Mooney M20J Owner's manual
PILOT'S
OPERATiNG
HANDBOOK
AND
FM
APPROVED
AIRPUNE
FLIGHT
MANUAL
Advanced
Trainer
THIS HANDBOOKINCLUDESTHE MATERIAL REQUIREDTO
BE
FURNISHED
TO THE PILOT
BY
THE FEDERALAVIATION WEGUUTIONS, AND
CONSTITUTESTHE
FM
APPROVED AIRPLANE FLIGHT MANUAL.
THIS
DOCUMENT
MUST
BE
CARRIED
IN
THE
AIRCRAm
AT
A
--------
MOONEV
AlRCRAR
CGORPORATlON
B.O.
BOX
72,
KERRVILLE,
TEm8
980280072
SERIAL. NUMBER:_"
REGISTRATIONNUMBER:-
FAA
APPROVED:
Airplane Certification
Offieo
FEDERALA\llKf'ION ABMINISTWATlON
Fort
Worlti,
Texas
761
9351
50
FM
APPROVED
In
Normal
Cetegcay
based
on
CAR
PART
3;
applimble
to
Mdel
M2OJ
SIN
listed
above
only.
ISSUED
8
-
89
REV.
A
3-90
RM.
B
1-92
MANUALNUMBER
3210
MOBNEY
AT
INTRODUCTEON
MODEL
M28J
LTGG
EFFECT~VEE~]
L--"-L=-"
----
ORIGINAL
....................
8
-
8
9
REVISION
A
...................
3
-
90
REVISION
B
...................
1
-
92
Always destroy supersededpages when inseflir~g
revis4
pages.
TITLE
PAGE
...............
B
"K
page
...................
Original
i
lhru iv
..................
v
thru
vi
..................
.
B
Original
I-
1
.....................
Original
1-2
.
.....................
A
1-3
thru
l-fi
.....................
B
1-9
thru
1-10
..................
Original
3-4,
3-2
3-3
thru
3-8
1
3-9,
3-10
,
3-'11
...
3-12
Ghi'LI
3-'I
4.
4-1
...
4-2 ...
4-3,
4-4
.
.
4-5,
4-6
.
,
4-7
Ghru 4-12
4-i3
...
4-94
...
5-1,
5-2
.
.
53,
5-4
,
,
5-5
thru
5-1
8
5-49 thru
5-32
5-331Rru 5-36
6-3
thru
6-5
.
6-6
6-7
lhru
6-i
Original
.A
.B
.A
Original
PBHIAFM
NUMBER
3218
1
~~~1810~da
i.
*---
This POWIAFM
effective
beginning
with
M203,9/N
24-lW14
ISSUED
8
-
89
7-1thru 7-8
7-40
...
7-11thru 7-4
4
7-15
...
8-1thru 8-5
8-6
8-7 thru8-4'0
4
0-1thru 10-4
2
T
OF
EFFECTIVE
PAQ
MQONEY
MODEL
M20J
Original
.B
.A
Original
.A
.
B
Original
.A
Original
Original
.a
Original
Original
Original
This PQHlAFM
effective
beginningwLh
M20J
SIN 24-1686-1
4.
REV.
B
1
-
92
ISSUED
8
-
89
MOONEY
MODEL
M20J
MOBNEY
MODEL
M20J
iv
REV.
B
1
-
92
ISSUED
8
-
89
MOONEV
MODEL
M20J
'l'l~is
I
'ilot's Ol-,uraiingIle#~dbcro!cconlom~:;
E(j
(4/41\9A
Sl~ocilic;iatior~
No.
i
:artcl Illcludasboll1
~r>i:lr~t~facttl~i>rs
I
hatoi
ialanti
FA/\
f1I'I"I
1O\/tYl)rr~nleri;ll~.etluirc?ci
to
bo
funii::llotl tc)
the:
s,ilu(r
Ijy
the applicable FederalAviation Regulations. SECTION
IX
contains supplementald&ta sup
plied
b
Mooney Aircraft Corporation.
sEGT~~N
I
contains informationof general interesttothe pilot.
it
alsocontainsdsfinnionaof
the terminology used inthis OperatorsManual.
This Pilot'sOperatingHaridbookis
not
designedas
a
substitMeforadeq~aateandcompetent
flight instruction,kr~owledgeofcurrent aiwrrrtkinessdirectives,applicablefederalair regula-
tions or advisory circulars It is not interldedto
be
a
guide for basic Right instruction or a
trainingmanualandshouldnot be us& for operationalpurposes~rrslesskeptinanuptodate
status
All limitations, procedures,safety practices, sewicing and maintenarlcerequiu~mentspup-
lished in this POH/AFM are consider& mandatoryfor the Continued Aiwo~h~nessof
thls
airplaneina conditionequal tothat of itsoriginal manufacture.
Number
of
engines
EngineManufacturer
Model
~ecornrnendid
TC
Tylse
. .
Number of cylinders
Bisplacerner?t
.
Bore
.
.
Stroke
.
.
Compressionratio
....
4
.
~~~kON-&comin
.
.10-3m-~3~68
...
2000 Hours
...
.Reciprocating,aircooled,
fuel
injected.
..
.4,
Horizontally
.....
361
Cia.
In.
(591
5.7
cc
.......
.......
.........
8.711
Fuel System
..........
Type Fuel injedion Flow
Make
.......
.
.
Bendix, RSA-5-AD1
F5.A
..
Aviation Gasolit7e
...
$06
Octane or
lC10Ll.
(min. grade)
Accessories
.........
Magnetos Bendix
D4LN
2021
or
WLN3024
......
Spark
Plugs
18
MM
X
.75Q-20 Thd. Connection
.........
Alternator Prestolite 12V, 6QA
..........
Starter Prestoli're
42
Volts
Ratings:
Maximurn
Continuous Sea
Level-BWP/RPM
....
PROPELLER
~imberof Blades
...
Diameter
Max.
.
Min.
...
Type
..........
SECTION
I
GENERAL
MOONEY
MODEL M20J
Governing
.
I-lydraulicallycontrolled by engine oil
BladeAngles
@
30 in. Sta.(75 cm):
Low
...
13.9degrees
+I-
.2
degrees*
High
...
33.0 degrees
+/-
.5degrees*
FUEL
v
MinimumFuel Grade (Color)
.
100 Octane (Green)/100 LL (Blue)
Total Capacity
......
.
66.5 U.S. Gal.
(251.8 b/ters)(55.4Imn. Gal.)
,-
-
-~,\--
Usable
........
.64.0
u$.
~a(
(242.4 L/ters)(53.3Imp. Gal.)
......
Total Oil Capacity
.
8
Qts. 7.57 Liters
Oil Capcity Minimumfor Flight
...
5 (11s. 14.73 Liter$
Oil Filter
......
.Full Flow
Oil grades, specificationsand changingrecommendationsare contained in SECTION VIiI.
MNDING
GEAR
TYPE: Electricallyoperated,fully retractabletricyclegear withrubber shockdiscs. The main
wheels havehydraulically operated disc brakes.The nosewheel isfully steerable 14' left or
right of center.
Wheel Base
......
71 9/16 in.
(1
81.73 cm
I
Wheel Track
.......
110 in. (279.4 cm)
Tire Size:
Nose
..
5.00
x
5 (6 plyType Ill
Main
.
6.00
x
6 (6 pldType Ill
Tire Pressure:
Nose
........
49PSI
Main
.........
30PSI
Min. Turning Radius
(No brakesapplied)
....
.41
M.
(12.5 m)
MAXIMUM CERTIFICATEDWEIGHTS
........
Gross Weight 2740 Lbs. (1243 Kg
Bag age Area
......
120 Lbs. 54.4 Kg]
HatWack
...
10 ~bs.14.54 ~g
argo(Rear ~eats'~oidkDown)
.
340Lbs. (154.2 Kg!
STANDARD AlRPURlE
WEIGHTS
&sic EmptyWeight
......
See Page 1-10
.....
UMLmd Varies with installedequipment
See S~fllOkIVI for specific airplaneweight.
1-4
REV.
8
1
-
92 ISSUED 8
-
89
MOONEY
AT
SECTION
1
MODEL
M28J
GENERAL
CABllN
AND
ENTRY
DIMENSIONS
Cabin Width Maximum)
...
43.5
In.
(410.5
ci~s
Cabin Length [Maimurn)
.
Cabin Hei
ht
Maximum)
...
Entry~id8binimum)
..
Entry Weight (Minimum)
.
BAGGAGE
SPACE
AND
ENTRY
DIMENSIONS
.
Compaf?meneWidth
..
Compafiment Length
.
Con?par%men%Height
....
Cam artment Volume
24-16%-14
.....
17.0cu.M.
,481
cum
SIN
24-1687-44
Zhru
24-2'%9
,
.
.
15.3
CU.
R.
1.933
cu mi
Cargo Area
(with
rear seats fold&
down)
...
33.0
CU.
~t.%.
j.924
cubic meters)
Entry Height (Minitrscim)
...
Entry Width
...
Groundto Bottom
csii
Sill
....
46.0
In.
(116.8
cm
Wing Loading
@
Mwimum Gross Weight
...
15.68
Lbs.lSq.
R.
(79.03
Kg/Sq.
rn)
Power Loading
@
Maxim~dmGross Weight
Ail correspundonceregalditlg your airplar:e should i!:clude tho
Serial
Niimbei
as
depicted
oil
the
identification
plate.The identificationpiateislocated
on
the [eft
!l~atfd
sir:le,
aft
et~i
08
tile Tail cone, belowthe horizorltalstabilizerloadirlgedge.
'The aircraft Serial Nurnberandtype cel-sificareare si-rown.
G
S
GROUND
SPEED
-
Speed
of
aur
airplane relative
lo
the
ground.
1
KCAS
KNOTS
CALIBRATED
AIRSPEED
..
The indicated
speed
d
an
aircraft, correcte,dfor position and instrumenterror.
Calibratedairspeed
is
equal tofr~ie
airspeed
in
standard
atmosphere
81
Sea
!BV@/.
KIA$
KNOTS
iNDiCKrED
AIRSPEED
-
Thc
speed
of
PXTI
aircraft as
show;?
on its aifspsed indicator.
lAS
vailies publisk~&
iin
this haitdbosk
assume
zero
irsstrumenlerror.
KTAS
KNOTS
TRUE MRSPEED
-
The airsped
d
an
airplanerelative
to
~~ridisturbd
air
irawirich
is the
KCAS
corrected for aitut~asdeand
temperature.
Va
MANEUVERING
SPEED
-
Ttse
n~aimumspeed at which
appiwtion
of
full available aoumynamic contrd
will
r~o%
a?\~e~s$r'@ss
ti-ie
alrflane.
Yf,
Ril,UiMklM
FLAP
EKrENDFD
SPEED
-The
highegt
SIJ&
imfn7hs8Me
with
wing
flaps
in
a aarescrrbed
ex%ef\ded
psWbf2.
MMIMUMLANDING GEAR EXTENDED SPEED
-
The maximum
speed at which an aircraft can be safely flown with the landing gear
extended.
MAXIMUM LANDING GEAR OPERATING SPEED -The maximum
speed at which the landinggear can be safely extendedor retracted
<
-
NEVER
EXCEED SPEED
-
The speed limit that may not be
exceded at any time.
MNIMUMSTRUCTURAL CRUISING SPEED -The speed that
should not be exceeded, except in smooth air, and then only with
caution.
STALLING SPEED -The minimum steady flight speed at which the
airplane is controllable.
STALLING SPEED
-
The minimum steady flight speed at which the
airplane is controllable in the landing configuration.
BEST ANGLE-OF-CLIMB SPEED
-
The airspeedwhich delivers the
greatest gain of altitude inthe shortest possible horizontaldistance.
BEST RATE-OF-CLIMBSPEED -The?airspeed which delivers the
ireatest gain in altitiide in the shortest possible time with gear and
aps up.
BHP
BRAKE
HORSEPOWER
-The power developed by the engine
CHT CYLINDER
HEAD
TEMPERATURE
-
Operating temperature of
engine cylincler(s) being monitoredby a sensor unit. Expressed inO~.
EGT EXHAUST GAS TEMPERATURE
-
Temperature of the exhaust gas
fuellair mixture during engine operation.
MCP MMIMUMCONTINUOUS POWER
-
The maximum powerfor
talteoff, norma1,abnormalor emergency operations.
MP MANIFOLDPRESSURE
-
Pressure measured in the engine's
inductionsystem and is expressed in inches of mercury (Wg).
WPM REVOLUTIONS PEW MINUTE
-
Engine speed.
Demon- The velocity of the crosswindcomponent for which adequate
strated control of the airplane during takeoff and landing test was
Crosswind actuallydemonstratedduring certification.The value shown Velocity
is
NOT
consideredto be limiting.
%
"
Acceleration due to gravity.
Service The maximumaltitudeat which aircraft at gross weight has the
Ceiling capabilityof climbing at the rate of
100
ftlmin.
ENGlaalf
CONTROLS
&
INSTRUMERn
9
TERMINOLOGY
-----
-.
-
.-
Propeller The control used to select engine speed.
Control
Throltle The control used to select engine power by controlling MP.
Control
REV.
B
1
-
92
ISSUED
8
-
89
ENGINE
CONTROLS
&
INSTRUMENTS
TERMINOLOGY
(eon?.)
-
---------. .
-
---
Mixture Provides
a
mechanicallinkageto the fuel Injector rnisdure
Control control to control the size of the fuel
feed
aperture, and
therefore the airlfuel mixture. It
is
the primary method
to
shut
engine down.
CHT
Cylinder
head
temperature indicator us& to determine'that
Gauge engine opsrstlngtemperature is within manufacturers
specifications.
EGT
Exhaust gas temperature indicator used
to
identifycorrect lean
Gauge fuel Row mixturesfor various power settings.
Tachomefer
AII
instrurv~entthat indicates rotationalspeed of the engine.
The spedis si.iownas propeller revolutions per I-ninuts
(RPM),
Propeller The device that regulates tlie
RPM
of the snginelpropeilerby
Governor increasir~gor decreasingthe propeller pitch,ehrouyl~a pitch
change mechanismin the propellerhub.
METEORQLQGIGAL
TERMINOLOGY
Density
Altitude
Pressure
Aititude
Station
Pressure
Above groussd level
Altitude as determind by pressure altitude anel existiorg ambient
ternmerature. Instardard almos~here(ISA) densitv and mressure
altitude are e
ual
For a ejiven bressure aliilude, the higherthe
temperalure.%lahigher the density altitude.
The altitude actually read from an aitirneter when, and
o~?iy
wl~en,the barometric s~rbscalehas
bsc?r~
set to Statiorr Prk?sslare.
INTERNATIONALSIANBARUATMPSPHERE assurnes that
(1)
The air is a dry perfect gas;
(2)
Tho tempesature at
sea
level is
$5
'
CelsI1.1~(59'
F);
(3)
The pressure
at
sea level is
29.92
inches Hg (19'13.2mb);
(4)
The;.te?mperal~aregradient frosl~s~a,level
to the altit~adeat which the temperatk~reis
-56.5'
C
(69.7
F)
IS
..1).00198~
@
(4.0035~~
F)
per foot.
CIUTSIDE
AIR TEBIIPEBATUFSE
-
T11e free air static tei?tperata"ure,
obtain& either from inflighttemperature iygicatiuns or grorirld
ruieteorologicai sources. It is exyresstx!
iiri
C.
I
The altitude indicatd when KajllsmanVJi;dow
is
s~t
to
29.92
in. klg. or
10-13.2
MW.
Inthis !lardbook,
altirnoter
instriirncnt
errors are
assurnecl
to
be
zc?ro.
Actual atmospheric pressure at field elevatioil
Arrur
The
brorizontal distancekomtire refwenco
datum
to
tiw @Blit~?P
of
gravity
(C.G.)
(3f
an item.
Basic
-D
The actrial
weight
of
tlw
airplat?@
and ir.tclirdes
all
opr?ratiilg
i-r.mpty
equipment (including optional equipmeilt)
ellat
has
a fixed
\iYc?igI~t iocaTic3n and
is
actually installed
in
the
aircraft.
;It
inc3:ides
.Else
weight
d
unusak~k
l~iei
auicflfiili
oii.
SECTION
!
GENERAL
MOONEY
MODEL
M20J
Center
of
Gravity
(C.G.)
C.G. Arm
C.G. in
%
MAC
C.G.
Limits
MAC
Maximum
Weight
Moment
Reference
Datum
Station
Tare
Usable
Fuel
Useful
Load
The pointat which an airplanewould balance
if
suspended.
Itsdistance from the refere~scedatum isfound by dividingthe
tdal rnomerit by the total weight of the airplane.
The arm obtainad by adding the airpiane's individualmoments
end dividingthe sum by thetotal weight.
Center of Gravity expressed in percent
d
mean aerodynamic
chord.
The extreme center of gravity iocationswithin which the airplane
mudbe operated at a given weight.
MeanAerdynamic Chord.
The maximum authorizedweight
of
the aircraft and its
contents as iid~dinthe aircrafi specifications.
product
d
the weight
d
an item multiplied by its arm. (Moment
divided by
a
constant is used to simplify balance calculations by
reducingthe number of digits.)
An imaginary vertical plane from which all horizorrtal
distancesare measurdfor balancepurposes.
A
locatiorlalon the airplane fuselage usually giver1 in terms of
distance from tkreferencedatum.
The weight sf
chocks,
blocks, starrds,
etc.
used when wsighing
an
airplar~e,and is included
in
the scale readin. s. Taro is
deducted
from
the
scaie
readingto obtain
tho
aciuai
:,el)
ailplaneweight.
Fuel remaining after
a
runout
nest
has bzen
completed in
accordance with governmental regula.tions.
Fuel avaiiable
for
airplane propulsion.
The basic empty weight subtractedfrom the rnaxirnurnweight of
the air@aM.This
load
consists
of
the pilot, crew
if
applicable, fuel,
passengers, and baggage.
REV.
B
1
-
92
MOONEY
MODEL. M20J SECTION
I1
i-IMITATIONS
Number of Engines
.......
1
EngineManufacturer
.....
T~~Tk~N~~corning
Engine Model Number
.
.lo-360-A356D
En ine Operating Limits for Talteoff
an$ Cont~nuo~tsOperations:
Maximum Power . ,200 BHP
MaximumEngineSpeed
,
.
.
,
.
.
2700 RPM
Transient Engine RPM Limit
..,.
2970 RPM
for 3 seconds or less
......
Max. cylinder nead iemperalure . .473OF
(246
C)
...........
~aximum'~ilTemperat~~re
.....
. 245O
F
..........
. . (1
18'
C)
Oil Pressure
Normal Operating
........
60-90-PSI
Minimum (IDLE ONLY)
.......
25 PSI
Maximum (cold oil)
......
100 PSI
Fuel Press~ire
Minimum
.
,
.
,
.
.
,
,
. . 14 PSI
Maximum
........
30 PSI
Fuel Grade (Color)
...
100113b (Green)
100LL. (Blue)
..........
Number of Propellers
......
..
.I
Propeller Manufacturer . . .
.
McCauley
Propeller Model Number
.
.
,
.
.
82~34~2i4/90~H~-l6~
Propeller Diameter:
Min.
....
73.0 In. (185.4 cm)
Max. (No cirtoff allowed)
...
74.0 In. (187.9cm)
Propeller Blade Angles
@
30 111.sta.:
Low
.........
13.9O -&-I-.2O
High
........
33.0~
+I-
.so
Propeller~~er~tingiin~its
.
,
.
,
. . 2700 RPM
100LLfuel is calibrated at 5.02 lb/ga1.(.69Kylliter)
1001130 octane fuel is calibrated at 6.0 lblya1.(.72Kglliter)
I
NOTE
I
No
cutoff allowed on propeller
when
de-ice boots are installed.
F/W
APPROVED
ISSUED 0
-
89 AIRPLANE i'LIGI-II
I\JIANUAl,
2-5
SECTION
ll
LIMITATIONS
MOONEY
MODEL
M%OJ
--
INSTRUMENT REDLINE GREEN ARC YELLOW REDLINE
(MINIMUM (NORMAL
ARC
(CAUTION
g4'-
1-!Mi9
OPERATING) RANGE) LlMIp
Tachometer
Cylinder Head
Temperature
OilTemperature
Oil Pressure 25 PSI
60
-
90
PSI (IDLE
ONLY)
100
PSI
25
-
60
PSI
*
Fuel Pressure Radial 14-30PSI
Red
Line
Min. 14 PSI
30 PSI
-
-
-
1
NOTE
1
---
Refer
ts
TEmRON-Lycoming Engine Maintenance and Qpewtore Manuel
Section on Engine Speciflmtions and Operating LimRs lor recommendd
cruise power and ternpenthare limbtions.
---
(
NOTE
I
---
A
reduced fuel quantity indicator is install& ineach tank. The LaoHom
ti
of
these indicators shows the
25
U.S. gallon
(94.7
I&%)
(20.8
IMP. ~a1.y
umblefuel level
in
each
&nk.
---
1
NOTE
1
-
-
-
An optional visual fuel quantBy gauge may be inHall& on asp of each
tank end
is
to
be used
as
a reference for refueling
Banks
only.
)
Standard Tanks: (2)
.
33.25 U.S. Gal. each
(126 Liters)(27.7 Imp. Gal.)
Total Fuel:
........
.
66.5 U.S. Gal
(252 bers)(55.4 Imp. Gal.)
Usable Fuel:
........
.
64.0
U.S. Gal
(247 iiters)(53.3 Im Gal
Unusable Fuel:
.......
2.5
U?i.
Gi)
(9.5 Liiers)(i.l Imp.Gal.)
Fuel Grade (and Color):
100 Octane
....
minimumgrade aviation
fuel
(green).
1OOLL
...
.
(low lead) aviation fuel (blue) with
a
Imd
..
content limitedto 2 cc per gallon is also appro\/&.
AIRPLANE FLIGHT
MANUAL
REV,
B
1
-
92
2
-6
MmNW
MODEL
MaJ
SECTION
II
LIMITATIONS
To
rsdiuce the possibilityof ice formation within the eireraft or engine fuel
system
M
Is
ermismbleto add
ISGPROPYL
alcohol to the fuel supply in
qualities
N~TTO
EXCEED
1%
of the
foUll
luel volume per
tank.
DO
NOT
add other additives tothe fuel system due to potential deteriorating effects
within the luel aystem.FUEL
LIMITATBONS
Maximum Weight (takeoff and landing)
.
.
.
.
2740 ib.(I243 Kg.)
MaximumWeight in Baggage Compfiment
.
.
.
4201b.
(54.4 kg.)
@
Fuse. Sta. 95.5
MaximumWeight in Hatrack
.
.
10 Ib.
(4.54
~~.j
@
&use. Sta. 119.0
MaximumWeight inCar o Area
(Rear seats folded downy
....
.
340 ibs.
(li4.2 kg) @'Fuse. Sta. 70.7
Most Foward
.
.
Fuse. Sta. 41.0 IN.(903 cm)
@
2250 kBS(1120
M
)
13.4%
MI48
Intermediate&sward
.
Fuse. Sta. 41.8 lN.(106 cm)
@
2470
LBS.(1120
M
)
14.7%
WIA~
ForwardGross
.
.
.
Fuse. Sta. 45.0 iN.(143 cm)
@
2740(1243 K
)
20.1
%
MAE
Aft
Gross
.
.
.
Fuse. %a. 50.1 lN.(126 cm)
@
2740 lb.(4243
K
)
38.7%
MA(!'
MAC
(at Wing Sta.
94.m)
(238 cm)
. .
.
.
.
59.1
8
IM.(I50 cm)
I
Datum (stationzero) is
ti
inches(42.5 cm) aft of the center line
of
the nosegear attaching
bolts,and
33
inches((34cm) fotwardof thewing leadingedgeatwing station59.25(150cm).
This airplane must be operated as a Normal Category airplane.
Acrobatic
maneuvers,
includingspins, are prohibited.
lllllllllllllllllll
//WARNING//
1111111/1/////////
Takeofl maneuvers, pr01ongd sideslips or steep descents when the
s@led&
fuel
tank
conDiwe less than
8
gallons
(m.0
Ibs.,
30.3
Biters,
6.8
lMP*
Gal.)
of
fuel
&we
nd
been
demsnswatd
and
may
cause
loss
d
power.
FM
APPROVED
fSSLJEB
8
-
89
REV,
B
Y
-
92
AIRPIANE
FliGMT
MANUAL.
2-7
SEC;TION II
LIMITATIONS
MOON&\/
MODEL
M20J
---
I
MOTE
I
-
-
-
Up
to
290
foot altitude
loss may
occur
during
stalls
at
mexlm~m
weight.
Slowthrottle movement requiredat airspeedabove
165
KIAS.Above
465
KiAS, rapidthrottle
movementmay result momentary propeller WPM overspeed.
-@
-
-"
..--.w-p.*-
FLIGHT
LOAD
FACTOR
LII~
-..----,--"-----,,..--
---"
Maximum Positive Load Factor
Flaps
Up
....
+3.8g.
Flaps Down
(33
O)
.......
+2.0g.
Maximum Negative Load Factor
Flaps Up
...........
-1.5
g.
Flaps Down
.........
0.0g.
1
FLIGHT
CREW
f
Pilot
............
.I
MaximumPassengerseating configuration
......
3
/
OPERATING
LIMITATlON8
1
Ifthisairplane is ndequippedwithan approvedoxygensystemand flightoperationsabove
12,500 feet are desired, this airplane must be,
(1)
equipped with supplemental oxygen in
accordancewith FAR
23.1441,
(2)
operatedinaccordancewith
FAR
91.32
and
(3)
equipped
with avionics in accordancewith FAR
91
or FAR
135.
This is a Normal Category airplane approved for VFRIIFR day or night operationswhen
equipped inaccordance with FAR
91.
DO
NOT OPERATE IN
KNOWN
ICING
CONDITIONS.
Autopilot Limitations
-
See SECTION IX.
The followingequipmentwas approvedduring Type Certificationand must beinstalledand
operablefor eachkindof operationas specified.
-
-
-
I
NOTE
I
-
--
The
KlWBB
OF OPERATION
EQUIPME#$
list
may
not
include
all
the
equipment
as
r~ulrd
by
epplkable
operating
rules.
BEE
NEXT
PAGE
FOR
L18Tll4G8,
FAA
AAPPROVEE
ISSUED
8
-
139
MOONEY
MODEL
M20J
EXTERIOR
The following placards must
be
installed on the exterior of the alrcraft
at
the
loca-
tions specified.
TIRE
PRESSURE
50
PSI
(207
KPA)
-761
ON MNN
GEAR
DOORS
I
TIRE
PRESSURE
4-9
PSI
I
(338
KPA)
ON NOSE
GEAR
DOOR
I
FUEL-100
GREEN)
or
?DOLL (ElLU&
MIN.
OCT.
32
U.S.
MI
ON
FUEL
TANK
CAPS
-
FUEL-I00
GREEN)
or
IOOU
(BWt!)
MIN.
OCT.
26.6
IMP
GAL
USk3W.E
TOWING
LIMITS
DO
NOT
PUSH
-009
ON LEADING EDGE
OF
HORIZONT881.
STABILIZER
AND
TWUNG EDGE
OF
BOTH
SIDES
OF RUDDER
-
DO
NOT
EXCEED
TOWING
LIMITS
NO
STEP
-009
ON INBOARD END OF
WS,
WlNG LEADING
I
EDGES
AND
WlNG AHEAD OF FLAPS
FAA
APPROVED
ISSUED
8
-
89 AIRPLANE FLIGHT MANUAL
2-17
SECTION
II
AT
MOOMEY
LIMITATIONS MODEL
M2QJ
HOIST POINT
ON UNDERSIDE OF WINGS
(2
PLCS)
FUEL
DRAIN PITOT DRAIN
UNDER
EACH
WING NEAR
SUMP
DRAINS UNDER LEFT HAND WING LEADING EDGE
NEAR FUSELAGE
GASCOLATOR STATIC
DRAIN
UNDER TAILCONE
AFT
OF
WlNG
UNDER FUSELAGE AFI OF TRAILING EDGE
NOSE WHEEL WELL
MRPME
FLIGHT
MANUAL
FAA
APPROVED
2-18
ISSUED
8
-
89
MBONEY
MODEL M20J
AT SECTION
1II
EMERGENCY
PROCEDURES
POWER
OFF
-
GEAR RETRACTED
OR
EmEHDED
Emer ency Locator Transmitter
.
ARMED
......
Seat #eltsl~houlderI-larnesses SECURE
Cabin Boor
...
UN~TCI-IED
Fuel Selector
..........
OFF
..........
Mixture
IDL~
CUTOFF
~agneto/Stal"ler
.......
OFF
Win Fla
s
......
.
~ull
DOWN
(33'Be
me$)
~anBingbear
.
DO~N
or
UP
DepeMing on fsrrain
Approach Speed
...
71
KlAS
.......
Master Switch
OFF,
prior to lading
POWER
ON
-
GEAR
RETRACTED
Emergency Locator Transmitter
..
ARMED
.....
Seat Belts and Shoulder Harnesses .SECURE
..........
Cabin Door UNMTCHEB
Fuel Selector
........
OFF
Throttle
..........
.CLOSED
Mixture
..
~LECURBFF
~a~netol~tarter
.........
Wing Flaps
.....
~ull
D~WN
(%
Master Switch
..........
OF
"7
Approach Speed
...
As Slow As Possible
Wings
...........
Keep
LEVEL
PROPELLER
PROPELLER
OVERSPEED
Throttle
.......
RmARB
Oil Pressure
.....
.
CkiECK
....
Propeller B~CRE~~SE,set if any contrdavaliable
Airspeed
...
.
.
.REDUCE
Thronle
...
AS
RE~UIREBto maintain
R~M
bf3iow
2900
RPPd'l
FUEL
LOW
FUEL
FLOW
..........
Check Mixture ENRICH
Fuel Selector
....
FuliiedTANK
If condition persists, use ~ue1'~oo~tPump as necessaryand
~$\N~ING
SHOULD
BE
MADE
AS SOON AS PRACTICABLE.
ELECTRICAL
ALTERHATOR
OVERVOLTAG
E
wol@ge
mming
light
iiluminetd
stmdyIAtwmtor GIB
may
be
&lpmd.)
Alternator Field Circuit Breaker
.
RESET or PULL out, then
PUSH
IN
IB
c~.cun
break%
will
not
reset,
thi
kllowaing
promdur~s
are
rqui~:
1.
Reduceelectrical load.
2.
Land,
when practical,to correct malfunction.
ISSUED
8
-
89
REV.
B
4
-92
3
-9
SECTION
ll!
AT
EMERGENCY.
PROCEDURES
MO0NEV
MODEL
M2QJ
ALTERNATOR OUTPUT
LOW
AND AMMETER
SHOWING
DISCHARGE
Vobge
wrning light fiaahing)
......
RadioMaster
Master Switch
.....
OFF
:
OFF: then ON
If
Wamin
LQM
is still fkshiw, the lollo~mstepare rquired:
Non-Essentid~lectricalEquipment
..
Turn OFF one at a time
.
CHECK
*
Ammktter
....
for char ing condition as each unit
dr
~ledtrical'Equipmeniis turned OFF
-
Itstill slowin discharge:
...
Alternator Field Circuit ireaker
...
PULL
Non-esentialelectricalequipment
. .
OFF ioconserve battery power
LAND AS SOON AS PRACTICABLE
I
NOTE
I
P
A
trippdmain aiternator circuit breaker can only be causd by a shofld
allemator eircuk and anndbe correct& by reseHingthe breaker. This
should
be
verifid by aHempting to reset the breaker not more than one
time.
If
this fails, pullallernator field circuit breaker. Turn off all
non-essential eledrimlquigment and terminate the flight
a8
soon
a8
praeti-l. Wepir the malf~ndioningafternator prior to nex$flight.
UNDING
GEAR
FAILURE
OF
UNDlNG
GEAR
TO EmEND
ELECTRICALLY
Airspeed
...
432
KIAS or less
LandingGear Actukor kircuii ~redker
..
PULL
Gear Switch
...
DOWN
ManualGear ~xtensionhec&nism
.
L~TCH
FORWARDILEVER
BACK,
to engage manual extension mechanism
---
I
NOTE
I
---
Slowly pull
"T"
handle
1
to 2 inches (2.5 to 5.1 em) to rdate elutch
mechanism
and allow
it
to engage drive shafi.
T-Handle
....
.
.PULL
(7
to
20
times
a(d
RE~URN
until ear is down and Ipcked,
GEAR DOWN
li
ht ~llumnated;§TO#when
resistance
1s felt.
-
-
-
SYSTEM MAY
BE~OME
DAMAGED
-
-
-
Visual Gear Down Indicator
. .
CHECK ALIGNMENT
by vieiingfrom directly above the indicator.
,vNF"NM,"
"
CAUTION
"
'-,
N N
N
N N
Continuing lopull onT-Handle after
GEAR
DOWN
light
ON will
bind
actuator; electrical retraction
MAY
NOT
be possible until binding is
eliminated.
Returnlever to normal positionand securewith latch. Reset LandingGear Actuator Circuit
Breaker.
lllllllllllllllllii
Do not operate landing gear elecMcall with manual edension system
engasJ
REV.
8
1
-
92
ISSUED
8
-
89
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5
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