion system (engine or propeller). c. Data and Data Collection System. (1) Information provided to the flight simulator manufacturer should be presented in the format suggested by the International Air Transport Association (IATA) - Flight Simulator Design and Performance Data Requirements, - as amended. This information should contain calibration and frequency response data. (2) The system used to perform the tests listed in Table A2A should comply with the following standards: (a) The specifications for octave, half octave, and third octave band filter sets may be found in American National Standards Institute (ANSI) S1.11-1986; (b) Measurement microphones should be type WS2 or better, as described in International Electrotechnical Commission (IEC) 1094-4-1995. (3) Headsets. If headsets are used during normal operation of the airplane they should also be used during the flight simulator evaluation. (4) Playback equipment. Playback equipment and recordings of the QTG conditions should be provided during initial evaluations. (5) Background noise. (a) Background noise is the noise in the flight simulator that is not associated with the airplane, but is caused by the flight simulator-s cooling and hydraulic systems and 110 VerDate Sep<11>2014 16:30 Jun 25, 2019 Jkt 247047 PO 00000 Frm 00120 Fmt 8010 Sfmt 8002 Q:\14\14V2.TXT PC31