Sonex Aircraft 883 Owner's manual
Sonex Aircraft, LLC
883
Pilot’s Operating Handbook
04/01/2015
Sonex 883 Pilot Operating Handbook 1
Pilot’s Operating Handbook
Make: Rui Sereno
Model: Sonex
Serial Number: 883
Owner Information
Name: Rui Sereno Melo
Address: Rua mário pais da costa nº12
Abravezes
3510 VISEU
Sonex 883 Pilot Operating Handbook 2
INDEX
Section PAGE
I Introduction and Description 3
II Aircraft Specifications 6
III Performance 10
IV Weight and Balance 16
V System Diagrams 21
VI Preflight Inspection Checklist 22
VII Normal Procedures 25
VIII Emergency Procedures 29
IX Servicing Requirements 31
X Equipment List 32
XI Revisions List 33
Sonex 883 Pilot Operating Handbook 3
I. Introduction and Description
The Sonex is a high-performance, homebuilt aircraft. Its compact
external size and extremely efficient design results in superb
performance and unequaled fuel economy using a relatively low
horsepower engine. Pitch control is provided by elevators mounted on
the horizontal stabilizer. Roll capability is provided by ailerons on the
outboard portion of the main wing. Yaw control is provided by a rudder
mounted on the vertical stabilizer, and is actuated by conventional
rudder pedals. The pitch and roll capability is provided by conventional
dual control sticks located at each seat.
Steering is provided by front wheel steering, providing exceptional
control at all times while on the ground. Even though the Sonex has
relatively low horsepower, it can outperform many general aviation
aircraft while retaining unequaled fuel economy. Typical cruise speed is
130 mph, burning under 4 gallons per hour, yielding fuel economy in
excess of 30 miles per gallon.
The structure of the Sonex is almost entirely 6061T6 aluminum, yielding
a design that is easy to construct, conventional to maintain, and
resistant the effects of weather and corrosion.
The engine that powers the Sonex is an Rotax 912S aircraft engine,
produced by Rotax.
Ventilation and Heating
Fresh air ventilation is provided by NACA scoops on the forward fuselage
sides. These scoops feed into rotating eyeball vents mounted in the
corners of the instrument panel. The flow of air can be directed and
controlled by adjusting the vent opening. No cabin heat is installed.
Landing Gear
Sonex 883 Pilot Operating Handbook 4
The main landing gear legs are 1 1/8” titanium rod. Due to the
mechanical properties of titanium, the Sonex gear is extremely robust,
yet forgiving. The titanium gear legs will bend gently under landing
loads, then rebound slowly without springing the aircraft back into the
air. Steering is accomplished through a direct linkage to the rudder and
front wheel, resulting in very accurate and positive directional control
while taxiing, and during takeoff and landing.
Baggage Compartment
A baggage compartment is provided aft of the occupants heads. The
baggage limit is 40 pounds. Depending on the pilot, passenger, and fuel
to be carried, baggage may have to be limited because of gross weight
or center-of-gravity (c. of g.) limits.
Flight Controls
Pitch and roll control is actuated by dual control sticks located between
the pilot’s and passenger’s legs. The rudder pedals are conventional. All
flight controls including the flaps are pushrod actuated.
An in-flight cockpit adjustable pitch trim system is provided. It works by
adjusting a movable control tab mounted on the left elevator half. The
trim system is completely independent of the normal pitch control
system, thus providing back-up pitch control system in the event of a
primary control problem. The primary pitch control system (i.e. the
stick) can override any position of the trim system.
Engine Cowling
The cowling is split into upper and lower sections. To remove the
cowling, loosen the ¼ turn SouthCo fasteners along the upper part to
separate it. Next, remove the lateral piano hinge pins, thereby
separating the lower cowling sections.
Sonex 883 Pilot Operating Handbook 5
Brakes
The braking system consists of two hydraulic brackes one for each
wheel dependent of a hydraulic pump actuacted by an aluminium lever
in along the left hand cockpit sidewall.
Fuel System
The 17 gallon main fuel tank is located just aft of the firewall above the
occupant’s legs. The unusable fuel quantity is less than ½ gallon. The
engine is gravity fed with a fuel shutoff valve located inside the cockpit
at the tank outlet. It consists of a brass ¼ turn ball valve. The valve is
closed by rotating the handle perpendicular to the valve body. The fuel
tank has a capacitance fuel probe installed to measure fuel quantity.
The fuel gauge should be checked while in level, balanced flight to avoid
inaccurate fuel quantity measurements. The fuel filler cap is provided on
the upper forward fuselage, accessible from the outside of the aircraft.
Approved fuels include 98 octane automotive fuel and 100LL aviation
fuel.
Sonex 883 Pilot Operating Handbook 6
II. Aircraft Specifications
3 View Diagram
Exterior Dimensions
Span: 22 ft
Length: 17 ft, 7 in
Height: 4 ft, 4 in
Wing Area: 98 sq ft
Sonex 883 Pilot Operating Handbook 7
Weights
Empty Weight: 271Kg
Gross Weight: 450Kg
Useful Load: 179KG
Fuel (17 gal): 43Kg
Max Baggage: 18,14Kg
CG Limitations
Datum 125,0cm from wing leading edge
Mean Aerodynamic Cord: 137,16cm
Forward CG Limit: 152,432 (20% MAC)
Aft CG Limit: 168,89 (32% MAC)
Loadings
Wing Loading: 494,5gr/dm2
Load Factor Limit
- 850 lbs +6.0, -3.0
- 1200 lbs +4.0, -2.0
Powerplant
Engine: Rotax 912S
Prop: Neuform (Two Blade)
Control Surface Deflections
Ailerons 20° up, 12° down
Flaps 0°, 10°, 30°
Rudder 25° right and left
Elevator 25° up, 20° down
Elevator Trim Tab 30° up, 30° dow
Engine Information
Specifications
Model: Rotax 912S
Serial #: 4427777
Carburetor: Bing x2
Type: 4 cylinder, 4 stroke, horizontally
opposed, normally aspirated
Sonex 883 Pilot Operating Handbook 8
Cooling: Air and water cooled, with external oil
and water cooler
Weight (complete, less oil) 58,3Kg
Rated HP: 100
Maximum RPM: 5800(5min.)
Cruise RPM: 4500
Idle RPM: 1400
Bore: 84mm
Stroke: 61mm
Compression Ratio: 10,5:1
Fuel
Approved Fuel Grades: 98 octane unleaded
100LL Avgas
Total Fuel Capacity: 60 l
Operating Conditions
Oil Temp: 90º:110º 130º Max
Oil Pressure (bar): 2,0:5:0 7,0 Max 0,8 Min
Fuel Pressure (bar): 0:15 Min, 0,4 Max
Cylinder Head Temp: 135º Max
Exhaust Gas Temp: 880º max
Sonex 883 Pilot Operating Handbook 9
Airspeed Limitations
Speed
IAS
Remarks
VNE
Never Exceed Speed
197 MPH
Do not exceed this speed
in any operations
VNO
Maximum Structural
Cruising Speed
125 MPH
Exceed this speed only in
smooth air
VA
Maneuvering Speed
125 MPH
Do not make full control
movements above this
speed. Full elevator
deflection will result in a
6 G load at this speed
VFE
Maximum Flap
Extended Speed
100 MPH
Do not exceed this speed
with flaps down
Vy
Best Rate of Climb
85 MPH
Vx
Best Angle of Climb
75 MPH
VS
Stall Speed Clean
46 MPH
VSO
Stall Speed Landing
Configuration
40 MPH
Airspeed Indicator Markings
Marking
Value / Range
Significance
White Arc
40–100 MPH
Full Flap Operating Range. Lower
limit is VSO. Upper Limit is
maximum speed with flaps
extended.
Green Arc
46–125 MPH
Normal Operating Range. Lower
limit is VS. Upper limit is
maximum structural cruising
speed.
Yellow Arc
125–197 MPH
Operations must be conducted
with caution and only in smooth
air.
Red Line
197 MPH
Maximum speed for all operations.
Sonex 883 Pilot Operating Handbook 10
III. Performance
Speed –Solo Weight
Top Speed 150 MPH
Cruise 75% power @ 8000 ft: 130 MPH
Stall Speed: 40 MPH
Speed –Gross Weight
Top Speed 150 MPH
Cruise –75% power @ 8000 ft: 130 MPH
Stall Speed: 40 MPH
Ground Performance –Solo Weight
Takeoff Distance: 500 ft
Landing Distance: 450 ft
Ground Performance –Gross Weight
Takeoff Distance: 850 ft
Landing Distance: 650 ft
Climb / Ceiling –Solo Weight
Rate of Climb: 900 fpm
Ceiling: 12500ft
Climb / Ceiling –Gross Weight
Rate of Climb: 750 fpm
Ceiling: 12500 ft
Endurance
Fuel Quantity: 60l
Fuel Consumption: 100% 27l
Fuel Consumption: 75% 18,5
Sonex 883 Pilot Operating Handbook 11
Rate of Climb at Vy
0
100
200
300
400
500
600
700
0 1 2 3 4 5 6 7 8 9 10 11 12 13
Density Altitude in Thousands of Ft
ROC (fpm)
Climb/Descent Performance
-10.00
-8.00
-6.00
-4.00
-2.00
0.00
2.00
4.00
6.00
010 20 30 40 50 60 70 80
Observed Airspeed (mph)
Flight Path Angle (deg)
Descent (Idle)
Climb (Vx)
Descent (4600 rpm)
Range: 75% @ 8000 ft: 674Km
Sonex 883 Pilot Operating Handbook 12
ASI Calibration
y = 0.7905x + 1.4197
0.0
10.0
20.0
30.0
40.0
50.0
60.0
70.0
80.0
90.0
010 20 30 40 50 60 70 80 90 100
Indicated Airspeed
Calibrated Airspeed
1200 lbs
40
40
40
40
40
40
40
40
40
40
40
40
CAS = 80% IAS
Sonex 883 Pilot Operating Handbook 13
TAKE OFF DISTANCE
Elevation
and Temperature
IAS
MPH
Ground Run
Feet
To Clear 50 ft
Obstacle (Feet)
Sea Level @ 59° F
2500 ft @ 50° F
5000 ft @ 41° F
1. Figures for clean, level, hard surface runway.
2. Takeoff Weight: 450Kg
3. Full Throttle
4. Increase distance 10% for each 35° F increase in temperature
above standard day temperature.
5. For operation on dry grass runway, increase distance by 7%
LANDING DISTANCE
Elevation
and Temperature
IAS
MPH
Ground Run
Feet
To Clear 50 ft
Obstacle (Feet)
Sea Level @ 59° F
2500 ft @ 50° F
5000 ft @ 41° F
1. Figures for full flap, no wind conditions, on clean, level, hard
surface runway.
2. Landing Weight: 450Kg
3. Decrease distance by 10% for each 4 knots of head wind.
4. Increase distance 10% for each 35° F increase in temperature
above standard day temperature.
5. For operation on dry grass runway, increase distance by 7%
Sonex 883 Pilot Operating Handbook 14
CRUISE PERFORMANCE
(Full Fuel 60lt)
Altitude
(Feet)
RPM
%
BHP
TAS
(MPH)
Fuel Flow
(GPH)
Endurance
(Hours)
Range
(Miles)
2500
3400
3300
3200
3100
3000
2900
2800
5000
3400
3300
3200
3100
3000
2900
2800
1. Maximum Cruise is normally limited to 75% power.
2. Endurance and Range are for no-wind conditions.
3. Figures do not include take off, landing, or reserve.
Sonex 883 Pilot Operating Handbook 15
Sonex 883 Pilot Operating Handbook 16
IV. Weight and Balance
Weight and Balance
Datum: Front Tip of spinner
Datum: 1250mm from Wing Leading edge
Maximum gross weight: 449,8 Kg
Empty Weight CG
Empty Weight
WtxArm
Weighing Point
Weight(Kg)
Arm(cm)
Moment
Right main
109
185,0
20165,0
Left main
105
185,0
19425,0
Nose
57
53,0
3021,0
Total
271
42611,0
Moment/Weight= Empty Weight CG(cm)
157,2
Forward CG Limit: 157,1 152,432 = 20% MAC
Aft CG Limit: 167,4 168,891= 32% MAC
Take off Max Weight,( ULM Cat)
Item
Weight(Kg)
Arm(cm)
Moment
Aircraft empty
271
157,2
42611,0
Pilot
75
185,7
13926,0
Passenger
75
185,7
13926,0
Fuel(40 l)
28,8
106,6
3068,8
Baggage
0
249,4
0,0
Total
449,8
73531,8
Most Aft CG
163,5
% MAC
28,1
Limit
168,891
Most Adverse AFT CG (ULM Cat)
Item
Weight(Kg)
Arm(cm)
Moment
Aircraft empty
271
157,2
42611,0
Pilot
75
185,7
13926,0
Passenger
75
185,7
13926,0
Fuel(0 l)
0
106,6
0,0
Baggage
0
249,4
0,0
Total
421,0
70463,0
Most Aft CG
167,37
% MAC
30,9
Limit
168,891
Sonex 883 Pilot Operating Handbook 17
Most adverse For CG (ULM Cat)
Item
Weight(Kg)
Arm(cm)
Moment
Aircraft empty
271
157,2
42611,0
Pilot
75
185,7
13926,0
Passenger
0,0
Fuel(60 l)
43
106,6
4603,2
Baggage
0
249,4
0,0
Total
389
61140,2
Most Aft CG
157,17
% MAC
23,4
Limit
152,432
Sonex 883 Pilot Operating Handbook 18
Measured Distance “E”= 74cm
Measured Distance “F”= 58cm
Main gear reference Arm”G”= 185cm
Main Wheel reference Arm”H”= 53cm
Right and Main Gear weight = 109Kg
Left hand Main Gear weight = 105Kg
Nose Wheel weight = 57 Kg
Sonex 883 Pilot Operating Handbook 19
Blank Weight and Balance Worksheet
The following table can be used to determine the aircraft’s weight and
center of gravity for any loading situation. Complete the weight column
in the table below using the fuel, baggage, and pilot/passenger weights
for the situation being considered. Next, using the moment charts on
the following pages, record the appropriate moments into the table. Use
the Total Weight and Total Moment from the table to find the aircraft’s
loaded center of gravity using the Allowable Weight and Balance chart.
Item
Weight
(Kg)
Arm
(cm)
Moment
(Kg*cm)
Aircraft, Empty
271
157,2
42611
Fuel
106,6
Baggage
249,4
Pilot & Passenger
185,7
Total
---
CG (cm)
=
Total Moment
=
Total Weight
CG (cm) =
Safe to Fly? YES □/ NO □
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