Jihlavan KP-5 ASA Owner's manual

Pilot Operating Handbook KP-5
1
PILOT OPERATING
HANDBOOK
of
KP – 5 ASA
(Including Aircraft Operating Instructions and Flight
Training Supplement)
Manufacturer: JIHLAVAN airplanes s.r.o.
Znojemská 64
586 01 Jihlava
Czech Republic
Production number: 5 198 209 Q
Registration mark: …………………
Category: Light Sport Aircraft
Date of issue: 2011

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OWNER – OPERATOR OF THE AIRCRAFT:
Owner of the aircraft:
Name:
Address:
Identity number:
Registration mark:
From: To:
The change of the ownership:
Name:
Address:
Identity number:
Registration mark:
From: To:
The change of the ownership:
Name:
Address:
Identity number:
Registration mark:
From: To:

Pilot Operating Handbook KP-5 ASA
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Owner of the aircraft:
Name:
Address:
Identity number:
Registration mark:
From: To:
The change of the ownership:
Name:
Address:
Identity number:
Registration mark:
From: To:
The change of the ownership:
Name:
Address:
Identity number:
Registration mark:
From: To:

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CONTENTS
PAGE
CONTENTS 4
CHAPTER 1: General information 5
CHAPTER 2: Operating limitations 18
CHAPTER 3: Weight and balance informations 23
CHAPTER 4: Performance 27
CHAPTER 5: Emergency procedures 31
CHAPTER 6: Standard procedures 36
CHAPTER 7: Placards and markings 47
CHAPTER 8: Aircraft ground handling and servicing 54

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1.0 GENERAL INFORMATION
Chapter contents Page
1.1 Introduction 6
1.2 Amendments 6
1.3 Abbreviations and definitions 8
1.4 Dimensions of the aircraft 9
1.5 Basic technical data 10
1.6 Engine 11
1.7 Propeller 12
1.8 Fluids 12
1.9 Instrumentation equipment 14
1.10 Cockpit 15

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1.1 Introduction
Validity: The Pilot Operating Handbook is valid exclusively for the
plane whose number is on the first page of the manual.
Notice: It is necessary for the crew to be familiar with this Pilot
Operating Handbook before the flight!
1.2 Amendments
1.2.1 All amendments and supplements of the Pilot Operating
handbook should be done as follows:
a) the manufacturer of LSA aircraft sends an operational
update with new and revised information to the owner of
the Pilot Operating handbook.
b) the holder of the Pilot Operating handbook is obliged:
1/ to change the original information with the revised
edition, which is marked by the abbreviation „REV“
and the date of the change.
2/ to make a record of receiving the amendment into the
amendment list. This list is found in art. 1.2.2.
on page 6.
Note: The changed and amended parts of the text will be marked on the
new pages by a vertical line on one side and by the
corresponding number of the amendment according to the
amendments list in art. 1.2.2., page 6 amendments

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1.2.2 Amendments list
Number
of the
change
Number of
amendment
update
Number of
concerned
pages
Issue date
of the new
pages
Date
of new pages
change
and signature
Note: The holder of the Pilot Operating handbook fills in this chart. For
instructions see art. 1.2.1.

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1.3 Abbreviations and definitions
CAS Calibrated airspeed. It is IAS corrected by errors due to
instrument and pitot port errors. CAS is equivalent to the true
airspeed at zero level of international standard atmosphere.
IAS Indicated airspeed. It is the reading of the in-built airspeed
indicator corrected by the instrument error.
TAS True airspeed. It is the aircraft velocity considering
“undisturbed” air.
IFR Instrument flight rules.
VFR Visual flight rules.
ISA International standard atmosphere.
MAC Mean aerodynamic chord.
VTU Vertical tail unit (fin with rudder).
HTU Horizontal tail unit (stabilizer with elevator).
VADesigned manoeuvring velocity.
VSO Stalling velocity in landing configuration.
VS1 Stalling velocity with flaps up.
VNE Never exceed velocity.
VFE Maximum velocity with flaps fully extended
VF0 Maximum velocity for flap extending and retracting.
RWY Runway
POH Pilot Operating handbook
LSA Light sport aircraft
Note: Unless otherwise stated, the indicated airspeeds in the manual are
CAS.

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1.4 Dimensions of the aircraft

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1.5 Basic technical data
1.5.1 Technical description
KP-5 is a two-seater, all-metal, self-contained, low-wing aircraft with
side-by-side seats. Supporting surfaces are with two spars. They are
composed of a rectangular center-section and a trapezoidal outer wing
with Fowler flap. The fuselage is of a semi-monocoque construction.
Tail units are self-contained, all metal with a forward HTU. The aircraft
is equiped with the fixed three-wheel undercarriage.
1.5.2 Dimensions of the aircraft
Wing span
Length
Height
Wing area
Depth of the mean aerodynamic chord
Dihedral of the wing
Dihedral of the center section
Dimensions of landing gear tire - nose
- main
Landing gear gauge
Landing gear wheel base
Nose leg tire pressure
Main leg tire pressure
32 ft 5,5 in
23 ft 7,3 in
7 ft 2,6 in
127,5 ft2
4 ft 2 in
6 o
0 o
300x85 (4")
350x115 (6“)
6 ft 7,7 in
4 ft 11 in
36 ±1,5 psi
36 ±1,5 psi

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1.5.3 Deflections of the control surfaces
Ailerons:
Flaps:
Elevator:
Rudder:
Trim
deflection –
deflection I
deflection II
deflection –
deflection –
deflection -
up
down
up
down
left
right
up
down
23
o
±1
o
16o ±1o
10o ±2o
35o ±2o
34o±3o
28o ±2o
28o±2o
28o±2o
30o±2o
30o±2o
1.5.4 Weights
Empty weight
Maximum T.O. weight
Maximum cabin baggage weight
787 lb (357 kg)
1279 lb (580 kg)
66 lb (30 kg)
1.6 Engine
Detailed data of the engine is stated in the Operator‘s Manual for
all versions of ROTAX 912. It is not stated in this handbook.
Type Rotax R 912 UL / Rotax R 912 ULS
T.O. RPM 5800 1/min (max. 5min.)
Maximum RPM 5500 1/min
Idle RPM 1400 1/min

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1.7 Propeller
Detailed data of the propeller is stated in the Propeller Technical
Manual. It is not stated in this handbook.
Manufacturer: DUC Swirl
Type: 12088/12117/12248
Diameter:
Direction of rotation:
Weight: ……………..
1.8 Fluids
For all the fluids, follow the instructions in the Rotax 912 Manual.
Operating propellants used by manufacturer:
Engine
912 UL
912 ULS
Fuel
Min. RON 90
Min. RON 95
EN 228 Normal
---------------
EN 228 Super
EN 228 Super
EN 228 Super plus
EN 228 Super plus
AVGAS 100 LL
AVGAS 100 LL
Canadian standard:
CAN/CGSB – 3,5
CAN/CGSB – 3,5
Quality :
1
3
Min. AKI :
Min. AKI
Min. AKI 91
Or car unleaded fuel equivalent to Canadian standard.
Max. fuel capcity
16,9 U.S. gal
Oil content of engine
Castrol GPS 10W-40, API SG
Max. oil capacity
0,66 U.S. gal
Cooling liquid
Mr. Vif Antifreeze BC + distilled water 1:1
Max. cooling liquid volume
0,71 U.S. gal
Brake fluid
SYNTOL HD 265
International standard: DOT 4,
SEA 1703

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1.8.1 Fuel tanks
Valid values for the aircraft with standart fuel tanks only:
Capacity
Max. capacity
Inexhaustible volume
Expansion capacity
Rest indicated by permanent light
2 x 8,45 U.S. gal
2 x 0,4 U.S. gal
5 %
1,3 ÷ 1,9 U.S. gal
Valid values for the aircraft equipped with additional fuel tanks:
Capacity
Max. capacity
Inexhaustible volume
Expansion capacity
Rest indicated by permanent light
2 x 11,9 U.S. gal
2 x 0,5 U.S. gal
10 %
3 ÷ 3,5 U.S. gal
Note: When taking off, open the fuel cock for pumping from the tank
with bigger amount of fuel.

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1.9 Instrumentation equipment
Flights instrument Type
Serial
number
Airspeed indicator
LUN 1106
522
Altimeter
BG-19
1820
Vertical speed indicator
BC-6
3141
Compass
CM-13
108 11 2009
Turn coordinator
WINTER
-
Elec. elevator trim control
RP3 LED
-
Flaps control
PFC 10
0925/65
DYNON
SKYVIEW 700
2216
SkyView module
SV-ADAHRS-200
3030
SkyView antenna
SV-GPS-250
-
Engine instruments
Type
Serial number
Engine speed indicator
XIF4.0008.03
C308949
Oil pressure indicator
ROAD
000531
CHT temp. indicator
XIH4.0018.00
30.11.2010
OIL temperature indicator
XIH4.0010.00
11.05.2010
Fuel pressure indicator
-
-
Engine-hours indicator
LR42455
AU1774
Manifold press. indicator
-
-
Fuel gauges (left, right)
CZECH REPUBLIC
443422065031
Fuel pump
7.21440.51
10T196
Voltmeter
AVIASPORT IM-561
9346
Other equipment
Type
Serial number
Battery
FORTE FG12170
12V/17AH
-
Strobe light (master)
AVE-POSW-001
AVE-0902-
00356
Emergency parachute sys.
GRS 5/560 soft B
5124.11.1662,
5923
DYNON - battery
SV-BAT 320
-
Other equipment Type
Serial
number
Transceiver
IC-A210E
2301194
Transceiver antenna
CI-121
353231
Transponder
GTX 327A
83742698

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1.10 Cockpit

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Key:
Note: The plane does not have to be equipped with all stated
instruments and controls. Equipment depends on customer’s
specification.
1. Airspeed indicator 48. Starter
2. Altimeter 49. Switches
3. Vertical velocity indicator 50. Socket
51. Transceiver
5. Attitude indicator 52. Transponder
6. Turn and bank indicator 53. Circuit breakers
7. Trim attitude indicator 54. Cooling
55. Heating
11. Engine-hours indicator
12. Engine speed indicator
13. Oil pressure gauge
14. Cylinder head temperature indicator
15. Oil temperature indicator
16. Exhaust gas temperature indicator
17. Fuel pressure gauge
18. Fuel gauge (left, right)
19. Manifold pressure gauge
21. Control stick
22. Rudder pedals
24. Fuel cock control lever
25. Choke lever
26. Throttle lever
27. Wing flap controller
32. Brake lever
42. Main switch
43. Magnetoes

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1.10.1 Operating switches of the left control stick
Key:
1. Transciever
2. Trim – nose down
3. Trim – nose up
4. Unused button
5. Intercom

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2.0 OPERATIONAL LIMITS
Chapter contents Page
2.1 Structural regulations 19
2.2 Operational speed limitatons 19
2.3 Colour code markings of airspeed indicator 19
2.4 Engine operational limitations 20
2.5 Wind operational limitations 20
2.6 Fuel capacity 20
2.7 Weights and C – G limits 20
2.8 Manoeuvres approved 21
2.9 Flight envelope 21
2.10 Load factors 22
2.11 Air temperature limitations 22
2.12 Other limitations 22

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2.1 Structural regulations
The KP - 5 aircraft construction, materials and performance correspond
with UL – 2 regulations issued by LAA ČR (Light Aircraft Association
of Czech Rep.)
2.2 Operational speed limitations
Airspeed
Abbrevia
tion
CAS
(knots)
CAS
(MPH)
Never exceed airspeed V
NE
140 162
Max. speed of horizontal flight
VH
120
138
Max. manouvering speed
- do not execute full deflections of control
surfaces above this velocity VA84 97
Maximum velocity with flaps fully
extended VFE 59 68
Stalling speed in landing configuration
VS0
35
40
Stalling speed with retracted flaps
VS
42
48
2.3 Engine operational limitations
Specifications stated in this article are not complete. For more
information, see Operator‘s Manual for all versions of ROTAX 912
Engine
Value
Oil pressure
max. 7 bar, min. 0,8 bar
normal 2.0 –5,0 bar
Oil temperature
R 912 UL
min. 50
°
C, max. 140
°
C
R 912 ULS
min. 50°C, max. 130°C
normal 90-110
°
C
Cylinder head
temperature
R 912 UL
max. 150°C
R 912 ULS
max. 135°C
Exhaust gas temperature
max. 880°C – at T-O
max. 850
°
C – during fly
normal 800
°
C
Fuel pressure
max. 0,4 bar, min. 0,15 bar
normal 0,15-0,4 bar

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Note:
- do not use increased power of engine during flight (allowed for take-
off and in emergency cases only)
- take-off is prohibited if engine is running unnaturally or if data on
engine instruments is not in operating ranges
-do not use change over of suction chamber for suction without filter
(preheated air) on the ground
2.4 Crosswind and wind limitations
Maximum wind speed component for take-offs and landings:
- in RWY direction (headwind) 23,3 kt
- crosswind 15,6 kt
2.5 Fuel capacity
Fuel capacity in one tank 8,45 (11,9) U.S.gal
Total fuel capacity 16,9 (23,8) U.S.gal
Min. allowed amount for take-off (in one fuel tank) 2,6 U.S.gal
The amount of fuel is indicated by electromechanical fuel gauges. The
reserved capacity of 1,3 ÷ 1,9 (3 ÷ 3,5) U.S. gal in each tank is indicated
by the yellow amber light in fuel gauges.
2.6 Service ceiling
Service ceiling [ft] 14750
2.7 Maneuvers approved
Manoeuvre
Max. initial airspeed in IAS
(knots)
(MPH)
Steep turn (60° bank)
84
97
Slip
54
62