RRPM droop compensation based on thrust le-
Beep capability becomes active for load match to
Full contingency power capability.
Over temperature protection throughout opera-
Engine shutdown in response to ECL being
placed at STOP
Tracking of primary mode during normal primary
mode operation allowing a smooth switchover when se-
If in reversionary mode for any reason (training) and
there is a reversionary failure, the FADEC will not auto-
matically switch back to the primary mode. The pilot must
manually select PRI mode.
If both the primary and reversionary sys-
tem fail, the engine remains at the fuel flow
being used at the time of the failure. When
a failed fixed fuel flow condition exists, the
ECL and the beep trim switch for the af-
fected engine is inoperative, therefore
there is no proportional control through
ECL except under some conditions STOP.
Engine shutdown may be accomplished
by moving the ECL from its present posi-
tion to STOP. Under these conditions, the
ENG 1 (2) FAIL and/or FADEC 1 (2) cau-
tions are illuminated.
If FADEC and/or REV and ENG FAIL lights
are illuminated (which signifies a fuel flow
fixed condition), toggling the PRI/REV switch
reboots the microprocessor in the DECU. If it
is a spurious fault, the lights extinguish except
the REV light. If the hard fault is real, the REV
and ENG FAIL lights illuminate again but not
the FADEC light.
When taking off with one engine in reversionary mode
the procedure is, before lift-off, the engine still in PRI
mode is used to set the correct rotor speed via the
FADEC NR% switch. The operator then uses the beep
switch of the engine in reversionary mode to match en-
2-3-31. ENG COND Panel. 714A
When adjusting controls or switches on
the overhead switch panel, make sure
gloves or sleeves do not catch and inad-
vertently move the ENG COND levers.
The ENG COND panel is located in the overhead switch
panel (fig. 2-3-5).
NO.1 and NO. 2 ENG COND Levers. The ENG COND
Levers (ECL) provide the pilot with proportional accelera-
tion and deceleration authority. The ECLS are spring-
loaded outboard creating a gated motion when ad-
vanced from the STOP to GND and to FLT positions.
ENG COND lever friction is provided to reduce the possi-
bility of over-torque transmissions by resisting rapid
movement of the levers.
2-3-32. FADEC Panel. 714A
The FADEC panel is located on the overhead switch
panel (fig. 2-3-6). It comprises of the following:
NR % Switch. The NR% switch controls a rheo-
stat which allows the operator to select any RRPM be-
tween 97% and 103%. There are detents at 97%. 100%
and 103%. With the ECL(s) in FLT, NR will be maintained
at the selected speed. 100% is the normal position.
PRI/REV Switches. The primary mode is the nor-
mal mode of operation. The REV (reversionary) mode is
selected as a backup mode or is automatically selected
if the primary system has a hard fault failure. A hard fault
failure is defined as one in which normal primary system
performance might be jeopardized. Other failures are
classified as soft failures when the system is fault tolerant
and can continue fully operational with the fault signal
BU/PWR Switch. The Back-Up Power switch
when ON connects the aircraft battery relay and essen-
Figure 2-3-5. Engine Condition Panel 714A