HPH Glasflugel 304S Technical specifications

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CZ ZE EC CH H R RE EP PU UB BL LI IC C
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[email protected]
HPH
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Document No.: G304S/AFM
Date of Issue: 08/14
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Mo od de el l: : Glasflügel 304 S
S
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.:
Date of Issue: 08/14
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 aboard the sailplane at all times.
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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
Signatu
re
R00 all all 08/14 EASA

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0.2 List of Effective Pages
Section Page
Date of
Issue Section Page
Date of
Issue
2-9 Appr. 08/14
0-1 08/14 2-10 Appr. 08/14
0-2 08/14 2-11 Appr. 08/14
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3 3-1 Appr. 08/14
1 1-0 08/14 3-2 Appr. 08/14
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1-3 08/14 4 4-0 Appr. 08/14
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1-6 08/14 4-3 Appr. 08/14
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Date of
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Date of
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4-17 Appr. 08/14 8-1 08/14
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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 S 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 EASA in accordance
with JAR-22, Amendement 7, 1
st
September, 2003
Type Certificate No.:
Issued on:
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 S is single seat 18m flapped sailplane of 18m
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. Fuselage is equipped
with engine compartment for further propulsion unit installation.
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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Cockpit interior
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.

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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

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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
2.12 Other limitations
2.13 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 EASA.
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 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 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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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.
Yellow
triangle
94 50 58
Approach speed at maximum
weight without water ballast
2.4 Weight
Max. take-off weight...................................600 kg 1322 lbs
Max. landing weight....................................600 kg 1322 lbs
Max. weight of all non-lifting parts..............373 kg 822 lbs
(i.e. all parts incl. cockpit and baggage compartment load, with
water ballast inside the fuselage, trim ballast, stabilizator & elevator)
Maximum weight in baggage compartment .10 kg 22 lbs
(incl. all installed equipment)

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CAUTION
Check the weight of non-lifting parts before each flight
The maximum baggage weight is 10 kg, 22 lbs including installed
equipment and must be considered when establishing the
maximum weight of non-lifting parts according to the table above.
CAUTION
The outboard wing tanks must be filled in advance.
2.5 Center of Gravity
Permitted C.G. range in flight..............................25-44,7 %MAC
i.e........................................................................251-387 mm
behind a reference point – point on the leading edge of the wing root
section at y=425 mm (16.7 in) out of the fuselage center line.
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.
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 3.49 kg (7 lbs) of the pilot‘s insufficient weight.
Maximum lead ballast capacity of the ballast box is 12 kg (26 lbs).
Suitable lead ballast plates are available from HPH Ltd. .
Permanent tail water ballast allows to pilot maintain the flight cg
position at optimum range. 1 kg (2.2 lbs) of the water ballast will
compensate for 4.8 kg (10 lbs) of the pilot‘s increased weight. Pilot
must check the minimum weight limitation given in ch. 6.3 before
use of this trim ballast
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.

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TRIM PLAN
G304S
400
450
500
550
600
650
700
250 270 290 310 330 350 370
SAILPLANE EMPTY WEIGHT
[ Kg ]
EMPTY CG POSITION
[ mm ]
NORMAL
RANGE
max.110kg
min. 70 kg
min. 75 kg
min. 80 kg
min. 85 kg
min. 90kg

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2.6 Approved maneuvers
This sailplane is certified in the UTILITY category.
Intentional aerobatic maneuvers are prohibited.
WARNING
Aerobatic maneuvers and intentional spins are prohibited.
2.7 Maneuvering load factors
The following load factors may not be exceeded during
maneuvers:
n = +5.3 at air speed VA = 200 km/h, 107 KIAS, 124 mph
-2.65 air brakes retracted
n = +4.0 at air speed VNE = 260 km/h, 140 KIAS, 161 mph
-1.5 air brakes retracted
n = +2 air brakes extended