Lightwing AC4 Technical specifications

AFM Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 1
23.03.2018
Aircraft Flight Manual
For the Airplane
Lightwing AC4
Document No: LW-RL-Z-002
This document is issued for the following airplane:
Registration: HB-WEB
Serial Number: 003
Date & Signature Lightwing:
04.04.2018, Marco Trüssel, Light Wing AG

Lightwing AC4 AFM
Page 2 Rev.:2 LW-RL-Z-002
0.1 Amendments
Any revision of the present manual has to be registered in the following
chart.
Rev.
Pages
Description
Date
Approval
-
1..85
1st Edition.
12-May-14
EASA.A.588, 17.6.14
Rev.:0
1..87
Renumbered to document
LW-RL-Z-002
- addition heating system
- addition gear fairings
02-Mar-16
ELA1-HB
LW-RL-Q-003
EASA 10056955
EASA 10056950
Rev.:1
1..88
Minor change “Project 06”
- Addition FLARM
- Addition LED sight
gauge illumination
- Addition of approved
secions
19-Sep-17
ADxC-48-DC-002
Rev.:2
1..88
AFM Change for
EASA project 10062701
Major change “Project 03”
- 912iS “Sport”
23-Mar-18

AFM Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 3
0.2 List of approved sections
Section
Name
Status
2.
3.
5.
6.1 & 6.2
Limitations
Emergency procedures
Performance
Weight and Balance
Approved (EASA.A.588)
Approved (EASA.A.588)
Approved (EASA.A.588)
Approved (EASA.A.588)

Lightwing AC4 AFM
Page 4 Rev.:2 LW-RL-Z-002
0.3 List of effective pages
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Date
Page
Date
Cover
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23-03-18
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AFM Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 5
0.4 Table of contents
This aircraft flight manual supplement consists of the following parts:
1General
2Limitations
3Emergency procedures
4Normal procedures
5Performance
6Weight and balance / equipment
7Aircraft and systems description
8Handling and maintenance
Following the recommended structure for flight manuals as defined in
GAMA Specification No. 1.
The following documents belong to this aircraft flight manual:
- Operation manual for engine ROTAX 912iSc/iS "Sport"
- manuals for installed avionics
oSkyview System
oPower Flarm
oRadio with Intercom
oTransponder
The Airplane flight manual must be carried on board the airplane at all
times. It should be stored in the aircraft.
0.5 Contact information
Light Wing AG
Riedenmatt 1
6370 Stans
Switzerland
www.Lightwing.ch

Lightwing AC4 General
Page 6 Rev.:2 LW-RL-Z-002
1 General
1.1 Introduction
This aircraft flight manual includes information and procedures for
pilots for safe and effective operation of this aircraft. This aircraft flight
manual includes information that should be made available to the pilot
according to CS-LSA regulations. It includes further information and
procedures which Light Wing AG Company considers useful for the
pilot.
The aircraft manual is corrected and amended by EASA
CAUTION: This airplane flight manual has to be carried
on board at all times.
1.2 Certification Basis
The AC4 is certified on 17-Jun-2014 by the European Aviation Safety
Agency (EASA) under CS-LSA with type certificate EASA.A.588.
Category: Light Sport Aircraft;
Noise certificate ICAO Annex 16, Chapter X.

General Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 7
1.3 Warnings, cautions and notes
Statements in this handbook, which are particularly important for safety
of flight or operation of the airplane, are highlighted by one of the
following notions:
WARNING: means that non-observance of the
respective procedure leads to immediate or
considerable reduction of flight safety.
CAUTION: means that non-observance of the respective
procedure leads to a reduction of flight safety
in the long term.
NOTE: shall bring attention to facts which are not
directly related to safety of flight, but which are
important or unusual.

Lightwing AC4 General
Page 8 Rev.:2 LW-RL-Z-002
1.4 Descriptive data
The Lightwing AC4 aircraft is a single engine two-seater light sport
airplane with side by side seating. It is built in a high strutted wing
configuration with a conventional strutted tail.
The aircraft has a dual control system with a single central control stick.
The undercarriage is fixed tricycle landing gear type, with the nose
wheel steering.
1.4.1 Dimensions and important data
Dimensions external
wing span (incl. wing tips): 9.446 m
wing span (incl. wing tips lights): 9.565 m
max. length (spinner to rudder tip): 6.950 m
max. height: 2.670 m
Wing
wing surface: 12.70 m2
Aileron
deflection up: 22° (± 2°)
deflection down: 20° (± 2°)
Flaps
control system: electric
deflection: 0°/10°/24°Down ± 2°
Horizontal tail
span: 2.910 m
deflection up: 30° ± 2°
deflection down: 30° ± 2°
Servo tab (right elevator):
Fletter tab geared to elevator deflection (angles are with respect to
elevator chord)
with elevator 30° UP 26° ± 2° dwn
with elevator neutral 12° ± 2° dwn
with elevator 30° DWN 7° ± 2° up

General Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 9
Pitch trim (left elevator):
Trim tab with an electric actuator at the left hand elevator trailing edge.
Geometric deflection versus elevator: 5° up / 27° dwn ± 2°
Vertical tail surfaces
surface: 1.207 m2
deflection: left/right 25° ± 2°
Undercarriage
fixed tricycle landing gear
shock absorption/nose gear: elastomer
shock absorption/main gear: steel leaf spring
wheel base: 1.851 m
wheel track: 1.916 m
main wheels/pressure: 15x6.00-6/3.0bar
nose wheel/pressure: 4.00-6/2.7bar
Brakes
Central braking at the main gear using floating disk brakes.

Lightwing AC4 General
Page 10 Rev.:2 LW-RL-Z-002
1.4.2 Powerplant
Engine:
Rotax 912iSc/iS "Sport" naturally aspirated, 4 Stroke petrol engine,
with 4 horizontally opposed cylinders with dry sump lubrication, dual
ignition with breakerless capacitor discharge design, fuel injection
supplied by a dual electric fuel pump, liquid cooled cylinder heads, ram
air cooled cylinders, prop drive gear reduction ratio of 2.43:1.
Propeller:
Type: fixed pitch
Blade: CR3-75 3-blade
Diameter: 1.75 m
Manufacturer: Neuform Composites GmbH&Co
Blade setting (gaugeable secant): 25° at 365mm from hub centre

General Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 11
1.4.3 Three side view

Lightwing AC4 Limitations
Page 12 Rev.:2 LW-RL-Z-002
2 Limitations
2.1 General................................................................................13
2.2 Speeds.................................................................................13
2.3 Airspeed indicator markings.................................................13
2.4 Powerplant...........................................................................14
2.5 Powerplant instrument markings ..........................................15
2.6 Miscellaneous instrument markings......................................16
2.7 Weight limits.........................................................................16
2.8 Approved manoeuvres .........................................................16
2.9 Manoeuvring load factors.....................................................16
2.10 Flight crew............................................................................17
2.11 Kinds of operation ................................................................17
2.12 Fuel......................................................................................17
2.13 Maximum passenger seating................................................17
2.14 Other limitations ...................................................................18
2.15 Limitation placards ...............................................................18
7.15 Cabin heating system...........................................................83

Limitations Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 13
2.1 General
This section deals with operating limitations, instrumentation and labels
required for the safe operation of the aircraft, its engine, systems and
equipment.
CAUTION: Any violation of the defined limitations must
be recorded in the airplane logbook!
2.2 Speeds
The speed limits are given in the unit “kilometres per hour” and relate
to established values in equivalent and indicated airspeed.
Limits for flight speeds and their importance for the operation are
shown in the following chart:
Description
Name
EAS
IAS
Comment
Never exceed
speed
VNE
196 km/h
210km/h
This speed must
never be exceeded
Maneuvering
speed
VA
163 km/h
176km/h
Do not make full or
abrupt control
movements above
this speed
Maximum
structural cruising
speed
VNO
163 km/h
176km/h
Speed range above
only usable in smooth
air
Flaps extended
speed
VFE
152 km/h
165km/h
Highest permissible
speed for flap
operation
2.3 Airspeed indicator markings
The following table defines markings for the airspeed indicator and
explains the meaning of colour codes.

Lightwing AC4 Limitations
Page 14 Rev.:2 LW-RL-Z-002
Mark
Range
km/h IAS
Description
White arc
76-165
Full flap operating range. (Lower
extreme is VS0 at maximum weight, flaps
set 24°, idle power; Upper extreme is
the maximum permissible speed with
flaps extended)
Green arc
82-176
Normal operating range (Lower extreme
is VS1 at maximum weight most forward
CG with flaps up, Upper extreme is
VNO).
Yellow arc
176-210
Caution range. Operation in this range
only in smooth weather conditions
Red line
210
Maximum speed for all operations (VNE)
2.4 Powerplant
Manufacturer: Rotax Aircraft Engines
Type: Rotax 912iSC/iS Sport
Max. take off power: 73.5 kW = 100 HP
Max. take off engine speed (max. 5 minutes): 5800 RPM
Max. continuous power: 72 kW = 97,9 HP
Max. continuous engine speed: 5500 RPM
Max. coolant temperature: 120C
Max. oil temperature: 130C
Normal operating oil temperature: 90 to 110C
Oil quantity Minimum: 2.5 liter
Maximum: 3.0 liter
Oil pressure: Minimum: 0.8 bar (below 3500 RPM)
Normal: 3-5 bar (above 3500 RPM)
Maximum: 7 bar (shortly, at cold start)
Fuel pressure: Minimum: 2.7 bar
Maximum: 3.4 bar
Fuel: MOGAS EN 228 Super / EN 228 Super plus
Alternative: AVGAS 100 LL = ASTM D910-76 = MIL-G5772
For usage of AVGAS adhere to instructions in
ROTAX 912iSC/iS Sport operating handbook

Limitations Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 15
Lubricant: high performance motorcycle oil with gear additives
with API classification „SG“ or higher, see also Rotax
information SI-912-i-001, last edition
Coolant: Conventional e.g. BASF Glysantine Protect Plus G48
anticorrosion, mixture ratio 50% concentrate to 50%
water, see Service Instruction SI-92 i-001
Propeller manufacturer: Neuform Composites GmbH&Co
Propeller type: CR3-75 3-blade
Diameter: 175cm
Blade angle (gaugeable secant 365 mm from hub center) 25°
Rotational speed restriction range: none
2.5 Powerplant instrument markings
The instrument markings are programmed in the Stock Flight EMU
912i. It is not permissible to exchange the software in this unit unless
mandated by a Service bulletin.
INSTRUMENT
Red
Yellow
Green
Yellow
Red
Minimum
limit
Caution
range
Normal
range
Caution
Range
Maximum
limit
RPM indicator
0 - 1500
1500 -1800
1800 -5500
5500 -5800
> 5800
Manifold Air
Pressure [hPa]
-
0 - 200
200 -1100
1100 -1150
> 1150
Manifold
Temperature [°C]
-
< -25
-25 - 40
40 - 65
> 65
Oil pressure [bar]
0 - 0.8
0.8 - 2.0
2.0 - 5.0
5.0 - 7.0
7.0
Oil temperature [°C]
-
-65 - 50
50 - 110
110 - 130
130
Fuel pressure [bar]
0.0 - 2.7
2.7- 2.8
2.8 - 3.2
3.2 - 3.4
3.4
Fuel Flow [l/hr]
-
-
0-20
20-25
> 30
Coolant
Temperature [°C]
-
< 50
50 - 110
110 - 120
> 120
Exhaust Gas
Temperature [°C]
-
-
-65 - 900
900 - 950
> 950
Ambient Air
Pressure [hPa]
-
< 400
> 400
-
-
Ambient Air
Temperature [°C]
-
< -25
-25 –40
> 40
-
ECU Supply Bus
Voltage [V]
< 10
-
10 - 12
-
> 15

Lightwing AC4 Limitations
Page 16 Rev.:2 LW-RL-Z-002
2.6 Miscellaneous instrument markings
none
2.7 Weight limits
Maximum take-off mass: 600 kg
Maximum permissible operational empty mass 405 kg
Maximum loading aft baggage compartment: 25 kg
Datum line for centre of gravity is 1 meter forward of the propeller
flange.
The centre of gravity has to be between the following established
limiting values aft of datum:
FWD CG limit for TOW<540kg 2885mm aft of datum = 12%MAC
FWD CG limit for TOW=600kg 2940mm aft of datum = 16%MAC
linear limit in between
AFT CG limit for TOW>450kg 3008mm aft of datum = 21%MAC
2.8 Approved manoeuvres
The airplane is certified under the CS-LSA category for which the
following manoeuvres are approved:
- All manoeuvres incident to normal flying
- Stalls
- Lazy eight
- Chandelles
- Steep turns, in which the angle of bank is not more than 60°
Aerobatic flight, including spins is not approved.
2.9 Manoeuvring load factors
Flap deflection
Permissible load factor
positive
negative
0°
+4
-2
10°/24°
+2
0

Limitations Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 17
2.10Flight crew
Minimum crew is one pilot.
In general the seat of the pilot in command is on the left side.
The airplane may be operated single seat only using the left seat.
2.11Kinds of operation
The airplane is certified for
- Flights following visual flight rules (VFR) during day
Maximum permissible flight altitude
- 12.000 ft
Not approved are:
- Flight at night
- Flight under instrument rules (IFR)
- Flight in known icing conditions
- Spins
WARNING: Being a light sport airplane category aircraft,
approved under CS-LSA, the aircraft does
not feature a lightning protection system.
Flights in the vicinity of thunderstorm activity
must be avoided.
2.12Fuel
The aircraft contains a single fuel tank behind the seats.
Fuel capacity: 94 liter
Usable fuel quantity: 90 liter
Unusable fuel quantity: 4 liter
NOTE: Acceleration during take-off run may cause
the low fuel warning light to illuminate with
less than 12 liter of usable fuel.
2.13Maximum passenger seating
AC4 has one (1) passenger seat.

Lightwing AC4 Limitations
Page 18 Rev.:2 LW-RL-Z-002
2.14Other limitations
Maximum permissible current 12V plug (charge&supply mode) 5Amp
Maximum permissible current on USB outlet 1Amp
2.15Limitation placards
"This airplane must be operated in VFR-day only conditions in
accordance with airplane flight manual LW-RL-Z-002"
"Manoeuvre speed VA176km/h IAS"
"No intentional spins"

Emergency procedures Lightwing AC4
LW-RL-Z-002 Rev.:2 Page 19
3 Emergency procedures
3.1 Introduction ..........................................................................20
3.2 Engine emergencies.............................................................20
3.2.1 Engine malfunction during takeoff run ...........................20
3.2.2 Engine malfunction after take off...................................21
3.2.3 Engine malfunction during flight (Restart Procedure).....21
3.2.4 Lane and Generator warning in flight.............................22
3.2.5 Exceeding engine limits.................................................23
3.2.6 Oil pressure below minimum on ground ........................23
3.2.7 Oil pressure below minimum during flight......................23
3.3 Fires.....................................................................................24
3.3.1 Engine fire on ground....................................................24
3.3.2 Engine fire during flight..................................................24
3.3.3 Electrical fire during flight ..............................................24
3.4 Glide.....................................................................................25
3.5 Landing emergency..............................................................26
3.5.1 Emergency landing without engine power.....................26
3.5.2 Precautionary landing with engine power......................26
3.5.3 Landing with flat tire ......................................................26
3.6 Recovery from unintentional spin .........................................27
3.7 Other emergencies...............................................................28
3.7.1 Malfunctions of electrical system...................................28
3.7.2 Fuel Pressure outside range .........................................30
3.7.3 Low fuel warning...........................................................31
3.7.4 Cockpit smoke/Exhaust gas/CO-contamination.............31

Lightwing AC4Emergency procedures
Page 20 Rev.:2 LW-RL-Z-002
3.1 Introduction
This section presents the checklist including description of
recommended procedure for emergency situations.
Emergency situations caused by failures on the aircraft or aircraft’s
engine are rare when the required maintenance and pre-flight
inspections are followed!
Not all emergencies can be foreseen and described in the aircraft flight
manual. For this reason, knowledge of the aircraft and its systems as
well as pilot’s experience in dealing with occurring problems are
required.
CAUTION: In all emergencies: stay calm and determine
the cause.
3.2 Engine emergencies
CAUTION: In case the engine fuel supply or ignition is
interrupted, the propeller will stop if airspeed is
too low. Once the propeller has fully stopped,
an airspeed approaching VNE would be
required to windmill. Therefore engine restart
with a stopped propeller must be performed
using the electric starter.
3.2.1 Engine malfunction during takeoff run
Throttle.................................................................................. IDLE
Fuel Shutoff Valve ............................................................CLOSE
Engine Key ............................................................................OFF
Brakes...................................................................... APPLY FULL