Aircraft performance theory for pilots by Peter J. Swatton

By Peter J. Swatton

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Since the requirement is usually to convert indicated altitude to true altitude, the procedure to adopt is as follows: (1) Apply the calibration correction to the indicated altitude. (2) Enter the right or left hand vertical axis of Fig. 4 with the corrected altitude. (3) Extract true altitude. 26 Fig. 3 scale). Aircrafi Performance Theory Altimeter temperature correction (for take-off and landing with QFE set on sub- If it is required to convert obstacle height or safety height to an indicated altitude, the reverse of this procedure should be used.

4 Wind Aircraft manufacturers are only obliged to provide take-off and landing performance data for a range of wind speeds from 15 kts head component to 5 kts tail component. If these limitations were observed, they would unnecessarily penalize the operator; so most Flight Manuals are produced with a wind component range from 40 kts head to 10 kts tail. 105(d)(1) require that all headwinds be reduced by 50% and all tailwinds be increased by 50%. This factorization, made for the purposes of safety, may already be incorporated in the scheduled data of the wind grids in the various graphs by changing the slope of the grid-lines or by varying the scale of the grid so that the forecast wind can be used directly on the wind grid without alteration.

Given: pressure altitude = 40000ft: JSA deviation = +lO°C. 5"C. S"C. S"C. (d) -465°C. SECTION 2 - AERODROME SURFACES CHAPTER 5 Field-Lengths Available The International Standards and Recommended Practices Annex 14 written and published by ICAO is a guide for airfield operating authorities to use as a basis for the construction, layout and modernization of aerodromes. In the UK this has been incorporated by the CAA in CAP 168. The standards recommended to the operating authority are primarily concerned with the safety of flying operations, but all are genuinely aimed at not being unnecessarily restrictive or limiting to the aircraft operator.

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