RAZAIR
‐
A1
‐
METRO
‐
III
‐
AFM
‐
001
1
‐
25
ENGINE
TORQUE
MONITORING
SYSTEM
The
torque
‐
measuring
system
monitors
the
twisting
force
being
applied
to
the
propeller
through
the
reduction
gear.
The
signal
is
sent
to
the
torque
indicator
(Figure
34)
in
the
cockpit.
IGNITION
SYSTEM
The
ignition
system
is
a
high
‐
energy
type
consisted
of
an
engine
‐
mounted
ignition
exciter
and
two
igniter
plugs
located
in
the
combustion
chamber.
An
independent
ignition
system
is
provided
for
each
engine.
Ignition
operation
is
indicated
by
amber
lights
located
below
the
EGT
gauges
(Figure
40).
The
associated
light
is
on
whenever
power
is
applied
to
the
ignition
exciter.
Fig.
46
Ignition
System
Switches
Fig.
47
Ignition
System
Switches
Location.
The
ignition
system
is
controlled
by
two
switches
on
the
left
console
labeled
AUTO/CONT
IGNITION.
The
AUTO
position
(default
position)
allows
the
SRL
‐
Autostart
computer
to
control
ignition
during
start.
An
additional
feature
of
the
AUTO
position
is
that
it
energizes
the
ignition
if
the
negative
torque
sensing
(NTS)
system
is
activated.
Engine
failure
or
flameout
permits
the
propeller
to
drive
the
engine
(negative
torque),
causing
the
ignition
to
be
energized
as
long
as
the
negative
torque
continues,
and
up
to
30
seconds
after
the
negative
torque
ceases.
Ignition
operates
continuously
when
the
switch
is
in
the
CONTinuous
position.
The
OFF
position
permits
normal
engine
operation
but
lacks
the
NTS
feature.
The
OFF
position
is
not
normally
used.
WARNING
Do
not
test
the
temperature
limiter
in
flight.
Engine
flameout
will
result.
