HPH Glasflugel 304 C Technical specifications

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Document No.: G304C/AFM
Date of Issue: 12/01
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Mo od de el l: :Glasflügel 304 C
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Se er ri ia al l N No o. .: : ..............................
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Re eg gi is st tr ra at ti io on n: : ..............................
Type Certificate No.: 98-03
Date of Issue: 12/01
Pages identified by “Appr” are approved by:
Signature: ..................................................
Authority: ..................................................
Stamp:
Original date of approval: ..................................................
Approved under Ref. No.: ..................................................
This English edition of the Glasflügel 304 C Flight Manual has been
translated with care and is accurate to best of our knowledge. However, in
all official matters the original Czech text is the authoritative and definite
document.
This sailplane is to be operated in compliance with information and
limitations contained herein.
This Flight Manual must be located aboard the sailplane at all times.
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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. ./ /f fa ax x: : + [phone] 13 34 44 41 1
HPHLtd.

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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

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0.2 List of Effective Pages
Section Page
Date of
Issue Section Page
Date of
Issue
2-9 Appr. 12/01
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Date of
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Date of
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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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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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1.1 Introduction
The sailplane flight manual has been prepared to provide pilots with
information for the safe and efficient operation of the Glasflügel
304 C 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 sailplane has been approved by Civil Aviation Authority
of the Czech Republic in accordance with LSFM regulation, issued
by LBA on 23rd October, 1975 and with
Section F and G of JAR-22, 28th October, 1995, Change 5
Type Certificate No.: 98-03
Issued on: 2nd April, 1998
Category of airworthiness: UTILITY

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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 an immediate or important degradation of the 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 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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1.4 Descriptive data
Glasflügel 304 C is single-seat all-fiberglass construction (GRP)
sailplane of FAI standard class.
Sailplane description
Fuselage
The fuselage tapers behind the wing, the faired-in one piece
canopy is hinged forward.
The fuselage shell is of GRP single skin construction, therefore
capable of large energy absorption. The fuselage shell is supported
by GRP profile frames.
The pilot is seated in a semi-reclining position.
The landing gear is retractable.
A C.G. release is fitted as standard, and an Aerotow nose release
can be fitted on request.
Wing
The two-piece wing is cantilever and double trapezoidal. It is
constructed as a GRP-Foam-Sandwich shell with spar caps of
parallel glass fibers, extruded by a method developed by Hütter and
Hänle, and shear webs of reinforced GRP-Foam-Sandwich. The air
brakes are located only on the wing upper surface aprox. in one
third of wing semi-span. The ailerons have an internal drive thus
the wing skin is not disturbed.
The two replaceable water ballast bags can carry up to 115 liters
i.e. 25.3 Ukgal, 30.4 USgal.
Horizontal Tail Unit
The horizontal tail unit consists of a stabilizer and elevator.
Trimming is by means of a leaf spring on the control column,
adjustment is possible by a touch-button on the handgrip of the
control column. The stabilizer is of GRP-Foam-Sandwich
construction.

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Vertical Tail Unit
The fin and the rudder are similarly as the stabilizer of GRP-Foam-
Sandwich Shell construction. The rudder has an internal drive thus
the fuselage outline is not disturbed.
Cockpit interior
Headrest, backrest and rudder pedals are adjustable in flight. Seat
cushions are as well the sailplane standard equipment.
The instrument panel is tilted together with the cockpit canopy,
which make possible easy boarding.
The cockpit ventilation is provided by the slots through the
instrument panel support. Fresh air is brought to the pilot by the
butterfly outlets located on both sides of the instrument panel. If
necessary the canopy sliding window (DV) may be also used for
ventilation.
A battery box, barograph tray, and a water ballast system are
installed in the cockpit, as well.

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Basic Technical Data
Wing
Span.................................15 m..................49.21 ft
Wing area......................9.88 m2..............106.35 ft2
Aspect ratio .................22.78
Fuselage
Length ...........................6.45 m..................21.16 ft
Width.............................0.62 m....................2.03 ft
Height............................1.36 m....................4.46 ft
Cockpit height................0.83 m....................2.72 ft
Horizontal Tail Unit
Span................................2.1 m....................6.89 ft
Area...............................0.99 m2................10.66 ft2
Aspect ratio ...................4.42
Vertical Tail Unit
Height............................1.15 m....................3.77 ft
Area...............................0.89 m2..................9.58 ft2
Aspect ratio ...................1.49
Landing gear
Main wheel........................5,00x5
Tail wheel........................ 210x65

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1.5 Three-view drawing

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SECTION 2
2. Limitations
2.1 Introduction
2.2 Airspeed
2.3 Airspeed indicator markings
2.4 Weight
2.5 Center of Gravity
2.6 Approved maneuvers
2.7 Maneuvering load factors
2.8 Flight crew
2.9 Kinds of operation
2.10 Minimum equipment
2.11 Aerotow and winch-launching
2.12 Other limitations
Limitations placards

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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 CAA, Czech Republic.
2.2 Airspeed
Airspeed limitations and their operational significance are shown
below:
Speed IAS
[km/h] KIAS
IAS
[mph] Remarks
VNE Never exceed
speed 250 135 155 Do not exceed this speed in any
operation and do not use more
than 1/3 of control deflection
VRA Rough air
speed 200 108 124
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 200 108 124
Do not make full or abrupt
control movement above this
speed, because under certain
conditions the sailplane may be
overstressed by full control
movement.
VTMaximum
aerotowing
speed 150 81 93 Do not exceed this speed during
aerotowing
VWMaximum
winch-launching
speed 150 81 93 Do not exceed this speed during
aerotowing

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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 vNE IAS
[m ISA] [ft ISA] [km/h] KIAS [mph]
0
-
4 000
0
-
13 000 250 135 155
5 000 16 000 240 130 149
6 000 19 500 226 122 140
7 000 22 900 214 116 133
8 000 26 000 202 109 126
9 000 29 500 191 103 119
10 000 32 700 179 97 111
12 000 39 300 159 86 99

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2.3 Airspeed indicator markings
Airspeed indicator markings and their color-code significance are
shown below:
Value or range IASMarking
[km/h] KIAS [mph] Significance
Green
arc 94-200 51-108 58-124 Normal operating range
Yellow
arc 200-250 108-135 124-155 Maneuvers must be
conducted with caution
and only in smooth air
Red
line 250 135 155 Maximum speed for all operation.
Yellow
triangle
85 46 53 Approach speed at
maximum weight
without water ballast
2.4 Weight
Max. take-off weight...................................450 kg 992 lbs
Max. landing weight ...................................450 kg 992 lbs
Max. weight of all non-lifting parts..............240 kg 529 lbs
(i.e. all parts incl. cockpit and baggage compartment load, with
water ballast inside the wing)
Maximum weight at basic
aerobatic maneuvers..................................380 kg 838 lbs
Maximum weight without water ballast ......380 kg 838 lbs
Maximum weight in baggage compartment.10 kg 22 lbs
(incl. all installed equipment)

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Maximum water ballast weight is shown in table as follows:
Cockpit load
65 kg 70 kg 80 kg 90 kg 100 kg 110 kg
Empty
weight 143 lbs
154 lbs 176 lbs 198 lbs 220 lbs 242 lbs
230 kg
507 lbs 115 kg
254 lbs
115 kg
254 lbs
115 kg
254 lbs
115 kg
254 lbs
115 kg
254 lbs
110 kg
242 lbs
240 kg
529 lbs 115 kg
254 lbs
115 kg
254 lbs
115 kg
254 lbs
115 kg
254 lbs
110 kg
242 lbs
100 kg
220 lbs
250 kg
551 lbs 115 kg
254 lbs
115 kg
254 lbs
115 kg
254 lbs
110 kg
242 lbs
100 kg
220 lbs
90 kg
198 lbs
260 kg
573 lbs 115 kg
254 lbs
115 kg
254 lbs
110 kg
242 lbs
100 kg
220 lbs
90 kg
198 lbs
80 kg
176 lbs
270 kg
595 lbs 115 kg
254 lbs
110 kg
242 lbs
100 kg
220 lbs
90 kg
198 lbs
80 kg
176 lbs
70 kg
154 lbs
280 kg
617 lbs 105 kg
231 lbs
100 kg
220 lbs
90 kg
198 lbs
80 kg
176 lbs
70 kg
154 lbs
60 kg
132 lbs
CAUTION
The shaded cockpit load requires a check, whether the maximum
weight of all non-lifting parts (240 kg, 529 lbs) will not be
exceeded.
The maximum baggage weight is 10 kg, 22 lbs including installed
equipment and must be considered when establishing the
maximum water ballast weight according to the table above.
2.5 Center of Gravity
Permitted C.G. range in flight...........................24.5-42.8 %MAC
i.e........................................................................200-325 mm
behind a reference point – point on the leading edge of the wing
root section.
Empty sailplane C.G. position for the cockpit load within 70-110 kg
(154-242 lbs) must fit into the crosshatched area in the following
diagram:

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If the pilot with a parachute does not reach the placarded minimum
cockpit load, the appropriate amount of lead ballast must be carried
in the nose. One kg of lead ballast (2.2 lbs) in the ballast box will
compensate for 2.4 kg (5.3 lbs) of the pilot‘s weight. Maximum lead
ballast capacity of the ballast box is 6 kg (13.2 lbs).
Suitable lead ballast plates are available from HPH Ltd. .
The empty sailplane C.G. may fit in some cases above or below the
crosshatched area of the diagram and the maximum cockpit load is
less than 110 kg (242 lbs) or minimum cockpit load is higher than
70 kg (154 lbs). In such case the modification should be approved,
at first, as well as recorded in the appropriate documents.