Tecnam P92-JS Technical specifications

P92-JS
I N T R O D U C T I O N
FLIGHT MANUAL
Date: Issue 3, 25th May 2010
i-1
FLIGHT MANUAL
Doc. n° 92/61 Issue n°3: 25th May 2010
Revision No.0
P92-JS
MANUFACTURER: COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
AIRCRAFT MODEL: P92-JS
TYPE CERTIFICATION: n° EASA A.412 (SO/A-340)
SERIAL NUMBER:............................................................….....
BUILD YEAR:..............................................................…….....
REGISTRATION MARKINGS: .......................................................
This manual contains information to be furnished to the pilot as required by EASA
in addition to further information supplied by manufacturer.
This manual must always be present on board the aircraft.
The aircraft is to be operated in compliance with information and limitations
contained herein.
Sections 2, 3, 4, 5 are approved by EASA: n° 10030344 on 11.06.2010
Section 9 (supp.1) is approved by EASA: n° 2004-1787 on 02.03.2004
Section 9 (supp. 2) is approved by EASA: n° 2004-6324 on 17.06.2004.
Section 9 (supp.3) is approved under DOA privileges: n° MOD92/51.10.06.2009
Section 9 (supp.4) is approved under DOA privileges: n° MOD92/52.10.06.2009
Section 9 (supp.5) is approved under DOA privileges: n° MOD92/53.10.06.2009

P92-JS
I N T R O D U C T I O N
FLIGHT MANUAL
Date: Issue 3, 25th May 2010
i-2
RECORD OF REVISIONS
Any revisions to the present Manual, except actual weighing data, must be
recorded in the following table and, in case of approved Sections, endorsed by the
responsible airworthiness authority.
New or amended text in the revised pages will be indicated by a black vertical line
in the left-hand margin; Revision No. and date will be shown on the left-hand side
of the page.
RECORD OF REVISIONS
Revision
No.
Affected
sections
Affected
pages
Date
Approval
EASA
Date
Date
Inserted
Signature

P92-JS
I N T R O D U C T I O N
FLIGHT MANUAL
Date: Issue 3, 25th May 2010
i-3
LIST OF EFFECTIVE PAGES
Section
Pages
Revision
Section 0
Pages 1 thru 4
Rev 0
Section 1
Pages 1 thru 12
Rev 0
Section 2
Pages 1 thru 10
Rev 0
Section 3
Pages 1 thru 8
Rev 0
Section 4
Pages 1 thru 12
Rev 0
Section 5
Pages 1 thru 14
Rev 0
Section 6
Pages 1 thru 12
Rev 0
Section 7
Pages 1 thru 16
Rev 0
Section 8
Pages 1 thru 4
Rev 0
Section 9
Pages 1 thru 24
Rev 0

P92-JS
I N T R O D U C T I O N
FLIGHT MANUAL
Date: Issue 3, 25th May 2010
i-4
TABLE OF CONTENTS
General
Section 1
Limitations
Section 2*
Emergency procedures
Section 3*
Normal procedures
Section 4*
Performance
Section 5**
Weight & Balance / Equipment list
Section 6
Aircraft and Systems description
Section 7
Aircraft handling, servicing and
maintenance
Section 8
Supplements
Section 9*
*Section approved by EASA
**Section partially approved by EASA

FLIGHT MANUAL
Date: Issue 3: 25th May2010
1-1
P92-JS
S E C T I O N 1
GENERAL
SECTION 1
GENERAL
TABLE OF CONTENTS
INTRODUCTION ......................................................................................................2
CERTIFICATION BASIS ..........................................................................................2
WARNINGS -CAUTIONS -NOTES ........................................................................2
THREE-VIEW DRAWING........................................................................................3
DESCRIPTIVE DATA...............................................................................................4
CONTROL SURFACES TRAVEL LIMITS ..............................................................4
ENGINE......................................................................................................................5
PROPELLER..............................................................................................................5
FUEL ..........................................................................................................................6
OIL SYSTEM .............................................................................................................6
COOLING...................................................................................................................6
MAXIMUM CERTIFIED WEIGHTS........................................................................7
STANDARD WEIGHTS............................................................................................7
SPECIFIC LOADINGS ..............................................................................................7
ABBREVIATIONS AND TERMINOLOGY.............................................................8
UNIT CONVERSION CHART ................................................................................11

FLIGHT MANUAL
Date: Issue 3: 25th May2010
I-2
P92-JS
S E C T I O N 1
GENERAL
INTRODUCTION
The P92-JS is a twin seat single engine aircraft with a strut-braced
rectangular high wing, fixed main landing gear and steerable nosewheel.
This Flight Manual has been prepared to provide pilots and instructors with
information for the safe and efficient operation of this aircraft.
This Flight Manual contains 9 sections. Section 1 provides basic data and
information of general interest. It also contains definitions and explanations
of symbols, abbreviations and commonly used terminology.
CERTIFICATION BASIS
Aircraft
This type of aircraft has been approved by EASA/ENAC in accordance
with JAR-VLA of April 26 1990 with amendments 91/1 and 92/1.
Noise Certification Basis
JAR-36 Sub. C Issue: 23 May 1997 ICAO/Annex 16 Chap.10 issue 1993
WARNINGS - CAUTIONS - NOTES
The following definitions apply to warnings, cautions and notes used in
the Flight Manual.
Means that the non-observation of the
corresponding procedure leads to an immediate or
important degradation of the flight safety.
Means that the non-observation of the corresponding
procedure leads to a minor or to a more or less long
term degradation of the flight safety.
Draws the attention to any special item not directly
related to safety but which is important or unusual.
WARNING
CAUTION
NOTE

FLIGHT MANUAL
Date: Issue 3: 25th May2010
1-3
P92-JS
S E C T I O N 1
GENERAL
THREE-VIEW DRAWING
Dimensions shown refer to aircraft weight of 550kg (and 600 kg) and
normal operating tire pressure.
Propeller ground clearance 320mm
Propeller ground clearance with deflated front tire and nosewheel
shock absorber compressed by 102mm
Minimum ground steering radius 5.5m
NOTE

FLIGHT MANUAL
Date: Issue 3: 25th May2010
I-4
P92-JS
S E C T I O N 1
GENERAL
DESCRIPTIVE DATA
WING
For 550 kg
MTOW
For 600 kg
MTOW
Wing span:
8.7 m
8.7 m
Wing chord
1.4 m
1.4 m
Wing surface
12 m2
12 m2
Wing loading
45.8 kg/m2
50.0 kg/m2
Aspect ratio
6.31
6.31
Taper ratio
1.0
1.0
Dihedral
1.5°
1.5°
FUSELAGE
Overall length
6.400 m
6.400 m
Overall width
1.100 m
1.100 m
Overall height
2.500 m
2.500 m
EMPENNAGE
Stabilator span
2.900 m
2.900 m
Vertical tail span
1.230 m
1.230 m
LANDING GEAR
Wheel track:
1.800 m
1.800 m
Wheel base:
1.600 m
1.600 m
Main gear tires: Air Trac;
Cleveland wheel hub and brakes kit:
5.00-5
199-102
5.00-5
199-102
Nose gear tire: Sava
4.00-6
4.00-6
CONTROL SURFACES TRAVEL LIMITS
Ailerons
Up 20° down 15 ° 2°
Stabilator
Up 18° down 3° 1°
Trim-Tab
2° ; 12° 1°
Rudder
RH 25° LH 25° 1°
Flaps
0° -38° 1°

FLIGHT MANUAL
Date: Issue 3: 25th May2010
1-5
P92-JS
S E C T I O N 1
GENERAL
ENGINE
Manufacturer:
Bombardier-Rotax GmbH
Model
912 S2
Certification basis
FAR 33 Amendment 15
Austrian Type-
Certification No.
n° TW 9-ACG of 27 Nov. 1998
Type:
4 cylinder horizontally-opposed twins with
overall displacement of 1352 c.c., mixed
cooling, (water-cooled heads and air-
cooled cylinders), twin carburettors,
integrated reduction gear with torque
damper.
Maximum power:
(engine’s rpm)
73.5 kW (98.6 hp) @ 5800 rpm (max.5 min.)
69.0 kW (92.5 hp) @ 5500 rpm (continuous)
PROPELLER
Manufacturer:
HOFFMANN Propeller
Certification basis:
CAR Part 14
Type-Certification No.:
SO/E 30 of 10/12/1999
Model:
HO17GHM A 174 177C
Number of blades:
2
Diameter:
1740 mm (no reduction permitted)
Type:
Fixed pitch - wood

FLIGHT MANUAL
Date: Issue 3: 25th May2010
I-6
P92-JS
S E C T I O N 1
GENERAL
FUEL
Fuel grade:
High octane gasoline DIN 51600,
O-NORM 1103 (red)
Unleaded gasoline DIN 51603,
O-NORM 1101
AVGAS 100LL (see Section 2.9)
Fuel tanks:
2 wing tanks integrated within the
wing's leading edge with fuel
strainer located in engine cowling.
Capacity of each wing tank
35 liters (optional 45 liters)
Total capacity:
70 liters (optional 90 liters)
Total usable fuel
66.8 liters. (86.8 liters)
OIL SYSTEM
Oil system type:
Forced, with external oil
reservoir
Oil:
Automotive grade API "SF" or
"SG" type oil preferably synthetic
or semi-synthetic
Oil Capacity:
3.5 liters
COOLING
Cooling system:
Mixed air and liquid
pressurized closed circuit
system
Coolant:
Antifreeze and water liquid
mixture
Capacity
3 liters

FLIGHT MANUAL
Date: Issue 3: 25th May2010
1-7
P92-JS
S E C T I O N 1
GENERAL
For 550 kg
MTOW
For 600 kg
MTOW
MAXIMUM CERTIFIED WEIGHTS
Maximum take-off weight:
550 kg
600 kg
Maximum landing weight:
550 kg
600 kg
Maximum baggage weight
20 kg
20 kg
STANDARD WEIGHTS
Standard Empty Weight
325 kg
325 kg
Maximum Useful Load
225 kg
275 kg
SPECIFIC LOADINGS
Wing Loading
45.8 kg/m2
50 kg/m2
Power Loading
5.6 kg/hp
6.1 kg/hp

FLIGHT MANUAL
Date: Issue 3: 25th May2010
I-8
P92-JS
S E C T I O N 1
GENERAL
ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
Knots Calibrated Airspeed is indicated airspeed corrected
for position and instrument error and expressed in knots.
KIAS
Knots Indicated Airspeed is the speed shown on the airspeed
indicator and expressed in knots.
KTAS
Knots True Airspeed is the airspeed expressed in knots
relative to undisturbed air which is KCAS corrected for
altitude and temperature.
VFE
Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended
position.
VNO
Maximum Structural Cruising Speed is the speed that should
not be exceeded except in smooth air, then only with
caution.
VNE
Never Exceed Speed is the speed limit that may not be
exceeded at any time.
VS
Stalling Speed.
VS0
Stalling speed in landing configuration
VS1
Stalling speed in clean configuration (flap 0°)
VX
Best Angle-of-Climb Speed is the speed which results in the
greatest gain of altitude in a given horizontal distance.
VY
Best Rate-of-Climb Speed is the speed which results in the
greatest gain in altitude in a given time.
Vr
Rotation speed: is the speed at which the aircraft rotates
about the pitch axis during takeoff
VLO
Lift off speed: is the speed at which the aircraft generally
lifts off from the ground.
Vobs
Obstacle speed: is the speed at which the aircraft flies over a
15m obstacle during takeoff or landing

FLIGHT MANUAL
Date: Issue 3: 25th May2010
1-9
P92-JS
S E C T I O N 1
GENERAL
METEOROLOGICAL TERMINOLOGY
OAT
Outside Air Temperature is the free air static temperature
expressed in degrees Celsius (°C).
TS
Standard Temperature is 15°C at sea level pressure altitude
and decreased by 2°C for each 1000 ft of altitude.
HP
Pressure Altitude is the altitude read from an altimeter when
the barometric subscale has been set to 1013 mb.
ENGINE POWER TERMINOLOGY
RPM
Revolutions Per Minute: is the number of revolutions per
minute of the propeller, multiplied by 2.4286 yields engine
RPM.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
Crosswind
Velocity
is the velocity of the crosswind component for which
adequate control of the airplane during takeoff and landing
is guaranteed.
Usable fuel
is the fuel available for flight planning.
Unusable fuel
is the quantity of fuel that cannot be safely used in flight..
g
is the acceleration of gravity.
TOR
is the takeoff distance measured from actual start to wheel
liftoff point
TOD
is total takeoff distance measured from start to 15m obstacle
clearing
GR
is the distance measured during landing from actual
touchdown to stop point
LD
is the distance measured during landing, from 15m obstacle
clearing to actual stop.
S/R
is specific range, that is, the distance (in nautical miles)
which can be expected at a specific power setting and/or
flight configuration per kilo of fuel used.

FLIGHT MANUAL
Date: Issue 3: 25th May2010
I-10
P92-JS
S E C T I O N 1
GENERAL
WEIGHT AND BALANCE TERMINOLOGY
Datum
is an imaginary vertical plane from which all horizontal
distances are measured for balance purposes.
Arm
is the horizontal distance from the reference datum to the
center of gravity (C.G.) of an item.
Moment
is the product of the weight of an item multiplied by its arm.
C. G.
Center of Gravity is the point at which the airplane, or
equipment, would balance if suspended. Its distance from
the reference datum is found by dividing the total moment
by the total weight of the airplane.
Standard
Empty
Weight
Standard Empty Weight is the weight of a standard airplane,
including unusable fuel, full operating fuels and full engine
oil.
Basic Empty
Weight
is the standard empty weight plus the weight of optional
equipment.
Useful Load
is the difference between takeoff weight and the basic empty
weight.
Maximum
Weight
is the maximum certified weight of the aircraft.
Maximum
Takeoff
Weight
is the maximum weight approved for the start of the takeoff
run.
Maximum
Landing
Weight
is the maximum weight approved for the landing touch
down.
Tare
is the weight of chocks, blocks, stands, etc. used when
weighing an airplane, and is included in the scale readings.
Tare is deducted from the scale reading to obtain the actual
(net) airplane weight.

FLIGHT MANUAL
Date: Issue 3: 25th May2010
1-11
P92-JS
S E C T I O N 1
GENERAL
UNIT CONVERSION CHART
MULTIPLYING
BY 
YIELDS
TEMPERATURE
Fahrenheit
[°F]
 
5
932 F
Celsius
[°C]
Celsius
[°C]
9
532




C
Fahrenheit
[°F]
FORCES
Kilograms
[kg]
2.205
Pounds
[lbs]
Pounds
[lbs]
0.4536
Kilograms
[kg]
SPEED
Meters per second
[m/s]
196.86
Feet per minute
[ft/min]
Feet per minute
[ft/min]
0.00508
Meters per second.
[m/s]
Knots
[kts]
1.853
Kilometers / hour
[km/h]
Kilometers / hour
[km/h]
0.5396
Knots
[kts]
PRESSURE
Atmosphere
[atm]
14.7
Pounds / sq. in
[psi]
Pounds / sq. in
[psi]
0.068
Atmosphere
[atm]
LENGTH
Kilometers
[km]
0.5396
Nautical miles
[nm]
Nautical miles
[nm]
1.853
Kilometers
[km]
Meters
[m]
3.281
Feet
[ft]
Feet
[ft]
0.3048
Meters
[m]
Centimeters
[cm]
0.3937
Inches
[in]
Inches
[in]
2.540
Centimeters
[cm]
VOLUME
Liters
[l]
0.2642
U.S. Gallons
[US Gal]
U.S. Gallons
[US Gal]
3.785
Liters
[l]
AREA
Square meters
[m2]
10.76
Square feet
[sq ft]
Square feet
[sq ft]
0.0929
Square meters
[m2]

FLIGHT MANUAL
Date: Issue 3: 25th May2010
I-12
P92-JS
S E C T I O N 1
GENERAL
INTENTIONALLY LEFT BLANK

FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-1
P92-JS
S E C T I O N 2
LIMITATIONS
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
INTRODUCTION ......................................................................................................2
AIRSPEED LIMITATIONS.......................................................................................2
AIRSPEED INDICATOR MARKINGS.....................................................................3
POWERPLANT LIMITATIONS...............................................................................4
PROPELLER..............................................................................................................5
POWERPLANT INSTRUMENT MARKINGS.........................................................6
OTHER INSTRUMENT MARKINGS ......................................................................6
WEIGHTS ..................................................................................................................7
CENTER OF GRAVITY RANGE .............................................................................7
APPROVED MANEUVERS......................................................................................8
MANEUVERING LOAD FACTOR LIMITS............................................................8
FLIGHT CREW..........................................................................................................8
KINDS OF OPERATION...........................................................................................9
FUEL ..........................................................................................................................9
MAXIMUM PASSENGER SEATING ....................................................................10
CROSSWIND LIMITATIONS ................................................................................10
LIMITATION PLACARDS .....................................................................................10

FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-2
P92-JS
S E C T I O N 2
LIMITATIONS
INTRODUCTION
Section 2 includes operating limitations, instrument markings, and basic
placards necessary for safe operation of the P92-JS, its engine, standard
systems and standard equipment.
Refer to section 9 for possible variations to:
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown below:
S P E E D
550 kg
MTOW
600 kg
MTOW
REMARKS
KIAS
KCAS
KIAS
KCAS
VNE
Never exceed
speed
134
128
141
135
Never exceed this
speed in any operation.
VNO
Maximum
Structural
Cruising Speed
106
102
110
106
Never exceed this
speed unless in smooth
air, and then only with
caution.
VA
Maneuvering
speed
93
90
97
94
Do not make full or
abrupt control
movements above this
speed as this may cause
stress in excess of limit
load factor
VFE
Maximum flap
extended speed
68
66
71
69
Never exceed this
speed for any given
flap setting.
NOTE

FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-3
P92-JS
S E C T I O N 2
LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code are explained in the following
table
Refer to section 9 of this Flight Manual for operational limitations for aircraft
fitted with optional equipment.
MARKING
550 kg
MTOW
600 kg
MTOW
SIGNIFICANCE
KIAS
White arc
43*- 68
41 - 71
Positive Flap Operating Range (lower limit
is VSO, at maximum weight and upper limit
is maximum speed permissible with flaps
extension to maximum positive)
Green arc
48*–106
46 - 110
Normal Operating Range (lower limit is VS1
at maximum weight and most forward c.g.
with flaps retracted and upper limit is
maximum structural speed VNO).
Yellow
arc
106 - 134
110- 141
Maneuvers must be conducted with caution
and only in smooth air.
Red line
134
141
Maximum speed for all operations.
For P92-JS with MTOW = 550kg the low limit of the white
arc is 1.1 VS0 while the low limit of the green arc is 1.1VS1
CAUTION

FLIGHT MANUAL
Date: Issue 3: 25th May 2010
2-4
P92-JS
S E C T I O N 2
LIMITATIONS
POWERPLANT LIMITATIONS
The following table lists operating limitations for aircraft installed engine:
ENGINE MANUFACTURER: Bombardier Rotax GmbH.
ENGINE MODEL: 912 S2
MAXIMUM POWER: (see table below)
Max Power
kW (hp)
Max RPM.
RPM prop (eng.)
Time max.
(min.)
Maximum
73.5 (98.6)
2388 (5800)
5
Max cont.
69 (92.5)
2265 (5500)
-
The static rpm range at full throttle (carburetors heat: Off) is 2100 100 prop.
rpm.
TEMPERATURES:
Max cylinder heads
135° C
Cooling liquid, monitored at cylinder heads
135° C
Max Oil:
130° C
Min Oil
50° C
OIL PRESSURE:
Min
0.8 bar
Max
5 bar
ENGINE START, OPER. TEMP:
OAT Min
-25° C
OAT Max
+50° C
Admissible pressure for cold start is 7 bar maximum for short periods.
WARNING
NOTE