Mooney M20K - Fuel Injection System Maintenance; Starter System Maintenance; Engine Mixture Control Rigging; Starter Trouble Shooting

SERVICE
AND
MAINTENANCE
MANUAL
M20K
MOONEY
AIRCRAFT
CORPORATION
K. FLIGHT
CHECK
Temperature
Mn‘ations
from
NASA
STD. DAY
S/N
25-0001 thru 25-0999
(conS~
TEMPERATURES
causes
approx
.7 IbsJhr. fuel
flow
(3)
If
a
discrepancy
in critical altitude
was
noted,
cha"ge
with
each
10
C.
Mriation,
minus if
hotter,
plus
if
adjust~the
exhaust
by-pass
valve.
CTuming
the
e~aust
Colder. The critical
attitude
will
vary
on
each
flight
by-pass
valve
screw
IN
one
full
tum
(CW)
will increase
depending
on
density
attitude
as
shown
on
Figure
71-4C
the critical altitude
approximately
1000
feet).
1500
ft. tolerance.
If
a
discrepancy
in
critical altitude
was
noted,
check
the
engine
indudion
system
for
leakage
CAUTION
or
blockage
or
turbocharger
for
malfunction,
until
problem
Adjustment
in
excess
of
one
turn
should
not
be
is
found.
indication
should be well
over
the
red line. DO
made, If
major adjustments
are
required
to
NOT MCEED 40.0 In.
Hg.
obtain
published
criticala~titudes,
troubleshoot
M. CLEAN UP
engine
as
to
exhaust
leaks,
turbo
and
engine
condition.
All
adjustments
are
interrelated,
After all
flight
checks
and
adjustments
are
complete,
engine
must
be
at
operating
temperatures,
and
condud
a
leak check of
all
connedions.
SM 250001
thru
adjustments
should be
rechecked
after
final
25-0999
safety
wire
the e~aust
by-pass
screw
and
set-up
to
detennine
all values
are as
specified.
check
nut to
the
by-pass
screw
housing.
Reconned
and
NOTE
secure
the
landing
light
wire
connedions
on
bottom
cowl
h induction
or
exhaust
system
leak
is
and
reconned
the
cowl
flap
rod ends.
suspected,
3
to
5
PSI
can
be
applied
to
either
system
and
check with
soap
solution.
’11-00-60 -FUEL INJECT(ON
SYSTEM
MAINTENANCE
Re-fly
aircraft
to
ven’fy
cn’tical
altitude
settings.
For
specific injection
system
inspection
and overhaul
Adjustments
of critical altitude
in
excess
of 500 feet
instructions,
consult
engine
manufacturer’s
overhaul
may
require
retn’mming
of fuel
flows
at
100%
power.
All
manual and
service instructions.
adjustments
to
fuel
flow
shall be
made
per
paragraph
71-00-50,
3,
A
thru
F.
3.).
71-00-70
STARTER SYSTEM
(4)
Wnh full
n’ch
m’ucture,
2700
RPM,
96
knots IAS
MAINTENANCE
airspeed,
and 1000
to
3000
feet
pressure
altitude,
Insped
and service
starter
per
TCM
Service
Instrudions.
check
the
operation
of
the
manifold
pressure
relief
valve.
Slowly
advance
the throttle
to
the wide
open
CAUTION
The manifold
pressure
should
stabilize
Do
not
operate
starter
in
excess
of
30
seconds;
g~;tfk0e";l
42.0 and
44.0 In.
Hg.,
there
should be
no
loss
allow
cooling
time before
re-engaging,
of
power,
and the fuel
flowindication
should be well
over
the
red
line.
DO NOT
U(CEED
40.0
in.
Hg
71 -00-80
ENGINE
MU(TURE
CONTROL
manifold
pressure
for
more
than
TEN SECONDS.
RIGGING
L.
FLIGHT
CHECK
1.
Disconnect
m’udure
control.
The
following
checks
shall be
performed
in
flight:
A. Remove
cotter
key.
S/N 25-1000 thru
25-TEA
B.
Remove
nut,
bolt,
and
two
washers
from clevis
(1)
Set altimeter
at
29.92 in.
Hg.
and
record
pressure
and
mi~dure
control
arm.
altitude
on
data table
(Figure
713).
Remove
calibrated
2. Reconnect
mi>dure
control.
gauges
pn’or
to
check
flight.
Aircraff is
not
approved
for
flight
with
these
gauges
installed.
Reconned
hoses,
A. Reverse
disconnect
procedure
to
reconned
fittlngs,
etc,
required
to
conned
the
ships
gauges.
Util’ne
mb<ture control.
recorded delta
for
the fuel
flow
gauges
dun’ng
this
fight.
3.
Adjustment
of
mixture
control
arm.
-S~N 25-1000
thru
25-2012
(-MB
ENGINE)
A. Loosen
locknut
on
control
rod
endand
adjust
27I?J~
Wnh
full
n’ch
mi~dure,
full
throttle
(36´•0
in.
Hg.),
control
arm
rod
as
required.
RPM
and
96
2 KIAS
climb
until
36.0 in.
Hg.
B.
Check for full
travel.
can
no
longer
be
maintained.
This is
termed critical
altitude.
Record
pressure
altitude
OAT and
fuel flow
C.
Check for
proper
thread
grip.
each
3000
ft. until
critical altitude
is
reached.
Fuel
flow
D.
Secure
locknut.
shall
be
125
to
135
Ibs./hr.
(21.5
to
23.2
GPH) dun’ng
the
entire climb
to
critical
altitude.
71-0090
STARTER
TROUBLE
SHOOTING
S/N 25-2013
thru
25-TEA
(-SB
ENGINE)
See
Section
24-39-04 for
procedure.
TCM
MAINTENANCE AND
OPERATORS
MANUAL should
26Sb
Wnh full
rich
mixture,
full
throttle
(39.0
in.
Hg~,
be
consulted.
RPM and
96
2 KIAS
climb
until
39.0
in.
Hg.
can
no
longer
be
maintained.
This
is
critical
altitude.
71-10-00
-ENGINE
COWUNG
Record
pressure
altitude
OAT and fuel
flow each 3000
ft.
until
critical altitude
is
reached.
Fuel
flow
shall be
The
engine
cowling
is
in
two
sections.
The
lower
cowl
151
to
157
Ibs./hr.
(25.5
to
26.5
GPH)
during
the entire
c0"tains the
Idnding
lights (250001
thru
25-0999)
and
climb
to
critical altitude,
cowl
flaps.
The
induction
inlet ducts
are
also located
on
the
lower cowl. The
top
cowl
contains the oil
filler
CAUTION
access
door.
Quick-disconnect,
1/4
tum
fasteners
Use
correct
fuel
flow
gauge
for
the
NIB
8 SE
attach
the induction duct
panels
to
the cowl and
the
engine (same
as
-LB
engine)
versus
-GB
engine,
upper
and lower
cowling
to
the
aircraff.
71-00-60
OLDWILLWAYNE