Caproni Vizzola C22J Technical specifications

CAPRONI VIZZOLA
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AIRPLANE FLIGHT MANUAL
CAPRONI VIZZOLA
C22J
Serial NO _____________
Registration NO _____________
Type Certificate NO _____________
THIS HANDBOOK INCLUDES THE MATERIAL, REQUIRED TO BE
FURNISHED TO THE PILOT BY REGRISTRO AERONAUTICO
ITALIANO REGULATIONS AND ADDITIONAL INFORMATION
PROVIDED BY THE MANUFACTURER.
Manufacturer Name: CAPRONI VIZZOLA
Address: https://www.mariosplanes.com/
MSFS-V1.2.7
I-CAVT
MND-2021

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TABLE OF CONTENTS
SECTION 1 General...............................................................................................................1-1
SECTION 2 Limitations..........................................................................................................2-1
SECTION 3 Emergency Procedures.......................................................................................3-1
SECTION 4 Normal Procedures.............................................................................................4-1
SECTION 5 Performance.......................................................................................................5-1
SECTION 6 Weight and Balance............................................................................................6-1
SECTION 7 Panel & Systems Manual....................................................................................7-1

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SECTION 1
GENERAL
1.1. Notes to Users......................................................................................................................1-2
1.2. Dimensions And Areas .........................................................................................................1-2
1.3. Engines .................................................................................................................................1-3
1.4. Fuel.......................................................................................................................................1-4
1.5. Oil .........................................................................................................................................1-5
1.6. Weights ................................................................................................................................1-5
1.7. Specific Loading....................................................................................................................1-5
1.8. Baggage compartment.........................................................................................................1-5
1.9. Definitions and Abbreviations..............................................................................................1-6

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1.1. NOTES TO USERS
General
It is the pilot’s responsibility to be familiar, at all times, with the content matter of this Flight
Manual, Information is contained in seven sections, viz:
Section 1 General
Section 2 Limitations
Section 3 Emergency Procedures
Section 4 Normal Operating Procedures
Section 5 Performance
Section 6 Weight and Balance
Section 7 Systems Manual
Information in this flight manual relates to an aeroplane typically equipped with acrobatic
certification standards.
Each section contains a detailed list of contents. Whenever the certification of airworthiness
is required to be carried, this flight manual must also be aboard the aeroplane as it is an
essential part of the above-mentioned certificate.
Applicability
Application of this flight manual is limited to the specific Caproni Vizzola C22J Flight
Simulator model designated by serial number on the face of the title page.
This manual is not to be used for real world operations.
Page Identification
The page numbers in each section include se section number and a dash (i.e. “3” for all pages
in the “Emergency Procedures” section) followed by serial number of the page beginning
with “1” for each section, such as 3-1. 3-3, etc.
Each page bears a page number at the bottom.
1.2. DIMENSIONS AND AREAS
A three-view illustration showing the pertinent details of the aeroplane appears in Fig.1 and
2.

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1.3. ENGINES
(a) Number of Engines 2
(b) Engine Manufacturers Microturbo
(c) Engine Model Number TRS 18-1-202
(d) Take-Off Thrust 145 daN
(e) Engine RPM at Take-Off 48750
(f) Maximum Continuous Thrust 130 daN
(g) Engine RPM 47000
(h) Engine type
Compressor stages and Type 1-centrifugal
Turbine stages and Type 1-axial
Combustion chamber Type annular reverse flow
Figure 1-1

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Figure 1-2
Turning Radius
1.4. FUEL
a) Fuel Capacity (total)
(US Gal / lit) 113.6 / 430
b) Usable Fuel (total)
(US Gal / lit) 110.6 / 418.5
c) Fuel Specification
FUEL TYPE
NATO
CODE
SPECIFICATIONS
COMMERICAL
DENOMINATION
FRANCE
U.K.
Kerosene + 50°C
(+ S 7.48)
F 34
AIR 3405/
C/F-34
D. Eng.
RD 2453
Fuel TRO Kerosene JP 5
AVTUR/ FS II
(with antifreeze additive)
MIL T 83133
Kerosene + 50°C
(without inhibitor)
F 35
AIR 3405/
C/F-35
D. Eng.
RD 2494
Fuel TRO Kerosene JP 5
AVTUR
ASTM-D-1655
JET A1 or JET A
(without antifreeze additive)

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For operations into forecast temperature below +5 °C the use of fuel anti-icing additive
Phillips PFS-55MB is required. The additive concentration by volume shall be a minimum of
0.08 and maximum of o.15 percent.
1.5. OIL
a) Oil Capacity (each engine)
(US Gal / lit) 0.211 / 0.8
b) Usable Oil
(US Gal / lit) 0.132 / 0.5
c) Oil Specification MIL-L-23699
or MIL-L-7808
1.6. WEIGHTS
Lb Kg
a) Maximum Take-Off Weight 2764 1255
b) Maximum Landing Weight 2582 1172
c) Maximum Zero-Fuel Weight 2037 925
Maximum Weight in the
baggage compartment 24 11
d) Standard Empty Weight 1628 739
1.7. SPECIFIC LOADING
a) Wing loading
(lb/ sq ft –Kg / sq mt) 33 / 161
b) Thrust Loading
(Max Thrust / T.O.W.) 0.235
1.8. BAGGAGE COMPARTMENT
Lb Kg
a) Maximum Load Allowed 24 11

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1.9. DEFINITIONS AND ABBREVIATIONS
(a) General Airspeed terminology and symbols
CAS
Calibrated Airspeed means 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.
KCAS
Calibrated Airspeed expressed in “knots”.
GS
Ground speed is the speed of an airplane relative to the ground.
IAS
Indicated airspeed is the speed of an aircraft as shown in the airspeed
indicator when corrected for instrument error. IAS values published in
this manual assume zero instrument error.
KIAS
Indicated Airspeed expressed in “Knots”.
M
Mach number is the ratio of true airspeed to the speed of sound.
TAS
True Airspeed is the speed of an airplane relative to undisturbed air
which is the CAS corrected for altitude, temperature and
compressibility.
KTAS
True Airspeed expressed in “Knots”.
VA
Maneuvering Speed is the maximum speed at which application of full
available aerodynamic control will not overstress the airplane.
VFE
Maximum Flap Extended Speed is the highest speed permissible with
wing flaps in a prescribed extended position.
VLO
Maximum Landing Gear Operating Speed is the maximum speed at
which the landing gear can be safely extended or retracted.
VLE
Maximum Landing Gear Extended Speed is the maximum speed at
which the aircraft can be safely flown with the landing gear extended.
VBE
Maximum Airbrakes Extended Speed is the maximum speed
permissible with airbrakes in extended position.
VBO
Maximum Airbrakes Operating Speed is the maximum speed at which
the airbrakes can be safely operated.
VMC
Air Minimum Control Speed is the minimum flight speed at which the
airplane is directionally and laterally controllable, determined in
accordance with Certification Regulations. Airplane Certification
conditions include one engine becoming inoperative, not more than a
5° bank towards the operative engine, takeoff power on operative
engine, landing gear up, flaps in takeoff position and most critical C.G.
NOTE: for this airplane it is not an operating limitation.

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VMO/MMO
Maximum Operating Limit Speed is the speed limit that may not be
deliberately exceeded in normal flight operations. V is expressed in
Knots and M in Mach number.
VS
Stalling Speed or the minimum steady flight speed at which the
airplane is controllable.
VSI
Stalling Speed or the minimum steady flight speed obtained in a
specific configuration.
VS0
Stalling Speed or the minimum steady flight speed at which the
airplane is controllable in the landing configuration.
VX
Best Angle-of-Climb speed is the airspeed which delivers the greatest
gain of altitude in the shortest possible horizontal distance.
VY
Best Rate-of-Climb Speed is the airspeed which delivers the greatest
gain in altitude in the shortest possible time.
(b) Meteorological terminology
ISA
International Standard Atmosphere in which:
The air is a perfect dry gas;
The temperature at sea level is 15°C (59°F);
The pressure at sea level is 29.92 In Hg (1013.2 mb);
The temperature gradient from sea level to the altiutude at which
temperature is -56.5°C (-69.7°F) is -0.00198°C (-0.003564°F) per foot
and zero above that altitude.
OAT
Outside Air Temperature is the free air static temperature obtained
either from inflight temperature indications or ground meteorological
sources, corrected for instrument error and compressibility effects.
INDICATED
PRESSURE
ALTITUDE
The number actually read from an altimeter when the barometric
subscale has been set to 29.92 In Hg (1013.2 mb).
PRESSURE
ALTITUDE
Altitude measured from standard sea level pressure (29.92 In Hg) by a
pressure or barometric altimeter. It is the indicated pressure altitude
corrected for position and instrument error. In this manual altimeter
instrument errors are assumed to be zero.
STATION
PRESSURE
Actual atmospheric pressure at field elevation.
WIND
The Wind Velocities recorded as variables on the chart of this manual
are to be understood as the headwind or tailwind components of the
reported wind.
HEIGHT
The vertical distance between the lower part of the aeroplane and the
relevant datum.

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(c) Thrust Terminology
TAKEOFF THRUST
Maximum thrust possible during takeoff.
MAXIMUM
CONTINUOUS
THRUST
Maximum thrust permissible for unrestricted periods of use.
(d) Engine Controls and Instruments
EGT GAUGE
Exhaust Gas Temperature Gauge indicates temperature of the gases
at the outlet of the gas producer turbine rotor.
(e) Airplane Performance and Flight Planning Terminology
CLIMB
GRADIENT
The ratio, in the same units, and expressed as percentage of:
Change in height
Horizontal distance travelled in the same time interval
DEMONSTRATED
CROSSWIND
VELOCITY
The demonstrated crosswind velocity is the crosswind component for
which adequate control of the airplane during takeoff and landing
was actually demonstrated during certification tests. Is not
considered a limitation.
(f) Weight and Balance
REFERENCE
DATUM
An imaginary vertical plane from which all horizontal distances are
measured for balance purposes.
ARM
The horizontal distance from the reference datum to the center of
gravity (C.G.) of the item.
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).
CENTER OF
GRAVITY (C.G.)
The pint at which the 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
dividing the sum by the total weight.
C.G. LIMITS
The extreme center of gravity locations within which the airplane
must be operated at a given weight.
USABLE FUEL
Fuel available for flight planning.

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UNUSABLE FUEL
Fuel remaining after a runout test has been completed in accordance
with certification regulations.
STANDARD
EMPTY WEIGHT
Weight of a standard airplane including unusable fuel, as defined by
the Equipment List.
BASIC EMPTY
WEIGHT
Standard Empty Weight plus optional equipment actually installed.
PAYLOAD
Weight of occupants, Cargo and baggage.
USEFUL LOAD
Difference between takeoff weight and basic empty weight. It
includes payload and usable fuel.
MAXIMUM
TAKEOFF
WEIGHT
Maximum weight approved.
MAXIMUM
LANDING
WEIGHT
Maximum weight approved for the landing touchdown.
MAXIMUM ZERO
FUEL WEIGHT
Maximum weight with no usable fuel.

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SECTION 2
LIMITATIONS
2.1. General.................................................................................................................................2-2
2.2. Airspeed Limitations.............................................................................................................2-2
2.3. Airspeed Indicator Markings ................................................................................................2-4
2.4. Power Plant Limitations .......................................................................................................2-4
2.5. POwerplant Instrument Markings........................................................................................2-6
2.6. Weight Limits........................................................................................................................2-6
2.7. Center of gravity limits.........................................................................................................2-7
2.8. Maneuvers Limits.................................................................................................................2-8
2.9. Flight Maneuvering Load Factor Limits................................................................................2-8
2.10. Flight Crew .......................................................................................................................2-8
2.11. Kinds Of Operation...........................................................................................................2-8
2.12. Fuel Limitation .................................................................................................................2-8
2.13. Maximum Operating altitude Limit..................................................................................2-9
2.14. Seating Limitation ............................................................................................................2-9
2.15. Placards............................................................................................................................2-9

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2.1. GENERAL
Section 2 of this manual presents the operating limitations, the significance of such
limitations, instrument marking, colour coding and basic placards necessary for the safe
operation or the airplane, its powerplant, standard systems and standard equipment.
NOTE:
The limitations included in this section are approved by the Registro Aeronautico Italiano.
2.2. AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in Figure 2.1.
Variation of airspeed limit with height is shown in Figure 2.2.
SPEED
CAS
IAS
REMARKS
Maneuvering Speed
VA(Knots)
228
231
Do not make full or abrupt control
movements above this speed.
Maximum Flap
Extended Speed
VFE (Knots)
150
152
Do not exceed this speed with a
given flap setting.
Maximum Landing
Gear Operating
Speed
VLO (Knots)
140
142
Do not extend or retract landing gear
above this speed.
Maximum Landing
Gear Extended
Speed
VLE (Knots)
140
142
Do not exceed this speed with
landing gear extended.
Maximum Airbrakes
Extended /
Operating Speed
VBE (Knots) / VBO
150
152
Do not exceed this speed with
airbrakes extended or for airbrakes
operation.
Maximum Operating
Speed Limit
VMO (Knots)
MMO (Mach #)
257
0.473
260
0.48
Do not exceed this airspeed or Mach
in any operation (VMO is limiting
speed up to 10700 ft)
Note: VMC is not a limitation for this airplane.
Figure 2-1
Airspeed Limitations

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Figure 2-2
Airspeed Limitation with Altitude
VMO=260
10700 ft
0
5
10
15
20
25
30
050 100 150 200 250 300
Altitude
x1000 ft
IAS
Knots

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2.3. AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color significance are given in Fig. 2.3
MARKING
IAS VALUE OR RANGE
SIGNIFICANCE
White
Arc
70 - 152 KTS
Full Flap Operating Range. Lower limit is the
maximum weight stalling speed in landing
configuration. Upper limit is maximum speed
permissible with flaps extended.
Blue
Sector
114 –124 KTS
One Engine Inoperative Best Rate of Climb at 1255
Kg (2767 lb) between S.L. and 14000 ft.
Red Lines
260 / 0.48
Maximum Speed for all operations (VMO / MMO)
Figure 2-3
Airspeed Indicator Markings
NOTE: The Flight Simulator model depicts the Airspeed indicator as mounted in the
prototype airframes. The markings are not present.
2.4. POWER PLANT LIMITATIONS
d) Number of Engines 2
e) Engine Manufacturer MICROTURBO
f) Engine Model Number TRS 18-1-202
g) Engine Operating Limits
See Fig. 2.4 and 2.5
h) Maximum starting altitude 20000ft
See Fig. 2.5
OPERATING
CONDITION
OPERATING LIMITS
N%
EGT (°C)
max
OIL PRESS.
(bar) max
OIL TEMP. (°C)
max
FUEL
PRESSURE
(bar)
TAKEOFF (1)
104
820 - 860
0.7 - 3
140
1.2 - 3
MAX
CONTINUOUS
100
820
0.7 - 3
140
1.2 - 3
(1) Max time for take-off thrust: 2 minutes.
Figure 2-4

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Figure 2-5
Operating Envelope

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i) Fuel Specification
FUEL TYPE
NATO
CODE
SPECIFICATIONS
COMMERICAL DENOMINATION
FRANCE
U.K.
Kerosene –50°C
(+ S 748)
F34
AIR
3405 /
C/F-34
D. Eng.
RD 2453
Fuel TRO
Kerosene JP8
AVTUR/ FS II
(with antifreeze additive)
MIL T 83133
Kerosene –50°C
(without inhibitor)
F35
AIR
3405 /
C/F-35
D. Eng.
RD 2494
Fuel TRO
Kerosene JP8
ASTM-D-1655
JET A1 or JET A
(without antifreeze additive)
For operations into forecast temperatures below +5°C the use of fuel anti-icing
additive Phillips PFS-S5MB is required.
The additive concentration by volume shall be a minimum of 0.08% and a maximum
of 0.15%.
(g) Oil Specification
Oil conforming to MIL-L-23699B or MIL-L-7808
(h) Ambient Temperature Limitations:
Maximum atmospheric Temperature at which compliance with cooling requirements is
shown: 37.8°C (100°F).
2.5. POWERPLANT INSTRUMENT MARKINGS
Meaning of instrument markings and the value of limits are in Figure 2.6.
INSTRUMENT
Red Line
Yellow Arc
Green Arc
Yellow Arc
Red Line
MINIMUM
LIMIT
CAUTION
RANGE
NORMAL
OPERATING
CAUTION
OR TAKEOFF
MAXIMUM
LIMIT
Engine Rotational
Speed
(N%) Indicator
53 - 100
100 –104
102
EGT Temperature
(°C)
Up to 820
820 –860
860
Oil Pressure
0.7
0.7 –3
Oil Temperature
0 –140
140
Fuel Pressure
0.55
0.55 –1.2
1.2 –3
Figure 2-6
Powerplant Limits
2.6. WEIGHT LIMITS
It is the responsibility of the airplane owner and pilot to assure that the airplane is properly
loaded. Maximum allowable weights are listed below. Refer to Section 5 “Weight and
Balance” for loading instructions.

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Lb Kg
a) Maximum Takeoff Weight 2767 1255
b) Maximum Landing Weight 2583 1172
c) Maximum Zerofuel Weight 2037 925
2.7. CENTER OF GRAVITY LIMITS
(Refer to Fig. 2-7)
(a) Forward Limit
92.95 in (2361 mm) aft of Datum at all weights
(b) Rearward limits
94.58 in (2402 mm) aft of Datum at maximum takeoff weight
97.02 in (2464 mm) aft of Datum at 2588 pounds (1172 Kg) or less
(The chord is 35.433 in (900 mm) long)
NOTES
Straight line variation between points indicated. The Datum is located 82.677 inches
(2100 mm) in front of wing leading edge.
Figure 2-7
Center of Gravity Limits
832
1172
1255
832
1172
2464
2402 2361
92 93 94 95 96 97
1764
1964
2164
2364
2564
2764
800
850
900
950
1000
1050
1100
1150
1200
1250
1300
2340 2360 2380 2400 2420 2440 2460 2480 mm
Kg
Lb
In
Weight
MAXIMUM LANDING WEIGHT

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2.8. MANEUVERS LIMITS
This is an acrobatic category aircraft. For the following maneuvers the corresponding entry
speeds are recommended:
Barrel Roll Entry Speed: 180 KIAS
Aileron Roll : 180 KIAS
Wing Over : 180 KIAS
Looping : 200 KIAS
Half roll at top of the loop : 220 KIAS
Half Cuban Eight : 200 KIAS
Chandelle : 200 KIAS
Spin (cruise configuration only) : Stall + 5 KIAS
Spin with flaps down and inverted spins are prohibited.
Negative g flight is limited to 30 seconds.
When above maneuvering speed (Refer to Figure 2-1) the controls must not be fully abruptly
deflected.
2.9. FLIGHT MANEUVERING LOAD FACTOR LIMITS
d) Positive Load Factor (Flaps Up 7.0 g
e) Negative Load Factor (Flaps Up) -3.5 g
f) Positive Load Factor (Flaps Down
and / or Airbrakes Open) 3.5 g
2.10. FLIGHT CREW
Minimum Crew One Pilot
2.11. KINDS OF OPERATION
The standard airplane is approved for day and night operations under VFR conditions
provided the minimum equipment required for the applicable operational rules is installed.
NOTE
Whenever oxygen is required, mask type MBU-5/P or similar must be used to be interfaced with
aircraft provisions.
Oxygen masks are not part of the aircraft, they are part of the crew equipment.
The airplane has not been approved for flight in known icing conditions.
2.12. FUEL LIMITATION
g) Unusable Fuel Quantity
(for the complete system) 3 US Gal (11.5 lt)
h) Usable Fuel Quantity
(for the complete system) 110.6 US Gal (418 lt)
Fill the internal tanks before fueling the tip tanks.
Close the wing fueling points before fueling the tip tanks.
Before fueling Connect the earth cable of the fueling vehicle to the nose landing gear.

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2.13. MAXIMUM OPERATING ALTITUDE LIMIT
Flight up to 25’000 ft is approved if the aircraft is equipped with oxygen in accordance with
the applicable operational rules.
2.14. SEATING LIMITATION
The maximum number of occupants is two (including the pilot).
Pilot must seat in the side of flight instruments.
2.15. PLACARDS
In Full view of the pilot: