Aeroprakt Ltd. AEROPRAKT-22LS Owner's manual

Aeroprakt Ltd.
24, Polevaya str., Kiev, Ukraine
Tel: [phone]
Fa : 0038 044 496-77-31
e-mail: [email protected]
www.aeroprakt.kiev.ua
AEROPRAKT-22LS
Pilot Operating Handbook
A22LS-XXX-POH-01
This manual must be carried in the airplane at all times

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
Model: AEROPRAKT-22LS (A-22LS)
Serial No:
Registration:
Document No: A22LS-XXX-POH-01
Date of issue:
Approved by:
Signature:
Position:
Stamp:
Date of approval:
This airplane is to be operated in compliance with information and limitations contained herein.

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
RECORD OF REVISIONS
No part of t is manual may be reproduced or c anged in any manner wit out a written
consent of t e Manufacturer.
Any revision of t e present manual, except actual weig ing data, must be recorded in t e
following table according to information from t e Manufacturer.
New or amended text in t e revised pages will be indicated by a black vertical line on t e
left and margin, and t e Revision No. and t e date will be s own on t e bottom left and
side of t e page.
Rev. No.
Affected
Section
Affected
Pages Date Approval
Date Date
Inserted Signature

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
LIST OF EFFECTIVE PAGES
Section Page Date Section Page Date

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
Table of contents
1 General information .....................................................................................................7
1.1 General ...................................................................................................................7
1.2 Tec nical data.........................................................................................................7
1.3 Airplane t ree-view drawing....................................................................................7
2 Airplane and Systems Descriptions ...........................................................................8
2.1 Airframe ..................................................................................................................8
2.2 Landing gear ...........................................................................................................9
2.3 Engine and its controls............................................................................................9
2.4 Propeller..................................................................................................................9
2.5 Fuel system...........................................................................................................10
2.6 Airplane control systems .......................................................................................11
2.7 Instrument panel ...................................................................................................17
2.8 Full and static pressure system.............................................................................20
2.9 Electric system ......................................................................................................21
2.10 Seats and arness belts........................................................................................26
2.11 Cockpit doors ........................................................................................................26
2.12 Baggage container................................................................................................26
2.13 Recovery system...................................................................................................27
3 Operating Limitations ................................................................................................28
3.1 General .................................................................................................................28
3.2 Airspeed................................................................................................................28
3.3 Crosswind limitation ..............................................................................................28
3.4 Service ceiling.......................................................................................................28
3.5 Maneuvering load factors......................................................................................28
3.6 Pro ibited maneuvers ...........................................................................................28
3.7 Operating weig ts and loading..............................................................................29
3.8 Engine...................................................................................................................29
4 Weight and balance....................................................................................................30
4.1 General .................................................................................................................30
4.2 Actual empty airplane weig t and CG position......................................................30
4.3 Computation of t e CG position before flig t ........................................................30
5 Performance................................................................................................................32
5.1 General .................................................................................................................32
5.2 Takeoff and landing distances...............................................................................32
5.3 Climb performance................................................................................................32
5.4 Level flig t at cruising speed.................................................................................32
5.5 Endurance.............................................................................................................32
5.6 "Bug" effect ...........................................................................................................32
6 Emergency procedures..............................................................................................33
6.1 General .................................................................................................................33
6.2 Engine failure ........................................................................................................33
6.3 Glide......................................................................................................................33
6.4 Restarting engine in flig t......................................................................................34
6.5 Emergency landing ...............................................................................................34
6.6 Smoke and fire......................................................................................................34

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
6.7 Recovery from unintentional stall and spin............................................................35
7 Normal Procedures ....................................................................................................36
7.1 General .................................................................................................................36
7.2 Preflig t c eck.......................................................................................................36
7.3 Engine starting ......................................................................................................39
7.4 Taxiing ..................................................................................................................39
7.5 Before takeoff........................................................................................................39
7.6 Normal takeoff.......................................................................................................40
7.7 S ort field takeoff ..................................................................................................40
7.8 Climb.....................................................................................................................40
7.9 Cruise....................................................................................................................41
7.10 Approac ...............................................................................................................41
7.11 Normal landing......................................................................................................41
7.12 S ort field landing .................................................................................................42
7.13 Balked landing.......................................................................................................42
8 Aircraft Ground Handling and Servicing ..................................................................43
8.1 General .................................................................................................................43
8.2 Servicing fuel, oil and coolant................................................................................43
8.3 Towing and tie-down instructions..........................................................................43
8.4 Airplane was ing...................................................................................................44
8.5 Disassembling and assembling t e airplane .........................................................44
9 Required Placards and Markings..............................................................................47
9.1 Airspeed indicator markings..................................................................................47
9.2 Miscellaneous placards and markings ..................................................................47
10 Supplements...............................................................................................................48
10.1 General .................................................................................................................48
10.2 Engine manual ......................................................................................................48
10.3 Avionics and special engine instruments ..............................................................48
10.4 Recovery system...................................................................................................48
10.5 Floats ....................................................................................................................48
10.6 List of installed equipment.....................................................................................49
10.7 Actual empty weig t and CG position data ...........................................................50
10.8 Flig t Training Supplement ...................................................................................51

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
1 General information
1.1 General
T is Pilot Operating Handbook as been prepared to provide t e airplane owner and
operators wit information required for t e safe and efficient operation of t is airplane.
AEROPRAKT-22LS (A-22LS) is a two-seat, ig -wing strut braced monoplane of "classic"
aerodynamic layout wit closed cockpit, non-retractable landing gear wit steerable nose
w eel, Rotax-912 engine wit tractor t ree-blade on-ground adjustable pitc propeller.
AEROPRAKT-22LS is intended for flying in VFR, simple meteorological conditions.
AEROPRAKT-22LS is certified in t e LSA category.
1.2 Technical data
Wing span: 9.55 m (31 ft 4 in)
Wing area: 12.62 m² (136 sq in)
Lengt : 6.23 m (20 ft 5 in)
Maximum takeoff weig t, landplane: 600 kg (1320 lb)
floatplane: 650 kg (1430 lb)
1.3 Airplane three-view drawing
Fig. 1

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2 Airplane and Systems Descriptions
2.1 Airframe
Wing: ig placed, strut braced, constant c ord. Wing section is P-IIIa-15%. Wing primary
structure consists of a single spar, ribs and aft web. Forward of t e spar t e wing as
2024T3 aluminum alloy skin of 0.5-0.8 mm (0.020-0.032 in) s eet, w ic toget er wit t e
spar web forms t e wing torsion box. Aft of t e spar t e wing is covered wit t e metal skin
on top and t ermos rinkable fabric on t e bottom side. Wing ribs are made of 6061T6
s eet of 0.5-0.8 mm (0.020-0.032 in) t ickness. T e spar is a riveted structure consisting
of a web, made of 0.8 mm (0.032 in) 6061T6 s eet, and caps, made of an extruded
section (D16c T alloy angle). T e wing strut attac ment bracket and front attac ment
bracket of t e wing are fixed to t e spar. T e rear attac ment bracket of t e wing is fixed
to t e aft web. T e flaperon (drooping aileron) inge brackets are fixed to ribs No. 1, 5, 9
and 13. All brackets are made of 5 mm 2024T3 s eet.
T e primary structure of t e flaperon consists of t e leading edge skin, spar, trailing edge
section and ribs. T e LE skin and spar comprise t e torsion box. Flaperon covering is
made of synt etic t ermos rinkable fabric.
T e fuselage is an all-metal structure. T e mid section is made of t e 2024T3 aluminum
alloy bent s eet sections of 1.5 to 2 mm (0.063 to 0.080 in) t ickness, w ic form t e
edges of t e mid section. T e tail boom is a monocoque structure made of 0.8 mm (0.032
in) 2024T3 aluminum alloy s eet.
Engine cowling is made of composites.
T e fuselage as 6 frames (bulk eads). Frames No. 1, 2, 4, 5 and 6 are press-formed of
an aluminum alloy s eet; frame No. 3 is made of bent s eet sections. Power plant and
nose LG attac ment points are attac ed to t e frame No. 1, t e engine mount taking part
in transferring t e loads from t e nose LG onto t e fuselage structure.
T e wing and strut attac ment brackets as well as t e main LG legs attac ment brackets
are attac ed to t e frame No. 3. Frames No. 4, 5, 6 are installed in t e tail boom.
T e fin and ventral fin wit t e tail w eel are attac ed to t e frames No. 5 and 6.
T e bottom and part of t e topside of t e mid fuselage section are covered wit aluminum
alloy s eets of 0.5 mm (0.020 in) t ickness.
T e doors, cockpit and part of t e fuselage ave windows of organic glass.
T e primary structure of t e stabilizer consists of ribs and a spar. T e skin is a 2024T3
aluminum alloy s eet of 0.5 mm (0.020 in) t ickness. T e stabilizer as brackets of its
attac ment to fuselage and 3 elevator inge brackets.
T e fin, structurally similar to t e stabilizer, is made as integral part of t e fuselage.
Elevator and rudder structures are similar to t at of t e flaperons.

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.2 Landing gear
Airplane landing gear is of tricycle type wit steerable nose w eel. T e main LG is of t e
cantilever spring type. T e main LG leg is a spring mac ined of a round aluminum bar. It is
attac ed to t e lower boom of t e frame No. 3 at two points: upper and lower supports.
T e support brackets are mac ined of aluminum alloy. T e main LG w eels are fitted wit
ydraulic disk brakes.
T e nose LG leg is steerable, of trailing link type. T e steering is ensured using t e rudder
pedals via pus rods, connecting t e left and rig t side pedals wit bellcrank on t e strut.
T e leg consists of a strut and a trailing link in form of nose w eel fork. T e trailing link is
connected to t e strut wit a s ock absorber/damper.
T e nose leg is attac ed to t e frame No. 1 at 2 points – on upper and lower supports. T e
upper support is made of 5 mm 2024T3 aluminum alloy s eet and t e lower one is build-
up. T e supports are fitted wit brass bearings.
Eac w eel is fitted wit a w eel spat (fairing) or mud screens (in case of t e low-profile
tires and 6.00×6 w eels).
Landing gear data:
w eel base – 1760 mm,
w eel track – 1300 mm,
min. turn radius – 2 m.
Main w eels:
size – 5.00×5 or 6.00×6
pressure – 1.6 kg/cm
2
(22.7 psi)
Nose w eel:
size – 5.00×5 or 6.00×6 brakeless w eel
steering angle ±30 degrees
pressure – 0.16 MPa (1.6 kg/cm2)
2.3 Engine and its controls
A-22LS can be equipped wit a four-cylinder four-stroke Rotax-912UL or Rotax-912ULS
carburetor combined cooling engine produced by BOMBARDIER-ROTAX Inc. (Austria).
T e engine is as t e flat-four layout, dry sump lubrication system wit a separate oil tank
of 3 l (0.8 US gal) capacity, automatic valve clearance adjustment, two carburetors,
mec anical membrane fuel pump, double electronic ignition system, integrated water
pump, electric starter, integrated gearbox of 2.273 or 2.43 reduction ratio.
All engine systems (fuel, electric, cooling) are assembled in accordance wit Rotax-912
engine operation manual.
T e engine can be fitted wit an air intake pre- eater box designed by Aeroprakt, w ic
improves engine operating conditions, preventing carburetor icing in cold weat er and
increasing t e engine output in ot weat er.
2.4 Propeller
A-22LS can be equipped wit any suitable propeller matc ing to Rotax-912 UL/ULS
engine power output and t e airplane speed range. One of t e optional propellers is
KievProp t ree-blade on-ground adjustable propeller of 1.8 m (5'11") diameter.

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.5 Fuel system
T e fuel system (Fig. 2) includes two wing fuel tanks 1 (eac of 45 l or 11.9 US gal
capacity) wit filler inlets 2 and fuel lines 9 connecting t e tanks to eac ot er and to t e
engine fuel pump 6 (t at is feeding fuel to t e engine carburetors 10) via two fuel valves 3
and fuel filter 5. Fuel can be drained from t e tanks using t e drain valve 4. T e fuel tanks
are connected wit t e atmosp ere via t e vent lines 8.
Fig. 2. Fuel system schematic

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
NOTE: W en bot tanks are full, fuel may flow from one tank to t e ot er (e.g. due to t e
lateral forces during side slipping or w en wings are not level on parking or during taxiing),
overfill it and spill out t roug t e vent line. To prevent t is close one of t e fuel valves.
CAUTION! At all times during the flight ensure fuel coming to the engine by opening
the valve(s) of the tank(s) WITH fuel. If one of the tanks is empty, close
its valve to prevent air getting into the fuel line and causing engine
malfunction or even failure.
Capacity of tanks: 2×45 l (2×11,9 US gal)
Total capacity: 90 l (23,8 US gal)
Usable fuel: 89 l (23,5 US gal)
Non-usable fuel: 1 l (0,3 US gal)
Fuel: unleaded avgas wit RON 95 or above
2.6 Airplane control systems
Airplane control systems include control systems for drooping ailerons (flaperons), elevator
wit trim tab, rudder and nose w eel, engine and brakes.
T e control system is combined consisting of foot- and and-actuated subsystems.
Ailerons and elevator are and-actuated and are controlled using yokes.
2.6.1 Elevator control system
T e elevator control system linkage (see Fig. 3) is rigid, comprising 3 pus rods and 2
bellcranks. “Pus ” and “pull” forces are applied by t e pilot to t e yoke 1 is passed via t e
control column 2 to t e pus rod 3, t en via t e bellcrank 4 to t e pus rod 5. T e force is
transferred to t e elevator via t e pus rod 7, attac ed to t e bellcrank 6. And t e pus rod
7 is supported by t e rollers 8 and connected to t e elevator arm 9.
Fig. 3

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.6.2 Elevator trim tab control system
Elevator trim tab is used for controlling t e force on control yokes in pitc . T e trim tab
control lever is accessible from bot pilot seats.
Fig. 4
T e trim tab control lever 1 (Fig. 4) is placed on t e central console. It is retained in place
by friction adjusted using t e w eel 2.
T e trim tab control lever is connected wit a cable 3 to t e trim tab control arm 4. T e
cable is running t roug t e flexible conduits 5 (in t e central console) and 6 (in stabilizer)
and cable fairleads 7 and 8 inside t e tail boom. T e trim tab is inged to t e elevator
trailing edge on a wire serving also as a torsion spring.
T e trim tab angles of deflection are: upward 21±1°, downward 22±1°.

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.6.3 Rudder and nose wheel control system
Rudder and nose landing gear are controlled using pedals. Rudder is connected to t e
pedals in t e cockpit wit two cables of 2.7 mm (0.11 in) diameter. T e pedals are
attac ed to two s afts (s aft for left pedals 1 and s aft for rig t pedals 2) inged to t e
lower fuselage beams (Fig. 5). Eac s aft as two arms. One of t e arms is connected
wit a cable to t e rudder control arm 3, t e ot er - wit a rod - to t e nose landing gear
control arm 4. Rudder control cables are running from t e pedals to t e rudder control
arms via pulleys 5, 6 installed at frames No. 3 and 4 and fairleads 8, 9 on pilot seat beam
and frame 5. Tension of t e cables is adjusted using turnbuckles 7 attac ed to t e pedal
s aft arms.
In its neutral position t e rudder is rotated to t e rig t by t e angle of +3° for compensation
of t e engine torque. T e rudder deflection angle is 25±1°.
Fig. 5. Rudder and nose landing gear control system

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.6.4 Control system of flaperons (drooping ailerons)
T e airplane is equipped wit flaperons (drooping ailerons), w ic serve as bot ailerons
and flaps. T e flaperon control system ensures independent function of flaperons as
ailerons and flaps using a differential mec anism.
Fig. 6. Control system of flaperons (drooping ailerons)
T e control force in roll (to turn t e yoke, Fig. 6) applied by t e pilot to t e yoke 1 is
passed via t e lever 2 to t e pus rod 3 and t en to t e central control s aft 5. T e yokes
are interconnected wit t e pus rod 4. T en from t e bellcrank 6 attac ed to t e s aft it is
passed via t e pus rods 7 to t e flaperon control s afts 8. T e s afts are attac ed via a
Cardan joint 9 to t e bracket at t e root end rib of t e flaperon 10 at one end and to t e
trunnion on t e levers 11 of t e flap control mec anism at t e ot er. Stops 12 limit t e
rotation angle of bellcrank 6 on t e central control s aft and, t erefore, angles of yoke
rotation and aileron deflection.
Deflection angles of t e flaperons (as ailerons): up – 20±1°, down – 13±1°.

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
Fig. 7. Flap e tension mechanism
As flaps (Fig. 7) t e flaperons are extended by setting t e flap extension lever 1 to t e
required positions and t us rotating t e flap s afts 5 by t e respective angles via link 3 and
levers 4. Locking of t e flap setting is ac ieved by means of t e stopper block 2 wit t ree
slots for t e locking pin on t e flap extension lever. Unlocking is ac ieved by bending t e
flexible flap extension lever to t e side and t us taking t e locking pin out of t e fixing slot.
W en t e required flap setting is selected t e locking pin is aligned wit t e fixing slot and
t e flap extension lever springs back inserting t e locking pin into t e fixing slot.
Deflection angles of t e flaperons (as flaps): 1
st
position – 10±1°, 2
nd
position – 20±1°.
2.6.5 Engine controls
T e engine controls are accessible from bot rig t and left side pilot seat. Engine RPM is
controlled using a single t rottle lever located on t e central console. Two control cables
connect t e t rottle lever to t e left and rig t carburetors on t e engine.
T e fuel mixture control (for engine starting) is ac ieved using t e c oke lever also located
on t e central console near t e t rottle lever. T e c oke lever is connected to t e
carburetors wit cables as well.
Carburetor eating control knob is located on t e instrument panel. It controls position of a
s utter in t e air intake box. W en t e s utter is open, t e colder outside air is coming
t roug t e air scoop into t e air intake box and t en to t e carburetors. W en t e s utter
is closed, t e carburetors are supplied wit t e otter air from t e engine compartment and
t us t e carburetor eating is ensured.

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.6.6 Brake control system
T e main w eel brakes (Fig. 8) are actuated ydraulically using t e brake lever 2 (installed
next to t e t rottle lever 3) controlling t e pressure supplied from t e master cylinder 1 to
t e slave cylinders 5 in t e w eels.
T e main LG w eels ave disk brakes. T e cylinders are connected to eac ot er wit
copper tubing 6 wit outside diameter of 3 mm. T e master cylinder 1 is connected wit a
ose 8 to t e extension tank 7, installed on t e firewall in t e engine compartment.
W en t e brake lever is pulled t e brake pads squeeze t e brake disc creating t e braking
moment proportional to t e applied force.
A-22LS is equipped also wit a parking brake, w ic is actuated wit a lever 4 on t e
central console. To use t e parking brake, set t e lever to 'Parking brake ON', t en pull
and release t e brake lever. T e brake pads will remain pressed to t e brake disc. To
release t e parking brake set its control lever to its initial position ('Parking brake OFF').
Fig. 8. Brake control system

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
2.7 Instrument panel
A-22LS as t ree variants of flig t instruments set and instrument panel arrangement:
1. Basic instrument panel, see fig. Fig. 9
2. Standard instrument panel, see Fig. 10
3. "Glass cockpit" instrument panel, see Fig. 11
Numbers in t e pictures denote t e following:
1. Placard wit passenger warning: "THIS AIRCRAFT WAS MANUFACTURED IN
ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS
AND DOES NOT CONFORM TO STANDARD CATEGORY AIRWORTHINESS
REQUIREMENTS"
2. Placard wit operating limitations: OPERATE UNDER VFR ONLY
NEVER EXCEED SPEED = 120 KTS IAS
MAX CONTINUOUS ENGINE SPEED = 5500 RPM
MAX TAKEOFF MASS = 600 KG (1320 LB)
LIMIT LOAD FACTOR = +4.0 / -2.0
3. NO CHARGE indicator and marking
4. ALARM indicator and marking
5. Carburetor eating control knob and marking "CARB HEAT ON - PUSH"
6. Cockpit eating control knob and marking "COCKPIT HEAT ON - PULL"
7. Left tank fuel level indicator and marking "FUEL L"
8. Rig t tank fuel level indicator and marking "FUEL R"
9. Landing lig t switc and marking
10. Navigation lig t switc and marking
11. Intercom switc and marking
12. ON marking for electric and ignition switc es
13. OFF marking for electric and ignition switc es
14. IGN A marking
15. IGN B marking
16. Ignition switc es
17. MASTER marking
18. Master and starter key
19. STARTER marking
20. Fuses

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
Fig. 9

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
Fig. 10

AEROPRAKT-22LS Pilot Operating Handbook A22LS-XXX-POH-01
Fig. 11
2.8 Full and static pressure system
T is system supplies t e full (dynamic) and static pressure of t e outside air to t e
instruments measuring t e flig t parameters: airspeed, rate of climb and altitude. T e
system consists of t e full and static pressure probe 1 and full 2 and static 3 pressure lines
connecting t e probe to t e instruments (see Fig. 12). Full and static pressure lines ave
joints 4 used to disconnect t e lines w en t e left wing is removed during aircraft
disassembly.
T e full and static pressure lines are connected to t e airspeed indicator(s). Static
pressure for altimeter and vertical speed indicator is supplied from t e cockpit.
Good condition of t e full and static pressure system is important for correct measurement
of t e flig t parameters and t erefore for flig t safety. Pilots must take measures to keep
t e system in good condition: protect t e full and static pressure probe wit a cover
(marked wit a red "Remove before flig t" flag) and inspect t e probe and lines during t e
preflig t c eck to make sure t at t ey are not damaged or blocked (by water, ice, dirt,
etc.).