Mooney M20TN Operating Manual
PILOT’S OPERATING HANDBOOK
AND
FAA APPROVED
AIRPLANE FLIGHT MANUAL
MOONEY
M20TN
THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY
THE FEDERAL AVIATION REGULATIONS, AND CONSTITUTES THE FAA APPROVED AIRPLANE
FLIGHT MANUAL.
THIS DOCUMENT MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES.
MOONEY AIRPLANE COMPANY, INC.
LOUIS SCHREINER FIELD
KERRVILLE, TEXAS 78028
SERIAL NUMBER:
REGISTRATON NUMBER:
FAAAPPROVED:
Michele M. Owsley
Manager, Airplane Certification Office
FEDERAL AVIATION ADMINISTRATION
2601 Meacham Boulevard
Fort Worth, Texas 76137--0150
DATE:
FAA APPROVED in Normal Category based on CAR PART 3, applicable portions of FAR PART 23,
and when applicable components are installed in accordance with Mooney Drawing 110080; applicable
This handbook meets GAMA Specification No. 1, SPECIFICATION FOR PILOT’S OPERATING HAND-
BOOK, issued February 15, 1975, revised October 18, 1996; Revision No. 2.
CopyrightE 2006 All Rights Reserved Mooney Airplane Company -- Louis Schreiner Field Kerrville, Texas 78028
December 22, 2006
to Model M20TN S/N listed above only.
ORIGINAL ISSUE -- 12--22--2006
Revision A -- 12-11-07
POH/AFM NUMBER -- POH003900
CAUTION
THIS AIRCRAFT IS CERTIFIED
TO USE 100LL (BLUE) OR
100/130 (GREEN) AVIATION
GASOLINE ONLY. IT IS THE
PILOT’S RESPONSIBILITY TO
INSURE THAT THE PROPER
FUEL IS USED AT EACH
REFUELING.
MOONEY
M20TN
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MOONEY
INTRODUCTION
M20TN
CONGRATULATIONS
WELCOME TO MOONEY’S NEWEST DIMENSION IN SPEED, QUALITY AND ECONOMY.
YOUR DECISION TO SELECT A MOONEY AIRCRAFT HAS PLACED YOU IN AN ELITE AND
DISTINCTIVE CLASS OF AIRCRAFT OWNERS. WE HOPE YOU FIND YOUR MOONEY A
UNIQUE FLYING EXPERIENCE, WHETHER FOR BUSINESS OR PLEASURE, THE MOST
PROFITABLE EVER.
-- NOTICE --
This manual is provided as an operating guide for the Mooney Model M20TN. It is important that
you, regardless of your previous experience, carefully read the handbook from cover to cover
and review it frequently. THIS AFM MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES.
All information and illustrations in the manual are based on the latest product information available at the time of publication approval and all sections including attached supplements are
mandatory for proper operation of the aircraft. The right is reserved to make changes at anytime
without notice. Every effort has been made to present the material in a clear and convenient
manner to enable you to use the manual as a reference. Your cooperation in reporting presentation and content recommendations is solicited.
REVISING THE MANUAL
The “i” pages of this manual contain a “List of Effective Pages” containing a complete current
listing of all pages i.e., Original or Revised. Also, in the lower right corner of the outlined portion,
is a box which denotes the manual number and issue or revision of the manual. It will be advanced one letter, alphabetically, per revision. With each revision to the manual a new List of
Effective Pages showing all applicable revisions with dates of approval and a “Log of Revisions”
page(s), with only the latest Revision shown, will be provided to replace the previous ones. It is
the operators responsibility to ensure that this manual is current through the latest published revision. This handbook will be kept current by Mooney Airplane Company, Inc. when the yellow
information card in front of this handbook has been completed and mailed to:
Service Parts Department
Mooney Airplane Company, Inc.
Louis Schreiner Field
Kerrville, TX. 78028.
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MOONEY
M20TN
INTRODUCTION
LOG OF REVISIONS
REVISION
NUMBER
ORIGINAL
ISSUE
REVISED
PAGES
ALL -- 12--22--06
Revision A ithruiv
1-8, 1-12 thru 1-14
2-6, 2-15
3-4, 3-15
4-8 thru 4-10, 4-12
4-14, 4-16
4-17
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5-40 thru 5-67
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DESCRIPTION
OF REVISIONS
Revised Data
Added Data
Revised Data
Revised Data
Added Data
Revised Data
Relocated Data
Revised Data
Added Data
Added Data
Revised Data
FAA
APPROVED
DATE
1 2 -- 1 1 -- 0 7
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TABLE OF CONTENTS
TITLE SECTION.................................................................
GENERAL I..................................................................
LIMITATIONS II...............................................................
EMERGENCY PROCEDURES III...............................................
NORMAL PROCEDURES IV...................................................
PERFORMANCE V............................................................
WEIGHT & BALANCE VI......................................................
AIRPLANE & SYSTEM DESCRIPTIONS VII......................................
HANDLING, SERVICE & MAINTENANCE VIII.....................................
SUPPLEMENTAL DATA IX.....................................................
SAFETY & OPERATIONAL TIPS X..............................................
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ORIGINAL ISSUE -- 12--22--2006
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SECTION I
GENERAL
TABLE OF CONTENTS
TITLE SECTION.................................................................
THREE VIEW 1--3................................................................
INTRODUCTION 1--4.............................................................
DESCRIPTIVE DATA 1--5.........................................................
ENGINE 1--5..................................................................
PROPELLER 1--6.............................................................
FUEL 1--6....................................................................
OIL 1--6......................................................................
LANDING GEAR 1--7..........................................................
MAXIMUM CERTIFICATED WEIGHTS 1--7.......................................
STANDARD AIRPLANE WEIGHTS 1--7..........................................
CABIN & ENTRY DIMENSIONS 1--7.............................................
BAGGAGE SPACE & ENTRY DIMENSIONS 1--7..................................
SPECIFIC LOADINGS 1--7.....................................................
IDENTIFICATION PLATE 1--8...................................................
GARMIN G1000 1--8
SYMBOLS, ABBREVIATIONS & TERMINOLOGY 1--9................................
GENERAL AIRSPEED TERMINOLOGY & SYMBOLS 1--9..........................
ENGINE POWER TERMINOLOGY 1--9..........................................
AIRPLANE PERFORMANCE & FLIGHT PLANNING TERMINOLOGY 1--10...........
ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY 1--10.....................
METEOROLOGICAL TERMINOLOGY 1--10......................................
WEIGHT & BALANCE TERMINOLOGY 1--11.....................................
MEASUREMENT CONVERSION TABLES 1--12
USE OF THE TERMS WARNING, CAUTION AND NOTE 1--14
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SECTION I
GENERAL
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1--2
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76”
(193.04 cm)
6’--7 1/2”
(201.9 cm)
26’ --8”
(812.8 cm)
36’--6”
(1112.5 cm)
SECTION I
GENERAL
8’--6”
(259.1 cm)
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11’ --9”
(358.1 cm)
9’--2”
(279.4 cm)
FIGURE 1--1 THREE VIEW
POHTN002
1--3
SECTION I
GENERAL
MOONEY
M20TN
INTRODUCTION
This Operators Manual conforms to GAMA Specification No. 1 and includes both Manufacturer’s
material and FAA APPROVED material required to b e furnished to the pilot by the applicable
Federal Aviation Regulations. Section IX contains supplemental data supplied by Mooney Airplane Company, Inc..
Section I contains information of general interest to the pilot. It also contains definitions of the
terminology used in this Operators Manual.
This Pilot’s Operating Handbook is not designed as a substitute for adequate and competent
flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training
manual and should not be used for operational purposes unless kept in an up--to--date status.
All limitations, procedures, safety practices, servicing and maintenance requirements published
in this POH/AFM are considered mandatory for the Continued Airworthiness of this airplane in a
condition equal to that of its original manufacture.
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SECTION I
GENERAL
DESCRIPTIVE DATA
ENGINE
Number of Engines 1..............................................................
Engine Manufacturer Teledyne Continental Motors (TCM)..............................
Model TSIO--550--G(1).............................................................
Recommended TBO 2000 Hours....................................................
Type Reciprocating, air cooled, fuel injected, turbocharged..............................
Number of Cylinders 6, Horizontally opposed.........................................
Firing Order 1--6--3--2--5--4.........................................................
Displacement 552 Cu. In. (9.05 Liters)...............................................
Bore 5.25 In. (13.3 cm)............................................................
Stroke 4.25 In. (10.8 cm)..........................................................
Compression Ratio 7.5 : 1.........................................................
Fuel System
Type Fuel Injection................................................................
Make TCM.......................................................................
Fuel -- Aviation Gasoline 100 octane --100LL.........................................
Accessories
Magnetos Bendix S6RSC--25P (pressurized).........................................
Ignition Harness Shielded/Braided...................................................
Spark Plugs AC 273 (or equivalent) (18 m/m)........................................
Oil Cooler TCM Full Flow..........................................................
Alternator 28 Volt DC, 100 AMPS...................................................
Starter 24 volt DC.................................................................
Intercooler TCM...................................................................
Turbocharger TCM/Kelly Aerospace Model TA36......................................
Turbocharger Controller System TCM................................................
Ratings:
Maximum Continuous Power 280 BHP at 2500 RPM...................................
Recommended Cruise Power 262 BHP at 2500 RPM..................................
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SECTION I
GENERAL
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PROPELLER
Hartzell
Number 1........................................................................
Manufacturer Hartzell.............................................................
Model Number PHC--J3YF--1RF/F7693DF--2.........................................
Number of Blades 3...............................................................
Diameter (MAX.) 76 in. (193.0 cm)..................................................
(MIN.) 75 in. (190.5 cm)...........................................................
Type Constant Speed..............................................................
Governor (Hartzell) Hydraulically controlled by engine oil...............................
Blade Angles @ 30.0 in. Sta.:
Low 16.5 degrees +/-- 0.2 degrees..................................................
High 38.0 degrees +/-- 1.0 degrees..................................................
FUEL
Minimum Fuel Grade (Color) 100 LL (Blue) or 100 Octane (Green)......................
Total Fuel -- Useable 89 U.S. Gal. (386.1 liters).......................................
Unusable Fuel 6 U.S. Gal. (22.7 liters)...............................................
OIL
Oil Specification or Oil Grade (First 25 Engine Hours) -- Non dispersant mineral oil conforming to
SAE J1966 shall be used during the first 25 hours of flight operations. However, if the engine is
flown less than once a week, a straight mineral oil with corrosion preventative MIL--C--6529 for
the first 25 hours is recommended.
Oil Specification or Oil Grade (After 25 Engine Hours) -- Teledyne Continental Motors Specification MHS--24. An ashless dispersant oil shall be used after 25 hours.
Oil Grades Recommended for Various Average Air Temperature Ranges
Below 40
Above 40
o
F(4oC) SAE 30, 10W30, 15W50 or 20W50................................
o
F(4oC) SAE 50, 15W50 or 20W50........................................
Total Oil Capacity 8 Qts. (7.57 liters).................................................
Oil Filter Full Flow.................................................................
Oil grades, specifications and changing recommendations are contained in SECTION VIII.
NOTE:
The first time the airplane is filled with oil, additional oil is required for the filter, oil
cooler and propeller dome. This oil is not drainable on subsequent oil changes. Added oil is mixed with a few quarts of older oil in the system.
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LANDING GEAR
SECTION I
GENERAL
TYPE: Electrically operated, fully retractable tricycle gear with rubber shock discs. The main
wheels have hydraulically operated disc brakes. The nose wheel is fully steerable 11
o
left to 13
right of center.
Wheelbase 6’--7 1/2” (201.9 cm)....................................................
Wheel Track 9’--2” (279.4 cm)......................................................
Tire Size:
Nose 5.00 x 5 (6 ply)..............................................................
Main 6.00 x 6 (6 ply)...............................................................
Tire Pressure
Nose 49 PSI.....................................................................
Main 42 PSI......................................................................
Minimum Turning Radius (No brakes applied)
Right 40 ft. (12.0 m)...............................................................
Left 48 ft. (14.4 m).................................................................
MAXIMUM CERTIFICATED WEIGHTS
Gross Weight 3368 Lbs. (1528 Kg)..................................................
Maximum Landing Weight 3200 Lbs. (1452 Kg).......................................
Useful Load (No Options) 1049 Lbs. (475.8 Kg).......................................
Baggage Area 120 Lbs. (54.4 Kg)...................................................
Rear Storage Area 10 Lbs. (4.5 Kg).................................................
Cargo (Rear Seats Folded Down) 340 Lbs. (154.2 Kg)................................
o
STANDARD AIRPLANE WEIGHTS
Basic Empty Weight See Page 1--11................................................
Useful Load Varies with installed equipment..........................................
See SECTION VI for specific airplane weight.
CABIN AND ENTRY DIMENSIONS
Cabin Width (Maximum) 43.5 In. (110.5 cm)..........................................
Cabin Length (Maximum) 126 In. (315 cm)...........................................
Cabin Height (Maximum) 44.5 In. (113 cm)...........................................
Entry Width (Minimum) 29.0 In. (73.4 cm)............................................
Entry Height (Minimum) 35.0 In. (88.9 cm)...........................................
BAGGAGE SPACE AND ENTRY DIMENSIONS
Compartment Width 24 In. (60.9 cm)................................................
Compartment Length 43 In. (109.2 cm)..............................................
Compartment Height 35 In. (88.9 cm)................................................
Compartment Volume 22.6 cu. ft.....................................................
Cargo Area (with rear seat folded down) 38.6 cu. ft.....................................
Entry Height (Minimum) 20.5 In. (52.1 cm)...........................................
Entry Width 17.0 In. (43.2 cm)......................................................
Ground to Bottom of Sill 46.0 In. (116.8 cm)..........................................
(0.63 cu. m)......................................................................
(1.09 cu. m)......................................................................
SPECIFIC LOADINGS
Wing Loading -- @ Maximum Gross Weight 19.26 lbs./sq. ft.............................
ORIGINAL ISSUE -- 12--22--2006
(94 kg/sq. m).....................................................................
1--7
SECTION I
GENERAL
Power Loading -- @ Maximum Gross Weight 12.03 lbs./HP.............................
IDENTIFICATION PLATE
All correspondence regarding your airplane should include the Serial Number as depicted on the
identification plate. The identification plate is located on the left hand side, aft end of the tailcone,
below the horizontal stabilizer leading edge. The aircraft Serial Number and type certificate are
shown.
GARMIN G1000 GENERAL
The GARMIN G1000 Integrated Avionics System is a fully integrated flight, engine, communication, navigation and surveillance instrumentation system. The system consists of a Primary
Flight Display (PFD), Multi--Function Display (MFD), audio panel (GMA), Air Data Computer
(ADC), Attitude and Heading Reference System (AHRS), engine/airframe processing unit
(GEA), and integrated avionics (GIA) containing VHF communications, VHS navigation, and
GPS navigation.
MOONEY
M20TN
(5.46 kg/HP)......................................................................
-WARNING-
Do not load a new arrival or departure procedure in the flight plan if one currently
exists without first removing the existing arrival or departure procedure. Failing
to observe this limitation can cause erroneous course deviation indications, loss
of GPS navigation information, and other display anomalies.
NOTE:
If display anomalies are noted after editing the flight plan, perform either a direct
to or activate leg operation as appropriate on the flight plan to ensure correct
flight plan sequencing and guidance.
The primary function of the PFD is to provide attitude, heading, air data, navigation, and alerting
information to the pilot. The PFD may also be used for flight planning. The primary function of the
MFD is to provide engine information, mapping terrain information and for flight planning. The
audio panel is used for selection of radios for transmitting and listening, intercom functions, and
marker beacon functions.
The primary function of the VHF Communication portion of the G1000 is to enable external radio
communication. The primary function of the VOR/ILS Receiver portion of the equipment is to
receive and demodulate VOR, localizer, and Glide Slope signals. The primary function of the
GPS portion of the system is to acquire signals from the GPS satellites, recover orbital data,
make range and Doppler measurements, and process this information in real time to obtain the
user’s position, velocity, and time.
Provided the GARMIN G1000 GPS receivers are receiving adequate and usable GPS and/or
VHF navigation signals, it has been demonstrated capable of and meets the accuracy specifications for the following types of flight operations:
VFR/IFR en --route, oceanic, and terminal operations as well as nonprecision instrument
approach (GPS, Loran--C, VOR, VOR --DME, TACAN, NDB, NDB--DME, RNAV) operation within the U.S. National Airspace System in accordance with AC20--138A.
Navigation in the North Atlantic Minimum Navigation Performance Specification
(MNPS) Airspace in accordance with AC91--49 and AC 120--33.
The GARMIN G1000 system meets RNP5 a irspace (BRNAV) requirements of AC
90--96 and in accordance with AC 20--138A, JAA AMJ 20X2 Leaflet 2 Revision 1, and
FAAOrder 8110.60 for oceanic and remote airspace operations, provided it is receiving
usable navigation information from the GPS receiver. (A separate software application
for prediction of GPS navigation availability may be required for oceanic and remote operations. Refer to appropriate limitations for the airspace you are operating in to determine if this GPS prediction software is required).
Navigation is accomplished using the WGS--84 (NAD--83) coordinate reference datum.
GPS navigation data is based upon use of only the Global Positioning System (GPS)
operated by the United States of America.
1--8
ORIGINAL ISSUE -- 12--22--2006
Revision A -- 12-11-07
MOONEY
M20TN
SYMBOLS, ABBREVIATIONS & TERMINOLOGY
GENERAL AIR SPEED TERMINOLOGY & SYMBOLS
SECTION I
GENERAL
GS
GROUND SPEED -- Speed of an airplane relative to the ground.
KCAS KNOTS CALIBRATED AIR SPEED -- The indicated speed of an aircraft,
corrected for position and instrument error. Calibrated airspeed is equal to
true airspeed in standard atmosphere at sea level.
KIAS KNOTS INDICATED AIRSPEED -- The speed of an aircraft as shown on
its airspeed indicator. IAS values published in this handbook assume zero
instrument error.
KTAS KNOTS TRUE AIRSPEED -- The airspeed of an airplane relative to undis-
turbed air which is the KCAS corrected for altitude and temperature.
V
a
MANEUVERING SPEED -- The maximum speed at which application of
full available aerodynamic control will not overstress the airplane.
V
fe
MAXIMUM FLAP EXTENDED SPEED -- The highest speed permissible
with wing flaps in a prescribed extended position.
V
le
MAXIMUM LANDING GEAR EXTENDED SPEED --The maximum speed
at which an aircraft can be safely flown with the landing gear extended.
V
lo
MAXIMUM LANDING GEAR OPERATING SPEED -- The maximum speed
at which the landing gear can be safely extended or retracted.
V
ne
NEVER EXCEED SPEED -- The speed limit that may not be exceeded at
any time.
V
no
MAXIMUM STRUCTURAL CRUISING SPEED -- The speed that should
not be exceeded except in smooth air and then only with c aution.
V
s
STALLING SPEED -- The minimum steady--flight speed at which the airplane is controllable.
V
so
STALLING SPEED -- The minimum steady flight speed at which the airplane is controllable in the landing configuration.
V
x
BEST ANGLE--OF--CLIMB SPEED -- The airspeed which delivers the
greatest gain of altitude in the shortest possible horizontal distance.
V
y
BEST RATE--OF--CLIMB SPEED -- The airspeed which delivers the greatest gain in altitude in the shortest possible time with gear and flaps up.
ENGINE POWER TERMINOLOGY
BHP
CHT CYLINDER HEAD TEMPERATURE -- Operating temperature of engine
BRAKE HORSEPOWER -- Power developed by the engine.
cylinder(s) being monitored by sensor unit. Expressed in
o
F.
TIT TURBINE INLET TEMPERATURE -- Temperature at turbine inlet used to
identify the lean fuel flow mixtures for various power settings. Expressed in
o
F.
EGT EXHAUST GAS TEMPERATURE -- The exhaust gas temperature mea-
sured in the exhaust pipe manifold. Expressed in
o
F
MCP MAXIMUM CONTINUOUS POWER -- The maximum power for take off,
normal, abnormal or emergency operations.
MP MANIFOLD PRESSURE -- Pressure measured in the engine’s induction
system and expressed in inches of mercury (Hg).
RPM REVOLUTIONS PER MINUTE -- Engine speed.
ORIGINAL ISSUE -- 12--22--2006
1--9
SECTION I
GENERAL
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
MOONEY
M20TN
Demonstrated
Crosswind
Velocity
The velocity of the crosswind component for which adequate control of the
airplane during take off and landing test was actually demonstrated during
certification. The value shown is not considered to be limiting.
g Acceleration due to gravity.
Service
Ceiling
The maximum altitude at which aircraft at gross weight has the capability
of climbing at the rate of 100 ft/min.
ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY
Propeller
The control used to select engine speed.
Control
Throttle
The control used to select engine power by controlling MP.
Control
Mixture
control
Provides a mechanical linkage to the fuel injector mixture control to control
the size of the fuel feed aperture, and therefore the air/fuel mixture. It is
the primary method to shut the engine down.
CHT
Gauge
Cylinder head temperature indicator used to determine that engine operating temperature is within manufacturers specifications.
Tachometer An instrument that indicates rotational speed of the engine. The speed is
shown as propeller revolutions per minute (RPM).
Propeller
Governor
The device that regulates RPM of the engine/propeller by increasing or
decreasing the propeller pitch, through a pitch change mechanism in the
propeller hub.
METEOROLOGICAL TERMINOLOGY
AGL
Density
Altitude
Above ground level.
Altitude as determined by pressure altitude and existing ambient temperature. In standard atmosphere (ISA) density and pressure altitude are
equal. For a given pressure altitude, the higher the temperature, the higher
the density altitude.
Indicated
Altitude
The altitude actually read from an altimeter when, and only when barometric subscale (Kollsman window) has been set to Station Pressure.
ISA INTERNATIONAL STANDARD ATMOSPHERE a ssumes that
1. The air is a dry perfect gas;
2. The temperature at sea level is 15 degrees Celsius (59
o
F);
3. The pressure at sea level is 29.92 inches Hg (1013.2 MB);
4. The temperature gradient from sea level to the altitude at which the
temperature is --56.5
o
C (--69.7oF) is --0.00198oC (--0.003564oF) per foot.
OAT OUTSIDE AIR TEMPERATURE -- The free air static temperature, obtained
Pressure
Altitude
either from in--flight temperature indications or ground meteorological
sources. It is expressed in
The indicated altitude when Kollsman window is set to 29.92 In. Hg. or
1013.2 MB. In this handbook, altimeter instrument errors are assumed to
o
C.
be zero.
Station
Actual atmospheric pressure at field elevation.
Pressure
1--10
ORIGINAL ISSUE -- 12--22--2006
MOONEY
M20TN
WEIGHT AND BALANCE TERMINOLOGY
SECTION I
GENERAL
Arm
The horizontal distance from the reference datum to the center of gravity
(C.G.) of an item.
Basic
Empty
weight
The actual weight of the airplane and includes all operating equipment (including optional equipment) that has a fixed location and is actually
installed in the aircraft.
It includes the weight of unusable fuel and full oil.
Center of
Gravity
(C.G.)
The point at which an airplane would balance if suspended. Its distance
from the reference datum is found by dividing the total moment by the total
weight of the airplane.
C.G. Arm The arm obtained by adding the airplane’s individual moments and divid-
ing the sum by the total weight.
C.G. in
%MAC
C.G.
Limits
Center of Gravity expressed in percent of mean aerodynamic chord
(MAC).
The extreme center of gravity locations within which the airplane must be
operated at a given weight.
MAC Mean Aerodynamic Chord.
Maximum
Weight
Maximum
Landing
The maximum authorized weight of the aircraft and its contents as listed in
the aircraft specifications.
The maximum authorized weight of the aircraft and its contents when a
normal landing is to be made.
Weight
Moment The product of the weight of an item multiplied by its arm. (Moment divided
by a constant is used to simplify balance calculations by reducing the
number of digits).
Reference
Datum
An imaginary vertical plane from which all horizontal distances are measured for balance purposes.
Station A location along the airplane fuselage usually given in terms of distance
from the reference datum.
Tare The weight of chocks, blocks, stands, etc. used when weighing an air-
plane, and is included in the scale readings. Tare is deducted from the
scale reading to obtain the actual (net) airplane weight.
Unusable
Fuel
Usable
Fuel remaining after a run--out test has been completed in accordance
with Federal regulations.
Usable Fuel available for aircraft engine combustion.
Fuel
Useful
Load
The basic empty weight subtracted from the maximum weight of the aircraft. This load consists of the pilot, crew (if applicable), useable fuel, passengers, and baggage.
ORIGINAL ISSUE -- 12--22--2006
1--11
SECTION I
GENERAL
MOONEY
M20TN
MEASUREMENT CONVERSION TABLES
On the following pages are conversion tables and charts to and from U.S. weights and measures
to metric and imperial equivalents. The conversion tables are included to help pilots who live in
countries other than the United States or pilots from the United States who are traveling to or
within other countries.
LENGTH
U. S. Customary Unit Metric Equivalents..........................................
1 inch 2.54 centimeters............................................................
1 foot 0.3048 meter...............................................................
1yard 0.9144 meter..............................................................
1 mile (statute, land) 1,609 meters..................................................
1 mile (nautical, international) 1,852 meters..........................................
AREA
U. S. Customary Unit Metric Equivalents..........................................
1 square inch 6.4516 sq. centimeters................................................
1 square foot 929 sq. centimeters...................................................
1 square yard 0.836 sq. meter......................................................
VOLUME OR CAPACITY
U. S. Customary Unit Metric Equivalents..........................................
1 cubic inch 16.39 cubic centimeters................................................
1 cubic foot 0.028 cubic meter......................................................
1 cubic yard 0.765 cubic meter.....................................................
U.S. Customary Metric Equivalents...............................................
Liquid Measure
1 fluid ounce 29.573 milliliters.......................................................
1pint 0.473 liter..................................................................
1 quart 0.946 liter.................................................................
1 gallon 3.785 liters...............................................................
U.S. Customary Metric Equivalents...............................................
Dry Measure
1pint 0.551 liter..................................................................
1 quart 1.101 liters................................................................
British Imperial U. S. Metric
Liquid and Dry Measure Equivalents Equivalents......... ........................
1 fluid ounce 0.961 U.S. 28.412 milliliters....................... .....................
fluid ounce ...................................
1.734 cubic inches
1 pint 1.032 U.S. 568.26 milliliters............................. .....................
dry pints
1.201 U.S.
liquid pts.
34.678 cubic inches
1 quart 1.032 U.S. 1.136 liters............................ .........................
dry quarts
1.201 U.S.
liquid qts.
69.354 cubic inches
1 gallon 1.201 U.S. 4.546 liters........................... .........................
277.420 cubic inches
1--12
ORIGINAL ISSUE -- 12--22--2006
Revision A -- 12-11-07
MOONEY
M20TN
WEIGHT
U. S. Customary Unit Metric Equivalents..........................................
(Avoir du pois)
1 grain 64.79891 milligrams........................................................
1dram 1.772 grams...............................................................
1 ounce 28.350 grams.............................................................
1 pound 453.6 grams..............................................................
PRESSURE
U.S. Customary Unit Metric Equivalents...........................................
1 PSIG 6.895 KPA.................................................................
1inchHg 3.388 KPA...............................................................
1 inch Hg 25.40 mm Hg............................................................
COMMON CONVERSIONS
1 pound/square foot 0.488 kg/meter square..........................................
1 pound/square inch 2.036 inch Hg..................................................
1 pound/HP 0.4538 kg/HP..........................................................
SECTION I
GENERAL
ATMOSPHERIC PRESSURE RELATIONSHIPS (IN. HG AND HECTOPASCAL)
PRESSURE
In. Hg hPa In. Hg hPa In. Hg hPa In. Hg hPa
27.70 938 28.70 972 29.70 1006 30.65 1038
27.75 940 28.75 974 9.75 1007 30.70 1040
27.80 941 28.80 975 29.80 1009 30.75 1041
27.85 943 28.85 977 29.85 1011 30.80 1043
27.90 945 28.90 979 29.90 1013 30.85 1045
27.95 946 28.95 980 29.92 1013 30.90 1046
28.00 948 29.00 982 29.95 1014 30.95 1048
28.05 950 29.05 984 30.00 1016 31.00 1050
28.10 952 29.10 985 30.05 1018 31.05 1051
28.15 953 29.15 987 30.10 1019 31.10 1053
28.20 955 29.20 989 30.15 1021 31.15 1055
28.25 957 29.25 991 30.20 1023 31.20 1057
28.30 958 29.30 992 30.25 1024 31.25 1058
28.35 960 29.35 994 30.30 1026 31.30 1060
28.40 962 29.40 996 30.35 1028 31.35 1062
28.45 963 29.45 997 30.40 1029 31.40 1063
28.50 965 29.50 999 30.45 1031 31.45 1065
28.55 967 29.55 1001 30.50 1033 31.50 1067
28.60 969 29.60 1002 30.55 1035 31.55 1068
28.65 970 29.65 1004 30.60 1036 31.60 1070
ORIGINAL ISSUE -- 12--22--2006
Revision A -- 12-11-07
1--13
SECTION I
GENERAL
USE OF THE TERMS WARNING, CAUTION AND NOTE
The following conventions will be used for the terms Warning, Caution and Note:
--WARNING--
The use of a Warning symbol means that information which follows is of critical
importance and concerns procedures and techniques which could cause or re-
sult in personal injury or death if not carefully followed.
-- C A U T I O N --
The use of the Caution symbol means information which follows is of significant
importance and concerns procedures and techniques which could cause or re-
sult in damage to the airplane and/or its equipment if not carefully followed.
NOTE:
The use of the term Note means the information that follows is essential to em-
phasize.
MOONEY
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1--14
ORIGINAL ISSUE -- 12--22--2006
MOONEY
M20TN
SECTION II
LIMITATIONS
TABLE OF CONTENTS
TITLE SECTION.................................................................
INTRODUCTION 2--3.............................................................
NOISE LIMITS 2--3...............................................................
AIRSPEED LIMITATIONS 2--4.....................................................
AIRSPEED MARKINGS 2--5.......................................................
POWER PLANT LIMITATIONS 2-- 6
POWER PLANT INSTRUMENT MARKINGS 2--7
FUEL LIMITATIONS 2--8..........................................................
WEIGHT LIMITS 2--8.............................................................
CENTER OF GRAVITY LIMITS (GEAR DOWN) 2--8..................................
MANEUVER LIMITS 2--9..........................................................
FLIGHT LOAD FACTOR LIMITS 2--9...............................................
FLIGHT CREW 2--9..............................................................
OPERATING LIMITATIONS 2--9....................................................
KINDS OF OPERATION LIMITS 2--9................................................
KINDS OF OPERATION EQUIPMENT LIST 2--10....................................
TYPES OF OPERATION 2--11.....................................................
GENERAL 2--11..................................................................
G1000 SYSTEM 2--11..........................................................
ADVISORY MESSAGES 2--13.....................................................
DECALS & PLACARDS 2--14......................................................
CABIN INTERIOR 2--14........................................................
CABIN INTERIOR 2--15
FUSELAGE INTERIOR 2--18....................................................
EXTERIOR 2--19..............................................................
........................................................
.................................................
.....................................
FAAAPPROVED
ORIGINAL ISSUE -- 12--22--2006
Revision A -- 12-11-07
AIRPLANE FLIGHT MANUAL
2--1
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