5£55722. 5£alvsbyflygklubb.se/instruk/dg500manualeng.pdf480(7.28 mmup in.)(18.9in.to ) behind...

1

Glaser-DlrksFlugzeugbau GmbHIm Sohollenga~ten 19-207520 Bruohsal 4, W.-Germany.Tel.: 07257/89-0 or $910Telex.: 7822410 gldg dTele~ax:07257/8922

r l. I G H T M..1 If D A L

f'or the

SAILPLAI'E

• Mikael Larsson~ Besiklningsing..Segelflygmaterlel

FOr WFTFARTSVERKET

If

ELAN Trainer

Model: DG-500 ELAN TRAINERGerman Data Sheet No.: 348

Factory.Serial No.:

Registration No.:

Date o~ Issue:

5£55722.5£ -uo};<

Deoember 1990

Pages as indicated by "App. ,.are approved by:

(Signature)

(Authority)

(Stamp)

(Original date o~ approval) O_7._D_ez_,_'9_9_0 _

This sailplane Is to be operated in compliance with information and limitations contained herein.The original German Language edition of this manual hasbeen approved as operating instruction aooording to"Paragraph 12{ 1) 2. of. Luft-Ger Po".

Approval of translation has been done by best knowledgeand judgement. In any case the original text in Germanlanguage is authoritative.

0.0

Flight Manual DG-SOOELAN TRAINER

0.1 Record of revisions

Any revision of the present manual, except actual weighing data, must berecorded in the following table and in case of approved sections endorsed by theresponsible airworthiness authority.

The new or amended text in the revised page will be indicated by a blackvertical line in the right hand margin, and the Revision No. and the date will beshown on the bottom left hand of the page.

Rev. AffectedDescriptionIssueLBAInsertedNo.

pages/ DateApprovalDatesection

DateSignature1

0.3,2.8, IN 348/1TMar. 9231.03.92

2.9,4.8 20.4,7.2 IN 348/3TOct. 9208.12.92

3

0.3,1.2, TN 348/4TOct. 9426.10.944.14 4

0.3,0.4,IN 348/9Oct. 9726.11.97

1.3,4.1 , 4.2,4.3,5.2,5.5,5.6,6.2,6.4,6.7,7.1,7.9,7.105

0.3,0.4,IN 348/15Jan. 0107.02.01

4.5,7.7, 8.20

,., c.N 348/16February25.£)') AA, . ,Parki

iggott-hook

Issued: February 2004 TN 348/16 0.1

0.1

Flight manual DO-500 ELAN TRAINER

lRev. Aff.ated Descriptionllo. Pagesl

section

Issued: see last item

Issue LBADate Approval

Date

InsertedDateS1gnature

0.2

Flight Manual DG-500 ELAN TRAINER

0.2 List of effective pages (cont.)Section

pageissued replacedreplaced

4

App.4.16May 905

5.1"

5.2Oct. 97l 5.3

App. 5.4 5.5Oct. 97

5.6Oct. 97

6

6.16.2

. Oct. 976.3 6.4

Oct. 976.5 6.66.7

Oct. 97

7

7.1 Oct. 977.2

Oct. 927.3 7.47.5

Febr.047.5a

Febr.047.6 7.7

Jan. 017.8 7.9

Oct. 977.10

Oct. 97

8

8.1May 908.2

Jan. 018.3 8.48.5

9

9.1May 90


Flight manual

0.3, Table of oontents

DG-50C ELAN TRAINER

Section

General (a non-approved section)

Limitations (an approved section)

Emergency procedures (an approved section)

Normal procedures (an approved section)

Performance (a partly approved section)

Mass (weight) and ba~ance(a non-approved section)

Sailplane and systems description(a non-approved section)

Sailplane handling, care and maintenance(a non-approved section)

Supplements

Issued: May 1990

2

3

4

5

6

7

8

9

0.5

Flight manual DG-500 ELAN TRAINER

Section

1.. General

1.1

Introduction

1.2

Certificationbasis

1.3

Warnings,cautionsandnotes

1.4

Descriptive data

, .5

Three view drawing

Issued: May 1990 1.1

Flight manual

1.1 Introdu~tion

DG-500 ELAN TRAINER

The sailplane flight manual has been prepared toprovide pilots and instructors with information forthe safe and efficient operation of the 00-500 ELANTRAINER sailplane.

This manual inoludes the material required to befurnished to the pilot by JAR Part 22. It also contains supplemental data supplied by the sailplanemanufacturer.

1.2 Certification basis

This type of glider has been approved by theLuftfahrt-Bundesamt (LBA) in accordance with:

JAR Part 22 sailplanes and powered sailplanesChange 4, issued 7th May, 1987.

The Type Certificate No. 348 has been issued onDecember 7th 1990.

Category of Airworthiness: "Utility" or "Aerobatic"if equipped properly.

Issued: Oct. 1994 1.2

Flight manual DG-500 ELAN TRAIW....R

1.3 warnings, cautions and notesi

The following definitions apply to warnings, cautions and notes used in the flight manual.l Warning:

Caution:

Note:

means that the non observation of the

corresponding procedure leads to animmediate or important degradation ofthe flight safety.

means that the non observation of the

corresponding procedure leads to aminor or to a more or less long term

degradation of the fli~ht safety.

draws the attention on any special itemnot directly related to safety but

which is important or unusual.

!I

Issued: October 1997 TN 348/9T 1.3


1.4 Descriptive dataThe DG-500 ELAN TRAINER is a twoplace high performance sailplane.

- automatic hook ups for all controls

- comfortable seating and modern oockpit designsimilar to the DG-single seaters - safety cockpit

- large 2 piece canopy for very good inflight visibility

- draught free canopy demist and 1 adjustable swivelair vent for.each pilot

- sealed airbrake- and landing gear box

- complete set of controls 1n each cgckpit

- a choise of retractable or fixed main wheel, bothspring mounted

- nose wheel and tail wheel

- ~arbonfibre wings

TECHNICAL DATA

wing span 18m 59ftwing surface

16.6m2 179ftZ

aspect ratio19.5

length8.66m 28.4ft

fuselage width0.73m 2.4ft

fuselage height1.00m 3.3ft

horizontaltailplanespan3·11m 10.4ft

empty weightca.390~kg 860Ibs

max.TOW 615kg 1356Iba

wing loadlng(payload 80 kg,116 Ibs) ca.28.3kg/m25.8Ibs/ftl!

wing loading max.31kg/m27.58Ibs/ft2


1.5


3 view drawing


Flight manual DG-500T ELAN TRAINER. !i

j

Section 2

2. Limitations

2.1 Introduction

2.2 Airspeed.

2.3 Airspeed Indicator Markings

2.4 Section not effective



2.7 Weight

.2.8 Center of Gravity

2.9 Approved manoeuvres

2.10 Manoeuvring load factors

2.11 ~light crew

'2.12. Kinds of operation

2.13 Minimum equipment

2.14 Aerotow and Winch- and Autotow - launching

2.14 .1 Weak links

2.14.2 Towing cable

2.14.3 Max. towing speeds

2.14.4 Tow Release

2.15 Cross wind

2.16 Tyre pressure

2.17 sectiOn not effective


2.19 Limitations Placards


Flight manual

2.1 IntroductioD

DG-500T ELAN TRAINER

,.---..

,--,

Section 2 includes operating limitations, instrumentmarkings and basic placards necessary for safeoperation of the sailplane, its standard systems andstandard eqUipment.

The limitations included in this section have beenapproved by the LBA~

Issued: May 1990 App. 2.2

Flight manual

2.2 Airspeed

DG-500 ELAN TRAINER

Airspeed limitations and their operational significance are shown below:

Speed (IAS) Remarkskm/h(kts)

VNE Never exceedspeedflaps 00 up to_lOo

270( 146)

Do not exceed this speedin any operation and donot use more than 1/3 ofcontrol deflection.

VT ·Maximum aerotowing speed

Maximum winch- 140

launching speed ( 76)

VRA

VA

vw

VLO

Rough air speed

Manoeuvringspeed

Maximum landinggear- operating.speed

205(111)"

205( 111)

205(111)

205(111)

Do not exceed this speedexcept in smooth air andthen only with cautionRough air is in lee-waverotor, thurlderclouds etc.

Do not make full or abruptcontrol movement abovethis speed, because undercertain condition thesailplane may be overstressed by full controlmovement.

Do not exceed this speedduring winch- orauto-tow-launching

Do not exceed this speedduring aerotowing

Do not extend or retractthe landing gear abovethis speed

Warning: At higher altitudes the true airspeed ishigher than the indicated airspeed, so VNE is"reduced with altitude see sect. 4.5.9.



2.3 Airspeed Indicator Markings

Airspeed indicator markings and their calor codesignificance are shown below:

Marking

Green Arc

(rAS) value orrangekm/h (kts)

80 205

(113 "1)

Significance

Normal Operating Range(Lower limit is maximumweight 1.1 VS, at mostforward C.g. with flapsneutral. Upper limit is.rough air speed.)

Yellow Arc

Red L1ne

YellowTriangle

205

( 111

270(1116)

100( 54)

270 Manoeuvres must be conducted with caution and

146) only in smooth air.

Maximum speed for alloperation5.

Approach speed at maximumweight


Flight manual

2.7 Mass (weight)

DG-500 ELAN TRAINER

Maximum Take-Off mass:

Maximum landing mass:

615 kg, 1356 lba

615 kg, 1356 Ibs

-~ Maximum mass of all

non lifting parts = 435 kg (959 lba)Maximum mass in baggagecompartment = 15 kg( 33 lbs)

Caution: Heavy pieces of baggage must be securedto the baggage compartment rloor (screwingto the floor or with belts). The max. masssecured on one half of the floor (left andright of fuselage centre line) should. notexceed 7,5 kg· (16.5 lbs).

Warning: Follow the loading proceduressee sect. 6.

2.8 Centerorgravity

Center

ofgravityrangeinflight is

185 mm

(7.28 in.)up to480 mm (18.9in. )behind

datum.

datum

= wing leading edge at therCiotrib

reference line = aft fuselage centre line horizontalC.G. diagrams and loading ohart see sect.5.

Warning: Flying is only allowed with the batteryZ 07 installed in the fin as otherwise the forwardC.G. limit may be exceeded.

2.9 Approved manoeuvres IAirworthiness category IIUt111ty":This sailplane is certified for normal gliding andsimple aerobatics.The following aerobatic manoeuvres are approvedsee sect. 4.5.12:

Manoeuvr~recommendedentry speedrASkm/h

ktsSpins

IIInside Loop

20010BStall Turn

200108Lazy Eight

200lOBChandelle

200108

Issued:

May 1990 App.2.5

. .

. 'Fligbtliiilnlla:l, . 'DG-~OO .. '. ELl\N .'1'RAIN~R ,

. "

··:~rr~;ri:e.::~~:~:~:';o!~:~~~~r:~~:'~~~~;MHht~',:.an4: .. '~ .. " .. ',' ' ,...... '.'Inverte d nigtit,;~co!DD.ieMt!,d. sp e~d ,.

.'~' '.". ~.--'" 130~200 ...kinlh J7tt"-,10"S .~~~)sio~ toll • 'entr:yspe~ds' .. ,. '. ,

.' " ." ,'_ '>f$0;';200kmjh(97':':fOB ,kts)HElif,I"i'11 and. h~l:r,lQ~p 150-110 kiillh (8~h92kt'$r,fIa.lf lo.op~.odtial:t i'~ll •..220'k:iii/li (119litsf .. . . .' . . .. . . '. ~..'. '.. '. '. - .. . - - .

2. 10 ~_.~beiJyeriJ1.~ib~4:'ta~~o~~' .•.. .The: fQJ,.i~tl:i"ng. itiad f~q:i~rs' ~iind~' t~·be,. ~;cqe~ded,:,' .....

.•..~~gf~:~;~~n:';;f;~"~!,~l~!~a=j:t~··tft~~r·.2.,11:Fi!gh~ ..,ct'e1t,".: ....,.':.. .

:~x~~ii~';~iri~~~t'~ron~,seat .. · 110 kg :2421bs .. mir!~ 1,q,aCl.in , t.~efl'otit~e~t' see placard 'incdck-, .

. . pit ,'and' iI~:t.ghi,pg rEl~. ,port page':6.5

.... ,'.

b) two.se~ted .. ',. .... .'... "m'ax,CiOO1<pit 108,d.",is .210' kg'T463'il?~)witl1 Ei,' !pax.of' 105 kg (2311"5)41 'the f'root s~4t;'or-1tO' Iq;!;

. (24? 1bll) in tij,e frQr-tseat antl90kg (198 Ib!;l) .inthe rear seat. .' .' . , ..... ' '.. ' ',. , . "

. 'mln~ c6:ckpit load' in the .frortt '$~at is the .min. 'oockpit load see' a} minus 40% of' the ioad in the 'rear . sea t; this" m-e~tls th~j;."O',kg' '(221 be) 'in.~he ' ..r~arseat replac~~ 4,kg(8.S IiJs) m.1.!!sing.cockpitload in the t'ron.t;sea t. ..' ....Wit~ thes~' lOl;lds, j;h~' i::~G.'r~p.$eglveb und.~r i.awill b~kept in the limits if the ei!l,pty wej.ght·C~G. is,lnitSlimhs..' . ,'. .

, see~ loadj,ng' chart in sect. 6. ~

C~uuori:,With lO~~~ pilot 'Weights the ne~es~arylea" bailal!itmust b,~ added" too tne seat.Balla.'st: put' 90'thesea:t (lead ballastCUshion) must be .fasj;;e,·neC!at the safety'belt anbh,!rat,e p'oint./J. . . ",llistallatfon~o,r ,iemOVi'lble trim balla!3t

. see sebt. 7.16;1~

Note:, For Australia theIil1I).10a,d, in the cO'cIq,l t.' should not exce~d' 66 kg (146 .Ibs). A provision· .

for removable baiiast $ee sec t. 7. 16.1 is man,datory ~.

Issued: May 1990 App.2.6.1

Flight manua.l DG-500 ELAN TRAINER

2.12 Kinds or operation- Flights according to VFR (daylight)- Aerotow- Winch- and auto-launching- Cloud flying (daylight); permitted when properly

inatrumented (aee. below).

- Simple aerobatics See sect. 4.5.12 (CategoryUtility)

- Aerobatics see aect. 4.5.12 (Category Aerobatic)if properly instrumented (see below)Note: Cloud flying is not permitted in the USA,Canada and Au~tralia.

--. 2 •13 Minimum equipmentAs minimum equipment only the instruments andequipment specified in the equipment list (seemaintenance manual) are admissible.Note: The actual equipment list is filed in the

enclosures of the maintenance ~anual.a} Normal operation

Airspeed indicatorRange: 0-300 km/h (0-165 kts)Speed range markings see sect. 2.3AltimeterAltimeter with fine range pointer,1 turn max. 1000 m (3000 ft.)Magnetic compass (compensated in the aircraft,only required in Canada)Four p~eoe symmetrical. sarety harnessVHF - transceiver (ready for operation) withnoise absorbing earphonesBattery Z 01 installed in the finParachute automatic or manual type or a backcushion approximately B cm ( 3 in.) thick.Required plaoards, check 1.1sts. and th18fl~ghtmanual

b} In addition tor cloud r11~ (Not permitted inthe USA, Canada and Australia)Magnetio Compass (compensated in the aircraft)VariometerTurn and ba~k indicatorRemark: Experience has shown that the installedairspeed indicator system may be used for cloudflying. .

c) In addition 'for aerobaticsAirworthiness category "Aerobatic";Accelerometer capable of retaining max. andmin. g-values with markings red radial lines at+7 g and -5 g.Sarety bows at the rudder pedals (standardequipment)



2.14 Aerotow. winch and autotov launahing

2.14.1 Weak links10 000 N2 200 lbs

+ 10')1,

+ lQ1.

2.14.2 Length ot the towing cablefor aerotow 30-70 m (96 - 225 ft)Material: hemp- or plastic fibres

2.14.3 Max. towing speedsAerotowWinch- and auto tow

.•.

VT = 205 km/h.VW = 140 km/ b.

111 kts76 kts

2.14.4 Tow Release

The C.G. tow release (installed in front of the

main wheel) ls suitable only for ¥inch- and autolaunching.

The nose hook 1s to be used only for aerotow.

2.15 CrosswindsThe maximum crosswind component aocording to theairworthiness requirements for take-off and landing is 15 km/h (8 kts).

2.16 Tyre PressureMain wheelNose wheelTail wheel

2.5 bar2.5 bar4 bar

363658

psipsipsi

Issued: Maroh 1992 TN 348/1 T App. 2-.8

Flight manual

2.19 Limitations placards

DG-500 ELAN TRAINER

TJPI: DCJ.IODIELAN Trainer V•• otCDMIrVlltIDflI

_-lIE T I I I••••• mum •• ,.,.. IDftIIl 1ltI.

=-...... ~~: 1~:I18nM1M1ngV.. .01 HDRoug"air 101 11D•••••••••• .,..... IDI 1tDII1uIl'lMllapelldV. 170 ,.Ajlprond MnIIlIllIc __ f.ldIIgory utility Uh••••• 1JIDp. IllIn Tum, CIWIdIIIa, IplnIn IlIdRlcn IIIltIltIIY A:1UI111llJlPanCll'lan roll, IIall roll andlUlll iDop, ,IOW I'DD.IIWIlNCI night

IIIultIun mIIUI f1,kg (1311IbI.)Lt ••••••••••••

.•.•..---r·•••f ••• "'r ••••

..-- no101

I HI'"I 11:11111I.

I ••••0 I 1'11b.

101 to I la1""- -1- Gepick mu. 15kgBaggage max.33/bs.

Relfendruct 2.5 bar~ pressure 3S psi

nose wheel

Relfendruck 2.5 bar1Jre pressure 36 psi

AJI. m . Q.2OllOVHE KIIlIh 270

All. ft D-66OlIVNE KII 146

3DDD2S8

,??OO138

4Dl1O 5000 &aDlI243 230 218

13DlJO 180llD 2ODDO131 124 117

main wheel

SolJbruchstelIB 10000 NRated lORd 22DO1bI.

Other cockpit. placards see sect. 7.

Relfendruck 4barTYre pressure 58 psi

tail wheel

Issued: March 1992 TN348/1 T App. 2.9


Section 3

.-----

3.Emer-gency procedures'

3·1

Intr-oduction

3.2

Canopy jettison

3·3.

Bailing out

3.4

Stallrecovery

3.5

Spin recovery

3.6

Spiraldive recovery

-

3.7 Recovery from unintentionalcloudflying


.....

' .....

. ' ....~ '

...' . :'.'

":.3·~.Sp1r.il;L 'd~v.,-*ec9~e&:'. : '.

,'Apply ,r1i'ti~er.a.n~'';iiler9P J,n opposite: ttireoHon .1:14'" , carefully' punou~,pr:~he'dive~

, Splral di~~':OC.~~~$:.d~iilih,en;'~Pi'nzii~gtn&ri 'than,2,turri~'li:f~h. itje~huliI,-:c"(r.·posl~Uon~I a~e .s~o1;:"4.5 .12~

. . . "; ...- -' . ~. . - -.... .' . . - -',.. . '. '.' ""'. _.:.'.: . . -". -. .

, To: pp~:v~r-t'.spfr:~i'~:ik~t:in~~ntio.n.*i'sPinn,i:p~ ,~P_ouid ,,'only'b:t!~J\:~i;iuteaattn~ C.•O.po.s~tlQn's $p~e!.fiea. lri ',>.. s.ei.1t; 1J~5.i2 ~itholit'waterbal1,fst~ ,,:,' " .',

.' ' .. '! ..:: •..• '.' ' .. _.•. :.... .'- ....• ' . ")!.: ..•.. ! ..••• c·.. .'

Re~o'V~·ry from 'u~itl.telltlq~aJ: spfnning Sh~U.l_d be' {lone .'immediately.". ,". ,.."

•.• ·.···.3.1 .;;r;;:;~1~i~~;i:'gt~~'~;~~~;'b;~~•.•.;.. , .' eXQe'~(jini"'a' epee" ·o.~ .'20.0: kiD/h'. ~tla,' "fly Hltli·~lfiax._ ->

, 20P ~m/~.( 1i:l:at<t~ )un):.if,l;aving' ,t~(;l'olol1d~ ".' ,At ,higher_~pe~ds ijpto':~NEJ pullCititt.h,~ '~1ve'\)iakesver'yC:a,r~ I'ul),ffie Ctl~~??t,higb :a~r'odYiJa.Qii~a:09''g-loads. "

~.

.' .. '

Issued: M"y'1990 App. 3.3

Flight manual DG-SOO ELPL~ TRAINER

4. ifSet the stabilizer on, so that the roller at

the fuselage side push rod is inserted into thefunnel at the elevator.

Watch carefully the procedure.

When the stabilizer is set down

and laying on the fin, push itaft. The roller will slide for

ward in the funnel if you holdthe elevator in the pertinentposition.

4.2.4

Release the securing device by pulling out withthe tool and engage the securing device bylifting the tool. The securing plate must beflush with the surface of the fin. Screw outthe tool.

Check for correct elevator connection by

looking from the rear into the gap at the righthand side of the rudder.

5. Tape the qap$ of the wing-fuselage junction.

6. Positive control check.

Derigging

Derigging follows the reverse of rigginq.Lock the airbrakes.

For disassembling the securing pins of the wingsthe tool W 38/2 must be screwed into the bolt

completely.

The brass part of the tool will then disengagethe securing of this bolt.

It is recommended to leave the securing bolt inthe right.wing as long as you derig the leftwing.

Issued: October 1997 TN 348/9T App. 4.3


4.4 Pre~ligbt inspection

1· Lead ballast (for under weight pilot)?

2. Parachute worn properly?

3. Safety harness buckled?

-4. Front seat: pedals adjusted?Hear seat: seating height adjusted?

5. All oontrols and knobs in reach?

6. Altimeter?

1. Dive brakes cycled and locked,

8. Positive control check? (One persOn at thecontrol surfaces).

9. Trim?

10. Both canopies locked?


Flight manual DO-SOD ELAN TRAINER

4.5 Normal procedures and and reco.mended speeds

4.5.3 LauncbDue to the towhook position being in the middleof the fuselage and the excellent e~fectiveneseof the ailerons and rudder, the pOBsibility o~wing dropping or ground loops, even on a slowstarting aerotow is reduced. Take-off with strongcrosswind is possible .

.lerotov

a) Aerotow is permitted only using the nose towrelease. Set trim to neutral for aerotow.

b) Pull the stick until the nose wheel li~ts offfrom the ground. Then control the airplane so,that nose wheel and tail wheel don't touch theground. Don't try to lift off b~fore you reachan airspeed of 80 km/h (4'3 kts) (withoutballast) .On a rough airfield hold the control sticktight. The undercarriage can be retracted atsafety height during the tow.

Normal towing speed is 120-130 km/h(65 - 70 kts).

For a cross oountry tow up to 205 km/h (110 kts).

Wincb launch (only allowed at the C.G. release)Set the trim fully nose down for winch launch.To accomplish this, ope~ate trimmer lever on thecontrol column and push the control knob on thele~t cockpit wall to its forwardmost position.

Caution: During ground roll and initial take-off.(especially when flying solo) push the cont~olstick to its forwardmost position or fully nosedown to prevent excessive nose up pitching rotation during initial take-off.

After ~eaching safety altitude gradually pull backsome on the stick, so that the g~ider will notpick up excessive speed. Don't pull too bard.

After reaching release altitude pull the tow release knob.

Recommended winch launch airspeed 100-120 km/h(54-65 kts).Caution: Do not fly at less than 90 km/h (49kts)or not more than 140 km/h (76 kts).

Issued: March 1992 IN 348/1 T App. 4.8

Flight manual

4.5.4 Free rl~gh~

DG-SOC ELAN TRAINER

StalliDg aharacte~istics (level and turning!light)When stalled the DO-SOC ELAN TRAINER will continueto fly level with high sink rate and buffeting.If the stick is pulled further the DG-500 ELANTRAINER will drop the nose or drop one wing.During the stall a l~rge angle of attaok will bereached. .

At forward C.G. positions the DG-500 ELAN TRAINERcan be flown in stall without wing or nose ~ropping.When reaohing the minimum speed, the angle ofattaok has to be increased signifioantly; beforethe DG-50C ELAN TRAINER stalls, so that thestalled flight is easy to recognize.With stiok forward and opposite ru4der if requiredthe DG-500 ELAN TRAINER can .be recovered withoutmuch lOBS of height. Rain does not influence thisbehaviour noticeably. The loss of height is oa.30 M. Stall airspeeqs see sect. 5.2.2.



4.5.7 Approacb and laudingAbeam the landing point extend the landing gear(Option) .In calm weather approach with approx.100 km/h(54 kts). With strong wind fly fasterl

The very effective Schempp-Hirth dive brakesmake a short landing possible. So a slip is notnecessary as ~ landing technique.

Caution: While slipping, the rudder isBucked in its displaced position.-So it is reoommended to practice slipping at a higheraltitude. -

Strong crosswind offers no problem.Do not approach too Slowly with fully extendedalrbrakes otherwise the aircrart\may dropduring flare out.When flaring out keep the airbrake setting youwere using, opening them further may drop thesailplane.Clean the landing gear and tow release afterlanding in an muddy field. Dirt in the frontstrut (Option retractable landing gear) can keepthe landing gear from locking over center nexttime. Simply hosing with water is the bestcleaning method.

Landing with the land1ng gear retracted-(Option retractable landing gear)It is reoommended to use this technique only onvery short fields or if there are furrows in a

cross direction in the field. After wh~el uplanding check the fuselage belly, the C.G. towhook and the tow hook bulkheads for damage.

Issued:" May 1990 App.4.10


4.5.9 Flight at high altitude and at low temperaturesWith temperatures below aoe (32°Y) for instancewhen wave flying or flying in winter, it ispossible that the control circiuts could becomestiffer. Special care should be taken to ensurethat there is no moisture on any section of thecontrol circuits to minimize the possibility offreeze up.

It could be advantageous to apply vaseline alongall the edges of the airbrake cover plates tominimize the possibility of freezing closed.

Apply the contrOlS in short periods.It is not allowed to carry waterballast.

eau'tien:1. At temperatures below -20oe (_4°F) there is

the risk of cracking the gelcoat.2. Attention must be paid to the fact that at

higher altitudes the true airspeed is graterthan the indicated airspeed.The max. speed VNE is reduced. See thefollowing table:

Altitude inmetres

0-20003000400050006000VNE IAS km/h

270256243230218

Altitude inft.

0-660010000130001600020000VNE IAS kts.

146138131124117

3. Do not fly below Doe (32°F) when your glideris wet (e.g. after rain).

4.5.10 Fligbt in rainWith light rain the stall speed and the sinkrate increases slightly and the approach speedhas to be increased.

4.5.11 Cloud flyingTake care to fly smoothly and coordinated. Itis prohibited to use a spin as a method forloosing altitude in the clouds. In case ofemergency, pull out the dive brakes fully before exceeding a speed of 200 km/h and divewith max. 200 km/h (108 kts) to leave the cloud.


Flight llIanual DG-500ELAN TRAINER

4.5.12 Aerobatics ("Utility" Category)

Execute only the approved manoeuvres.

(108 kts)(108. kts)(108 kts)

(108 kts)

200 km/h200 km/h200 km/h200 km/h

Entry SpeedEntry SpeedEntry SpeedEntry Speed

Approved manoeuvres<Utility Airworthiness category)1. Spins2 .·Inside Loop3. Stall turn4. Chandelle

5. Lazy Eight

Spins:

Caution: Prolonged spinning is only possibleat art C.G. positions, this means single seated.It is not necessary to extend the dive brakes .during spin recovery. The DO-50D ELAN TRAINERshows a very large nose down pitch after leavingthe spin. So you have to flare out oorrespondingly.With fo~vard C.G. pos~tlons prolonged spinningis not possible. The DG-SOO ELAN' TRAINER willterminate the spin by itself arter a certain number or turns dependent on the C.G. position. Thenose down pitch and speed will be high so withthese C.G. positions not more than 1 turn spinsshould be executed, to avoid high g-loads.

With medium C.G. positions there is.a tendencythat the spin will turn into a spiral dive after1 or 2 turns. Reaching' this state you have to recover immediately.Recover always with the ailerons neutral.

Induoing tbe spin: (Normal procedure)Gradually bring the sailplane into a stall.When 1tstarts to burbIe, pull the stick backcompletely and kick in full rudder in the spindirection.

Recovering fro. the spin:Apply full opposite rudder against directionof the spin, pause, then ease the stick forwarduntil the rotation ceases, centralize the oontrolsand carefully pull out of the dive. The aileronsshould be kept neutral during recovery.Height loss during recovery is approx. 50-80 m(160-260 ft), the max. speed is max. 200 km/h(108 kts). .



11.5.12 rrStall turn:

After reaching the entry speed of 200 km/h(10H kts) pull back the stick quickly but notabruptly. After reaching a vertioal flight pathreturn the stick to neutral.When a speed of 130-140 km/h (70-75 kts) isattained, push the rudder quickly, but not abruptly, fully into. the desired direotion.

After the rotation starts slightly oppositeaileron and stick forward gives best result.

When reaching the vertical dive you should flareout immediately to minimize speed increase andg-load.

Warning:If the rudder is pushed too late and the rotationis insufficient, it oould be that the glidertailslides (falls tailwards).If this happens, it is important to hold all controlls strongly, preferable at one of the stopsuntil the nose swings dowo and then flare outimmediately.



recommended speed130-200 km/h (70-108 kts)entry speeds180-200 km/h (97-108 kts)

Slow roll

Aerobatics (Aerobatic Category)Execute only the approved manoeuvres.Don't execute aerobatics below the safetyaltitude required by national law.Approved manoeuvres (Aerobatic Category):All manoeuvres approved for Utility categoryand:Inverted flight

,"~

Half roll and half loop 150-170 km/h (80-92 kts)Half loop and half roll 220 km/h (119 kts)

Caution: The DG-500 ELAN TRAINER is a high performance sailplane. Therefore the speed increasein the dive, especially in inverted flight is high.Therefore training aerobatics should only be executed after a rating with an experienced pilot orif you can master the manoeUvres on other sail-plane types. .In any case don't try to execute the manoeuvreswith entry speeds other than those listed above.

Inverted rligbt:the speed in inverted flight should preferably bechoosen between 130-200 km/h (70-108 kts). Atspeeds greater than 205 km/h (111 kts) no fullcontrol deflections are allowed.

Warning: When the speed is reduced below theminimum speed (depending on weight and e.g. position 105 - 125 km/h, 57-67 kts) the DG-500 ELANTRAINER enters an inverted stationary stall withhigh sink-rate. This will be indicated by buffeting of the tailplane.The aircraft nose may point far below the horizonand the airspeed may show 130 - 150 km /h (70 - 81kts). The efficiency of the ailerons and rudderwill be reduced considerably.

Note:The inverted stalled flight must be recovered byneutralizing the stick until the buffeting of thetailplane stops. The airspeed will increasevery quickly. As soon as this condition isreached, raise the glider nose above the horizonby gradually pushing the stick forward.Regain normal flight by a half roll.

Issued: Oct. 1994 IN 348/llT App. 4.14

Flight manual DG-50a ELAN TRAINER

4.5.12 rrHalt loop and haIr roll:After reaching the entry speed of 220 km/h (119kts) pull the stick quickly, but not abruptlyuntil· reaching the inverted position, where thespeed should still be 130 to 140 km/h (70-75 kts).Then return the stick to neutral and keep the noseslightlYcabove the horizon. Then apply fullaileron in the desired direction. After the

wing passes the vertical position apply upperrudder to keep the nose above the horizon untilnormal flying position is reached.

Note:If the nose is raised too mUch above the horizon

or the inverted speed is too slow, a stall canoccur when the wing reaches the vertical positionand the glider finishes the rolling motion as a"flicked" roll into normal flying position.

Half roll and half loop:After reaching the entry speed of 150-170 km/h(80-92 kts) the nose must be raised to 10 - 20°above the horizon. After returning the stick toneutral apply full aileron into the desireddirection to start the half roll. After the wingpasses vertical position the stick has to bepushed slightly (never abruptly) forward to keepthe nose above the horizon. When reaching inverted flight the ailerons must be neutralized andthe speed must be reduced to 120-130 km/h (65-70kts) by pushing the stick forward before startingthe half loop to level out.

·Note:If during the entry the nose is raised too highor the entry speed is too low, it could be thatit is impossible to stop the rotation in the inverted position and the glider continues the··-..·roll into normal position. .


·Flight manual DG-500 ELAN TRAINER

..~

1J.5.12 ffSlow roll:

After reaching the entry speed of 180 - 200 km/h(97-10B kts) the nose must be raised slightlyabove the horizon. After returning the stick toneutral, full aileron haS to be applied in thedesired direction. After the wing has passed thefirst vertical position the stick is to bepushed slightly (never abruptly) forward to keepthe nose above the horizon. When the wing passesthe second vertical position the rudder must beapplied upwards to keep the nose above the horizon until normal flying position is reached.

Note:

If during the inverted flight, the nose is raisedtoo high above the horizon and the speed is reduced too much a stall could occur when the wingreaches the second vertical positon and the rollis finished as a "flicked"

The stall is indicated by buffetting of the tailplane.



Section 5

5. .Performance

5.1 Introduction

5.2 Approved Data

5.2.1 Airspeed indicator system calibration

5.2.2 Stall speeds

5.3. Add~tional Inrormat~oD

5.3.1 Demonstrated crosswind performance

5.3.2 Gliding performance

5·3.3 Flight Polar



5.2 Approved data

5.2.1 Airspeed indicator system calibration

AS

o

s

o

o

o

o

40SO6070ao901001101201301~Okti ;I .I, . ,I

L-_ ..~

I

. . i : ~jL>-: .

__ .1.! i : : :·-14L

...•_..-.·_·_··...1i-_·t· -"'-i'" -· ..-t·..· ,......i7;:......

•. : ' : ., ! . ,i_.-.1--W._.

~_..._.-'1-...·_·----._-_.!.._-+._-;..-"'i- _.~.......-13· · i i!,VC/I i, i-..·..· !!--1-*~_ ..-:-.--•...j....-..._--' -- --.-- ..-_,_.on ••_ ..•.":'.-~~'"i" ---12,

Li.1. !. j//'i •

l,, !-_.._...!_._- ..~-ifI

._.!--.-..- .:--•.•....••••"'!""~_••_ ...__ ...--"-": ...._.~---..r- ..--110

~; iI:!~

j

l. i:jIi---I

11...-+-··u_.;......._.. r"'--"'-~_··t""-'-r .__ ...;... •..-_ ...--

-'-r-~-"-'10I.

~II : i ~!j ,

I- .;...._ ...~...... "..: ;

71'_..___.1. --..~.--,-9

..-•....... .--...•-.--'-i--'IIi!!

,

! !! i. 1 I•

,!

... ~...n·.. ·I_....

71-~i

...__ I--- _ ....•.. _--8i

I,li •Ij•i

jI1i•!

~. ! k.~~.

i- - -..,

-- ...-~

_.ur' ....0

··70

i!~

i1AS•••CAS-;i•~

.:...._.. =_ •..•u ••

!,:!-- _..-..._--.--'" .............'-60

J...._Jy~~• .i j,i.,i.. ;

I-;. I

..._.

1-._ ••.••.._ ... _.!._........i........•..,.._._nu,;,._ n._l .............•....·50

JL:

!i~;j!,!i II;!

.__. ~....~....... __ .-f ····--i·-......-?--··--r ..·····-40·

..~,

!i,· . i, i70

90"01301501701902102302502J0(

130

90

IAS

270

70

230

150

170

210

110

. 250

kmlh

IAS r indicated airspeedCAS r calibrated airspeed

Caution: The airspeed indicator is to be connected tothe static ports and pitot probe in the fuselage nose.


5.2.2 Stall spe~~9Mlri:i,mT,lDlairspeeds1n liw~U ':flight

.ir~r.k~8.r.et~~~ied,

2,8 3337kg/m"5:7

6".87.6Iba/r,t"

7b

16.8rikm/1li23lJ4143kts..

Wing lOB!1ing2.83331kg/m25.1

6~81.6".lbsl.ft2S,tall

speed53687~"kuilh.34

31,39kts"

,Alrbrakea exte~d~

,,·Wingloaditig ,

·--...... ..

Flightmas~kg, . Ib'a ,410:.'036 .500, ',,1162550, '12;3'600' 132361"5·'356

. ,

"W;ing loa~ti.ng' .''kg/~i!i "Ibs/ ft228 '. 5.7

,30 6~1,;336.8', 36 '7.4

37 7~(I

Th!! loss ot'i).dght for stall, reC(jv~ry' is,approxima. te:tY30 m (100 ft) ifreilovl;lredimmed,tatel):. ' ,

App. 5.4


5.3 Additional Information

5.3.1 Demonstrated crosswind performanceThe demonstrated crosswind velocity is 15 y~/h

-~ (8 kts) according to the airworthiness require-ments.

5.3 .2 Gliding performance.

Performance data

Wing kg/m·(Ibs/ft;)28(5.7)33(6.8)37(7.6)loa.ding Min.

5inkrn/s(ft/rninl0.58(100)0.62 {lOa)0.66(116)rate at V

km/h(lets)73(39)79(43)8~(45)Best glide -

3939.540ratio at V

km/h(kts)89(48 )97{52) 103(56)

A variation in speed by ± 10 km/h (5 kts) from the

above will decrease .the best glide angle by 0.5glide points and increase the min. sink rate by1 cm/sec. (2 ft/min).

The polar curves can be seen on the next page.

For optimum performance, the aircraft should beflown with a e.G. towards the rear of the allow

able range. This especially improves thermaiingperformance.However the aircraft will be more pitch sensitive.

The wing fuselage joint, wing parting and thetailplane fin joint should be taped up and theaircraft thoroughly cleaned to obtain maximum performance.

The polars apply to a "clean" aircraft.

With dirty wings or flight in rain, the performance drops accordingly.


Flight manual DG-500 ELk~TRAINER

5.3.3 Flight polar

0..-•...l lii~> 00.•..

0

C'l

~

WZ<0

c::

lXl

I- Z:)WCl

0Cl 10I'"-

I 00looIII'0Q. 0- .r:.

lXl

Cl i!

L

010

~

IIj,

I II

I

1/I.

I

/I

/1I 1""-,, V j

l~~JI '//

II r

I

IIIII

!

!

II

II II

j

IIiI I

Issued: october 1997 TN 34B/9T

o oo•..Ioa~

oo<?

oavI

oo~

5.6


seotion6

"'"\

6 •Mass(weight)and balance

6 .1

Introduc.tion

~.

6.2Weighingprocedures

6.3

Weighingrecord

6.4

Basio emptymass and e.G.

6.5

Mas8of allnon-lifting parts

6.6

Max.mass

6.7

Useful loads

6.8

Loading chart

~

6.9C.G.caloulation


~--- ---- ------------- ~---------_._-~--------


1

6.1 IntroductionThis section contains the payload range within thesailplane may be safely operated.A procedure for calculating the inf1ight e.G. isalso provided.

A comprehensive list of all equipment available forthis sailplane is contained in the maintenancemanual.

6.2 Weighing proceduresSee maintenance manual DG-500 ELAN TRAINER.

Datum: Wing leading edge at the rootrib.Reference line: aft fuselage centre line horizontal.The weighing is to be executed with the engine retracted and all tanks emptied.

6.3 Weighing recordThe result of each e.G. weighing is to be entered onpage 6.5. If the min. cockpit load has changed thisdata is to be entered in the cockpit placard as well.When altering the equipment, the new data can begathered by a e.G. calculation. (see sect.6.9}.The actual equipment list is enclosed in the maintenance manual.

6.4 Basic empty mass and e.G.Actual data see page 6.5.With the empty weight e.G. and the cockoit loads inthe limits of the diagram on page 6.6, the inflighte.G. limits will not be exceeded.

6.5 Mass of all non-lifting parts (WNLP)The max. mass of all non-lifting parts is 435 kg(959 Iba).

WNLP is to be determined as follows:WNLP = WNLP empty + cockpit load (pilot, parachute,baggage, barograph, cameras etc.).WNLP empty = Total empty weight minus weight of thewings.

6.6 Max. mass (weight)Max. weight without waterballastMax. weight

WNLP + W wings615 kg (1356 Ibs)

6.7 Useful loads

Max. load max. weight - empty weightThe data is recorded on page 6.5.



table On page 6.5.

6.8 Loading chart

Cockpit load seea) single seatedmax. load in themin. load in the

front seatfront seat

110 kg 242 Ibssee placard in cockpit and weighing report page 6.5

b) two seatedmax. cockpit load is 210 kg (463 Ibs) with a max.of 105 kg (231 Iba) in the front seat or 110 kg(242 Ibs) in the front seat and 90 kg (198 Ibs) 1nthe rear seat.

min. cockpit load in the front seat is the min.cocpit load see a) minus 40~ of the load in therear aeat.

With these loads, the C.G. range given under 2.8will be kept in the limits if the empty weightC.G. ia in its limits.With lower pilot weight necessary ballast must beadded in the seat. Ballast put on the seat (leadballast cushion) must be fastened at the connectionsof the safety belts.

Removable Ballast (Option) see sect. 7.16.1.

Baggage: max. 15 kg (33 lbs)Heavy pieces of baggage must be secured to the baggage compartment floor (screwing to the floor orwith belts). The max. mass secured on one half ofthe floor (left and right of fuselage centre line)should not exceed 7,5 kg (16.5 Ibs).

Battery In the rin:_______ Only the use of the factory supplied battery Z 07,

(12 V, 10 Ah, Mass 4.3 kg, 9.5 Iba) is permitted.Warning: Flying is only allowed with the batteryin the fin aa otherwise the forward C.G. limit maybe exceeded.


Flight manual DG-500 ELAN TRAINE~

Date of

weighing:Executed by:Date ofequipmentlist:Tail wheel

Plastic/plastic!Plastic!Plastic!Plastic/

(see

remarks!brassb:t:assbrassbrassbras""

Empty massEmpty mass

e.G.Max.

mass

Max.

load

IMin.

cockpitload

infrontseat Max.

load in

both seatsInspectorSignture,Stamp

Weighing report (for 6.3)Distances in mmr ma~ses in kg

25.4 mm = 1 inch 1 kg 2.2046 Ibs.

Remarks: 1. The weighing is .to be executed with thebattery (Z 07 r mass 4.3 kg - 9.5 Ibs)installed in the fin.

2. Weighing was done with a plastic/brass-hub(5. 7.16.4).(Delete which is inapplicable)


Flight manual DG-SOO ELAN TRAINER

6.5

empty weight

cockpit load

art C.G. limit6

ty weightrange

ward e.G. limit

105 kg orkg in front andg in rear seat

3Bc) J'O '100 'lID 410 4JO '1.0 HO Kg25.4 mm = 1 in., 1 kg = 2.2046 lb6

Issued: May 1990

rol:' 6.4 Empty weigb~ C.G. limits ..-i

",1 i/..

/" ~ V'\..

"'-/"-

-'\../

"

"/.•."-'"-- -, ..•.•..

"'.". - ......

~ .••.•..t'-...

Irk, 1•.. -¥ !'.. ~) ,85.. ~"~ - .•.~

" "'40 \ r-.

.'... •.....

'110

'\'. ,."-fJOI~

j ......

'110

\...•."'-. .......

'"'\ ,...empI C.G.

7tD

....•.•

\......•.•... "'-'15"' ~ •......, "\ '.

7fJO.....•.~:\

00

,..•.....70~

..no

\.r-.....

rol:'.--~"'"fiS2 x

&70 ."110

90 k"0

"-

-

"0

"JIJO

t.•. '.•••.1.~

Flight manual· DG-500 ELAN TRAINER

6.9 C.G. ca1oulatloDThe actual C.G. can be determined as follows:

For each item, the moment mass x C.G. has to be determined and to be added up and divided by the total mass. See the following example:

1 kg = 2.20~6 lba = .264 us gal.water 0.305 m = 1 rtItem mass C.G. behind moment

datumkg m ID kg

-----------------------------------~-------~-----------

aircraft empty 380 0,74 281,2

Pilot frontrear

Sum

7565

540

- 1,35- 0,27

XS:O,291

- 101,2522,95

157.0

CG=moment/mass

The limits of the inflight C.G. 0.185 m - 0.48 mshould not be exceededl

The most important C.G. positions (behind datum):

Pilot:The C.G. position i5 dependent on the pilots shape,mass and thickness of the parachute. The pilot C.G.position can be determined by executing a weightand balance measurement with glider empty andequipped with the pilot etc. see maintenancemanual. Please note, that the distance a has to bemeasured with both configurations, as it may changedue to deflection of the landing gear.The pilot C.G. can be determined by the followingequation:

XP = (XSF. HF - XSE • ME)/MP

MFME

flight massempty mas::J

XSF = flight C.G.XSE = empty C.G.

MP = pilot ma::Js


Flight manual DG-500 Eh~ TRF.INER

If the actual pilot e.G. is not known, you have to takethe values from the following table:

Flight: f near the forward e.G.r ~ near the aft e.G.

Pilot C.G. [m]Pilotmass[kg] Frontcockpit Rearcockpit

frfR

110-1,348-1,295-0,277-0,232

105-1,350-1,296-0,278-0,233

100-1,351-1,297-0,279-0,234

95-1,352-1,298-0,280-0,235

90-1,353-1,300-0,281-0,236

85-1,355-1,301-0,283-0,237

80-1,356-1,302-0,284-0,238

75-1,357-1,303-0,285-0,239

70-1,359-1,304-0,286-0,240

65-1,360-1,305-0,288-0,241

60-1,361-1,306-0,289-0,242

55-1,362-1,307-0,290-0,243

Further e.G. positions:

compartment:Baggage or battery in baggageInstruments in front panel:Instruments in rear panel:

Removeable ballast (Option seeRemoveable ballast (Option seeBattery in fin (s.sect. 6.B)Tailwheel

Issued: October 1997

7.16.1a) :7.16.1b):

TN 348/9T

0,31 ID.

-1,870 ID.

-0,7 . ID.

-2,455 ID.

-1,920 ID.

5,306 ID.

5,345 ID.

6.7

Flight manual DG-SOO ELAN T~~IN~R

Section 7

7. Sailplane and systems description

7.1 Introduction

7.2 Airframe

7.3 Cockpit, cockpit controls. and placards

7.4 Flight controls

7.5 Airbrake system

7.6 Landing gear system

7./ Tow hooks

7.8 Seats and safety harness

7.9 Baggage compartment




7.13 Electrical system

7.14 Pitot and static system

7.15 Canopy a~ergency release

7.16 Miscellaneous equipment (Options)

7.16.1 Removable ballast

7.16.2 Oxygen system

7.16.3 ELT

7.16.4 Heavy Tailwheel

Issued: october 1997 TN 348(9 7.1

Flight manual

7.1 Introduction

DG-500 ELAN TRAINER

This section provides description and operating ofthe sailplane and its systems.

Refer to section 9 "Supplements" for details of optional systems and equipment.

M.M. = Maintenance manual

7.2 AirframeThe DG-50C E~AN TRAINER is a twoseater high performance sailplane.

Construction

.Wings.

Ailerons

Horizontal tailplaneand rudder

Fuselage

CFRP-foam-sandwich-shellCFRP-Rovingspar capsAFRP-foam-sandwich-shell

GFRP-foam-sandwich-shell

GFRP-shell. fuselage boomwith Tubus core

CanopyTwo canopies hinged at the right fuselage side.Canopy glass made from clear Plexiglas or PlexiglasGS green 2422 as option.

TailplaneT-Tail with conventional stabilizer-ele.ator and

spring trim.

Col or Airframe: white

registration numbers: grey

or red

or blue

RAL 7001

RAL 3000

RAL 5012

Issued: Oot. 1992 TN 348/3T 1.2


7.3 Cockpit, oockpit oontrols and placards

Issued: May 1990

18-1 20~

7.3

Flight manual DG-500 ·ELAN TRAINER

1) Control Column

The rear control stick is removable. Therefore openthe snap shakle at the trim release lever and disengage the trim cable. Pull out the ·stick afteropening the cap nut.

2) Release lever for the trim mechanism - green.Operation see sect. 7.4 elevator control ..

3) Trim position indicator and trim preselection leVer

I<~·I~>I4)

Tow release knob - yellow. ~

5) Rudder pedal adjustment knob - black(only in front cockpit)

By pulling on the knob, the locking pinwill be disengaged and the rudder pedalscan be· pulled back towards the pilot orpushed forward away from the pilot.

6) Front instrument PanelAfter removing the side screws at the base 2 x M 6and after removing the screws attaching the cover tothe panel 6 x M 4, the cover can be removed towardsthe front. The panel remains in the aircraft.

7) Compass installation position.

8) Radio installation position.

9) Rear Instrument Panel

After removing the side screws attaching the panelto the cover (4 x M 4) the panel can be hinged backwards into the cockpit (take out the control stickfirst! ).

10) Undercarriage retraction - extension handle (Option) black

forward - undercarriage downback - undercarriage retracted


Flight Manual DG-SOOELAN TRAINER

The undercarriage is locked in the extended position by an overcentrelocking arrangement and an additional safety catch. The handle is to beturned towards the cockpit wall, so that the locking catch will engage.

11) Airbrake handle - blueThe wheel brake is operated at the end of the airbrake handle travel.

1[1 _~[

(Piggott-hook): Pull the airbrake handle back to actuate t e brake androtate the handle to the cockpit wall. A detent w' age in one of 4 notchesto hold the system in this position.In case the airbrakes mista aven't been locked, a detent engages in oneof several notche oid inadvertent deployment of the airbrakes. To openand to e airbrakes the operating handle must be rotated into the

12) Constantly open de-misting air vents

13) Main air vent

14) Main air vent operating knobpushed to front closedpulled = open

15) Swivel air vents

= closed

= open

Canopy opening handle - white-red

towards the nose

into cockpit~ ~ ~

Canopy emergency release handle - red ( Jtowards the nose = closed ~~into cockpit = open __'

16)

17)

Emergency release procedure see sect. 3.2.


Flight Manual DG-500 ELAN TRAINER

18) Adjustment strap for the rear seat shell (to be operated on the ground)

19) Push to talk button (Option)

20) 12 V socket for charging the batteries.

Issued: February 2004 TN 348/16 7.5a

Flight manual

7.4 Flight controls

DG-500 ELAN TRAINER

lRudder control:

Cable system with adjustable pedals in the frontcoc~pit. See diagram 2 M.M.

Elevator control:

All pushrods slide in maintenance free nylon ballguides.Automatic control hook up system.Spring trimmer with release lever at the controlstick and oontrol knob at the left cockpit wall.See diagram 1 M.M.To trim, you have to operate the release lever atthe control stick and place the control knob tothe desired position.

Aileron control:

Pushrods slide in maintenance free nylon ballguides.Automatic control hook up system.See diagram 3 and 4 M.M.

7.5 Airbrakes see diagram 3 and 4 M.M.

Double storey Schempp-Hirth type airbrakes on theupper wing surface.The wheel brake is operated by the airbrake system.Push rods in the wings slide in maintenance freenylon ball guides.Automatic control hook up system.

7.6 Landing gear see diagram 2 M.M.al) Main wheel: non retractable, spring monnted with

steel compression springs, fullysealed landing gear box, drum brake,tyre 380 x 150 GPRdiameter 380 mm (15.0 in.)tyre pressure 2.5 bar (36 psi)

a2) Main wheel:(Option)

Issued: May 1990

retractable, assisted by a gas strut,spring mounted with steel compressionsprings, locked in retracted positionby an overcentre locking device,fully sealed landing gear box,hydraulic disc brake.tyre 380 x 150 6 PRdiameter 380 mm (15.0 in.)tyre pressure 2.5 bar (36 psi)

7.6


b) Tailwheel:

c) Nosewheel:

Tyre 200 x 50 2 PRDiameter 200 mm (7.&7 in)

Tyre pressure 4 bar (58 psi)

Tyre 260 x 85Diameter 260 mm (10.2 in.)Tyre pressure 2.5 bar (36 psi)

Option: See diagram 10 MM.The nose wheel is connected to the rudder control with springs.

7.5 Tow hooksSee diagram 5 M.M.Safety release "Europa G 88" for winch launch installed near the e.G."nose release E 85" installed in the fuselage nose for aerotow.

Both hooks are operated by the same handle.

7.8 Seats and safety harnessThe front seat is constructed as an integral inner shell.

The rear seat is height adjustable. The adjustment is by means of a strapsimilar to the shoulder harness.

As safety harness only symmetric 4-point harnesses fixed at the givenfixing points are allowed.

7.9 Baggage compartmentMax. load 15 kg (33 lbs.).Heavy pieces of baggage must to be secured to the floor.

Issued: January 2001 TN348/15 7.7

Flight manual DG-50a ELAN TRAINER

Electrical Syate.Battery in the finFor C.G. reasons the. battery Is installed in thefIn. Only the use of the factory supplied batteryZ 07 (12 V, 10 Ah, mass ij.3 kg, 9.5 Iba) ia permitted.The battery fuse is installed at the battery,type: G fuse 250 V with indicator 5 x 25 mediumslow I 4 A.

After inserting the connector plug in the fin thebattery Is oonneoted to the electrical system ofthe glider. If the battery shall be charged inside the glider this can be done via socket 22,see section 7.3.To charge the battery to its full capacity anautomatic charger with 14.4 V max. charging voltage is necessary (normal automatic chargerscharge only up to 13.8 V).Such a charger is available through Glaser-Dirkscode no. Z 08.All current - carrying wiring confirms to LNaeronautical specifications.

7.14 Pitot and static syste. see diagram 8 M.M.Pitot probe in ruselage nose, and static ports ashort distance behind fuselage nose.The airspeed indicator and the altimeter are tobe connected to these ports and probe.Additional holder for a Multiprobe in the fin isto operate variometer and rlight computersystems.To preserve the sealings inside the holder theend of the probe should be greased with vaselinefrom time to time.

7.15 .Canopy emergenay releaseTo bailout the red canopy emergency releasehandle (right) and the white-red canopy openinghandle (left) have to be operated simultaneously.Push canopy upwards. The retaining lines willtear off. .Reinstalling th~ canopy. .Open emergency release and canopy locking lever.Place canopy in vertical direction onto the fuselage. Close emergency release. Open canopy andsnap in retaining cable.

Issued: May 1990

------------------------------ .._- .._----

Flight manualDG-500 ELAN T~~INER

7.16 Miscellaneous equipment (Options)

7.16.1 Removable ballast

a) Up to 4 ballast weights (code no. Z 10) of-2.16 kg (4.76 lbs) each can be fixed at the M 8

insert in front of the front rudder pedal

mounting point. Each weight compensates a pilotmass of 3.7 kg. (8.16 Ibs) in the front seat.The ballast weights must be fixed with an M 8

bolt which is min. 10 mm (.4 in.) longer than thethickness of all ballast weights.

b) For serial no. SE140 and up:

The ballast box (option) at the right hand side

of the instrument console underneath the carpet canaccomodate 3 lead ballast weights of min 2.2 kg(4.85 Ibs) each. Each weight compensates a pilotmass of 2.9 kg (6.4 lbs). With 3 weights 8.7 kg(19-.2 lbs) missing pilot mass can be compensated.The lead ballast weights are to be fixed in thebox with a M 8 wingnut. -

7.16.2 Oxygen systema)Oxygen bottle installation

Max. size of oxygen bottle is 7 I capacity withdiameter 140 mm (5.S in.)- If a bottle with less

diameter is_used, this bottle must be wrappedwith.plastic to come to the same diameter of140 nUn;- The bottle must be fixed at its neck with

a bracket Z 14 (available at DG-Flugzeugbau GmbH) .b) Installation of the oxygen equipment

To ensure a safe installation ask DG-FluqzeuqbauGmbH for an installation instruction.

For the installation of the Drager Hohenatmer_E 20088 you will find an installation plan 5 EP 34in the maintenance Mamual.

7.16.3 ELT Emergency Locator Transmi ttar

To ensure a safe installation ask DG-FlugzeuqbauGmbH for an installation instruction.

For the Pointer Inc. ELT Model 3000 you willfind an installation plan 5 EP 30 in themaintenance manual.

Issued: October 1997 TN 348/9T

Flight manual DG-500 E~~ T~~INER

Caution: Concer~ing 7.16.2 and 7.16.3

The installation of such equiment has to be accomplished

by the aircraft manufacturer or by an approved servicestation and to be inspected and entered in the aircraftlog book by a licensed inspector.

7.16.4 Heavy tailwheel

Instead of the standard tailwheel with plastichub a tailwheel with brass hub S 27/1 may beinstalled. The installation kit S 27/4 is available at DG-FLUGZEUGBAUGInbH.The difference in mass between both hubs is 3.1 kg(6.84 lbs). With the brass hub, the min. front

cockpit load is increased by 8.5 kg (18.74 lbsl.This higher value must be entered in the cockpit

data placards and on page 6.5. Even if the heavy

tailwheel is installed only sometimes, the higgermin. cockpit load must be entered.



Seotion 8

8. Sailplane handling, care and maintenance

8.1

Flight manual nG-soo ELAN TRAINER

8.1 Introduction

This sectioncontains-manufacturer's recommended procedures for properground handling and servicing of the sailplane. It also identifies certaininspection and maintenance requirements which must be followed if thesailplane is to retain that new-plane performance and dependability. It iswise to follow a planned schedule of lubrication and preventivemaintenanCe based on climatic and flying conditions encountered.

8.2 Inspection period, maintenanceThe "Instructions for continued airworthiness (maintenance manual) for the00-500 ELAN TRAINER have to be followed.

A Before each rigging all the connecting pins lind bushes should be cleanedand greased. This includes the control connectors.

B The contact surfaces of the canopies to the fuselage are to be rubbed withcolourless floor·polish (canopy and fuselage side) to reduce grating noisein flight Polish at the beginning of the flightseason and then every month.

C Once a year all the bearings and hinges should be cleaned and greased. Seethe greasing programme of the maintenance manual.Each year the control surface displacements, adjustments and generalcondition must be checked. (See the maintenance manual).

8.3 Alterations or repairsIt is essential that the responsible airworthiness authority be contactedprior to any alterations on the airplane, to ensure that the airworthiness ofthe sailplane is not impaired. It is prohibited to execute the alterationwithout the approval of the airworthiness authority. The manufacturer willnot be liable for the alteration or for damages resulting from changes in thecharacteristics ofthe aircraft due to alteration. So it is stronglyrecommended to execute no alternatives which are not approved by theaircraft manufacturer.

External loads such as external camera installations are to be regarded asalterations! Repair instructions can be found in the DG·500 ELANTRAINER repair manual. No repairs should be carried out withoutreferring to the manual.

Issued: January 2001 TN348/15 8.2


8.4 Tie Down. ParkingTo tie down the wings use the wing cradles of yourtrailer. The fuselage should be tied down just aheadof the fin. On sunny days the cockpit should beclosed and covered.

Note: Longer parking with exposure to sun andhumidity will cause premature aging of the skin ofyour sailplane.

8.5-Trailering

It is recommended to carry this valuable sailplanein a factory approved closed trailer.

Approved fitting points:Wing panels:

1.Wing spar as close to wing rootrlb as possibleor a rootrib wing cradle.

2.A wing cradle at the taper change.

Stabilizer:Cradles as desired.

Fuselage:1.A felt lined fiberglass nose cap which does notextend over the canopy, secured to floor.

2.Fuselage dolly in front of the tow hook.3.Tail wheel well in trailer floor. Secure

fuselage with a belt in front of the fin orhold it down with the trailer top (soft foam intop).

All aircraft structures should not be subject to anyunusual loads_ With high temperatures that canoccur inside trailers, these loads in time can warpany fibre reinforced plastic sailplane.

The trailer should be well ventilated so as to prevent moisture build up which could result in bubblesforming in the gelcaat.A solar powered ventilator is recommended.

Issued: May 1990


8.6 Towing OD the ground

a) by towing from the nose hook using a rope withthe standard double ring authorized for the release.

b) by using a tow bar which is fixed at the taildolly and a wing tip wheel.

The tow bar and wing tip wheel may be orderedthrough the Glaser-Dirks· factory.

8.7 Cleaning and Care

Exterior surfaces Or· the fibrereioforced

plastic parts .The surfaces are coated by a UP-gelcoat. This gelcoat is protected by a hard wax coating which hasbeen applied during production with a rotating disc(lTschwabbel" procedure). Do not remove the wax, because this would lead to shading; swelling andcracking of the surface. In general, the wax coatis very resistant. As soon as the wax coat is damaged or worn, a new coat has to be applied (seemaintenance manual sect. 3.1). If you store youraircraft often outside, this may be necessary everyhalf year!

Hints for care:

- Wash the surface only with clear water using asponge and chamois.

- The adhesive remains of tape may be removed withpetroleum ether (pure petroleum spirit) which .should be applied and removed immediately, otherwise this may lead to swelling of the gelcoat.

More stubborn dirt which cannot be removed bywashing may be cleaned off with siliconefree,wax containing car polishes (e.g. lZ Extra,Meguiars in USA)

- Longterm dirt and shading can be removed byapplying a new hard wax coat (see maintenancemanual sect. 3.1).


8.7 ff


- Never use alcohol, acetone, thinner etc •. Do notuse detergents for washing!

- Protect the surface from intense sunlight~

- Protect the aircraft from water and moisture. Seesect. 8.4 and 8.5.

- Remove water that has entered and allow the aircraft to dry out.

- Never store your wet aircraft in a trailer.

Plexiglas canopy:

- Use clear water and a chamois for cleaning.

- Stubborn dirt and small scratches can be removedby use of the "sohwabbel procedure" (see maintenance manual sect. 3.1).

Meta~parts:

The pins and bushes for rigging the aircraft arenot surface protected and must be covered withgrease all the time.The other metal parts, espeoially the controlstick and all handles should be preserved withmetal polishes occasionally.


Flight manual DO-500 ELAN TRAINER

0.

L

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Section 9

Supplements

Section not eff8~tive

Issued: May 1990

5£55722. 5£alvsbyflygklubb.se/instruk/dg500manualeng.pdf480(7.28 mmup in.)(18.9in.to ) behind...

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