Diamond Aircraft HK 36 TC with ROTAX 912 S Technical specifications

•
Diamond
AIRCRAFT
AIRPLANE FLIGHT MANUAL
for the Powered Sailplane
HK 36 TC
with ROTAX 912 S
Engine
Model
Serial No.
TC Data Sheet No.
Date of Issue
Doc. No.
Rotax 912
53
HK 36 TC
SF 3/82
January 9t
h, 2002
3.01.12-E
Pages identified by "ACG-appr." in the List of Effective Pages are approved by:
Signature
Authority
Stamp
Original date of approval
AUSTRO CONTROL GmbH
Ab tcilung Flugtcchni k
Zc nir alc
1\-1030 \ViClI, Sch lljrchga ~ ~e 11
26. A P~. Ze0 2
This powered sailplane must be operated in compliance with the information and
limitations contained herein,
Prior to operating the powered sailplane, the pilot must take notice of all the informa-
tion contained in this Airplane Flight Manual.
DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A.
OTTO -STR. 5
A-2700 WIENER NEUSTADT
AUSTRIA Page0-0, Rev. °

HK 36 TC-100
AFM •
Diamond
AIRCRAFT Introduction
0 .1 PREFACE
Congratulations on your choice of the HK 36 TC powered sailplane.
Skilful operation of an airplane will ensure your safety and provide you with hours of
enjoyment. Therefore, you should take the time to get familiar with your new
HK 36 TC.
We ask you to read this manual thoroughly and to pay attention to the recommenda-
tions given in it. If you do, you can expect many hours of incident-free flight operation
from your powered sailplane.
Translation of this Airplane Flight Manual has been done by best knowledge and
judgement. In any case, the original document in the German language (Doc. No.
3.01.12) is authoritative.
This document is protected by copyright. All associated rights, in particular those of
translation, reprinting, radio transmission, reproduction by photo-mechanical or similar
means and storing in data processing facilities, in whole or part, are reserved.
Copyright ©by: DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. Otto-Strafse 5
A-2700 Wiener Neustadt, Austria
Phone [phone]
Fax [phone]
E-Mail [e-mail]
09 Jan 2002
Rev. 0
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HK 36 TC-100
AFM •
Diamond
AIRCRAFT
Introduction
0.2 RECORD OF REVISIONS
Any revision of the present manual, except current weighing data, must be recorded in
the following table and in the case of approved sections endorsed by Austro Control
GmbH (ACG).
The new or amended text in the revised page will be indicated by a black vertical line
in the left hand margin, and the Revision No. and the date will be shown on the bottom
of the page.
In the event that you have obtained your HK 36 TC second-hand, please let us know
your address, so that we can supply you with the publications necessary for the safe
operation of your airplane.
Rev . Re ason
Chap - Page (s) Date of App roval
Date of Dateln- Signature
No. ter
Revision Approval serted
09 Jan 2002Rev. 0
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AIRCRAFT
Introduction
Rev . Reason
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Approval Date of Date In-
Signature
No . ter
Revision Approval serted
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AIRCRAFT
Introduction
0.3 LIST OF EFFECTIVE PAGES
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AIRCRA FT Introduction
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HK 36 TC-100
AFM •
Diamond
AIR CRAFT
Introduction
0.4 TABLE OF CONTENTS
Chapter
GENERAL
(a non-approved chapter) 1
OPERATING LIMITATIONS
(an approved chapter)2
EMERGENCY PROCEDURES
(an approved chapter) " . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
NORMAL PROCEDURES
(an approved chapter)4
PERFORMANCE
(a partly approved chapter) 5
MASS (WEIGHT) AND BALANCE
(a non-approved chapter) 6
POWERED SAILPLANE AND SYSTEMS DESCRIPTION
(a non-approved chapter)7
POWERED SAILPLANE HANDLING, CARE AND MAINTENANCE
(a non-approved chapter) 8
SUPPLEMENTS
(a partly approved chapter)9
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HK 36 TC-100
AFM General
CHAPTER 1
GENERAL
Page
1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . .
.. . . . . . . . . . . . . . . . . . . . 1-2
1.2 CERTIFICATION BASIS 1-2
1.3 WARNINGS, CAUTIONS AND NOTES . . . . . . . . . . . . . . . . . . . . . .
.. 1-3
1.4 EXPLANATIONS AND ABBREVIATIONS 1-4
1.5 UNITS OF MEASUREMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
.. 1-6
1.6 DESCRIPTIVE DATA 1-7
1.7 THREE-
VIEW DRAWINGS 1-8
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HK 36 TC-100
AFM General
1.1 INTRODUCTION
This Powered Sailplane Airplane Flight Manual has been prepared to provide pilots
and instructors with all the information that is necessary for the safe and efficient
operation of the powered sailplane.
This manual includes the material required to be furnished to the pilot by JAR-22. It
also contains supplementary data supplied by the powered sailplane manufacturer.
This Flight Manual conforms to the current version of the customer's airplane. How-
ever, any optional equipment (COM, NAV, etc.) is not considered. For their operation,
the operation manuals of the respective manufacturers must be followed.
This must always be kept onboard the airplane.
1.2 CERTIFICATION BASIS
The HK 36 TC powered sailplane with Rotax 912 S engine has been type certified by
Austro Control GmbH (ACG) in accordance with Change 5 of JAR-22 for sailplanes
and powered sailplanes as a derivative of the HK 36 TC. The Type Certificate Data
Sheet No. SF 3/82 has been amended.
Category of Airworthiness: Utility.
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AIRCRAFT
General
1.3 WARNINGS,CAUTIONS AND NOTES
The following definitions apply to warnings, cautions and notes used in the Airplane
Flight Manual.
WARNING
Means that the non-observation of the corresponding procedure
leads to an immediate or important degradation in 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 in
flight safety.
NOTE
Draws the attention on any special item not directly related to
safety but which is important or unusual.
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1.4 EXPLANATIONS AND ABBREVIATIONS
a) Airspeeds
lAS Indicated Airspeed.Airspeed read on airspeed indicator without
any correction of errors.
CAS Calibrated Airspeed. Indicated airspeed, corrected for installa-
tion and instrument errors.
TAS True Airspeed. The speed of the airplane relative to the air. TAS
is CAS corrected for errors due to altitude and temperature.
b) Meteorological terms
Pressure altitude Altitude indicated by the altimeterwhen the subscale is set to
1013.25 hPa or 29.92 inHg.
c) Flight performance
Take-off roll Distance between the start of the take-off run and the lift-off
point.
Take-off distance Distance between the start of the take-off run and the point
above which the airplane is able to clear a 15 m (50 ft) ob-stacle.
Service ceiling Maximum altitude that can be reached with a climb rate of at
least 0.5 m/s (100 fpm).
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AIRCRAFT
General
c) Mass and balance
Non-lifting parts Fuselage, rudder, horizontal tail surfaces and useful load
Useful load Occupants, baggage and fuel
d) Miscellaneous
ACL Anti Collision Light (Strobe Light)
AGL Above Ground Level
CG Center of Gravity
ELT EmergencyLocator Transmitter
GFRP Glass fiber reinforced plastic
CFRP Carbon fiber reinforced plastic
ACG Austro Control GmbH (formerly Bundesamt tur Zivilluftfahrt,
BAZ)
MAM
Mandatory Design Change Advisory
OAM
Optional Design Change Advisory
IPage 1 - 5 I
09 Jan 2002
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AFM •
Diamond
AIRCRA FT
General
1.5 UNITS OF MEASUREMENT
Dimensi on SI Units US Units
Convers ions
Length [mm] millimeters [in] inches [mm] I25.4 =[in]
[m] meters
[ft]
feet [m] I0.3048 =
[ft]
[km] kilometers [NM] nautical miles [km] I1.852 =[NM]
Volume [I] liters [US gal] US gallons
[I] I3.7854 =[US gal]
[qts] US quarts
[I] I0.9464 =[qts]
Speed [km/h] kilometers [kts] knots [km/h] I1.852 =[kts]
per hour [mph] miles per hour [km/h] I1.609 =[mph]
[m/s] meters per [fpm] feet per minute [m/s] x 196.85 =[fpm]
second
Speed of [RPM] revolutions per minute --
rotation
Mass [kg] kilograms [Ib] pounds [kg] x 2.2046 =[Ib]
Force, weight [N] newtons [Ibf] pounds force [N] x 0.2248 =[Ibf]
Pressure [hPa] hecto- [inHg] inches of [hPa] =[mbar]
pascal mercury [hPa] I33.86 =[inHg]
[mbar] millibar [psi] pounds per [bar] x 14.504 =[psi]
[bar] bar square inch
Temperature [
0C]
degrees [
OF]
degrees [°C]x1.8 +32 =[
OF]
Celsius Fahrenheit WF] - 32)/1.8 =[
0C]
Intensity of [A] amperes --
electric
current
Electric [Ah] ampere-hours
charge --
(battery
capacity)
Electric [V] volts
potential --
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AIR CRAFT General
1.6 DESCRIPTIVE DATA
The HK 36 TC is a two-seated powered sailplane in fiber-composite structure, de-
signed in compliance with JAR-22; Category of Airworthiness: Utility.
It is a low wing airplane with T-tail, side-by-side seating configuration, tricycle landing
gear and Schempp-Hirth type air brakes in the upper surface of the wings.
In order to enable a fast disassembly and a space-saving storage the airplane can be
furnished with a wing folding mechanism.
The power plant is a Rotax R 912 S3 engine with an mt-Propeller hydro-mechanically
variable pitch propeller, type MTV-21-A-C-F/CF175-05.
Span (with winglets)16.33 m 53 ft 7 in
Length 7.28 m 23 ft 11 in
Height 1.78 m 5 ft 10 in
MAC 1.004 m 3 ft 31/2in
Wing area 15.30 m2165 sq.ft
Max. wing loading 50.30 kg/m210.3 Ib/sq.ft
Aspect ratio 17
.1 1
Airfoil Wortmann FX 63-137
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HK 36 TC-100
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1.7 THREE-VIEW DRAWINGS
D imens ions in m il l imeters .
For conve
rs ion to inches,
refer to Sect
ion 1.5.
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AIRCRAFT
Operating
Limitations
CHAPTER 2
OPERATING LIMITATIONS
Page
2
.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
2.2 AIRSPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
2.2
.1 AIRSPEED LIMITATIONS 2-3
2.2.2 MISCELLANEOUS AIRSPEEDS 2-5
2.3 AIRSPEED INDICATOR MARKINGS 2-6
2.4 POWER-PLANT 2-7
2.4.1 ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
2.4.2 PROPELLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9
2.5 POWER-PLANT INSTRUMENT MARKINGS 2-9
2.6 MASS (WEIGHT) 2-10
2.7 CENTER OF GRAVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
.. 2- 11
2.8 APPROVED MANEUVERS . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11
2.9 MANEUVERING LOAD FACTORS 2-12
2.10 FLIGHT CREW 2-12
2.11 KINDS OF OPERATION 2-12
2.12 MINIMUM EQUIPMENT LIST 2-13
2
.1 3 FUEL 2-14
2.14 AEROTOW, WINCH UNO AUTO-TOW LAUNCHING 2-14
2.15 OTHER LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15
2.16 LIMITATION PLACARDS 2-15
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HK 36 TC-100
AFM Operating
Limitations
2 .1 INTRODUCTION
Chapter 2includes operating limitations, instrument markings, and basic placards
necessary for the safe operation of the powered sailplane, its engine,standard
systems and standard equipment.
The limitations included in this chapter and in Chapter 9have been approved by
Austro Control GmbH (ACG).
WARNING
All operation values must be kept within the limits stated
herein during flight.
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Diamond
AIRCRAFT
Operating
Limitations
2.2 AIRSPEED
NOTE
The airspeeds shown below must be understood as lAS.
2.2.1 AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown below:
Remarks Airspeed
VNE Never exceed 261 141 162 Do not exceed this speed in any
speed operation and do not use more
than 1/3 of control deflection.
vRA Rough air 210 113 130 Do not exceed this speed except
speed in smooth air, and then only with
caution. Examples of rough air are
lee-wave rotors,thunderclouds,
etc.
VA
Maneuvering 176 95 109 Do not make full or abrupt control
speed movements above this speed, as
the powered sailplane structure
could be overstressed by full con-
trol movement.
VABF Maximum ad- 150 81 93 Above this speed the air brakes
missible speed can be extended inadvertently
with air brakes over the half-extended position by
fixed in half-ex- aerodynamic forces.
tended position
I :
The WARNINGS on the following page must be complied with.
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AIRCRAFT
WARNING
Operating
Limitations
In order to ensure the flutter safety of the airplane, the
never exceed speed VNE (lAS) is reduced at pressure alti-
tudes above 2000 meters or 6500 ft (see Paragraph 4.5.7
HIGH ALTITUDE FLIGHT).
WARNING
At speeds beyond the rough air speed vRA the airplane may
be overstressed by heavy gusts (lee-wave rotors, thunder-
clouds, whirlwinds and turbulence at close range to moun-
tain ridges).
WARNING
The maneuvering speed stated on the previous page ap-
plies to the maximum TIO mass of 770 kg (1698 Ib). At
lower flight masses, the following limits must be complied
with:
TIC mass Maneuvering speed vA
kg Ib kmlh
kts mph
700 1543 168 91
104
650 1433 162 87
101
600 1323 155 84 96
WARNING
These speeds are not marked on the airspeed indicator.
Simultaneous full deflection of elevator and rudder can
overstress the airplane even at speeds below the maneu-
vering speed v
A-
Rev. 0 09 Jan 2002