HPH Glasflugel 304 MS Technical specifications

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FO OR R T TH HE E P PO OW WE ER RE ED D S SA AI IL LP PL LA AN NE E
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CZ ZE EC CH H R RE EP PU UB BL LI IC C
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[email protected]

Document No.: G304MS/AFM
Date of Issue: 07/14
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FL LI IG GH HT T M MA AN NU UA AL L
f
fo or r P Po ow we er re ed d S Sa ai il lp pl la an ne e
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Mo od de el l: : Glasflügel 304 MS
S
Se er ri ia al l N No o. .: :
R
Re eg gi is st tr ra at ti io on n: :
Type Certificate No.:
Date of Issue: 07/14
Pages identified by “Appr” are approved by EASA:
Signature: ..................................................
Authority: ..................................................
Stamp:
Original date of approval: ..................................................
Approved under Ref. No.: ..................................................
This sailplane is to be operated in compliance with information and
limitations contained herein.
This Flight Manual must be located onboard the sailplane at all times.
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Čá ás sl la av vs sk ká á 2 23 34 4
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CZ ZE EC CH H R RE EP PU UB BL LI IC C
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te el l: : + [phone] 12 26 63 33 3
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fa ax x: : + [phone] 13 34 44 41 1
[email protected]

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Document No.: G304MS/AFM
Date of Issue: 07/14
0 -1
0.1 Record of revisions
Any revision of the present manual, except actual weighing data,
must be recorded in the following table and in case of approved
Sections endorsed by the responsible airworthiness authority.
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 left hand of the page.
Rev.
No. Affected Section Affected Pages
Date
of
Issue Approval Date
of
approval
Date
of
Insertion
Signature
R00 all all 07/14

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Date of Issue: 07/14
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Section Page
Date of
Issue Section
Page
Date of
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Document No.: G304MS/AFM
Date of Issue: 07/14
0 -5
0.3 Table of Contents
Section
General....................................................................................1
(a non-approved section)
Limitations ..............................................................................2
(an approved section)
Emergency procedures .........................................................3
(an approved section)
Normal procedures ................................................................4
(an approved section)
Performance ...........................................................................5
(a partly approved section)
Weight and balance / equipment list....................................6
(a non-approved section)
Sailplane and systems description ......................................7
(a non-approved section)
Sailplane handling, care and maintenance.........................8
(a non-approved section)
Supplements...........................................................................9

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Document No.: G304MS/AFM
Date of Issue: 07/14
1-0
SECTION 1
1. General
1.1 Introduction
1.2 Certification basis
1.3 Warnings, cautions and notes
1.4 Descriptive data
1.5 Three-view drawing

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Document No.: G304MS/AFM
Date of Issue: 07/14
1-1
1.1 Introduction
The Flight Manual for this powered sailplane has been prepared to
provide pilots with information for the safe and efficient operation of
the Glasflügel 304 MS powered sailplane.
This manual includes the material required to be furnished to the
pilot by JAR-22. It also contains supplemental data supplied by the
sailplane manufacturer.
1.2 Certification basis
This type of self-launching powered sailplane has been approved by
EASA in accordance with JAR-22, Amendement 7, 1
st
September,
2003.
Type Certificate No.:
Issued on:
Category of Airworthiness: utility
Noise Certification Basis: CS-36 Amdt. 2 and
Section G36.101(a) FAR36

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Document No.: G304MS/AFM
Date of Issue: 07/14
1-2
1.3 Warnings, cautions and notes
The following definitions apply to warnings, cautions and notes in
the flight manual.
WARNING
Means that the non-observation of the corresponding
procedure leads to immediate or important degradation of
the flight safety.
CAUTION
Means that the non-observation of the corresponding procedure
leads to minor or to more or less long term degradation of the
flight safety.
NOTE
Draws the attention of any special item not directly related to
safety but which is important or unusual.

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Document No.: G304MS/AFM
Date of Issue: 07/14
1-3
1.4 Descriptive data
Glasflügel 304 MS is single seat 18 m flapped powered sailplane
(capable of self-launching) of 18 m FAI class, constructed from fiber
reinforced plastics (FRP), featuring camber-changing flaps and a T-
tail (with fixed horizontal stabilizer and elevator).
Sailplane description
Fuselage
The fuselage shell is pure CFRP shell construction reinforced with
Carbon Aramid hybrid fabrics in the pilot area, therefore capable of
large energy absorption.
The fuselage tapers behind the wing, the faired-in one piece canopy
is hinged forward. Canopy jettison mechanism incorporates the
Rögger pivot hook.
The pilot is seated in a semi-reclining position.
The landing gear is retractable and damped.
A C.G. release is fitted as standard, and an Aerotow nose release
can be fitted on request.
Wing
The four-piece wing is cantilever and double trapezoidal.
Removable wing extensions are optional. It is constructed as a
CFRP-Foam-Sandwich shell with extruded spar caps of parallel
carbon fibers and shear webs of reinforced GFRP-Foam-Sandwich.
Airbrakes are of the Schempp-Hirth type.
Two integral water ballast tanks carry a total of 194 liters.
Horizontal Tail Unit
The horizontal tailplane has a stabilizer and elevators. Trimming is
by means of a spring on the control drive. The stabilizer is of GFRP-
Foam-Sandwich construction.
Fin and Rudder
The fin is similar to the stabilizer of GFRP-Foam-Sandwich Shell
construction. The rudder is of the CFRP construction.

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Document No.: G304MS/AFM
Date of Issue: 07/14
1-4
Cockpit interior
Head-rest, back-rest and rudder pedals are adjustable in flight. The
back-rest rotation point can only be adjusted on the ground.
When the canopy is opened the instrument carrier pivots upward
and renders possible a comfortable and unrestricted pilot entry and
exit.
The canopy is ventilated by slots in the canopy frame, fresh air for
the pilot is provided by an outlet right of the canopy frame. If
necessary the sliding window (DV) in the canopy may be used for
ventilation, too.
Battery box, barograph tray and a water ballast system are installed.
Power plant
The „Glasflügel 304MS“ is the self-launching variant of
sailplane model “Glasflügel 304S”. Model 304MS is mostly identical
with the 304S model. Points of difference are only at the engine
compartment fuselage section.
The “Glasflügel 304MS ” is powered by an liquid-cooled 39 kW (53
HP) SOLO engine type 2625 01 - having a 3 : 1 toothed belt
reduction drive.
The power plant is housed in the fuselage aft of the wing, and an
electrical spindle drive pivots it such that the propeller pylon extends
from the engine bay.
Main fuel tank is installed in fuselage. Wing tanks may be optionally
installed in inner part ofone or both wings.

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Document No.: G304MS/AFM
Date of Issue: 07/14
1-5
Basic Technical Data
Wing
Span.................................18 m..................59.06 ft
Wing area......................11.8 m
2
..............127.01 ft
2
Aspect ratio .................27.43
Fuselage
Length............................6.79 m..................22.28 ft
Width.............................0.62 m....................2.03 ft
Height............................1.48 m....................4.86 ft
Cockpit height................0.83 m....................2.72 ft
Horizontal Tail Unit
Span................................2.5 m....................6.89 ft
Area...............................0.99 m
2
................10.66 ft
2
Aspect ratio ...................6.33
Vertical Tail Unit
Height............................1.25 m....................3.77 ft
Area...............................1.05 m
2
..................9.58 ft
2
Aspect ratio ...................1.52
Landing gear
Main wheel ......................5,00x5
Tail wheel ........................210x65
Powerplant
Engine type......................SOLO 2625 01
Manufacturer ..................Solo Kleinmotoren GmbH, Germany
Power at 6250 RPM........39 kW (53 HP)
Propeller type ..................KS–1G–152–R–122
Manufacturer ..................Technoflug Leichtflugzeugbau
GmbH, Germany
Reduction ratio ................1:3

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Date of Issue: 07/14
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1.5 Three-view drawing

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Document No.:G304MS/AFM
Date of Issue: 07/14
2-0
Approved
SECTION 2
2. Limitations
2.1 Introduction
2.2 Airspeed
2.3 Airspeed indicator markings
2.4 Powerplant, fuel and oil
2.5 Powerplant instruments markings
2.6 Weight
2.7 Center of Gravity
2.8 Approved maneuvers
2.9 Maneuvering load factors
2.10 Flight crew
2.11 Kinds of operation
2.12 Minimum equipment
2.13 Aerotow and winch launch
2.14 Other limitations
2.15 Limitations placards

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Document No.:G304MS/AFM
Date of Issue: 07/14
2-1
Approved
2.1 Introduction
Section 2 includes operating limitations, instrument markings, and
basic placards necessary for safe operation of the sailplane,
standard systems and standard equipment.
The limitations included in this section and in Section 9. have been
approved by the EASA.

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Document No.:G304MS/AFM
Date of Issue: 07/14
2-2
Approved
2.2 Airspeed
Airspeed limitations and their operational significance are shown
below:
Speed IAS
[km/h] KIAS IAS [mph] Remarks
VNE Never exceed
speed 260 140 161 Do not exceed this speed in any
operation and do not use more
than 1/3 of control deflection
VRA Rough air speed 200 107 124
Do not exceed this speed except
in smooth air, and then only with
caution.
Examples of rough air are lee-
wave rotor, thunderclouds etc.
VAManeuvering speed
200 107 124
Do not make full or abrupt
control movement above this
speed, because under certain
conditions the sailplane may be
overstressed by full control
movement.
VFE Maximum
speed
with flaps
+1,+2
L
200
160
107
86
124
99
Do not exceed this speeds in
any operation and do not use
more than 1/3 of control
deflection with flaps set on
+1, +2, L
VTMaximum
aerotowing speed 150 80 93 Do not exceed this speed during aerotowing
VWMaximum winch-
launching speed 130 70 80 Do not exceed this speed during winch - or autotow launching
VLO Maximum landing
gear operating
speed 180 97 111 Do not extend or retract the
landing gear above this speed
VPOmax Maximum
powerplant
extension and
retraction speed
120 64 74 Do not extend or retract the
retractable powerplant outside of
this range speed
VPOmin Minimum
powerplant
extension and
retraction speed
90 49 56
VPE Powerplant
extended maximum
permitted speed 180 97 111 Do not exceed this speed with
the powerplant extended

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Document No.:G304MS/AFM
Date of Issue: 07/14
2-3
Approved
CAUTION
Keep in mind, that a difference between Indicated Air Speed (IAS)
shown by your airspeed indicator and True Air Speed (TAS) is
increasing with an altitude increase.
This has no influence on the sailplane strength or load, however
due to flutter safety the IAS limits shown in table below must not be
exceeded in given altitudes.
Altitude Never exceed speed v
NE
IAS
[m ISA] [ft ISA] [km/h] KIAS [mph]
0
1000
0
3281
260
260
140
140
161
161
2000
3000
4000
5000
6000
7000
8000
9000
10000
6562
9843
13123
16404
19685
22966
26247
29528
32808
260
260
260
248
234
221
209
197
185
140
140
140
133
126
119
112
106
99
161
161
161
154
145
137
129
122
114

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Document No.:G304MS/AFM
Date of Issue: 07/14
2-4
Approved
2.3 Airspeed indicator markings
Airspeed indicator markings and their color-code significance are
shown below:
Marking
Value or range IAS Significance
[km/h] KIAS [mph]
White arc 85 - 200 45 - 107 52 - 124
Allowed range for Flaps set to
positive position
L – white mark and letter at
160 km/h
+1, +2 – white mark and
letters at 200 km/h
Green
arc 94-200 50 - 107 58-124
Normal operating range
Yellow
arc 200-260 107-140 124-161
Maneuvers must be
conducted with caution and
only in smooth air
Red
line 260 140 161
Maximum speed for all
operation.
Blue
line 100 54 62
Best rate-of-climb speed v
y
Yellow
triangle 94 50 58
Approach speed at maximum
weight without water ballast

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Document No.:G304MS/AFM
Date of Issue: 07/14
2-5
Approved
2.4 Powerplant, fuel and oil
Engine manufacturer: Solo Kleinmotoren GmbH
Stuttgarter Straße 41
71069 Sindelfingen
Germany
Engine model: SOLO 2625 01
Take-off power at
6200 RPM (MSL, ISA): 39 kW (53 HP)
Max. continuous
power at 6200 RPM: 39 kW (53 HP)
Maximum permitted
coolant liquid temperature: 115° C (239° F)
Fuel: Two-stroke mixture
AVGAS 100 LL or unleaded
premium gasoline EN 228,
not below RON 95
Oil (lubrication): Fuel / oil mixture, mixing proportion
for „CASTROL Super TT“
50:1 (2 %)
Propeller manufacturer: Technoflug Leichtflugzeugbau
GmbH. 78713 Schramberg,
Germany
Propeller model: KS-1G-152-R-122
Reduction ratio: 1:3
Fuel capacity: 13,5 l (3.57 US Gal.; 2.97 Imp. Gal)