Mooney M20J 1978 Owner's manual

CONGRATULATIONS . . .
WELCOME TO MOBNEYvSNEW DIMENSION IN SPEED
AND ECONOm. YOUR DECISION TO SELECT A NEW
MOONEY HAS PLACED YOU IN
AN ELITE AND DISTINC -
TIVE CLASS OF AIRCRAFT OWNERS. WE HOPE
THAT
YOU FIND YOUR NEW MOONEY A UNIQUE FLYING
EXPERIENCE, WHETHER FOR BUSINESS OR PLEASmE,
THE MOST PROFITABLE EVER.
This manml is provided asan operating guide for the
Mooney
201, Model M20J. It is important that you --
regardless of your previous experience - - carefully
read the handbook from cover to cover and review it
frequently.
A11 information and i%%ustrationsin the manual are based
on the latest product information avaibble at the time of
publication approval.
The right is reserved to make
changes at any time without notice* Every effort has been
n2ade to present the material in a clear and conveniea2t
manner to enable you to use the manual as a ready
reference, Yobar cooperation
in reporting presentation
and content recommendations
is solicited.
IZEVISPNG THE MAWUA %
Page i of this manual is a " List of Effective Pages "
containing a complete etarent listing of aXB pages
ie e. , Original or Revised. Also, in the lower
corner of the outlined portion,
is a box which denotes
the issue or revision of the manual.
It will be advanced
one letter, a%phabetica%%y,per revision, With each
revision to the manual a new List of Effective Pages will
be received to replace the previous one*
This handbook will be kept current by Mooney Aircraft
Corporation when the revision card in the front of this
handbook
has been filled in and mailed to Mooney Aircraft
Corporation,
P.O. Box 72, Kerrville, TX 78028.
A ISSUED 11 - 15 - 77

TABLE OF CONTENTS
SECTION
................
GENEGAL a
.............
LIN.w~ITATIONS. 2
......
EMERGENCY PROCEDURES 3
........
NORMAL PROCEDURES 4
PERFORMANCE ............. 5
..........
WEIGHT & BALANCE 6
AIRPLANE (k SYSTEM
...........
DESCRIPTIONS 7
WANE>L1.NG9 SERVICE
......... & MAINTENANCE. 8
........ SUPPLEMENTAX,DATA 9
ISSUED 1%-15-77
fsr . 4 v/v6 BLANK

SECTION I.
TABLE OF CONTENTS
TITLE PAGE
%RREEwE&SP. . . o o a . . . . a el-2
mTRODUCT%ON a * * * 01-3
DESCmPTIVE DATA * * a * *I-3
LANDmGGEAR * - * * * * a -1-3
~N~~~~~~~~~~~~~~~~~~ 01-3
PROPELLER* a 0 o e * e o e o o . el-4
~~~~~~~~~~~~~~~oo~~ *I-4
OIL. ............... .I-4
MAXMUM CERTIFICATED WEIGHTS -1-4
STANDARD MRPLANE WEIGHTS * * 0 1 - 5
BAGGAGESPACE& ENTRY
DIMENSIONS, .......... -1-5
SPECIFIC LOADINGS . 0 . . 0 a . 1-5
SYMBOM, ABBREVUTPONS & TERMI-
NOLaP ............ .I-5
GENERA18 AIRSPEED TERmNOLmV
& BYMBOW. ....a.e.... 1-5
ME TEOROLWICAL TERMINO
AmPUNE PERFORMANCE &
FLIGHT PUNNNG TERmO
WEIGHT & BAUNCE TERmO
ISSUED 11-15-77

FIGmE 1-1 THREE mEW
ISSUED f 1 - 15 - 77

This Rlot 's Operating hndbsok contaim 9 dscections
and includes the material rquired to be fwnished to
the pilot by CAR Part 3. It also con%ea%msupplemental
data supplid
by Mooney Aircrdt Corporation,
Section I contains informtian of general interest tothe
pi%&, It aalo contains &finitions of the terminol~
used in this Pilot's 9eratiqandbook.
DESCRIPTIVE DATA
LANDING GEAR
TYPE : Electri ca%Q operated tricycle gear with ri~bber
shock discs, steerable nose wheel, and hydraealfc disc
brakes.
Wheel Base 5 We 11 - 9/16 in.
Wheel Tread 9 ft. 3/4 tn,
Tire Size:
Nose (8 Ply) 6.00~ 5
Main
(6 Ply) 6 80 x 6
Tire Pressure:
Nose
49 PSI
Main 30 PSI
Mino Tuning mdius 41 ft*
(No Brakes Applied)
ENGWE
TYPE : Four-cylinder, horizontally opposed, air cooled,
and fuel
- injected engine with a wet - sump lubricatiw sys -
tem.
Number of Engines 1
Mode% (Lycomiw) IO-860-A3B6D
Recommended TBO 1BOO Hrs-
mted HP @ 29106 RPM
200 BNP @ Sea Level

Bore 5.3125 in.
Sroke 4.375 in.
Msphcement 361.0 Cu. In-
Compression Ratio 8.7:1
Fuel Injector, Bend& RSA-5-AD1
Magnetos, Bendix MLN 2021
PROPELLER
TYPE : Constant - speed, hy&aulically controlled pro -
peller with a siwle-acting governor.
Mdel (McCauley) ~2~34@214/90~~~- 16E
Diameter
974 in. mm,
73 in, miw.
Number of Blades 2
Blade Angle @ 30 In. Sa. :
Low 13.9~ - + ,2"
Nigh 33" - -I- .5"
'Total Ftas%, Capaci,ty
66-5 11.8. Gal.
Usable Fuel Capacity
64 U.9. Gal.
Minimum Fuel Octane Rali2x & Color
Grade
P
1.08
100 LL Blue
oil Capacity
(6 QTS MIN for flght)
8 WS.
Oil grades, speciffeatioaasand changing recornmen&-
tloaas are contained in Seetion WE.
MAXMUM CERTIFICATED WEIGHTS
Maimurn Loading (mlssslimited by loading envelope):
Gr sss Weight 2'740 LBS.
Baggage Area 120 LBS.
Hat Rack 10 LBS.
ISSUED 11 - 15 - 77

STANDARD AIRPLANE WEIGIlTS
Basic Empty Weight (See page
6 - 4)
Standard Useful Load 1100 LBS.
BAGGAGE SPACE' AND ENTRY DIMENSIONS
Baggage Area 24"x
35"x 35"M (199 cu. ft. )
Hal Rack
30"Wx 19"D x 12H (Max.)
(2.6 CU. fe.)
Baggage Door Opening
Above Ground
(Sill) 46 "
Entry Width 1'9"
Elltry Height 20.5 "
SPECIFIC LOADINGS
Wing Loading @ G. W.
16.4 PSP
Power Loading @ C. W.
13. '7 PHP
SYMBOLS, ABBREVIATIONS & TERMBNOLOGV
GENERAL AIRSPEED TERMINOLOGY & SYIMBOLS
CAS Calibrated Airspeed means the ia~dicatedspeed
of an aircraft, corrected for position and instru
-
ment error. Calibrated airspeed is equal to
true airspeed in standard atmosphere at sea
Bevel.
GS Ground Speed is the speed of an airplane
relative to the ground.
IAS Indicated Airspeed
is the speed of an aircraft
asshown on its airspeed indicator. IAS values
published
in this handbook assume zero instru -
ment error.
TAS True Airspeed is the airspeed of an airplane
relative to undisturbed air.
REVISION
A
'- J

Maneuvering -- Speed is the maximuin speed at
which application of full available aerodynamic
control will not overstress the airplane.
Maximum Flap Extended Speed is the highest
speed permissible with wing flaps in a pre
-
scribed extended position.
Maximum b,andiiagGear Extended Speed
is the
maximum speed at which an aircraft can be
safely flown with the landing gear extended.
Maximum Landing Gear Operating Speed
is the
maximum speed at which the landing gea.r can
be safely extended or retracted.
Never Exceed Speed or Mach Number is the
speed linait that may not be exceeded at any
time.
Maximum Striactriral Cruising Speed is the speed
Chat should not be exceeded except in smootla air
and thela only wit la caution.
Stalling Speed or the 1aainirnu.m steady flight
speed at which tlae airplane is contm-obkable.
Stalling -- Speed or the rni.nimum steady flight
speed at which the airplane is controllable in
the landing configuration
Best Angle
- of - Climb Speed -. is the airspeed
which delivers the greatest gain of altitude
in
the shortest possible horizontal distance.
Best Rate
- of - Climb Speed is the airspeed which
delivers the greatest gain in altitude in tlae
shortest possible time with gear and flaps up.
ISSIJED 11 - 15 - 77

OAT is the free air
static temperature, obtained either from
inflight temperature indications or ground
meteorological sources. It
is expressed
in degrees Celcius krefiously Centigrade).
(2) The temperatwe atvsealevels kQ
Celeius; (3) The pressure at sea level is
29.92 inches Hg; (4) The temperature
gradient
from sea level tothe aanfteads at
which the temperature
is -56.5oC is
-0.00198~~ per foot.
Indicated The number actually read from an alti -
Pressure meter when and only when, the barometric
ARLMuds
subscale has been set to 29.92 inches of
mercusy.
Reasears
Pressure altitude is the tx~dicatedpressure
Altitude
altitude corrected Pos position and fnstru-
mealt error, In this handboolc, altimeter
instrument errors are assumed to be zero.
Density Altitude
as determined by pressme altitude
Altitude and existing ambient temperature. In
stan&rd atmospiaere (ISA) density and
pressure altitude are equal, For a given
pressure altitude, the higher
the tempera -
ture, the higher the density altitude.
&atio%%
Actual atmospheric presswe at field
Pressure elevation.
ENGINE POWER TERMINOLaY
BHP
Brake Horsepower is the power developed
by the engine.

RPM
Revollutions Per Minute is @winespeed.
MP
Manifold Reaeure is a presswe measured
&%on syatem awd ts ax -
Demon - is the
etratd velocftv d the crosswind component for
Croeswiond which idqmte control of the itrplane
VelmiQ
dw%w takeoff and landing wae actmlly dem-
onadrated desriw certificationtests. The
mllue shown is n& considered to be lirnitim,
E!
g is the acceleration due to gravity.
&tpdee
is the altitude where the
Ceiligg
airera8 has the capability of climbing at
the rats d 100 lt/min.
WEHCBT AWD BALANCE TERMINQImU
p7-.--p----p."p
Reference
An imaginary vertical plans from which
htum
all horizontal distances are measured lor
balance purposes,
Wation
A location along the airplane fuselage
usw%%ygiven in terms of distance from
the reference datum*
Ar rn The horizontal distance from the reference
datum to the center of gravity (C. G. ) of an
item.
Moment The prduct of
the weight of an item mu%-
tiplied by its arm. (Moment divided by a
constant is used to simp%i$gvbalance cal -
culations by rdiacing the number of digits. )
C . G. Arm The arm obtained by addiw the airplane's
individual moments and di~ding the sum
by the total wsigkat.

C.G.
The extreme center of gravity locations within
Limits which the airplane must
be operated at a given
weight.
Center of The point at which an airplane would balance if
Gravity suspended. Its distance from the reference
(C . G. ) datum is found by dividing the total moment by
the total weight of the airplane.
Usable
Fuel Fuel available for airplane pro;ulsion.
Unusable Fuel remaining after a runout test has been
Fuel completed in accordance with governmental
regulations.
Maximurn The maximum weight isthe maximum authorized
Weight weight
of the aircraft and its contents aslisted
in the aircraft specificatio~as.
Basic
The basic empty weigh"c. of an aircraft is the actual
Empty.
weightof the airplane and includes all operating
Weight egurnpmclat (imcliading optional equipment) tkt
has a fixed location and is actually installed in
the airc-sa.ft. It includes the weight 0%: the
unusable fuel and full. oil,
Useful 'Fhe useful load
is the empty weight subtracted
Load from the maximum weight of the aircraft. This
load consists of the pilot, crew if applicable,
fuel, passengers, and baggage,
Tare Tare is the weight of chocks, b%oclns,stands,
etc. used when weighing an airplane, and is
included
in the scale readings. Tare is de
-
ducted from the scale reading to obtain the
actual (net) airplane weight.
1-9 (1 - 10 Blank)