SECTION 4
PERFORMANCE DATA
INTRODUCTION
The performance data presented herein is derived from the engine manufac-
turer’s specification power for the engine less installation losses. This data is
applicable to the basic helicopter without any optional equipment which would
appreciably affect lift, drag, or power available.
NOTE
Data shown at -30°C are provided to allow interpolation at -25°C.
POWER ASSURANCE CHECKS
The Power Assurance Check charts are provided in order to let the pilot
determine if the engines can produce the installed specification power.
A power assurance check should be performed daily. Additional checks should
be made if unusual operating conditions or indications arise.
The hover check is performed prior to takeoff and the in-flight check is
provided for periodic in-flight monitoring of engine performance.
Either power assurance check method may be selected at the discretion of the
pilot. It is pilot’s responsibility to accomplish the procedure safely, considering
passenger load, terrain being overflown and the qualification of persons on
board to assist in watching for other air traffic and to record power check data.
If either one of the two engines does not meet the requirements of the hover
or the in-flight check, the minimum performance requirements as per pub-
lished data may not be obtained.
The cause of engine power loss, or excessive TOT or GAS PRODUCER RPM
(N1) should be determined as soon as practical.
Refer to Engine Maintenance Manual.
RFM A109E
R.A.I. Approved 4-1/(4-2 blank)
Rev. 23
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