1. Manuals
  2. Brands
  3. HPH Manuals
  4. Aircrafts
  5. Glasflugel 304S
  6. Manual

HPH Glasflugel 304 S Manual

Hide thumbs Also See for Glasflugel 304 S:
Table of Contents

Advertisement

Quick Links

Download this manual
H
P
O
P
E
R
A
T
I
N
G
O
P
E
R
A
T
I
N
G
H
Ltd.
T
E
C
H
N
I
C
A
L
T
E
C
H
N
I
C
A
L
,
M
A
I
N
T
E
N
A
,
M
A
I
N
T
E
N
A
F
O
R
T
H
E
F
O
R
T
H
E
Č
á
s
l
a
v
s
k
Č
á
s
l
a
v
s
k
2
8
4
0
1
K
2
8
4
0
1
K
C
Z
E
C
H
R
C
Z
E
C
H
R
t
e
l
.
:
+
4
2
0
t
e
l
.
:
+
4
2
0
f
a
x
:
+
4
2
0
f
a
x
:
+
4
2
0
i
n
f
o
@
h
p
i
n
f
o
@
h
p
D
E
S
C
R
I
P
T
I
D
E
S
C
R
I
P
T
I
N
C
E
A
N
D
R
N
C
E
A
N
D
R
S
A
I
L
P
L
A
N
E
S
A
I
L
P
L
A
N
E
á
2
3
4
á
2
3
4
u
t
n
á
H
o
r
a
u
t
n
á
H
o
r
a
E
P
U
B
L
I
C
E
P
U
B
L
I
C
3
2
7
5
1
2
6
3
3
3
2
7
5
1
2
6
3
3
3
2
7
5
1
3
4
4
1
3
2
7
5
1
3
4
4
1
h
.
c
z
h
.
c
z
O
N
,
O
N
,
E
P
A
I
R
M
A
N
E
P
A
I
R
M
A
N
U
A
L
U
A
L

Advertisement

Table of Contents
loading
Need help?

Need help?

Do you have a question about the Glasflugel 304 S and is the answer not in the manual?

Questions and answers

Related Manuals for HPH Glasflugel 304 S

Summary of Contents for HPH Glasflugel 304 S

  • Page 1 Č á á Č á á á á Ltd.
  • Page 2 Č á á Č á á á á Ltd. Glasflügel 304 S Document No.: 304S/MM Date of Issue: 08/14...

  • Page 3: Table Of Contents

    Ltd. Table of Contents ......................IST OF FFECTIVE AGES ......................... ECORD OF REVISIONS BASI C TECHNICAL DATA.....................1-0 ......................1-1 ASIC ECHNICAL DATA ......................1-2 ECHNICAL ESCRIPTION 1.2.1 Fuselage ..........................1-2 1.2.2 Wing ...........................1-2 1.2.3 Horiz ontal Tail Unit .......................1-2 1.2.4 Vertical Tail Unit ........................1-2 1.2.5 Water ballast system ......................1-2 .........................1-3...
  • Page 4 Ltd..........................4-1 ENERAL ..........................4-1 ERVICE INSPE CTIONS ........................4-1 CHE CK OUT PROGRAM ......................4-1 INSPE CTION RES ULTS ............C HYBA ÁLOŽKA NENÍ DEFINOVÁNA OBLIGA TORY INSPECTIONS ....................4-2 ....................4-2 IMITED OMPONENT ECTION CENTER OF GRAVITY ......................5-0 ....................5-1 ENTER OF RAVITY POSITION ........................5-3 AYLOAD ANGE...

  • Page 5: List Of Effective Pages

    Ltd. List of Effective Pages Section Page Date Section Page Date Section Page Date Cover page 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14 08/14...

  • Page 6: Record Of Revisions

    Ltd. 0.2 Record of revisions Any revision of this Manual 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.

  • Page 7: Basi C Technical Data

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 8: Basic Technical Data

    Ltd. 1.1 Basic Technical data Wing Span....... 18 m....59.06 ft Wing area....11.8m ....127.01 ft 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..

  • Page 9: Water Ballast System

    Ltd. 1.2 Technical Description 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) 1.2.1 Fuselage The fuselage tapers behind the wing, the faired-in one piece canopy is hinged forward.

  • Page 10: Sailplane Systems

    Ltd. 1.3 Sailplane systems 1.3.1 Control systems in the fuselage Elevator, ailerons, and air brakes control systems in the fuselage FIG.1 Document No.: 304S/MM Date of Issue: 08/14...

  • Page 11: Control Systems In The Wing

    Ltd. 1.3.2 Control systems in the wing Ailerons and air brakes control systems in the wing FIG. 2 Document No.: 304S/MM Date of Issue: 08/14...

  • Page 12: Rudder Control System

    Ltd. 1.3.3 Rudder control system FIG. 3 Document No.: 304S/MM Date of Issue: 08/14...

  • Page 13: Main Landing Gear System

    Ltd. 1.3.4 Main landing gear system FIG. 4 Document No.: 304S/MM Date of Issue: 08/14...

  • Page 14: Control Surface Deflections And Dimensions

    Ltd. 1.3.5 Control surface deflections and dimensions FIG. 5 Document No.: 304S/MM Date of Issue: 08/14...

  • Page 15: Electric System

    Ltd. Table of control surfaces deflections and tolerances Control surface Deflection Tolerance 25° left ±2° Rudder 25° right ±2° 18° up ±2° Elevator 18° down ±2° 30° up ±2° Inner flaperon 20° down ±2° 30° up ±2° Middle flaperon 17° down ±2°...
  • Page 16 Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 17: Hangaring, Transport, Riggi Ng

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 18: Hangaring, Parking, And Ground Handling

    Ltd. 2.1.1 Hangaring, Parking, and Ground Handling The sailplane should only be stored or parked in well ventilated areas. Closed trailers should be equipped with sufficiently large ventilation. Always store with empty water tanks. Take note to store the sailplane without stresses. This is particularly important at higher temperatures.

  • Page 19: Rigging

    Ltd. 2.2 Rigging 1. Clean and grease pins and bearings. 2. In the cockpit, the flap lever is set at high speed, the brake lever in the medium position, and the water ballast lever set in the closed position. 3. First rig Port wing, temporarily lock with the main pin by engaging it only into the front spar fork bush.

  • Page 20: D E - Rigging

    Ltd. 2.3 De-rigging 1. Pull front tailplane connection pin out, with the help of the tool, and lift up tailplane. 2. Unlock and remove connecting pins of the wingextensions and apply the hand force to take the wingextension out of the wingtip . 3.

  • Page 21: Maintenance

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 22: Mandatory Maintenance

    Flugzeuggerätebau, München, are applicable for the installed releases (Sonderkupplung SH-72, Bugkupplung E-72, E-75, E-85,SH-72,Europa G 88, E-22 ). For the installed instruments, and other equipment, instructions of the corresponding manufacturers are applicable. Suppliers HPH Ltd. Čáslavská 126 P.O.Box.112 Kutná Hora CZ-284 01 CZECH REPUBLIC clamps, cables, main and tail wheel, gas struts R.

  • Page 23: Regular Maintenance

    Ltd. 3.2 Regular Maintenance Within the framework of the yearly inspection, the following maintenance should be carried out: The controls are accessible as follows: 1) Flaperon control system within the wing is accessible through pushrod openings in the root rib and through the flaperon drive opening when the ailerons drive caps are dismantled.
  • Page 24 Ltd. Landing Gear Clean brake drum, check brake linings and if necessary renew. Check and adjust bowden cable or brake lever, check side play of the wheel hub. In addition, observe the instructions of TOST. Ensure that the wheel axle and the two landing gear hinge-tubes are not bent, and that the fiberglass bearings on the wheel box are not damaged.

  • Page 25: Special Inspection Procedure

    Ltd. 3.3 Special Inspection Procedure 3.3.1 After hard landing and ground loops Workflow Donne by check landing gear bulkheads below forward shear carry through tube check landing gear mounting at forward main bulkhead check upper and lower part (trailing fork) of landing gear; check folding struts and dumper rings check fuselage to wing joint (shear pins, carry through tubes and their integration into the fuselage shell)

  • Page 26: Free Play In The Control Circuits

    Ltd. 3.4 Free Play in the Control Circuits With fixed controls, the following free play on the control surfaces must not be exceeded: Aileron 2.5 mm measured 102 mm behind control hinge line, Flaps 3 mm measured 122 mm behind control hinge line, measured 190mm above upper surface with full Airbrakes 2 mm...

  • Page 27: Free Play In Wing And Tail Plane Attachments

    Ltd. 3.5 Free Play in Wing and Tail plane Attachments Tangential play of ± 0,936 in (24 mm) at the wingtip is permissible. If this play is larger, washers of 0.00787 to 0.01181 in (0.2 to 0.3 mm) thickness should be packed under the wing attachment bolts until the main spar rigging pin is firm.

  • Page 28: Repairs

    Ltd. Scratches and small cracks in the surface can be repaired by the owner. Small repair kit with all necessary materials for minor repairs is available from the sailplane manufacturer. Read carefully the “Repairs“ on the following pages prior to any repair. Major repairs must only be carried out by the manufacturer.

  • Page 29: Removal And Re-Installation Of Releases

    Ltd. 3.9 Removal and Re-Installation of Releases To remove the C.G. release, the hinge and adjusting cable (Port side) of the backrest has to be removed. Then remove the seat tray and wheel-box cover. The release is now visible, and the bolted joint between release and the black link should be undone.

  • Page 30: Control Surface Moments

    Ltd. 3.10 Control Surface Moments After repairs or new paint work, the following control surface moments must not be exceeded: Weight / Moment Weight / Moment Without static balances With static balances Elevator m = 1,3 … 1.7 kg M = 2.29 ... 2.9 kgcm Siderudder m = 4.6 …...

  • Page 31: Placards And Markings In The Cockpit

    Ltd. 3.11 Placards and markings in the Cockpit See also the Sailplane Flight Manual - Section 2 and 7 Type: Glasflügel 304 S Serial No.: 003 - S Production year: 2007 Producer: Ltd. KUTNÁ HO R A CZECH R EPU BLIC EX PERIMENT A L CANOP Y JETT ISON CANOP Y LOCK...

  • Page 32: Cleaning And Care

    Ltd. 3.12 Cleaning and care Wash the surface only with clean water, sponge and chamois. Never use petrol, alcohol or thinners. Soap additives in water should not be used too often. Polish as often as you wish, but take care not to heat up the surface when using a polishing machine, as otherwise the surface quality will suffer.

  • Page 33: Lubrication Scheme

    Ltd. 3.13 Lubrication scheme Ball Bearings: The grooved ball races used are permanently grease packed and sealed; no further lubrication is required. The 14 C6 swiveling rose bearings in the push rods and the dural bell cranks are pre-greased and protected by felt seals, and these also are maintenance- free over a long period.

  • Page 34: Tightening Torque Moments Table

    Ltd. 3.14 Tightening Torque Moments Table maximum permissible torques for bolts 3.15 Safety Harness For the "Glasflügel 304 S" a 4-point safety harness is required. The following types are approved. LAP STRAPS • GADRINGER Bagu 5202 or latter approved versions Attachment points: On GRP loops through seat tray SHOULDER STRAPS...

  • Page 35: Pitot And Static Lines And Instrument Connections

    Ltd. 3.16 Pitot and Static Lines and Instrument Connections the G 304S is equipped with the following pressure ports as standard: • Pitot tube in the fuselage nose and on the top of the fin. Source of the pitot pressure can be selected by the pilot.

  • Page 36: List Of Instruments

    Ltd. 3.17 List of instruments 3.17.1 Airspeed Indicators Any approved aircraft airspeed indicator with an effective range of at least 30- 270 km/h (16 - 150 kts, 19 - 170 mph) can be used. The approved maximum instrument error is ±2.5% (±7.0 km*h, ±3.75kts, ±4.25mph). The airspeed indicator must be marked in compliance with the Sailplane Flight Manual, Section 2, Par.

  • Page 37: Comm

    Ltd. 3.17.6 COMM Any approved electric (12V powered) transceiver for use in aircraft can be used. Suitable transceivers : Dittel ATR 720, FSG 40 S, FSG 50 S, FSG 60 S, Becker AR 2008/25 , AR 3201, AR 4201, Microair Electronics Pty. Ltd. and their latter approved versions.

  • Page 38: Oxygen System

    Ltd. 3.18 Oxygen system In the center part of the fuselage a oxygen bottle (diameter 11,11 cm; length 32,38 cm) can optionally be fitted. The bottle can be opened and closed from pilot seat. 3.19 Service instructions Note: Some of the information for the maintenance of the 304S sailplane are provided in the Flight Manual on section 1.4, 1.5, 4.2, 4.3 and 7.

  • Page 39: Airworthi Ness Limitations

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 40: General

    4.4 Check out program If the inspection will not be carried out by the manufacturer , than the current Check out program should be required from the manufacturer : HPH Ltd. , Čáslavská 234 , Kutná Hora 284 01 , CZECH REPUBLIC .

  • Page 41: Inspection Results

    Ltd. 4.5 Inspection results The Inspection results should be written down in Check out program - each point of this program should be checked . If the inspection will not be carried out by the manufacturer , than the carbon copy of filled up program should be sent to the manufacturer for evaluation .

  • Page 42: Center Of Gravity

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 43: Center Of Gravity Position

    Ltd. 5.1 Center of Gravity position To establish the C.G., the sailplane is rigged with closed canopy. The tail wheel is placed on a scale in such a way that the rear fuselage cone is angled down towards the rear (wedge pattern 100:8.77 measured between the horizontal plane and fuselage rear upper surface).
  • Page 44 Ltd. The C.G. of the empty sailplane with normal loading between 154 and 275 Ibs, (70 - 125kg) should fall into the crosshatched area of a diagram in 5.2. Should the sailplane, in particular cases, be trimmed so that the C.G. falls above or below the crosshatched area, and the maximum loading is lower than 275 lbs, (125kg) or the minimum loading is higher than 154lbs.,(70kg) *), these loading should be placarded in the cockpit (e.g.

  • Page 45: Payload Range

    Ltd. 5.2 Payload Range T R IM PLA N G 304S 7 00 6 50 m in. 90 kg m in . 85 k g 6 00 m in. 8 0 kg m in. 75 kg 5 50 m in. 7 0 kg N O R M A L 5 00 m ax.

  • Page 46: Instructi Ons For Rep Airs

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...

  • Page 47: Checklist

    Ltd. 6.1 CHECKLIST 6.1.1 General • Check for proper positioning and fit of wing, HTU, and VTU • Check the angularity of all axis. • Wing frequency must be identical to the latest inspection report. • For annual inspections the datum points and other requirements are obtained from chapter 3 "Maintenance".

  • Page 48: Fuselage

    Ltd. 6.1.3 FUSELAGE Check for white or cracked areas, Fuselage/Wing-Connection : excessive play, loose bearings Check for white or cracked areas Horizontal Stabilizer-Connection : around fittings, excessive play Horizontal stabilizer Check for excessive play, white spots near hinges Elevator Torsion test: Hold fuselage near front Tailboom/Vertical-Stabilizer-Junction and push sidewise on fin.

  • Page 49: Structure Of Components

    Ltd. 6.2 Structure of Components Simplified Structure List The reinforcements of extremely loaded areas and force acting points are not listed hereinafter. The burning test is suitable to recognize the structure of the damaged part. The direction from external to internal layers is valid for the layers order. Let the repaired area to cure for at least 24 hours, and to temper within 50°- 55°C for at least 15 hours.

  • Page 50: Materials

    Ltd. 6.3 MATERIALS Material Manufacturer's Manufacturer Marking Epoxy resin 100 weight parts L-285 Scheuffler with hardener 38 weight parts H-287 (H-286) * Scheuffler Glass cloth 92 110 Interglas Finish I 550 or FK 144 92 125 Interglas 92 140 Interglas 92 145 Interglas 90 070...

  • Page 51: Type Of Waves

    Ltd. 6.4 Type of waves Unidirectional weave A special kind of plain weave. There are many fibbers in one direction, but only enough to hold things together in the other direction. Such cloth is used in the outer wing skin INTERGLAS 92 145, ECC Style 763 FIG.

  • Page 52: Basic Techniques And Tools

    Ltd. 6.5 Basic Techniques and Tools ATTENTION ! You should NOT make any repair yourself (for specification please see ch. 3.6) 1. If the wing main spar is damaged. 2. If main fittings in wings, fuselage or tailplane are torn out; or if around such fittings white overstressed areas are visible in the normally green fiberglass laminates.
  • Page 53 Ltd. A) It is of course easier to repair, so let's begin with it first: Grind off the afflicted area with 40 - 60 grit sandpaper, until the paint is removed from the outer skin and the structure of the glass cloth is visible about 6 mm (1/4 in.) around the rim of the hole.
  • Page 54 Ltd. Cut some glass cloth patches to cover the area - use the same kind and lay as original in that area (Exception: On wing skins, instead of 2 layers 92145, use 3 layers 92110. The 92145 weave can't be blended too well). Thoroughly wet the patches and the area with freshly mixed epoxy and lay them in place.
  • Page 55 Ltd. B) Now we consider case B), the awful hole through both the inner and outer skins. It will be necessary to rebuild the inner skin first. B1) Suppose that one can’t reach the area from behind, and that the hole through the inner skin is small.
  • Page 56 Ltd. B2) For larger damage: prepare as shown on Figure 47, but the weaving must cover the slanted surfaces and extend beyond those slanted surfaces. These "ears" lie on the spliced edge of the outer FRP layer. From there follow as shown on Figure 43 For holes big enough to admit a couple of fingers, or where the inner skin hangs down and flops around most disconcertedly, one must build a light platform under the inner skin to hold it in place while new fabric is glued to it.
  • Page 57 Ltd. The re-established inner layer is now sanded off and one can lay in a piece of foam and proceed as shown in picture B 2 - 4 and continued as on Figure 55. FIG. 55 This support platform remains forever inside and we must insure that it remains there in fact, and also does not interfere with any steering mechanism.

  • Page 58: Solid Fiberglass Skin Repair

    Ltd. 6.5.2 SOLID FIBERGLASS SKIN REPAIR In contrast to the wing a fuselage shell consists only of fiberglass. This design provides spring flexibility. In case of a smaller damage do nothing but splice around the area, approximately 1 - 1.5 inches (20 - 30 mm). Observe the kind and direction of the glass cloth and replace accordingly.

  • Page 59: Paint Job

    Ltd. Example 2: You make a mould on the outside. This is not too hard to make FIG. 58 First wax the opposite symmetrical side of the airplane perfectly (hoping this area was not damaged too!), lay on one layer of saturated glass cloth of 300 or 400 weight (12 oz./sq yd), let it harden and sand it as desired without removing from the plane's contour!

  • Page 60: Extra Equipment

    Ltd. 6.5.4 Extra Equipment Attachment Point Reinforcement If you have to attach something on t he shell, the same rules apply as in wood construction. The area must be strengthened before cutting ' any holes or inserting screws. To accomplish this, roughen the place and put some layers of glass onto the area, each larger than the proc eeding layer, and also changing the direction of the weave.

  • Page 61: Tools

    Ltd. 6.5.5 Tools In addition to the usual tools of an aircraft shop, especially recommended for fiberglass work: • Clean vessels for resin, hardener, and mixing • Brushes with small bristles; and one big brush • Sharp scissors • Sandpaper of various grits •...

  • Page 62: Inserted S Upplements

    Ltd. Document No.: 304S/MM Date of Issue: 08/14...
  • Page 63 Ltd. INTENTIONALY LEFT BLANK Document No.: 304S/MM Date of Issue: 08/14...

Table of Contents