Aircraft Operations. Volume II - Construction of Visual and Instrument ...

Appendix A to Chapter 4
TEMPERATURE CORRECTION
1.1 Requirement for temperature correction
The calculated minimum safe altitudes/heights must be adjusted when the ambient temperature on the surface is much
lower than that predicted by the standard atmosphere.
1.2 Tabulated corrections
For FAS angle calculation the cold temperature correction should be obtained from Tables III-3-4-App A-1 and III-3-4-
App A-2. These tables are calculated for a sea level aerodrome. They are therefore conservative when applied at higher
aerodromes (see paragraph 3).
1.3 Calculation of corrections
1.3.1 To calculate the corrections for specific aerodrome elevations, altimeter setting sources above sea level, or
for values not tabulated, use Equation 24 from Engineering Science Date Unit Publication, Performance Volume 2,
Item Number 77022 1 . This assumes an off-Standard atmosphere.
ΔhCORRECTION
= ΔhPAirplane – ΔhGAirplane =(–ΔTstd/Lo)ln[1+Lo ΔhPAirplane /(To + Lo.hPAerodrome)]
where: ΔhPAirplane = Aircraft height above aerodrome (pressure)
ΔhGAirplane = Aircraft height above aerodrome (geopotential)
ΔTstd = temperature deviation from the standard day (ISA) temperature
Lo = standard temperature lapse rate with pressure altitude in the first layer (sea level to
tropopause) of the ISA
To = standard temperature at sea level
Note.— Geopotential height includes a correction to account for the variation of g (average 9.8067 m sec 2 ) with
heights. However, the effect is negligible at the minimum altitudes considered for obstacle clearance: the difference
between geometric height and geopotential height increases from zero at mean sea level to –59 ft at 36 000 ft.
1.3.2 The above equation cannot be solved directly in terms of ΔhGAirplane, and an iterative solution is required.
This can be done with a simple computer or spreadsheet programme.
1. Reprinted by permission of ESDU International plc., 27 Corsham Street, London, N1 6UA, UK.
III-3-4-App A-1 23/11/06