Page 6-3
Pilot’s Operating Manual
P/N 140-590032-0007
Revision A4: Sep, 2010
Section IV Sub-section 6
SINGLE ENGINE
INTRODUCTION
This Sub-section contains one engine inoperative data.
SINGLE ENGINE CEILING
This Sub-section provides the following data:
A summary of single engine ceilings for a range of weights and temperatures, at:
• En-route climb speed.
• Minimum cruise speed.
• Long range cruise speed.
More comprehensive data is provided at minimum cruise speed:
• Maximum cruise altitude versus weight and temperature.
• Maximum cruise weight versus altitude and temperature.
These ceilings are based on average airplane performance and are intended only for estimating
altitudes for use in fuel planning. Since they do not contain any margin they must not be used for
checking obstacle clearance.
Where obstacle clearance after engine failure is relevant, it should be checked using the en-route net
gradient data in the Airplane Flight Manual. This will show a net ceiling lower than the en-route data
given in this Sub-section (SUMMARY OF SINGLE ENGINE CEILINGS).
Ceilings obtained from the AFM for an en-route net gradient of zero are shown in this Sub-section
(OBSTACLE CLEARANCE).
SINGLE ENGINE DRIFT DOWN
This Sub-section (SINGLE ENGINE DRIFT DOWN) contains tables of time, distance and fuel used from
engine failure to final sustainable altitude versus weight and altitude at engine failure. These tables
cover temperatures from ISA -15° C to ISA +20° C with antice off.
It is assumed that the drift down is conducted at maximum continuous thrust at the minimum cruise
speed for the weight at engine failure.