Mooney M20K - Page 285

MOONC/ AIRCRAFT
CORPORATION
M20K SERVICE
AND
MAINTENANCE MANUAL
with
fuel flow
per
Section
71-00-60,
L
(2)
CAUTION
control
in
full
n’ch
position.
Cloclcwise
s
by
turning
knob.
adjustment
of
screw
decreases fuel
flow
reading;
one
full
tum
will
cause a
6.0
to
9.0 IbJhr.
change.
Record
NOTE
difference
in
reading
between
calibrated
fuel flow
gauge
Any
vemhr control which tends
to
creep
can
be
and aircraft
gauge
for Mure
reference,
tightened by
loosening housing
nut
in
back
of
panel
and
tightening
face
nut at
pilot
side
of
panel.
G.
RECHECK.
Recheck
as
follows:
(3) Adjust
controls
by adjusting
rod
end
on
the
(1)
Recheck
idle
settings
as
specified
in
A,
B and
forward end of
the control. If
additional
adjustment
is
C
above and
adjust
as
required.
required
the control
arm
may
be
repositioned
to
adjust
(2)
Recheck 100
percent
power
fuel
flow
as
the throttle
or
m’udure.
Additional
adjustment
may
be
specified
in
D
for
25-0001 thru 25-0999
and
E
for
obtained
on
the
prop
govemor
by removing
the
safety
25-1000&ON,
wire
thru the six
screws
on
the
govemor
head and
loosening
those
screws.
After
loosening
the
screws
(3)
Recheck
full
power
manifold
pressure
as
rotate
governor
head
to
obtain
required adjustment.
specified
in
E
for
25-1000
3
ON.
(4)
Tighten
all
screws
and
resafety.
H. GROUND
CRITICAL
ADJUSTMENTS
S/N 25-0001
thru
25-0999
J. PROPELLER RPM ADJUSTMENT. Run
engine
and.verify
that
propeller
govemor
will allow
engine
to
(1)
Set
altimeter
to
29.92 inches
and record
operate
at
2700 RPM.
Adjust
forward
stop
screw
on
pressure
altitude.
With
engine
operating
at
2300
RPM,
govemor
head
as
required
to
obtain
required
RPM.
m’udure control
FULL RICH
proceed
as
follows:
Recheck
control
for
required
cushion after
setting
RPM.
(2)
Reduce
engine speed
to
2000
RPM with
the
K FLIGHT CHECK
propejler
control.
S/N 25-0001
thru 25-0999
(3)
Set
throttle
FULL OPEN.
The
following
checks
shall be
performed
in
flight:
(4)
Using propeller
control,
increase
engine
(1)
Set altimeter
at
29.92
In.
Hg.
and record
speed
until
40
In.
Hg.
.2
manifold
pressure
pressure
altitude
on
data
table,
(Figure 713).
Remove
obtained.
Engine
speed
should
be within
ground
critical
calibrated
gauges
prior
to
check
flight.
Aircraft
is
not
limit band
(Figure
71-4).
If
engine
RPM is
outside
approved
for
flight
with these
gauges
installed.
these
limits
readjust
turbocharger
by-pass
valve.
(One
Reconnect the
hoses,
fRtings,
etc,
required
to
connect
tum
in
equalsappro~a’mately
100 RPM
reduction).
the
ships
gauges.
Utilize recorded delta for the
fuel
flow
Safety
wire before
flight. (9
threads
showing (fine thds~
gauges
dun’ng
this
flight
check.
is
starting point
if
no
reference is
known)
(2)
Wrth full rich
mixture,
throttle
at
40.0 In.
Hg.,
I.
CHECK
AND
ADJUST ENGINE
CONTROL
2700
RPM
and
96
2
knots IAS climb
until 40.0
In.
RIGGING
as
follows:
Hg.
manifold
pressure
can
no
longer
be
maintained,
this is termed
critical altitude. Record
pressure
altitude,
(1)
Operate
each control thru its
full
range
of
OAT
and
fuel flow
each
2000
feet until
critical altitude
is
travel
and check that it
operates
smoothly
and
contacts
reached. Fuel
flow
shall be 135
to
145
Ib.
per
hour
the
stops
at
each
end
oftravel.
(23.0
to
24.7
GPH) dun‘ng
the
entire climb
at
NASA
(2)
Check
each control
at
instrument
panel
for.06
Standard
Day
temperature.
to
.12 cushion
with the control
pushed
full forward.
71-00-50
OLDWILLWAYNE