Tecnam P92 Eaglet Technical specifications

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
1
FLIGHT MANUAL
US-LSA
P92 Eaglet
Manufacturer
COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
Type Certificate: ASTM SLSA
Serial number: ________________
Build year: ___________________
Registration:__________________
Introduction
This manual contains information to be furnished to the pilot as required by the FAA in addition to further information
supplied by the 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. All sections follow the
ASTM guidelines as finalized 14 December 2007.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
2
Record of Revisions
Any revisions to the present Manual, except actual weighing data, must be recorded in the following table.
New or amended text in the revised pages will be indicated by a black vertical line in the left-hand margin; Revision
Number, and date will be shown on the right-hand side of the amended page.
Log of Revisions
Revision No. Date released Chapters Approved By
1.0 12-14-2007 All Tecnam

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
3
List of Effective Pages
Page Date Page Date Page Date
1 12-14-2007 36 12-14-2007
2 12-14-2007 37 12-14-2007
3 12-14-2007 38 12-14-2007
4 12-14-2007 39 12-14-2007
5 12-14-2007 40 12-14-2007
6 12-14-2007 41 12-14-2007
7 12-14-2007 42 12-14-2007
8 12-14-2007 43 12-14-2007
9 12-14-2007 44 12-14-2007
10 12-14-2007 45 12-14-2007
11 12-14-2007 46 12-14-2007
12 12-14-2007 47 12-14-2007
13 12-14-2007 48 12-14-2007
14 12-14-2007 49 12-14-2007
15 12-14-2007 50 12-14-2007
16 12-14-2007 51 12-14-2007
17 12-14-2007 52 12-14-2007
18 12-14-2007 53 12-14-2007
19 12-14-2007 54 12-14-2007
20 12-14-2007 55 12-14-2007
21 12-14-2007 56 12-14-2007
22 12-14-2007 57 12-14-2007
23 12-14-2007 58 12-14-2007
24 12-14-2007 59 12-14-2007
25 12-14-2007 60 12-14-2007
26 12-14-2007 61 12-14-2007
27 12-14-2007 62 12-14-2007
28 12-14-2007 63 12-14-2007
29 12-14-2007 64 12-14-2007
30 12-14-2007 65 12-14-2007
31 12-14-2007
32 12-14-2007
33 12-14-2007
34 12-14-2007
35 12-14-2007

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
4
Table of Contents
Unit Conversion Chart................................................................................................................................................... 10
SECTION 1 GENERAL........................................................................................................................................................ 11
1.1 Introduction............................................................................................................................................................ 11
1.2 Certification Basis.................................................................................................................................................. 11
1.3 Descriptive Data..................................................................................................................................................... 13
1.3.1 Airframe.......................................................................................................................................................... 13
1.4 Powerplant ............................................................................................................................................................. 13
1.4.1 Engine............................................................................................................................................................. 13
1.4.2 Propeller......................................................................................................................................................... 13
1.4.3 Oil System....................................................................................................................................................... 14
1.4.4 Cooling........................................................................................................................................................... 14
1.4.5 Fuel................................................................................................................................................................. 14
1.5 Weights................................................................................................................................................................... 14
1.5.1 Maximum Weights.......................................................................................................................................... 14
1.5.2 Standard Weights............................................................................................................................................ 14
1.5.3 Specific Loadings............................................................................................................................................ 14
1.6 Standard Equipment............................................................................................................................................... 15
1.6.1 Flight Instruments .......................................................................................................................................... 15
1.6.2 Engine instruments......................................................................................................................................... 15
1.6.3 Warning Lights and Indicators....................................................................................................................... 15
1.6.4 Controls.......................................................................................................................................................... 15
1.6.5 Interior............................................................................................................................................................ 15
1.6.6 Exterior........................................................................................................................................................... 15
1.6.7 Powerplant and Accessories........................................................................................................................... 15
1.7 Airframe ................................................................................................................................................................. 16
1.7.1 Wing ............................................................................................................................................................... 16
1.7.2 Fuselage ......................................................................................................................................................... 16
1.7.3 Empennage..................................................................................................................................................... 16
1.7.4 Flight controls................................................................................................................................................ 16
1.7.5 Instrument Panel ............................................................................................................................................ 17
1.7.6 Carburetor Heat............................................................................................................................................. 17
1.7.7 Cabin Heat / Defrost ...................................................................................................................................... 17
1.7.8 Throttle Friction Lock .................................................................................................................................... 17
1.7.9 Seats, Seatbelts, and Shoulder harnesses....................................................................................................... 17
1.7.10 Doors.............................................................................................................................................................. 18
1.7.11 Baggage compartment.................................................................................................................................... 18
1.8 Powerplant ............................................................................................................................................................. 18
1.8.1 Engine............................................................................................................................................................. 18
1.8.2 Propeller......................................................................................................................................................... 18
1.8.3 Fuel system..................................................................................................................................................... 19
1.9 Electrical System.................................................................................................................................................... 21
1.9.1 Generator light............................................................................................................................................... 21
1.9.2 Voltmeter ........................................................................................................................................................ 21
1.9.3 Oil temperature gauge.................................................................................................................................... 22
1.9.4 Cylinder head temperature............................................................................................................................. 22
1.9.5 Oil Pressure.................................................................................................................................................... 22

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
5
1.9.6 Fuel Pressure ................................................................................................................................................. 22
1.9.7 O.A.T. Indicator.............................................................................................................................................. 22
1.9.8 Stall Warning System...................................................................................................................................... 22
1.9.9 Avionics .......................................................................................................................................................... 22
1.9.10 Exterior Lighting............................................................................................................................................ 22
1.10 Pitot and Static Pressure Systems .......................................................................................................................... 23
1.11 Landing Gear ......................................................................................................................................................... 24
1.11.1 Brake System .................................................................................................................................................. 25
SECTION 2 OPERATING LIMITATIONS......................................................................................................................... 26
2 Introduction................................................................................................................................................................... 26
2.1.1 Airspeed Limitations....................................................................................................................................... 26
2.1.2 Airspeed Indicator Markings.......................................................................................................................... 26
2.1.3 Powerplant Limitations .................................................................................................................................. 27
2.1.4 Temperatures.................................................................................................................................................. 27
2.1.5 Oil Pressure.................................................................................................................................................... 27
2.1.6 Operating & starting temperature range ....................................................................................................... 27
2.1.7 Fuel Pressure ................................................................................................................................................. 27
2.1.8 Lubricant........................................................................................................................................................ 28
2.1.9 Coolant........................................................................................................................................................... 28
2.1.10 Propeller......................................................................................................................................................... 28
2.1.11 Fuel................................................................................................................................................................. 28
2.1.12 Approved Fuel................................................................................................................................................ 29
2.1.13 Powerplant Instrument Markings................................................................................................................... 29
2.1.14 Other Instrument Markings............................................................................................................................ 29
2.1.15 Weights........................................................................................................................................................... 29
2.1.16 Center of Gravity Limits................................................................................................................................. 29
2.1.17 Approved Maneuvers...................................................................................................................................... 30
2.1.18 Maneuvering Load Factor Limits................................................................................................................... 30
2.1.19 Flight Crew..................................................................................................................................................... 30
2.1.20 Kinds of Operations........................................................................................................................................ 30
2.1.21 Day VFR......................................................................................................................................................... 31
2.1.22 Night............................................................................................................................................................... 31
2.1.23 IFR.................................................................................................................................................................. 31
2.1.24 Demonstrated Crosswind Safe Operations..................................................................................................... 31
2.1.25 Service Ceiling................................................................................................................................................ 31
2.1.26 Limitation Placards........................................................................................................................................ 31
3 Introduction................................................................................................................................................................... 32
3.1 Aircraft weighing procedures................................................................................................................................. 32
3.1.1 Preparation .................................................................................................................................................... 32
3.1.2 Calculate empty weight Weighing.................................................................................................................. 32
3.1.3 Determination of C.G. location...................................................................................................................... 32
3.2 Weighing report...................................................................................................................................................... 33
3.2.1 Center of Gravity Limits................................................................................................................................. 33
3.2.2 Distances from the datum............................................................................................................................... 34
3.3 Weight and Balance................................................................................................................................................ 35
3.3.1 Loading........................................................................................................................................................... 37
3.4 Equipment List........................................................................................................................................................ 37

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
6
SECTION 4 PERFORMANCE ............................................................................................................................................ 39
4 Introduction................................................................................................................................................................... 39
4.1 Use of Performance Charts.................................................................................................................................... 39
4.2 Airspeed Indicator System Calibration .................................................................................................................. 40
4.3 ICAO Chart ............................................................................................................................................................ 41
4.4 Stall Speeds............................................................................................................................................................. 42
4.5 Crosswind............................................................................................................................................................... 43
4.6 Takeoff Performance .............................................................................................................................................. 44
4.7 Landing Distance ................................................................................................................................................... 45
4.8 Climb Performance ................................................................................................................................................ 46
4.9 Cruise ..................................................................................................................................................................... 47
4.10 Balked Landing....................................................................................................................................................... 48
4.11 Effects of Rain and Insects ..................................................................................................................................... 48
4.12 Noise Data.............................................................................................................................................................. 48
SECTION 5 EMERGENCY PROCEDURES ...................................................................................................................... 49
5 Introduction................................................................................................................................................................... 49
5.1 Engine Failures...................................................................................................................................................... 50
5.1.1 Engine Failures on Ground............................................................................................................................ 50
5.1.2 Engine Failure during Flight ......................................................................................................................... 50
5.2 Smoke and Fire....................................................................................................................................................... 51
5.2.1 Engine Fire while parked ............................................................................................................................... 51
5.2.2 Engine Fire during Takeoff ............................................................................................................................ 51
5.2.3 Engine Fire in-flight....................................................................................................................................... 51
5.2.4 Cabin Fire during Flight................................................................................................................................ 52
5.3 Landing Emergency................................................................................................................................................ 52
5.4 Recovery from Unintentional Spin ......................................................................................................................... 53
5.5 Other Emergencies................................................................................................................................................. 53
5.5.1 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS ............................................................................ 53
5.5.2 Carburetor Ice................................................................................................................................................ 53
5.6 Electric Power System Malfunction ....................................................................................................................... 54
5.6.1 GENERATOR LIGHT ILLUMINATES........................................................................................................... 54
5.7 Trim System Failure ............................................................................................................................................... 54
5.7.1 LOCKED CONTROL ..................................................................................................................................... 54
SECTION 6 NORMAL PROCEDURES.............................................................................................................................. 55
6 Introduction................................................................................................................................................................... 55
6.1 Removing and Reinstalling the Engine Cowling .................................................................................................... 55
6.1.1 Upper Cowling ............................................................................................................................................... 55
6.1.2 Lower Cowling ............................................................................................................................................... 55

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
7
6.2 Checklist Procedures.............................................................................................................................................. 56
6.2.1 Pre-Flight Inspection...................................................................................................................................... 56
SECTION 7 GROUND HANDLING & SERVICE ............................................................................................................. 62
7 Introduction................................................................................................................................................................... 62
7.1 Aircraft Inspection Periods .................................................................................................................................... 62
7.2 Aircraft Alterations or Repairs............................................................................................................................... 62
7.3 Ground Handling ................................................................................................................................................... 62
7.3.1 Towing............................................................................................................................................................ 62
7.3.2 Parking and Tiedown ..................................................................................................................................... 62
7.3.3 Jacking............................................................................................................................................................ 62
7.3.4 Leveling .......................................................................................................................................................... 62
7.3.5 Road Transport............................................................................................................................................... 63
7.3.6 Cleaning and Care ......................................................................................................................................... 63
7.3.7 Ground anchorage.......................................................................................................................................... 63
8 Placards and Markings ................................................................................................................................................. 64
WARNINGS - CAUTIONS - NOTES
The following definitions apply to warnings, cautions and notes used in the Flight Manual.
WARNING
Means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight
safety
CAUTION
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
NOTE
Draws the attention to any special item not directly related to safety but which is important or unusual.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
8
Abbreviations & Terminology
Airspeed Terminology
KCAS Calibrated Airspeed is the indicated airspeed corrected for position and
instrument error and expressed in knots.
KIAS Indicated Airspeed is the speed shown on the airspeed indicator and
expressed in knots.
KTAS True Airspeed is the airspeed expressed in knots relative to undisturbed
air, which is KCAS, corrected for altitude and temperature.
V
A
Design maneuvering speed
V
C
Design cruising speed
V
FE
Maximum Flap Extended Speed is the highest speed permissible with
wing flaps in a prescribed extended position.
V
H
Max Speed in level flight with Max continuous power
V
LO
Lift off speed: is the speed at which the aircraft generally lifts off from the
ground.
V
NE
Never Exceed Speed is the speed limit that may not be exceeded at any
time.
V
NO
Maximum Structural Cruising Speed is the speed that should not be
exceeded except in smooth air, then only with caution.
V
S
Stalling Speed or minimum steady flight speed flaps retracted
V
S0
Stalling speed or minimum steady flight speed in landing configuration
V
S1
Stalling speed in clean configuration (flap 0°)
V
X
Best Angle-of-Climb Speed is the speed, which results in the greatest gain
of altitude in a given horizontal distance.
V
Y
Best Rate-of-Climb Speed is the speed, which results in the greatest gain
in altitude in a given time.
V
R
Rotation speed: is the speed at which the aircraft rotates about the pitch
axis during takeoff.
Meteorology Terminology
OAT Outside Air Temperature is the free air static temperature expressed in
degrees Celsius (°C).
T
S
Standard Temperature is 15°C (59°F) at sea level pressure altitude and
decreased by 2°C for each 1000 ft of altitude.
H
P
Pressure Altitude is the altitude read from an altimeter when the
barometric subscale has been set to 29.92”
Engine Power Terminology
RPM Revolutions Per Minute: is the number of revolutions per minute of the
propeller, multiplied by 2.4286 yields engine RPM.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
9
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 lift off point
TOD is total takeoff distance measured from start to clearing a 50’ obstacle
GR is the distance measured during landing from actual touchdown to stop point
LD is the distance measured during landing, from clearing a 50’ obstacle 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 gallon of fuel used
Weight and Balance Terminology
Datum “Reference 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
Empty Weight Empty Weight is the weight of the airplane with engine fluids and oil at
operating levels
Useful Load is the difference between takeoff weight and the empty weight
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 then deducted from the scale
reading to obtain the actual (net) airplane weight

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
10
Unit Conversion Chart
Multiplying by Yields
Temperature
Fahrenheit [°F]
( )
5
9
32⋅ −FCelsius [°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 [m
2
] 10.76 Square feet [sq ft]
Square feet [sq ft] 0.0929 Square meters [m
2
]
Torque
foot-pounds 1.3558 Newton-meters
foot-pounds 0.1383 kilogram-meters
foot-pounds 12.0 inch-pounds
inch-pounds 0.0115 kilogram-meters
inch-pounds 0.1130 Newton-meters
inch-pounds 0.0833 foot-pounds
kilogram-meters 7.233 foot-pounds
kilogram-meters 86.7964 inch-pounds
kilogram-meters 9.8067 Newton-meters
Newton-meters 0.7376 foot-pounds
Newton-meters 8.8508 inch-pounds
Newton-meters 0.1020 kilogram-meter

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
11
SECTION 1
GENERAL
1.1 Introduction
The P92 Eaglet is an all metal, high wing, two-place, single-engine airplane equipped with tricycle landing gear. It is an
ASTM compliant airplane designed to be flown by sport pilot rated pilots as well as higher rated pilots.
This aircraft is designed and built in Italy and as such, was built using the metric system. Therefore, the primary numbers
are in metric and the US conversion is in parenthesis for your information.
This Flight Manual has been prepared to ASTM standards to provide pilots and instructors with information for the safe
and efficient operation of this aircraft.
This Flight Manual contains the following sections:
1. General Information
2. Operating Limitations
3. Weight & Balance
4. Performance
5. Emergency Procedures
6. Normal Procedures
7. Aircraft Ground Handling and Servicing
8. Required Placards and Markings
1.2 Certification Basis
This aircraft is certificated as a Special Light Sport Aircraft under FAR part 21.190 and complies with all applicable ASTM
standards.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
12
THREE VIEW DRAWING
Figure 1-1 General Views
Wing Span 8.7m (28.5’)
Length 6.5m (21,3’)
Tail height 2.5m (8.2’)
Propeller ground clearance 320mm (12.6”)
Minimum ground steering radius 5.5m (18’)
NOTE
•Dimensions shown refer to aircraft weight of 600 kg (1320 lbs) and normal operating tire pressure

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
13
1.3 Descriptive Data
1.3.1 Airframe
1.3.1.1 Wing
Wing span 8.7m (28.5’)
Wing area 12 m
2
(129 sq ft)
Aspect ratio 6.31
Taper ratio 1.00
Dihedral 1.5º
Wing chord 1.400 m (4.6’)
1.3.1.2 Fuselage
Overall length 6.5m (21,3’)
Overall width 1.143 m (45”)
Overall height 2.5m (8.2’)
1.3.1.3 Empennage
Stabilator span 2.9 m (9.5’)
Stabilator area 1.972 m
2
(21.2 ft
2
)
1.3.1.4 Landing Gear
Wheel track 1.8 m (5.9’)
Wheel base 1.6 m (5.2’)
Main gear tires Air Trac 5.00-5
Nose gear tire Sava 4.00-6
Wheel brakes Marc Ingegno 199-102
1.4 Powerplant
1.4.1 Engine
Manufacturer Bombardier-Rotax GmbH
Model 912 ULS or 912 S2
Certification basis ASTM F2239 or FAR Part 33
Type 4 stroke carburetor engine
Maximum power 73.5 kW (98.5 hp) @ 5800 rpm (max. 5 minutes)
69.0 kW (92.5 hp) @ 5500 rpm (cont.)
1.4.2 Propeller
Manufacturer GT Tonini
Model GT-2/173/VRR- FW101 SRTC
Number of blades 2
Diameter 1730 mm (68”) (no reduction permitted)
Type Fixed pitch – wood / composite

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
14
1.4.3 Oil System
Oil system Forced, with external oil reservoir
Oil See Rotax operator’s manual
Oil Capacity Max. 3.0 liters (3.2 qt) – min. 2.0 liters (2.1 qt)
1.4.4 Cooling
Cooling system: Combination air and liquid cooled system
Coolant: See Rotax operator’s manual
Capacity 3.0 liters (3.17 quarts)
1.4.5 Fuel
Fuel grade:
Auto fuel
Avgas
Min. RON 95 (AKI 91 Premium USA)
100LL
Fuel tanks 2 integral wing tanks
Capacity of each wing tank 45 liters (11.9 gal)
Total capacity 90 liters (23.8 gal)
Total usable fuel 86.8 liters (22.9 gal)
1.5 Weights
1.5.1 Maximum Weights
Maximum take-off weight: 600 kg (1320 lbs)
Maximum landing weight: 600 kg (1320 lbs)
Maximum baggage weight 20 kg (44 lbs)
1.5.2 Standard Weights
Empty weight 325 kg (715 lb)
Maximum payload weight 275 kg (605 lb)
1.5.3 Specific Loadings
Wing Loading 50 kg/m
2
(10.23 lb/ft
2
)
Power Loading 6,1 kg/hp (13.5 lb/hp)
NOTE
Standard weights are estimates based on standard equipment.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
15
1.6 Standard Equipment
1.6.1 Flight Instruments
Airspeed Indicator, Altimeter, Vertical Speed Indicator, Compass
1.6.2 Engine instruments
Tachometer, Oil Pressure, Fuel Pressure, Oil Temperature, Cylinder Head Temperature, Hour Meter, Left and
Right Fuel Quantity, Volt Meter
1.6.3 Warning Lights and Indicators
Trim Indicator, Flap Indicator, Generator Warning Light
1.6.4 Controls
Dual Stick Flight Controls and Rudder Pedals, Dual Throttles, Throttle Friction Control, Engine Choke, Electric
Flaps, Hydraulic Disc Brakes with Parking Brake, Left and Right Fuel Selector Valves, Direct Nose Wheel
Steering
1.6.5 Interior
Adjustable Pilot and Copilot Seats, Acoustic Cabin Soundproofing, Adjustable Cabin Air Ventilators, Steel Roll
Cage, Cabin Heat and Windshield Defrost, 12V Power Outlet, Metal Instrument Panel
1.6.6 Exterior
All Aluminum structure, Landing Light, Strobe Light, Fixed Landing Gear, Nose Gear Strut Fairing, Nose and
Main Wheel Fairings
1.6.7 Powerplant and Accessories
Rotax 912 ULS Engine (100 hp), Composite Covered Wood Propeller with Spinner, 12Volt 18 Ah Battery, 18
Amp Alternator, Engine Driven Fuel Pump, Electric Starter, Engine Exhaust Muffler, Gascolator with Quick
Drain, Integral Wing Fuel Tanks, All Electric Circuits Fuse Protected

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
16
1.7 Airframe
1.7.1 Wing
The wing is constructed of a central light alloy torque box; an aluminum leading edge with integrated fuel tank is attached
to the front spar while flap and aileron are hinged to rear spar. Flaps are constructed of a center spar to which front and rear
ribs are joined; wrap-around aluminum skin panels cover the flap structure. The aileron is constructed of an aluminum spar
to which a formed sheet metal leading edge and metal ribs are attached; a wrap-around. Aluminium material covers aileron
structure.
1.7.2 Fuselage
The front part of the fuselage is made up of a mixed structure: a truss structure with special steel members for cabin
survival cell, and a light-alloy semi-monocoque structure for the cabin's bottom section. The aft part of the fuselage is
constructed of an aluminum alloy semi-monocoque structure. The engine housing is isolated from the cabin by a stainless
steel firewall; the steel stringers engine mount is attached to the cabin's truss structure in four points.
1.7.3 Empennage
The vertical tail is entirely metal: the vertical stabilizer is made up of a twin spar with load carrying skin while the rudder
consists of an aluminum torque stringer connected to light alloy ribs and skin. The horizontal tail is an all-moving type
(stabilator); its structure consists of an aluminum spar connected to ribs and leading edge; the entire structure is covered
with aluminum material.
1.7.4 Flight controls
The control surfaces are manually operated using a control stick for ailerons and stabilator and rudder pedals for the rudder;
longitudinal control acts through a system of push-rods and is equipped with a trim tab. Aileron control is of mixed type
with push-rods and cables; the cable control circuit is confined within the cabin and is connected to a pair of push-rods
positioned in the wings that control ailerons differentially. Aileron trimming is carried out on ground through a small tab
positioned on left aileron.
Flaps are extended via an electric servo actuator controlled by a switch on the control stick. Flaps act in a continuous mode;
a panel mounted indicator shows surface position. A fuse positioned on the right side of the panel protects the electric
circuit.
Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servo actuator by
pushing an Up/Down push-button located on the control stick.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
17
1.7.5 Instrument Panel
The instrument panel is of conventional type, allowing space for a broad range of equipment.
Fig. 1-2 Instrument Panel
1.7.6 Carburetor Heat
Carburetor heat control knob is located just to the right of the center throttle control. When the knob is pulled fully outward
from the instrument panel, carburetors receive maximum hot air. During normal operation, the knob is OFF.
1.7.7 Cabin Heat / Defrost
The cabin heat control knob is positioned on the lower of the instrument panel; when knob is pulled fully outward, cabin
receives maximum hot air. Vents are located by the rudder pedals and above instrument panel. If necessary, outside fresh
air can be circulated inside cabin by opening the vents on the panel.
1.7.8 Throttle Friction Lock
Adjust the engine's throttle friction by tightening or loosening the friction lock located on the panel near center throttle
control.
1.7.9 Seats, Seatbelts, and Shoulder harnesses
The P92 Eaglet usually comes with three point safety belts with waist and diagonal straps adjustable via a sliding metal
buckle. Optional four point harnesses are available.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
18
Standard seats are aluminum with cushions. Seats are adjustable fore and aft by using the handle located under the seat on
the outboard sides. Pushing the lever towards the center of the aircraft will release the locking pin allowing you to move the
seat fore and aft. Release the lever when the desired position is found making sure that the locking pin reengages in the seat
track. WARNING
Make sure that the locking pin is securely installed or the seat will not lock in position.
1.7.10 Doors
Standard doors feature a light alloy tubular frame supporting a clear or tinted window. An internal safety latch mechanism
is positioned in proximity of door's upper edge and must be used before flight to secure door. Mechanism rotates, before
flight, to engage doorframe to cabin tubular framework.
1.7.11 Baggage compartment
The baggage compartment is located behind the seats. Baggage shall be uniformly distributed and its weight shall not
exceed 20 kg (44 lbs) and the c.g. must be computed before flight. Always tie down the baggage by using the adjustable tie-
down net provided.
1.8 Powerplant
1.8.1 Engine
Rotax is an Austrian engine manufacturer, founded in 1920 in Dresden, Germany. In 1970 Bombardier bought Rotax. The
company constructed only two-stroke engines until 1982, when it started building four-stroke engines. In 1989, Rotax
received Type Certification for its 912 A aircraft engine.
The Rotax 912 ULS engine is an ASTM compliant engine. The 912 is a four stroke, horizontally opposed, spark ignition
engine with single central camshaft with hydraulic tappets. The 912 has liquid cooled cylinder heads and ram air cooled
cylinders and engine. It is rated at 5800 RPM and can be run continuously at 5500 RPM.
The oil system is a dry sump, forced lubrications system. The oil tank is located on the passenger side of the engine
compartment and holds 3 liters (3.2 quarts) of oil.
The dual ignition system is a solid state, breakerless, capacitive discharge, interference suppression system instead of a
mechanical magneto system. Each ignition system is powered by individual and totally independent AC generators which
are not dependent on the aircraft battery.
The electrical system consists of an integrated AC generator with an external rectifier – regulator. An external alternator
can be installed. The Rotax engine is equipped with an electric starter.
The dual carburetors are constant depression carburetors that automatically adjust for altitude.
The fuel system is equipped with an engine driven mechanical pump.
The cooling system is a mixture of liquid and air cooling.
The engine uses a reduction gearbox with a gear reduction ratio of 2.4286:1.
Two throttles in the cockpit control the engine. The throttles are bussed together and will not move independently. The two
throttles are installed to allow the pilot to fly with either hand as well as giving the pilot the option of using the left hand
throttle while operating the center mounted brake handle.
The owner can register and get important information from the following website: http://www.rotax-owner.com/.
1.8.2 Propeller
The GT propeller is a wood composite propeller built by GT Tonini in Italy. The Tonini brothers began building propellers
in 1969.
The propeller is finished with a white polyurethane lacquer and an additional layer of transparent lacquer. The tips are
painted in bright yellow and red so that when the propeller is turning it is obvious to personnel on the ground. The back of
the propeller is painted black to prevent reflections. More information on the company and the propeller can be found at
http://www.gt-propellers.com. Check with your dealer for propeller options.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
19
1.8.3 Fuel system
The system is equipped with two aluminum fuel tanks integrated within the wing leading edge and accessible for inspection
through dedicated covers. Capacity of individual tank is 45lt (11.9 gal) and total usable fuel is 86.8lt (22.9 gal). Each fuel
tank is equipped with a cabin installed shutoff valve. A strainer cup with a drainage valve (Gascolator) is located on the
engine side of the firewall. Fuel level indicators for each tank are located on instrument panel. Fuel feed is through an
engine-driven mechanical pump. All fuel lines located in the engine compartment are protected with fireproof braiding to
avoid possible fire. Figure 1-3 illustrates the schematic of the fuel system.
WARNING
Fuel quantity should be checked on a level surface or a false reading may result. Always visually verify fuel quantity by
looking in the tanks.

P92 Eaglet
Flight Manual
Revision Date: 12-14-2007
Revision Number: 1.00
Doc n° 27-13-100-00
20
Left Fuel Tank
Right Fuel Tank
Firewall
Meshfilteranddrain
Filter
M
MechanicalFuelPump
ElectricFuelPump
LeftCarb
Right carb
FuelPressuregauge
Balanceline
FuelSelector
Valves
Right wing fuel tank vent Left wing fuel tank vent
Left fuel quantity indicator
Rightfuelquantityindicator
Drain
Figure 1-3 Fuel System