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LET, a. s. 686 04 KU NOVICE, CZECH REPUBLIC . SAILPLANE FLIGHT MANUAL Serial Nos.eligible : 938101, and subsequend Model: Serial No.: Registration : Document Number. : Do - L13AC.1013.3 Date of Issue : Nov 30, 1998 Section 2, 3, 4 and 5 have been approved by The Civil Aviation Authority of the Czech Republic in Prague. S . t -7 / 1gna ure : / , , .<----------.., Authority : CAAJ?.rague Stamp: " Original date of approval: 15.7.1999 THIS FLIGHT MANUAL MUST BE CARRIED ABOARD THE SAILPLANE AT ALL TIMES WHEN IN OPERATION. This Sailplane Flight Manual constitutes an FAA Approval Flight Manual for US Registreted asilplanes in accordance with FAR 21.29

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Page 1: SAILPLANE FLIGHT MANUAL - Puget Sound Soaring … -13 AC BLANIK SAILPLANE FLIGHT MANUAL Do -L1 3AC .1013 3 1.1 INTRODUCTION This Flight Manual contains the instructions, performance

LET, a. s. 686 04 KUNOVICE, CZECH REPUBLIC .

SAILPLANE FLIGHT MANUAL Serial Nos.eligible : 938101, and subsequend

Model:

Serial No.:

Registration :

Document Number. : Do - L 13AC.1013.3

Date of Issue : Nov 30, 1998

Section 2, 3, 4 and 5 have been approved by The Civil Aviation Authority of the Czech Republic in Prague.

S . t ~ -7 / 1gna ure : / , , .<----------.., Authority : CAAJ?.rague

~Oc1>11~~

Stamp: fli~ "

Original date of approval: 15.7.1999

THIS FLIGHT MANUAL MUST BE CARRIED ABOARD THE SAILPLANE AT ALL TIMES WHEN IN OPERATION.

This Sailplane Flight Manual constitutes an FAA Approval Flight Manual for

US Registreted asilplanes in accordance with FAR 21.29

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do~ L 13AC.1013,3

0.1 RECORD OF REVISIONS

The Sailp lane owner will be notified by the Czech Republ ic , Civil Aviation Autho rity approved Bulletins of any revision or amendment to th is manual. The owner must replace the old pages with the new ones and enter the revis ions into the Record of Revisions. The manufacturer must be informed of any change of owner or owner's address to keep the service and fl ight documents current

Manufacturer 's address: LET, a.s. 686 04 KUNOVICE Czech Repub lic Telephone: + 420-632-51 1111 Fax: + 420-632-56 4102

Revised or amended parts of the text will b~ marked by vertical li ne in page margin , and the number of the revision and date of its issue will be shown at th e bottom of th e page.

Rev. No. Section Affected Pages Date of Number of Date of Carried Out On, Issuing Bulletin Bulletin Signature Revised Covering Approval Pages Revision

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Nov 30/98 0 - 1

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013 .3

Rev. No. Section Affected Pages Date of Number of Date of Carried Out On, Issuing Bulletin Bulletin Signature Revised Covering Approval Pages Revision

I

I

I I

I

I

I I I I I ! !

I f I

I I I i ! I

Nov 30/98 0 - 2

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~ L - 13 AC BLANIK AA Ayres Comporry

SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

0.2 LIST OF EFFECTIVE PAGES

Section Page Date Section Page Date

0 1 Nov30/98 4 21 Nov 30/98 2 Nov30/98 22 Nov30/98 3 Nov 30/98 23 Nov30/98 4 Nov 30/98 24 Nov30/98

25 Nov 30/98 1 1 Nov30/98 26 Nov 30/98

2 Nov30/98 27 Nov 30/98 3 Nov30/98 28 Nov 30/98 4 Nov30/98 29 Nov 30/98 5 Nov30/98 30 Nov 30/98 6 Nov30/98

5 1 Nov30/98 2 1 Nov30/98 2 Nov 30/98

2 Nov30/98 3 Nov 30/98 3 Nov30/98 4 Nov 30/98 4 Nov30/98 5 Nov30/98 6 1 Nov30/98 6 Nov 30/98 2 Nov 30/98 7 Nov30/98 3 Nov30/98 9 • Nov 30/98 4 Nov 30/98 9 Nov 30/98 5 Nov30/98 10 Nov 30/98 6 Nov30/98

7 Nov30/98 3 1 Nov 30/98 8 Nov30/98

2 Nov30/98 3 Nov 30/98 7 1 Nov 30/98 4 Nov30/98 2 Nov 30/98

3 Nov 30/98 4 Nov 30/98

4 1 Nov 30/98 5 Nov 30/98 2 Nov30/98 6 Nov 30/98 3 Nov30/98 7 Nov30/98 4 Nov30/98 8 Nov 30/98 5 Nov30/98 9 Nov 30/98 6 Nov 30/98 7 Nov30/98 8 1 Nov 30/98 8 Nov30/98 2 Nov30/98 9 Nov30/98 3 Nov30/98 10 Nov30/98 4 Nov 30/98 11 Nov30/98 12 Nov 30/98 9 1 Nov 30/98 13 Nov 30/98 2 Nov 30/98 14 Nov 30/98 3 Nov 30/98 15 Nov 30/98 4 Nov 30/98 16 Nov 30/98 17 Nov 30/98 18 Nov 30/98 19 Nov 30/98 20 Nov 30/98

Nov 30/98 0·3

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.10 13.3

0.3 TABLE OF CONTENTS

Section

General 1

Limitations 2

Emergency Procedures 3

Normal Procedures 4

Performance 5

Weights and Balance 6

Sailplane and Systems Description 7

Sailplane Handling, Care and Maintenance 8

Supplements 9

Nov 30/98 0-4

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r;"'i~ ,..-~

-~

Nov 30i99

L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L13AC .1013.3

Section 1

General ·

Contents

1.1 Introduction

1.2 Regulation Basis

1.3 Warnings, Cautions, Definitions and Abbreviations

1.4 Basic Data

1 .5 Three-View Drawing

1 - 1

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L1 3AC .1013.3

1.1 INTRODUCTION

This Flight Manual contains the instructions, performance information and limitati ons for the L - 13 AC BLANIK Sailplane. Pilots are as sumed to be familiar with basic theory o f flying and therefore this Manual contains only in structions spec ific for the L - 13 AC BLANIK Sail plane

1.2 REGULATION BASIS

This sailplan e has be en approved by Civil Aviation Authority of the Czech Republic in accordance with BCAR-E, issue 1960 in Aerobatic Category of Airworthiness .

1.3 DEFINITIONS AND ABBREVIATIONS

WARNING: MEANS THAT NON-OBSERVATION OF THE CORRESPONDING PROCEDURE LEADS TO AN IMMEDIATE OR IMPORTANT DEGRADATION OF FLIGT SAFETY.

CAUTION: Mea ns th at no n-o b serv ati on o f the c o rre s pond ing procedure leads to a minor or more or less long term degradation of flight safety.

NOTE : Draws attention to any special item not d irectly related to safety but which is important or unusual.

km/ h IAS ind icated a irspeed in k ilometres per hour

KIAS ind icated a irspeed in knots

FM . Flight Manual

QFE. atmospheric pressure at aerodrome level (altim eter reads O)

QNH .. . . ... setting o f altimeter p ressure scale to obtain sailp lane a ltitu de leve l

MAC Mean Aerodynamic Chord

VFR . Visual Flight Rules

VA . . . . .. . ... . manoeu vring speed

never exceed speed in smooth air

VRA rough air speed

Nov 30/99 1 - 2

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L13AC .1013.3

VT .. . ... . ... . maximum aerotowing speed

Vw .... . ... .. . maximum winch-launching speed

VLO .. . maximum landing gear operating speed

1.4 BASIC DATA

1.4.1 Brief Description

The L - 13 AC BLANIK is a two-seat cantilever high-wing monoplane of ~ all -met al structure with iabric -covered control surfaces. Both flight

compartments are covered by s ing le-section canopy which may be emergency jettisoned in flight. In both flight compartments are located all elements to control the sailpla­ne including instrument pane ls with flight and navigation instruments. The sailplane is provided with hooks to enable winch and aerotow launching. Both flight comportments are vented by air bled from fuselage nose, and its supply may be controlled. There is a baggage compartment beh ind the rear f light compartment. Both f light compartments are upholst ered. The wing inc luding ailerons and air brakes is attached by six bolts to the fuselage. A vert ical f in with rudder is attached to the rear fuselage. The hor izontal tail is also attached to the end of fuselage . The elevator and ailerons are manual controls by contro l cables and push-pull rods. The rudder control is also manually operated by the feet, using control cab les and rods. The air brakes are controlled by levers. The elevator t ri m tab is also lever controlled. The sailplane is fitted wi th a main and tail-wheel type landing gear. The main landing gear is mechanically retractable with a hydropneu­matic shock absorber and a wheel with mechanically actuated brake. The tail landing gear is a tail wheel with shock absorber.

Main land ing gear retraction

To retract t he main landing gear li ft the handle on the right-hand side panel up and pu ll to the rear. Push the handle downwards to lock it in th e retracted pos ition.

Main land ing gear extens ion

To extend the main landing gear, liit the handle and move it fo rward. Push the handle down to lock it in the extended position. The landing gear is in the locked posit ion if the handle cannot be moved rearward.

Nov 30/99 1 - 3

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~ L - 13 AC BLANIK An AVte.s Comoonv

SAI LPLANE FLIGHT MANUAL

1.4.2 Basic Dimensions

1. Main dimensions

Wing span .

Length

Height

2.Wing

Area

Aspect rat io .

Dihedral ...

Sweep angle

Mean aerodynamic chord .

Geometric twist .

Ailerons

Area

Span

Deflections: up

down

Air brakes

Area

Span

3. Horizontal tail

Area (total)

Span ....

Aspect ra tio .

Dihedral angle

Nov 30/99

Do- L 13AC .1013.3

. 46.59 ft (14.2 m)

. 27.56 ft (8.4 m)

. 6.86 ft (2 .09 m)

. 187.72 sq .ft (17.44 m2)

. 11. 186

. 4.26 ft (1. 298 m)

. .30

. 19.1 6 sq.ft (1. 78 m2)

. 9 .13 ft (2.783 m)

. 34° + 2°

. 6.97 sq.ft (0.648 m2)

. 4.61 it (1.404 m)

' 2 . 28 .63 sq .ft (2 .66 m )

. 11.32 ft (3 .45 m)

. 4.3

. 50

1 - 4

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L -13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L13AC .1013.3

Elevator

Area .. . 10.76 sq.ft (1.0 m2)

Deflection: up . . 32° + 2°

down

Trim tab area .. . 1.25 sq.ft (0.116 m2)

Trim tab deflection:up . . 12° + 1°

down

4.Vertical tail

Area (total} . 16.15 sq.ft (1.5 m2)

Height ... . 5.25 ft (1.6 m)

Aspect rat io . . 1. 7

Rudder

Area .. . 8.50 sq.ft (0.79 m2)

Deflection (both sides - perpendicular to axis of rotation) ........... . . 29° + 1°

5.Fuselage

Fuselage width . 2.165 ft (0.66 m)

Fu se lage height . 3. 61 ft ( 1 . 1 0 m)

(cont.)

Nov 30/99 1 . 5

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1.4 Three-View Drawing

27.56 ft/8400 mm

Fig. 1-1

Nov 30/99 1 - 6

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - U3AC.1013.3

section 2

Limitations

Contents

2.1 Introduction

2.2 Airspeeds

2.3 Not used

2.4 Not used

2.5 Power-plant Instrument Marking

2.6 Weight

2. 7 Centre of Gravity

2.8 Approved Manoueuvres

2.9 Manoeuvring Load Factors

2. 10 Flight Crew

~ · 2.11 Kinds of Operation

2.12 Minimum Equ ipment

2.13 Aerotow and Winch Launching

2. 14 Other Limitations

2. 15 Limitation Placards

Nov 30/98 2 - 1

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~ L-13 AC BLANIK Af'IA'(feSCompony

SAILPLANE FLIGHT MANUAL Do - L13AC.1013.3

2.1 INTRODUCTION

Section 2 inc ludes operating limitations and basic p lacards necessary for safe operation of the sailplane, its standard systems and standard equipment.

2 .2 AIRSPEED LIMITS

KIAS

Speed (km/ h IAS)

Remarks

VNE Never exceed speed in 124 This speed must not be exceeded smooth air and contro l deflection must not be

(230) more than 1 / 3

VRA Rough air speed 86 This speed must not be exceeded in !severe turbulence

(160)

VA Manoeuvring speed 86 No full or abrupt contro l deflections may be made above th is speed

(160) because the sa i lp lane structure might be overstressed

Vw Maximum 65 This speed must not be exceeded winch- launching speed during w i nch-towi ng or motor-

(120) vehicle towing

VT Maxi mum aerotowing 76 This speed must not be exceeded speed during aerotowing

(140)

VLO Maximum landing gear 124 Do not extend or retract the land ing operating speed gear above this speed

(230)

(cont.)

Nov 30/98 2 - 2

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L- 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

V NE limits above 8 ,200 ft (2,500 m) of pressure altitude are as follows:

Pressure altitude ft 8,200 10,000 13,000 16,500 20 ,000 23,000 26 ,000 30,000

VNE KIAS 124 120 113 105 98 92 85 79

Pressure altitude m l2.500 3,000 4,000 5,000 6,000 7,000 8,000 9,000

V NE km/ h IAS I 230 223 209 195 182 170 158 147

2.3 AIRSPEED INDICATOR MARKINGS

Mark ing I

KIAS (km/h IAS)

Signif icance

Green arc 40 - 86 Normal Operating Ran~e (lower limit (72 - 160) is maximum weight 1. Vs 1 at most

fo rward e.g . pos ition , upper lim it is rough air speed) .

Yellow arc 86 - 124 Speed range in smoot h air. (160 . 230 )

Red line

I 124 Maximum pe rmi ssib le speed for all

(230) operations

Yellow tr iangle

I 49

(90) !Approach speed at maximum jwe1ght

(fl ight)

2 .4 Not used

2.5 Not used

Nov 30i98 2-3

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

2.6 WEIGHT AND CENTRE OF GRAVITY POSITION

Maximum take-off weight:

- with two occupants ...... . . 1100 lb (500 kg)

Empty weight of the sai lplane with standard equipment ....... . 672 lb ± 2% (305 kg ± 2%)

and the corresponding centre of gravity position: 1) from fuselage nose ......... . . xr=120.866 ±0.51 in

(3,070 ± 13 mm),

2) from reference plane (starting point of the wing rib No. 1)

Pilot 's weight ( including parachute):

- minimum pilot's weight (solo) .

- maximum pilot's weight (solo)

Maximum useful load ...

Weight of non-lifting parts:

i.e. 65.5 ± 1% MAC

xr = 27.323 ± 0.51 in (694 ± 13 mm). i.e. 65.5 ± 1% MAC

154 lb (70 kg)

250 lb {113 kg)

430 lb (195 kg)

- maximum weight of non-lifting parts . . . 783 lb (355 kg)

WARNING: IT IS NECESSARY TO USE SEAT WITH BALLAST OF 33 LB (15 KG) IN THE FRONT COCKPIT WHEN FLOWtl BY A PILOT WEIGHING FROM MIN. 121 LB (55 KG) TO 154 LB (70 KG) .

NOTE: Installation of the front seat ballast is described in Section 7, paragraph 7.2 of this Flight Manual.

2.7 CENTRE OF GRAVITY

Permissib le centre of gravity range

- front limit .. • . ... . . .. . .... . • . . 23% MAC 99.134 in(2,518 mm), i.e. from fuselage nose

- rear li m it .. . ......... . . . ... . . . .. . . . .. 38% MAC 106.811 in(2,713 mm) i.e. from fuselage nose

Nov 3Q/g8 2- 4 _..._. ____ _

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - U3AC.1013.3

2.8 APPROVED MANOEUVRES

Manoeuvre Dual Solo Entr~ airspeed IA (KIAS)

Loop yes yes Section 4.3.6, item 1.

Stall turn yes yes Section 4.3.6, item 2.

Half loop and half roll yes yes Section 4.3.6, item 3.

Half roll and half loop yes yes Section 4.3.6, item 4.

Lazy eight yes yes Section 4.3.6, item 5.

Inverted flight yes yes Section 4.3.6, item 6.

Slow roll yes yes Section 4.3.6, item?.

Spin yes yes Section 4.3.6, item a.

Chandelle (climbing) yes

I yes Section 4.3.6,

item 9.

Steep turn yes yes Section 4.3.6, item 10.

Flick roll yes yes Section 4.3.6, item 11.

Flick half roll and half loop yes yes Section 4.3.6, item 12.

Nov 30/98 2-5

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

2.9 MANOEUVRING LOAD FACTORS

n 6

5

2

0

-1

-2

-3 _, -5

0

W•IOlll 880 lb (400 ~O)

,.. .J.. . // ~ ! - - --// --

// . '/

,:.?'

.-l..P'

- ~-,--.::::- 100 150 2 )J I) 12So $pHd.

·...,i::'--- V/ I'-. '-

r< ~ vv

"" x ;< WoloM ' 1 oo 10 ($0

I I I o •ol

25 50 75 100 125

Fig. 2 - 1

2.10 FLIGHT CREW

The flight crew may consist of one or two pilots. If the sailplane is to be flown solo, the pilot must sit in the front seat and his we igt1t (fr1::;1ucling parachute) must be at least 154 lb (70 kg). If th e pilot 's weight is loss than 154 lb (70 kg), it is necessary to use the cushion with 33 IL; (15 kg) bal last in front cockpit. The rear seat must be secured aft using th e safety belt and shoulder harn esses.

2.11 KINDS OF OPERATION

The sailplane is certified in aerobatic category to allow approved aerobatic manoeuvres (see para. 2.6). Onty day VFR flights and cloud flights are permitted. Intentional flights in icing conditions are prohibited

CAUTION:

Nov 30/98

It Is necessary to record the aerobatic manoeuvres ot the sallplane Into the sailplane log book so as to be able to find out total flight time of aerobatics from date of sailplane manufacture.

. ~

• - <.. 0

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2.12 MINIMUM EQUIPMENT

Instruments and additional equipment added to the minimum equipment must be approved .

A. Flights according to VFR conditions

2 Airspeed indicators with colour-markings according to item 2.3

2 Altimeters

2 Turn and bank indicators

2 Magnetic compasses

2 Accelerometer

2 Five -point safety harnesses

2 Manua l parachutes

B. Cloud fly ing

Added to minimum equipment as per para A

1 VHF transceiver

Nov 30/98 2 - 7

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2.13 AEROTOW AND WINCH LAUNCHING

Aerotow

- the maximum cable strength or cab le safety device to aerotow the sailplane is 1,400 lb (6,230 N) .

- minimum cable length for aerotowing is 100 ft.

Winch- launching

- th e maximum cable strength for winch-launch ing of the sailplane is 1,400 lb (6 ,230 N).

2.14 OTHER LIMITAT IONS

Maximum demonstrated crosswind component

- maximum demonstrated crossw ind c ompo nent for safe approach, land ing and aerotow launchi ng is 16 kt.

Determinat ion ·of maximum wind spee d at winch-l aunch ing :

o· 1) "

24 "' 22 "' 20 "'

RELATIVE ANGLE TO WIND OIRECTIO

18 "'

15 "' 14 "' 12 kt

10 kt

8 let

5 let

' let ao· 2 let

Wind an gle relat ive to co nnect ing line: Take-off - Winch

Fig. 2 - 2

Nov 30/98 2 - 8

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2.15 LIMITATIONS PLACARDS

Operati ng lim itations are emphasized on limitation placards both in front and rear cockp it. For location of the p lacards see Section 7, pages 7-4 and 7-5. Values given on the placards must comply with the installed instrument (e .g. airspeed indicator) .

a) front cockpit

- without ballast

o I

b) both front and rear cock pits

(-R) c~) Air brakes Air brakes extended retracted

(~) (~) Landing gear Landing gear retracted extended

(~b~ ) Trim

(~~) ( ~- ) Seat back Air vent

( t::-! - ~) Pedal adjustment

(~) (&;c1) Canopy lift off

(~) Wheel brake

Canopy jettison

Baggage (rear seat only)

Release

Nov 30/98

No baggage (rear seat only)

2-9

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. ..-...._

L-13AC BLANIK SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

I

PRESSURE

MAX. GROSS WEIGHT EMPTY WEIGHT (STANDARD) APPROVED MANOEUVRES: LOOP HALF LOOP AND HALF ROLL HALF ROLL AND HALF LOOP INVERTED FLIGHT STEEP TURN FLICK ROLL FUCK HALF ROLL AND HALF LOOP

1100 1b 6721b

STALL TURN LAZY EIGHT CHANDELLE (CLIMBING) SLOW ROLL SPIN

SOLO FLIGHT FROM FRONT SEAT ONLY

MAX. ALOWABLE SPEED VS ALTITUDE

ALTITUDE (Fl) UP TD 8,200 10,000 13,000 16,SOO 20,000 23,000 26,000

VNE (KIAS) 124 120 113 105 98 92 85

or

MAX. ALOWABLE SPEED VS Al TITUDE

PRESSURE Al TITUDE (m) UP TO 2,500 3,000 4,000 5,000 6,000 7,000 8,000

VNE (km/h) IAS 230 223 209 195 182 170 158

30,000

79

9,000

147

MAX. WINCH - LAUNCHING SPEED: 6S KIAS VNE 124 KIAS ~AERO - TOWING SPEED: 76KIAS VAA 86KIAS

. MANOEUVRING SPEED: 86 KIAS or

or VNE 230 km/h

MAX. WINCH - LAUNCHING SPEED: 120 km/h VAA 160 km/h MAX. AERO - TOWING SPEED: 140 km/h MAX. MANOEUVRING SPEED: 160 km/h

c) exterior markings

Near the static pressure sensor.

8

Nov 30/98 2 - 10

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~ L-13 AC BLANIK AA Ayres Compony SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

SECTION 3

Emergency Procedures

Contents

3.1 Introduction

3.2 Canopy Jettison

3.3 Bailing out

3.4 Stalls

3.5 Spin

3.6 Spiral

Nov30/98 3- 1

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L13AC.1013.3

3.1 INTRODUCTION

Section 3 provides procedures for handling emergency situations.

3.2 CANOPY JETTISON

Pilot (front or rear)

1.Canopy jettison lever (the red lever on the right upper cockpit frame, Fig. 3-1, pos. 1)

rotate the lever 180° in the direction of the arrow shown below the lever

Note: Turning the lever (front or rear) 180° (upwards and forward) pulls the hinge pins on the right and left side of the cockpit. The canopy strap is also released .

2.lf the canopy does not jettison: hold the emergency jettison lever in its end position and at the same time push the canopy upward, using the other hand.

3.2 BAILING OUT

Release the safety harnesses and stow them. Grasp cockpit rails, pull your legs under you, as much as possible and bail out over the side. If possible, exit below the sailplane wing .

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CANOPY JETTISON DURING FLIGHT:

1

Fig. 3 - 1

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3.4 STALLS

Pre-stall warning first is a gentle buffeting in the control stick (elevator), followed by a gentle nose down pitching at stall. Stall recovery at a high speed is the same. If the sailplane wing stalls, the control stick must be gently eased forward up tp pushing forward. If wings are not level, correct with simultaneous application of opposite rudder. Elevator and rudder control must be energetic to prevent an inadvertent entry into a spin. Stall recovery from turn is to be done by an energetic forward movement of the control stick and at the same time by applying the rudder against the stalling wing (in case the sailplane stalls to the right, we apply left rudder and vice versa). If we apply the control surfaces in time and energetically, the sailplane will stop slightly below the horizon which is enough to adjust speed to let it continue its controlled gliding. If it is not corrected, the sailplane may enter a spin.

3.5 SPIN

A spin usually results from a disproportional application of rudder at stall.

Standard procedure to recover from a spin is:

1. Prior to spin recovery, neutralize the ailerons.

2.Apply opposite rudder (i.e. against the direction of rotation).

3.Short pause.

4. Ease the control column forward until the rotation ceases.

5.Centralize rudder and recover from the dive.

3.6 SPIRAL

The spiral mode is noted by speed increasing rapidly.

The rapid airspeed increase is tile difference between the spin and the spiral.

Spiral dive recovery: timely cormol the bank and sideslip by co-ordinated movement of the ruddl:r and aileron and recover from the dive.

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4. 1 INTRODUCTION

Section 4 provides procedures for perform ing normal ope rations.

4 .2 FIEL D SAIL PLANE ASSEMBLY AND DISASSEMBLY

Prior to removing wings, tilt upwards hotizontal tail (see item 4.2.3).

4.2.1 Wing removal

Four peop le are needed for wing removal.The first one holds the fuselage, the second one holds the wing tip and the th ird and fourth one hold the wing root (see Fig. 4 -1). Level the sailplane in horizontal position .

Remove the fair ings between the fu selage and the wing. Remove electrical ground straps on aileron control tie rods. Discouple the aileron control tie rods by unlocking safety pins and removing p ins on rocker levers pivoted in consoles on outside ribs (from the fuselage s ide). Remove lock pins from the front hinge p ins and wing main p ins and knock out the front pin .

Gently move the wing up and down when instal ling or removing the pins. Pu ll the wing from the fuselage by a slow and carefu ! movement and p lace it perpendicularly with the leading edge pointing downwards on a special handl ing equipment .

4.2 .2 Wing installation

The wing installation is the opposite procedure . For easier installation of the centre hinge pins use the centering pin (see Fig . 4-1, deta iled view A) before inserting the pins. When sliping wing hinges on fuselage hinges make sure that the globular joint of the ai r brakes control (see Fig . 8 -1, detailed view 6) is set in a posit ion to fit into the control drivers in th e wing . When assembling , first slide in the wing ma in hinge pin and only then the wing front h inge pin .

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Section 4

Normal Procedures

CONTENTS

4.1 Introduction

4.2 Field Sailplane Assembly And Disassembly

4.3 Daily Inspection

4.4 Pre-flight Inspection

4.5 Normal Operations and Recommended Speeds

4.5.1 Not used

4.5.2 Take-Off and Climb

4.5.3 Flight

4.5.4 Approach

4.5.5 Landing

4.5.6 Flight with Water Ballast

4.5.7 High Alti tude Flight

4 5.8 Flight in Rain

4.5.9 Aerobatics

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Q"i~ A'"IAyes Comoonv

Nov 30/98

L-13 AC BLANiK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

~.· c ~/

,..,,..~·

® "(::.,

A - Centering the front hinge

B - Control joint between the wing and the fuselage

C - Wing main hinges with the main pin

Fig. 4 - 1

4-3

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4 .2.3 Instructions for folding the horizontal tail unit control surfaces into the vertical position

The horizontal tail unit control surfaces can be fo lded upwards for sailplane transportation. (see Fig. 4-2, det.B) Fold the fuselage tail portion upwards f irst. During this, the rudder is to be def lected to one side. Unlock and take out the middle securing pin (see Fig.4-2, item 5) which secures the position of both tail unit control horizontal surfaces. The hinged port ion of the fuselage tail can be set back, the rudder set in its neutr al position and horizonta l tai l unit control surfaces folded upwards. When fo lding these surfaces, care should be taken to not damage the hinged part of the fuselage end. This can be prevented by proper deflection of both halves of th e elevator . When fold ing the tail unit control surfaces upwards, the elevator control countershaft takes p lace automatically (see Fig .4-2, item 4 ). The tail unit surfaces shall be secured in th eir fo lded vertical position by a horizontal ta il unit surface securing strut o r both surfaces may be secured by a securing strap (see Fig.4-2 , item 9) . The latter shall be inserted into the cut out in the fuselage in f ront of the bulkhead 15 and secured in the m iddle by means of the pin , which can be removed f rom the ho le in bulkhead No. 15 (see Fig.4-2, det. 8 ) . The p in shall be secured with a safety pin. Extended parts of the tailplane spars shall be inserted into the clevises on both ends of the strut and secured with pins. The latter shall be locked with safety p ins. To avoid damage to the elevator during sailplane transit, both rudder and elevator shall be secured by means of st rap (text ile) bound over them.

4.2 . 4 Returning the horizontal tail unit surfaces back to their normal (i.e. flight) position

See Fig. 4-2) Three poeple are needed fo r this p rocedure. Two men to hol d the tail unit surfaces in the ve rtical position, the third - having fo lded the fuselage tail portion upwards - unlocks and removes 3 p in s (Fig .4-2 . item 5, 7 , 8) and th en the st rut. After removing out the secu ring strut o r securing strap both halves o f horizontal tai l unit surfaces shall be sl owly folded down. Meanwhile , the mechanic working close to th e fuselage, hold s th e elevator control countershaft so that it fits with it s channe ls in th e carriers on both halves of the elevator. When folding both halve s down, it is necessary to keep the elevator in such a position that its extended ribs d b not contact the hinged part of the fuse lage tai l. As soon as the countershaft channels a re meshed wi th the carrier s on the elevator and tail unit control surfaces are in th eir normal position, th e securing p in shall be inserted into th e bushing on the bulkhead No. 15.

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The pin should be secured with a safety. The hinged portion of fuselage tail should be returned to its normal position and secured w ith two screws .

Fig. 4-2

( 1)Hinged fuse lage tail portion, (2) Left half of elevator, (3)Right half e levator, (4) Elevator control countershaft, (S)Securing pin , (6)Securing strut, (7) and (8)Strut securing p in, (9)Securing strap

WARNING:

Nov 30/98

ENSURE THE CORRECT POSITION OF THE ELEVATOR CONTROL COUNTERSHAFT AFTER TILTING THE ELEVATOR INTO THE NORMAL FLIGHT POSITION: RED MARKED PART OF THE DRIVING MUST BE ON ITS LEFT

SIDE IN THE BACK VIEW IN FLIGHT DIRECTION.

4-5

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4.3 DAILY INSPECTION

After each flight day

- inspect the fuselage surfaces

- check the operation of the control mechanism of the towing equipment

- inspect the canopy glass and side windows

- inspect the wing surfaces and the movable parts of the wing

- inspect tail surfaces and the deflection of the control surfaces

- inspect controls for proper operation arid security

- check the pressure in tire

- inspect the bay of the main landing gear and the tai l wheel unit, check ope ration of the brakes and the shock absorber

- inspect the attachments of the instrument panels and inspect the instruments tor damage

- inspect ventilation system

- inspect attachment of the first aid kit

- inspect battery bay

- check the voltage of airborne battery and charge t he battery if necessary

- inspect the moisture trap

For more details see Maintenance Manual item 2.2.2 Operational Maintenance

4.4 PREFLIGHT INSPECTION

Before getting into the sailplane , the pilot must check the whole sailplane for proper condition in accordance with the inspection . checklist. Perform the inspection in a systematic manner so no items are omitted. Perform the inspection as shown in Fig. 4-3.

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Sequence of the Walkaround Inspection of the Sailplane:

Fig. 4.3

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4.4.1 PREFLIGHT INSPECTION CHECKLIST

Route Subject Check/activity item No.

1 Front fuse lage section

Fuselage skin no damage, deformation, loosened rivets

Static-pressure sensors no"dirt, no clogging

Cockpit canopy surface no damage, no dirt

Pitot tube no damage, no clogging

2 Cockeit interior

Instruments no damage

Altimeters correct QNH (QFE) setting

Transceiver (if installed) proper operation

Nose ventilation no clogging, proper function

Safety harnesses no damage

Control system , trimmimg, proper function air brakes

3 Landing gear wheels

Tire no damage , correct inflation: - main landing gear

36.26 psi (250 kPa)

(cont.)

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Route Subject Check/activity item No.

4 Left wing

Wing - fuelage connection no damage to pins (ma in and front hinges), p ins lock ing.wing- fuselage control connection

Wing skin includ ing leading no damage, no deformations, edge loosened rivets

Ai leron surface no damage to fabr ic cover, no damage to trailing edge

Ai leron easy movement

Ai rbrake locking in hinges no damage t o locking in hinges and control t ie rods

5 Rea r fuselage section

Fuselage surface no damage, no deformations, loosened rivets

Inspection cover proper attachment of control elements, connections securing

(cont .)

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Route Subject Check/activity item No.

6 Emeennag e

Empennage surface no da mage, no def ormat i on s and loosened rivets

Probe of compensator of removed cap, no damage vertical speed indicator

Eievators easy movement

Locking of rear pin non-damaged condition of horizontal tail of locking wi re securing th e rear

pin of the horizontal ta il unit

Rudder easy movement

7 Tail landin9 9ear

Land ing gear attachment no damage of attachment

8 Right wing see item 4 - left wing

9 Front fuselage section

Pins for canopy open ing p rope r posit ion in re lati on to h inges

Nov30/9B

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4.4.2 Before Take-Off Checklist

Front seat

Before entering the front cockpit, adjust the front seat back rest to a position allowing safe control of the sailplane when the safety harness is fu lly adjusted.

Rudder control

The posit ion of the rudder pedals should be ad justed with fu lly adjusted the safety harness so that both left and right rudder pedals can be moved fu ll travel. The rudder pedals in the front cockp it can be adjusted by use of a crank. In the rear cockpit the pedal adjustment should be done on the ground only. Three pedal positions are possible. The pedals are secured with lock ing pins.

Contro l column

Check the control column for free movement left and right, and fore and aft. ·

Instruments

Set t he altimeters to ONH value (to read field alti tude). The altimeters set to zero wil l indicate pressure at aerodrome level (QFE) . Check all instruments and note that the vertical speed indicates zero.

Safety harnesses

Fasten the safety harnesses .

Cockpit canopy

Close and lock.

Trim

Set the elevator tr im tab position to "O" .

Air brakes

Check for easy movement and confirm their re tracti on .

Tow rope release

Check for proper function of the tow rope release and connect the tow rope. Ground-service personnel shall pull it to check its proper fastening .

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4.5 NORMAL OPERATIONS AND RECOMMENDED SPEEDS

4.5.1 Not used

4.5.2 TAKE-OFF AND CLIMB

1. Aerotow launching

The take-off technique by aerotow is entirely conventional and does not require any special pilot skills. The elevator and rudder efficiency is high enough during the initial stages of the take-off run to prevent any directional or roll oscillations. With the elevator trim tab control set between •o• and •nose heavy• position hold the control stick in neutral position - on the landing gear wheel; then, while gently pulling the control stick, the sailplane will unstick. At a height of about 3 ft (1 m), hold a level attitude until the tow plane starts to climb. During cross wind take-offs, unstick the sailplane at a higher speed. The tow rope is to be attached to the front hook only.

NOTE: Before take-off at an airport where dirt may get into the cockpit close the ventilators. The ventilators can be opened during the climb. For take-offs close to o0 c and high humidity fu l ly open all venti lators to prevent condensation.

2. Winch-launching

CAUTION: Use either side hooks, or lower hook (depending wh ich hook is installed).

The flying technique is the same as with other models of sailplanes. The trim ta b contro l l ever shou ld be set in "zero" position. The recommended speed range is between 43 - 54 KIAS (80 - 100 km/h IAS). When performing the traffic pattern after winch launch or aerobatics, do not retract the landing gear.

(cont.)

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3. Aerotow

a)Climb

When safe height is reached retract the landing gear (unlock the handle and pu ll it to the rear) and lock it. Trim the sailplane for the c limb speed . The recommended tow speed is 59 · 70 KIAS (11 0 - 130 km/h IAS) . Aerotowing procedures are not different than normal techniques.

b)Level f li ght

Can be pe rfo rmed up to speed Vr = 76 KIAS (140 km/h IAS).

c)Descend ing

Nov 30/98

When descending on aerotow, observe the approved lim itations of this sailplane . As necessary, apply air b rakes or side slip to increase the vertical descent rate.

4 . 13

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4.5.3 FLIGHT

1. Turns and circling

Since the sailplane is very manoeuvreable and controllable, its behaviour is very good in tu rns with bank angles up to 60° .

2. Side slipping

The technique for the side slipping is entirely conventional. ·Moving the control stick to the left, we are performing left side slip; to maintain straight descent, apply almost full right rudder. The angle of bank of the sailplane will be between 1 o0

- 20°. The side slip as a means of increased rate of descent is effective only with simultaneous application of air brakes. The steady speed can be maintained by maintaining constant pitch angle. When performing slip manoeuvre, the airspeed readings are unreliable.

Fig. 4-4

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3. Intentional stalls

Slow and continuous pull ing aft on the control stick causes the sailplane to stal l. Ailerons and rudder should be used to control bank. Prior to stall , pre-stall buffet warning wil l be noted approximatelly 5 % higher than stall. At stal l, the nose p itch down below the horizon. To recovery from the stall move the control stick forward.

CAUTION: Before stalling, spinning and performing aerobatics the following important procedures must be completed:

Trim: "O" pos ition

Air brakes: retracted and secured

Cockpit canopy: locked and secured

ventilation: shut

U ncommended banking at stall must be corrected by releasing aft stick pressure and even pushing of the control stick forward with simultaneous application of opposite rudder.

4. Use of air brakes

The ai r brakes are to be used to avoid exceeding the VNE speed, i .e. :

a) at stall into an abnormal position, e.g. during aerobatics

b) when disoriented during c loud f lying

It is recommended to use the air brakes as a means for speed decrease in any case when the sailplane starts to increase its speed excessively and the pilot is uncertain of his orientation and how to manage the s ituation. Use oi air brakes will enhance the safety and wi!I make fly ing easier. The control lever should be held fi rmly during air brake extension, especially at high speeds.

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4.5.4 APPROACH

The following approach speeds are recommended tor approach-to-land:

Descent l Air brakes Approach speed

Normal retracted 40 - 46 KIAS (75 - 85 km/h IAS)

extended 43 - 49 KIAS {80 - 90 km/h IAS)

Steeper extended 49 - 59 KIAS (90 - 110 km/h IAS)

When using higher approach speeds, anticipate a longer landing distance.

4.5.5 LANDING

Landing on the airport

The land ing manoeuvre is entirely conventional. The recommended attitude for landing should allow the main gear wheel to touchdown before the tail wheel contacts the ground (to reduce shock to the tail wheel from uneven ground). Do not flare prematurely in order to prevent the sailplane from dropping from a higher height on the tail wheel.

Off-field landing

The p il ot must make a decision on the landing gear posi t ion. It is recommended to land with the landing gear retracted, if landing off-field on a soft ground. In this case , extend the landing gear on the ground prior to next take-off. The landing gear can be extended on ly when manually lifted. If need be , the take -off may be accomplished with retracted and secured landing gear.

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4.5.6 FLIGHT WITH WATER BALLAST

This sailplane does not have provisions for water ballast

4.5.7 HIGH ALTITUDE FLIGHT

For the high altitu de flight :

- monitor the never exceed speed VNE as a function of the altitude (see Section 2, item 2.2)

- an approved oxygen equipment must be installed

4.5.8 FLIGHT IN RAIN

Flight in rain has little effect on the pilot's view. Excessive moisture from pitot static system can be drained from the moisture trap. There are no rain induced airspeed errors.

4.5.9 AEROBATICS

The sailplane is <1ble to perform the approved aerobatic manoeuvres provided limitations contained in Section 2.2, 2.6 and 2. 7 are observed.

Instructions for performing the listed aerobatic manoeuvres are given on the following pages. ·

WARNING: DURING AN UNINTENDED TAIL SLIDE HOLD THE CONTROL STICK AFT AND THE AILERONS AND RUDER FIRMLY IN NEUTRAL POSITION (USE BOTH HANDS).

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1. Loop

Enter a moderate dive with slight forward movement of the control stick to gain the entry speed of 86 KIAS (160 km/h IAS) when flying solo, and a speed of 97 KIAS (180 km/h IAS) when flying dual. Raise the nose of the sail plane by slight backward movement of the control stick taking care to comply with "g-load" lim its. After reach ing the position "nose up", the control force drops slightly due to speed decrease. However, maintain the backward stick movement, but do not use more than about 60% of the control stick full deflection in the inverted position. Also the load factor must drop in the upper part of the loop arc. A fter passing the inverted position the speed will increase and the control stick must be eased s lightly so the flight path remains smooth. When beginning the loop , pay attention to precise directional control to avoid loop "diverting•.

86-97 KIAS

86- 97 KIAS (160 - 180 km/h IAS)

Fig.4 - 5

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2. Stall turn

This manoeuvre should be beg in at the speed of 92 KIAS (170 km/h IAS) when flying solo , or 97 KIAS (180 km/h IAS) when flying dual. Pull the control stick gently backward to bring the nose to a position of about 60° to 70° above the horizon. After reaching this angle ease the control stick slightly forward to assure straight climbing path. As soon as the speed fa lls to about 70 • 81 KIAS (130 - 150 km/h IAS), start to apply rudder slowly in the required direction of turn. As the force on the rudder decreases, gradually apply full rudder. Full deflection of the rudder should be reached when the sailplane heads about 45° in the direction of turn. At this moment also start to use ai lerons against the direct ion of stall turn which supports quicker turning and at the same time prevents sa i lp lane roll ing to the inverted position. When approaching the reciprocal heading with the nose down, neutralize the rudder, keep the wings level by use of the ailerons, and ease out of the resulting dive, taking care not to apply excessive "g" limits.

70-81 KIAS® \ (130 - 150 km/h IAS) . ~

~~~ ~ &

Nov 30/98

92-97 KIAS @ (170 - 180 km/h IAS)

Fig.4 · 6

4. 19

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3. Half loop and half roll

To perform this manoeuvre, select the entry speed rather higher than for the loop, i.e. about 103 - 113 KIAS (190 - 210 km/h IAS). Also, the sailplane must be raised in a more energetic way than at the loop. However, too violent backward movement of the control stick may cause unnecessary braking and subsequently loss of speed needed for the manoeuvre. As the inverted position is reached, move the pulled control stick gently forward to ach ieve almost gravity-free state of the sailplane. Then apply full ail eron so as to roll the sai lplane into the normal position. When the sailplane is banked by 90°, it is necessary to apply fu ll rudder deflection upwards to maintain the sai lplane nose in the horizon and to avoid sailplane turn . Contin ue rolling, pushing gently stick forward, so that the direction may remain constant without turn ing.

.l,k::=:;:::b>-- - --

~76KIAS ~ (140 km/h IAS)

t 103 - 113 KIAS © (190 - 210 km/h IAS)

~~

Fig. 4- 7

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4. Half rol l and half loop

To perform this manoeuvre, se lect the entry speed of 70 KIAS (130 km/h IAS). Raise the sailplane nose to a position of about 25° above the horizon . Ease the control stick forward to prevent the sailpla­ne to continue arc path , but to fly straight, and apply ailerons. When banking the aircraft, and in particu lar at an angle of bank exceeding 45°, support the slightly climbed attitude of the sailplane by applying top rudder (usually deflection 25 to 30% is enough). As bank increases beyond 90°, when the sailplane goes inverted, the rudder should be centra lized and the control stick moved forward in the way required so as to keep the orig inal fuselage attitude. After reaching the inverted posit ion, bring the ail erons into their orig inal posit ion, ease the control stick aft and begin slight pu lling it back, as in the second phase of the loop. We recommend to observe strictly the initial ai r speeds because at high speeds the sailplane reaches at half roll and half loop recovery a speed coming c lose to maximum permitted speed.

Nov 30/98

f;i\ 97 KIAS

~--~ {180 km/h IAS)

Fig. 4 - 8

4 - 21

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5. Lazy eight

(the manoeuvre consisting of two following steep turns).

Move the control stick slowly forward to attain the entry speed of 97 KIAS (180 km/h IAS), flown solo or dual. Perform a steep climbing turn to the selected side, smoothly pulling the control stick with simulta­neous coordinated use of ailerons and rudder. At a speed of 54 KIAS (100 km/h IAS) do transition of the sailplane to a descent and after reaching 97 KIAS (180 km/h IAS) perform the steep turn to the opposite side. smoothly pulling the control stick with simu ltaneous coordinated use of ailerons and rudder. The flight path intersects at the lowest point of the manoeuvre.

54 KIAS 97 KIAS

97 KIAS

(180 km/h IAS) /

©~ (100 km/h IAS)

(180 km/h IAS)

Fig.4 · 9

Nov 30/98 4. 22

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L13AC.1013.3

6. Inverted flight

We recommend to bring the sailplane into the inverted position through half roll, exactly in accordance with the procedure described in the first part of perform ing the half roll and half loop. A speed of 70 - 76 KIAS (130 - 140 km/h IAS) is recommended for inverted flight. It is recommended that a pilot lacking enough experience with flying sailpla­ne recovers from the inverted position by pushing the control stick forward, thus decreasing speed below 54 KIAS {1 oo km/h IAS), and the n pull it back as during the half roll and half loop. When recovering by means of a half roll , the speed should be slightly increased first to about 76 to 81 KIAS (140 km/ h - 150 km/ h IAS) , and then the nose raised to about 25° above the horizon and kept there. Then full aileron deflection should be applied. When banked vertically at 90°, it is necessary to apply full top rudder to maintain straight flight. As soon as the bank is less than 90° and the sailplane rolls into the level flight position, the sailplane shows tende ncy to turn. This should be overridden with full rudder and in particular by moving the stick forward.

Nov 30/98

70- 76 KIAS (130 - 140 km/h IAS)

~

~~ ici I l

~~=3~? \ \ . \ I '\ \J

Fig. 4 - 10

4 - 23

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c-·~ L-13 AC BLANIK M-~ SAILPLANE FLIGHT MANUAL Do-L13AC.1013.3

7. Slow roll

The slow roll is one of the most difficult aerobatic manoeuvres and therefore it should not be attempted urrtil the pilot is fully proficient in the half roll and half loop, half loop and half roll and inverted flight. After reach ing an entry speed of 92 KIAS (170 km/h IAS). ra ise the nose to a position of about 25° above the horizon, and ease the stick forward to keep straight-level flight. By applying full aileron deflection you will be inverting the sailplane. As the vertical bank position approaches and if the nose drops down, apply slightly top rudder deflection. If the beginning of the slow roll is performed correctly. it is not generally more than 25% of its full range. When banked vertically and when the sailplane is inverted, the control stick should be pushed forward to maintain the pitch. Keep the full aileron deflection. Quite a big top rudder deflection is to be applied again as the sailplane rolls once more into the normal position, mainly at bank of 90° to 45°, and tendency to turn should be overridden with the elevator down deflection. Usually the sailplane nose will be about 15° below the horizon when the slow roll is completed.

92 -97 KIAS (170 - 180 km/h IAS)

Fig. 4 - 11

Nov 30/98 4 - 24

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8. Spin

The sailplane performs the spin without any tendency to enter a f lat spin at all operating centre of gravity range. The sailplane has a tendency to recover from the spin by itself when at the forward centre of gravity. Entering the spin is entirely conventional. Pull the control stick slowly and smothly back to approach the stall, then use ful l deflection of the rudder at minimum speed of 35 KIAS (65 km/ h IAS ) - see Fig. 4-12 -and full aft deflection of the control stick. Before spin recovery bring the ailerons into neutral position. In itiate recovery from the spin by applying full opposite deflection of the rudder and easing the control stick forward . When the sailplane stops rotation, neutralize the rudder. Recover the sailplane from the dive in the usual way. The attitude during the spin is 60° - 70° nose down and the loss of height in one turn is approximately 260 ft (80 m) when flying solo, and 400 ft (120 m) in one turn when f lying dual. The time of one revolution of the spin is appro­ximately 3.5 sec .

CAUTION:

Nov 30/98

1. Before spinning accomplish the important procedures given in the flight manual, section 4, paragraph 4.2.

2. IAS error The airspeed indications become erroneous at large yaw angles because the static vents on the sides of the fuselage are by-passed asymetrically.

4- 25

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L-13 AC BLANIK S AILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

min. 35 KIAS (65 km/h IAS)

)) © 43 -54 KIAS

(80 - 100 km/ h IAS)

~76 -86 KIAS ~ (140 -160 km/h IAS)

~-Fig.4 - 12

Nov 30/98 4 - 26

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L- 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

9. Chandelle (cl imbing)

Move the control stick slowly forward to attain the entry speed of 97 -103 KIAS (180-190 km/ h IAS) when flown solo or dual. Do transition of the sailplane to a steep climb at an angle of approximately 45° above the horizon by pulling back the stick smoothly and continuously (do not increase the angle) . At a speed of 76 KIAS (140 km IAS) apply the rudder to the selected side of the turn and by coordinated pos itive use of the ailerons make a transition to gliding f light in the opposite direction at a min imum speed of 43 KIAS (80 km/ h IAS).

43 KIAS (80 km/h IAS)

76 KIAS ~ ' (140 km/h IAS)

\© 97 - 103 KIAS (180 - 190 km/h IAS)

® ~~

Fig.4 · 13

Nov 30/98 4 . 27

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,

L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L1 3AC.1013. 3

10. Steep turn

To perform this manoeuvre, keep th e entry speed o f 92 KIAS(1 70 km/h IAS) when flying solo, or 97 KIAS (180 km/h IAS) when flying dual. Enter the climb simultaneously with a bank of approximately 45°. After turning by about 150° start transition to gliding flig ht so that the manoeuvre will be finished in the opposite direct ion with the speed not decreasing below 43 KIAS (80 km/h IAS).

~43 KIAS ~ (80 km/h IAS)

~~

~/ --~-..--~ 92 - 97 KIAS

~ (170 - 180 km/h IAS)

Fig.4 - 14

Nov 30/98 4 - 28

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L-13AC BLANIK SAILPLANE FLIGHT MANUAL Do-L13AC. 1013.3

11.Flick roll

To perform this manoeuvre, select the entry speed of 70 KIAS (130 km/ h IAS ). while the sailplane nose is approximately 15° below the horizon. Pull vigorous ly the control stick (about 1 s) and immediately afterwards apply full rudder. As soon as the sailplane starts rolling, apply immediately the aileron deflection in the direction of rotation. The flick roll is finished by neutralizing controls.

65 • 70 KIAS (120 - 130 km/h IAS)

Fig.4 - 15

Nov 30/98 4 - 29

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

12. Flick half roll and half loop

To perform this manoeuvre, select the entry speed of 51 KIAS (95 km/h IAS). Energetically pu ll back the control stick fully (0.5 - 1 s). Immediately afterwards apply ful l rudder. The sailplane starts to rotate at increasing descent. Approximately at an angle of 45° before reaching the inverted flight centrali se the rudder with maintaining the control stick fully back. Ease the stick gently forward before reaching the level flight. The speed should not exceed 65 KIAS (120 km/h IAS). The whole manoeuvre is performed within design manoeuvring speed, therefore full deflections may be used vigorously.

65 KIAS (120 km/h IAS)

Fig.4 - 16

Nov 30/98 4 -30

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

Section 5

Performance

Contents

5. 1 Introduction

5.2 Approved Data

5.2.1 Airspeed Indicator System Cal ibratio n

5.2.2 Stall Speeds

5 .3 Non-approved Further Information

5.3. 1 Demonstrated Crosswind Performance

5. 3 . 2 Flight Polars

Nov 30/98 5 - 1

/

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1 0 13 .3

5.1 INTRODUCTION

Section 5 p rovides approved data for airspeed cali bration and stal l speeds and non-approved further information fro m the Manufacturer.

5.2 APPROVED DATA

5.2.1 Airspeed indicator system calibration

The diagram is effective fo r maximum flight weight of 1100 lb (500 kg) .

(/)

< 0 160

f/) £ < -- 150 OE ~ 7140 u Ql Q)

0.

"' .... ~ 'O Q)

iii .... .D

iO ()

130

120

110

100

90

80

70

60

50

40

30

280

240

200

160

120

80

20 40

10

0

Nov 30/98

actual speed calculated speed

\ '\ ' '\ I/

I'\ ,,.. \ I'\. ' V

I\. 'V vv

\ v v vv

- vv [) v ·- - - - - - ·- ~ I? --

/ / / /

- /

. I

II V,

v, /

ii/ ~

: ~ ~

/ /

/

v 0 40 80 120 160 200 240 280

0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160

Flight speed - km/h IAS - KIAS

Fig . 5 -1

5 -2

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L- 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do -L 13AC .1013.3

5 .1 INTRODUCTION

Section 5 provides approved data for airspeed calibrat ion and stall speeds and non-approved further information from the Manufacturer.

5.2 APPROVED DATA

5.2.1 Airspeed indicator system calibration

The diagram is effective for maximum fl ight weight of 1 102 lb (500 kg) .

(/)

< 0 160

r.tJ I:. <--150 OE

280

~ ~ 14-0 . ' u 130 240 «> «> a. 120

"' ~ < 110 200 u ~ 100 co ... 90 .D 160 = co 80 (.)

70 120

60

50

40 80

30

20 40

10

0

Nov 30/98

actual speed calculated speed

\ '\ I \ ' v

I'\. I.I". I \ "' " V I fC ... v I vv

I \ VI /

1/ V I I f/ 7

I I I "V I I I I/

I / f I / /

I I /

v I I I //

I I V/ I I / I

I I ti I I 1,.

I ''· I I I l~ I I . ~

I I ,.,,, I I I I/ I I

I I/ I 1,1 1 I I I

-; I I I / 1 I I I I I I I

0 80 120 160 200 240 280

0 10 2~ 30 40 50 60 70 80 so 100 110 120 130 140 15-0 160

Fig. 5 - 1

Flight speed · km/h IAS - KIAS

5 -2

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L- 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do- L13AC.1013.3

5.2.2 Stall speeds

Stall speed versus f light weight re lationship is shown in Fig. 5-2. The figure is valid for wing span 46.59 ft (14.2 m).

CAUTION:

(/)

~ 70 (/) .c. < ....... -E ~ .;;;{.

"O 35

Q) Q) _..-0.. (/)

60 2 (/) ....-

30

50

25

40

The stall warning speed Is for all configurations (in Fig. 5·2) 2 • 3 KIAS (4 • 6 km/ h IAS) higher than stall speed.

/ / '

/ " / ~

/ ...... f ~V

~·-/ /_..--· !.--.... Air brakes extended

.Yr --n Air brakes retracted

I 380 400 420 440 460 480 500 Weight - kg

$00 1000 1100 Weight - lb

Fig. 5-2

Nov 30/98 5 - 3

Page 60: SAILPLANE FLIGHT MANUAL - Puget Sound Soaring … -13 AC BLANIK SAILPLANE FLIGHT MANUAL Do -L1 3AC .1013 3 1.1 INTRODUCTION This Flight Manual contains the instructions, performance

/'"""'\

L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

~~~~~~~~~_.:;....:..;.::;:..:_:;:..:_:...:..=_:__:::..:....:.:__:.....:..;.:....:..;.::...::...c.=...~~~;._;;__:.__;~~..:...._ • • ~

5.3. Non-approved further Information

5.3.1 Demonstrated crosswind performance

Maximum demonstrated crosswind component is shown in the Sect. 2 i tem 2 .14 .

5.3.2 Flight speed polar

Maximum flight weight of 1100 lb (500 kg) .

Airspeed - KIAS - km/h IAS

0 10 20 30 40 50 60 70 80 90 100 •·

0 0

20 40 60 80 100 120 140 160 180 200 -- . l I I I I -~ ~ air brakes retracted -

-1 ' - ~ landing gear retracted

....... - ./ r--..... / "-... ~ - 300 '

Q)

a. (/)

co (!)

.... '.)

>

·2 r-...

- 600 -3

-4

-900 -5

-6 • 1,200

-7

Fig.5 - 3

Nov30/98

"f"... '!'-.

' -I\.

\

\ I\

\

5 - 4

Page 61: SAILPLANE FLIGHT MANUAL - Puget Sound Soaring … -13 AC BLANIK SAILPLANE FLIGHT MANUAL Do -L1 3AC .1013 3 1.1 INTRODUCTION This Flight Manual contains the instructions, performance

c El/)

L-13 AC BLANiK SAILPLANE FLIGHT MANUAL Do -L 13AC. 1013 .3

5.3 Non-approved further Information

5.3.1 Demonstrated crosswind performance

5.3.2

M,aximum demonstrated crosswind component is shown in the Sect. 2 item 2.14.

Flight speed polar .., 1

Maximum fl ight weight of 110 2 lb (500 kg). '"' ' ~ /

0

0 0 ~

10

20

20

40

30 , 60

/ .. " c ·I"

I' 4S 50 60 70

'

80 100 120

80 '

140

Airspeed - KIAS ·km/h IAS

90 100 I

160 180 200

. I I I I I air brakes retracted -

I • landing gear retracted ......... v

..............

.:: E -1 . "O Q) Cl> a. I/)

(I)

.~ .. Q)

>

-300 ·2

• 600 -3

-4

• 900 -5

• 1,200

·7 I

Fig.5 · 3

Nov 30/98

t"'-.... /

"-re.... ...,

!'.. 'I\.

' '\. \

\. I\

\

I

5 - 4

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~ L-13 AC BLANIK An AVfOS Compony SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

Section 6

Sailplane Weights and Balance

CONTENTS

6 .1 Introduction

6.2 Weigh ing Record

6.3 Basic Empty Weight and Moment

6.4 Balance Chart

6.5 Equipment List

6.6 Balance Record

Nov 30/98 6 . 1

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L - 13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

6.1 INTRODUCTION

Sect ion 6 describes procedures to check flight weight and balance of loaded L - 13 AC BLANiK sailplane (pilots, ·baggage , optional equipment).

6.2 W EIG H ING RECORD

Weight record including procedure for calculating centre of gravity position is given on page 6-5.

6.3 BASIC EMPTY WE IG HT ANO MOMENT

,,.--... Sailplane empty weight, equiped with needed instruments(see page 6-6) . . . 672 lb(305 kg) : 2%

Moment to the reference plane . . . . . . 18,371.34 in-lb (211.670 kgm)

True values of sailplane empty weight are provided in the table on page 6-8.

6.4 BALANCE CHART (FIG. 6· 1)

1. Balance chart description

The varying load scales are in the upper part of the chart. One division of every scale corresponds to the value given in the column on the left and is marked with an arrow indicating direction of progress in chart.

The chart of the centre-of-g ravity vs. sailp lane weight is given in the bottom part. The region of non-allowable centre of gravity range is horizontally hatched and relates to all flight conditions.

2. Directions for the balance chart use

See FIG.6-1 on Page 6-4, Line 0 .

. Make a dot on the Empty Sailplane Center of Gravi ty Range corresponding with the value shown on the Balance Record on page 6 · 5. Draw a vert ical down to Line 1. The intersection of the vertical and Line 1 is Point A .

. Next, use Scale 1 at the top of the char.t. Measure the distance from O on that scale to a number corresponding with the weight of the front pilot + parachute + ballast seat (if used). Transfer th is distance from Point A to the left, draw a vertical, and mark the intersection with Line 2 as Point B.

(cont.)

Nov 30/98 6-2

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

. Next , use Scale 2. Measure the distance from O on that scale to a number corresponding with the weight of the rear pilot + parachute. Transfer this distance from Point B to the left, draw a vertical, and mark the inte rsection with Line 3 as Point C .

. Next, use Scale 3 for any changes i.n the front instrument panel. Measure the distance from 0 on that scale to a number corresponding with the weight of any instrument added or removed. Transfer this distance from Point C to the left (if an instrument is added) , to the right (if removed). Draw a vertical , and mark the intersection with Line 4 as Point D .

. Next, use Scafe 4 for any changes in the rear instrument panel in the same fashion as in the previous paragraph. That is how you arrive at point E. Draw a vertical on down to the lower part o f the chart .

. Now, use the weight scale on the lower left part of the balance chart. Mark the sum of al l weights: Empty sailp lane + front pi lot + parachute +ballast seat + rear pilot + parachute + instrument changes + baggage .

. Draw a hor izontal line from the mark to th e right . The center of gravity position is at the intersection of this horizontal line with t he vertical from Po int E .

. If this intersection is inside the s lanted shape, the glider is loaded correct ly. If the intersection is outs ide , the glider has to be reloaded .

Note: The baggage weight is to include any battery , oxygen bot tle, wate r bot tle etc. Items in the baggage compartment have no influence on the cent re of gravity position .but they must be included to th e sum of all the weights.

(cont. )

Nov 30/98 6-3

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~~--~ L-13 AC BLANIK AAAytCl COmpony SAILPLANE FLIGHT MANUAL Do - L 13AC.1013.3

Balance chart:

300 250 200 150 100 ·50 0 Scale 1 lb

300 200 100

Scale 2 lb 30 10

Scale 3 lb 10

Scale 4 lb

~ 65.S

EMPTY SAILPLANE CENTER OF GRAVITY RANGE 62 70

Line 0

Froot Pilol + par<ll'hute +seat balast 300 250 200 150 100 50 Line 1

Rear Pi iot + p .. uachute 300 200 100 A line 2

Front instrument panel change' 30 10 line 3

Rea r Instrument p.anet chano es 10 Line 4

line 5 Bagoaoe A ft or rear pilot seat • no lnnuenc.e

E on centre ot g ravrty po11t>on

Weight lb

23 38

Fig. 6 - 1

Nov 30/98 6 - 4

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4/18/2001

N213TA Weight and Balance

" Weight Arm Moment

Beginning 691.80 27.43 18,976.07

Add

Radio 1.25 -23.0" -28.75

Frt Mic .so -45.0" -22.50

Rr Mic .so - 5.0" - 2.50

Batteries 9.60 20.0" 192.00

New Totals 703.65 27.17 19,116.82

MAC=65.18% Empty Sailplane -·

P.O. Dox 869 675 Airport Road Driggs, ID 83422 Phone 208-354-3100 Fax 208-354-3200

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L- 13 AC BLANiK SAILPLANE FLIGHT MANUAL Do - L13AC.1013.3

Mass and balance record

ill

Type L • 13 AC BLANiK

Manufactured by LET, a.s. KUNOVICE

Serial number Ot?J'~ O,b Registration mark N 2-t/3Tf/

The sailplane weighed on supports. All dimensions are in inches. The landing gear extended.

A. Values obtained by weighing:

Weights [lb] Dimensions

gross tare net

R1 J2.6 f; Xl = 22.32 in

R2 16£/J X2 = 185.83 in

B. Values obtained by calculation: centre of gravity position of the empty sailplane

a/ relative to the reference plane b/ relative to then mean aerodynamic chord

R2 x 185.83 - R1 x 22.32 (XL + 6. 14) X 100% XL = GL

XT = 51.102

XL = £9-11/-U;> in XT = 6~Gi7 %MAC

The centre of gravity position of the empty sai lplane calculated in Part B meets the type sailplane specification, and makes it possible to achieve the required operational (flight) centre of gravity range from 23 and 38 % MAC. The centre ol gravity of empty sailplane have to be 65.5 ± 1% MAC. The operating centre of gravity calculation is carried out according to paragraph 6.4 of this Flight Manual.

Kunovice - Date

Nov 30/98 6 - 5

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L-13 AC BLANIK SAILPLANE FLIGHT MAN.UAL Do - L 13AC.1013.3

,--... 6.5 EQUIPMENT LIST

Items marked with an "X' letter are included in the empty weight standard equipped sai lp lane (see item 6.4).

A s I Subject Type Wegrr Arm from the

I b reference datum

(.l<g) (rib No. 1) in(mm)

!Altimeter UI 5934P-3 0.84 ·69.8(-1773.5) x

front instr.panel I (0.38) I -21.8(-553.5) I ' rear insir.panei

x Airspeed LUN 1106.14·8 0.88 -69.9(-1775.5)

indicator front instr.panel (0.40) -21 .9(-555.5) rear instr.panel

x JElectric LUN 1211 .1 0.79 -69.9(-1775.5) turn-and- front instr.panel (0.36) -21 .9(-555.5) I bank/ side rear instr.panel indicator

I

x !Vertical speed LUN 1141.04 1.06 -70.4(-1788.5) I indicator front instr.panel (0.48) -22.4(-568.5)

:t 10 knots rear instr.panel

I x Vertical speed LUN 1147.23·8 1.10 -69.6(-1768.5)

indicator front instr.panel (0.50) ~ 60 knots

I x jMagnetic LUN 1221.1-8 0.23 -69.5(-1 766.5) ,compass i front instr .panel (0.105) -21 . ~(-546.5)

'rear instr.panel

x Accelero- AM 10 0.55 -66.1 (-1 680)

meter front instr.panel (0.25) -21 .9(-555.5) rear instr.panel

A: standard

B: non-s tandard

(con t.)

Nov 30/98 6-6

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L -13 AC BLANIK SAILPLANE FLIGHT MANUAL Do - l13AC.1013.3

A B Subject Type Wfil;;#. Arm from the b reference datum

(kg) (rib No. 1) in(mm)

x Side hooks A 001 023 L 0.99 -0.6(-16) A 001 023 P (0.45)

x Cable Tube 0.26 -0.6(-16) protection (0.12)

x Transceiver unit

x Paint Polyuretan 18.74 40.9(1038) (8.5)

A: standard

B: non-standard

Nov 30/98 6 - 7

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) ) ) )

z Q

§ co

It is valid for ser. No. . . . . . . • . . . . . . . . . • . .

Permitted rew and baggage weight with (lb) [kg): Empty Approved weight C.G. Max.baggage weight 221b(1 O kg) Half baggage 11 lb(5 kg) No baggage O lb(O kg)

No.: lb pos.

C1>

l~ Oi OJ )> j r )> z (') m

(kg) %MAC Front seat Rear seat Front seat Rear seat Front seat Rear seat Date Signed

::tl m (')

Max. Min. Max. Min. Max. Min. Max. Min. Max. Min. Max. Min. 0 :Il

1.

~: (dqp_ ~f',6l ~so 451 / / gso l!J£r! '"'/ / !.IlD tf9f ./ / 9.0:~ 1.P~o

-- - - -·----·

2.

~: r;-qp_ 6J./66 2.50 / 1J.6 / 2J;O / 1r+ / 2£'0 / ,f5!> / :;..6. ~ il.P l fJ

----------3.

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do -L 13AC .1G13.3

Section 7

Sailplane and Systems Description

CONTENTS

7.1 Introduction

7.2 Cockpit Control

7.3 instrument Panel

7.4 Landing Gear System

7.5 Seats and Safety Harness

7.6 Pitot and Static Sytem

7.7 Air Brake System

7.8 Baggage Compartment

7.9 Water Balast System

7.10 Not used

7.11 Not used

7.12 Electrical System

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7.1 INTRODUCTION

Section 7 describes sailplane, its operation and systems. Dupl icity data are not shown.

The detailed description and operation of the sailplane and its systems is given in the Maintenance Manual of the L - 13 AC BLANIK sailplane.

7.2 COCKPIT CONTROLS

See item 7.3

7.3 INSTRUMENT PANEL

The front and rear cockpit with instrument panels, instruments and contro l elements is represented schematicaly in this item.

See Fig. 7-1 and 7-2.

(cont.)

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L-13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC .101 3.3

7.3.1 FRONT COCKPIT. valid from ser. No. 008606

Fig. 7 - 1

(1) Control column, (2) Rudder pedals, (3) Airbrake handle, (4) Elevator trim handle, (5) Wheel brake handle, (6) Landin g gear hand le. (7) Rope re lease mechanism, (8) Rudder pedals adjustment, (9) Cockpit canopy opening handle, (10) Handle for emergency cockpit canopy jettison, (11) Vent handle, (12) Turn-and -bank indicator switch, {13) Altimeter, (14) Airspeed ind icato r, (1 5) Turn -and -bank indicator, (16) Compass, (17) and (18) Vertical speed indicators, (19) Label "Canopy lift off ", (20) Label "Air brakes extended". (21 ) Label "Air brakes retracted", (22) Label "Elevator trim control ", {23) Label "Wheel brake", {24) Label "No smoking•, (25) Label "Tow release•, (26) Label "Max. airspeeds", {27) Identification number, (28) Label "TURN-AND-BANK INDICATOR", (29) Accelerometer, (30) Label "Air vent•, (3 1) Label "Landing gear extended", (32) Label "Landing gear retracted", (33) Label "Adjustment of pedals". (34) Label "Min. pilot weight ", (35) Label •canopy jettison", (36)Label ' Max. alowable speed vs altitude", (37) Label "Seat posit ion", (38)Label "Approved manoeuvres", (39) Transceiver control button (opt ional), (40) Battery for turn-and-bank Indicator (opt ional), (41) Microphone (optional), (42) Positional pin for landi ng gear In extended and locked position (the landing gear handle must be located in front of the posit ional pin in flight di rection).

(43)Label "Max. airspeeds" , (44) Deviation plate, (45) Label "Center of gravity range".

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7.3.2 REAR COCKPIT - valid from ser. No. 008606

r' Fig. 7 · 2

(1) Control column, (2) Rudder pedals, (3) Airbrake handle, (4) Elevator trim handle, (5) Wheel brake handle, (6) Landing gear handle, (7) Rope release mechanism, (8) Cockpit canopy opening handle, (9) Transceiver control button (optlonal) , (10) Handle for emergency cockpit canopy jettison. (11) Battery for turn-and-bank Indicator (optional), (1 2)Turn-and-bank indicator switch. (13) Altimeter , (14) Airspeed indicator, (15) Turn-and-bank indicator, (16) Compass, (17) Vertical speed indicator, (18) Microphone (opt ional) , { 19) Label "Air brakes extended" (20) Label "Air brakes retracted". (21 ) Label •Canopy lift off" , (22) Label ' Elevator trim control• , (23) Label "Wheel brake", (24) Label "No smoking• , (25) Label "Tow rel ease• , (26) Label •Max. airspeeds", (27) Identification number, (28) Label "TURN-AND-BANK INDICATOR",

(29) Accelerometer. (30) Label "Canopy jettison•, (31) Label "Max. alowable speed vs --.. alti tude". (32) Label "Approved Manoeuvres ", (33) Label"Landing gear extended",

(34) Label "Landing gear retracted", (35)Posit ional pin ior landing gear in extended and tocked position (the landing gear handle must be located in front of the positional pin in flight direction), (36) Deviation plate, (37) Label "Max. airspeeds", (38) Label "Center of gravity range•.

Nov30/98 7-4

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7.4 LANDING GEAR SYSTEM

See item 1.4.1 of th is f light manual for desc.ription and using of the landing gear.

7.5 SEATS AND SAFETY HARNESS

The front and rear cockpit is equipped with seats with the back -rests and safety harnesses. The front seat is put freely on the floor, the rear seat is attached to the floor by means of the locks. The front back-rest is adjustable (see Fig.7-3, v iew P) - it is attached on the bottom into one of four positions by means of the positioning mechan ism - it is continuously adjustable in the upper part by means of the strap (10) which is attached by the bolt w ith washers on the left s ide and by the shortening device (18) on the right side of the frame. The rearback-rest is fixed attached to the floor on the bottom, it is fo lding in the upper part for the acces into the baggage compartment and locked with the lock to the frame No.5. The ins tallation and d ismantling of the seat w ith the load is mentioned on the next page.

@]

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Fig . 7-3

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v

(1) Front seat, (2) Front back -rest, (3) Safety harnesses, (4) Rear seat , (5) Rear back-rest , (6) Lock , (7) Gu iding , (8) Positioning mechanism, (9) Con trol levers of positioning mechanism, (10) Strap, (11) Attaching eye - optional , (12) Lock , (13) Bolt with washers, (14) Bolt w ith nut , (15) Cushion - optional , (16) Rest - opt ional. (17) Attaching eye - optional, (18) Sho rteni ng device

Nov30/98 7 - 5

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~!~ L-13 AC BLANIK M AyosCOmoonl<

SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

A. Seat installation, Fig. 7-4

1. Disassemble and remove the seat from the front cockpit.

2. Put the seat with ballast (pos.1) into the free space and insert stirrups (pos. 2) in the rear part of the seat into the chamber on the rest suspender.

3. Move the levers (pos.3) on the seat sides upwards (pawls will shift in the seat face) and fold the seat (pos. 1) to the floor.

4. Move the levers (pos. 3) downwards, the pawls will shift out of the seat by this and they must shift into the holes on the floor frame (if the pawls do not shift in the holes. move the seat to both s ides to enable shift ing of the pawls in the holes).

B. Seat removal

Removal is to be carried out in a reverse order to installation .

Fig . 7-4

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7.6 PITOT STATIC SYSTEM

5

8

\_

~ Fig. 7-5 (1) Airspeed indicator , (2) Alt imeter, (3)Vertical speed indicato r , (4) Vert ical speed ind icator. (5) Total pressure tube , (6) Static pressure sensors, (7) Compensated pressu re tube , (8) Moisture trap

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7.7 AIR BRAKES

The air brakes of DFS .type are , w ith the ir attachments, overhung -mounted in th ewing into the ribs No. 15 and 17. They are flush w ith the wing surface in closed posit ion. The structure of the air brake upper and lower is sim ilar. The skeleton consist of the steel tube w ith welded-on sheet ribs on a strap of duralumin sheet is riveted with f lush rivets. The edges of the strap are stiffered w ith longitudal stiffener. With the air brakes retracted the tie rod of' air brakes control is set to the neutral posit ion in re lation to the double-armed lever . It is possible too complete ly exclude the suction of the upper air brake during fl ight by adjust ing both tie - rods without any a of the forces in the control mechanism. The air brake is secured in the open position with a stop.

Air brakes are extended or retracted by sh ifting of the lever on the cockpit left side (see Fig.7-1 and 7-2).

Air brakes using during f light is described in this flight manual on the page 4-15, item 4 .5 .3 .

7.8 BAGGAGE COMPARTMENT

Two baggage compartments are formed between 5th and 6th frame. The lower baggage compartment is provided w ith the net for attaching of the baggage on the requirement of the customer.

The acces into the baggage compartment is ensured by unlock ing of the back-rest lock and its folding.

Baggage mass and area for puling is shown on the placards (see Fig. 7-6).

Fig . 7-6

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7.9 WATER BALAST SYSTEM

This sailplane does not have provisions for water ballast.

7.10 Not used

7.11 Notused

7.12 ELECTRICAL SYSTEM

See item 7.10.

L - 13 AC BLANIK sailplane has electrical turn-and-bank indicators on the front and rear instrument panel.

Wiring diagram of LU N 1211 . 1 turn-and-bank indicator :

A - on the sailplanes with the connection through the voltage regulator type of 12/4.5 Vss and on the board battery of 12 V

B - on the sailplanes with the con nec tion on the battery of 4.5 Vss 4 3

5

6

Fig. 7-7 (1) Turn-and-bank indicator. (2) Voltage regulator type of 12/4.5 v DC. (3) Switch, (4) Connecting block, (S) Board battery - optional , (6) Battery of 4.5 V DC

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L - ·13 AC BLANIK SAILPLANE FLIGHT MANUAL Do-L 13AC.1013.3

Section 8

Sailplane Handling, Care and Maintenance

CONTENTS

8.1 Introduction

8.2 Sailplane Inspection Period

8.3 Sailplane Alternation or Repairs

8.4 Ground Handling/Road Transport

8.5 Cleaning and Care

-

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8.1 INTRODUCTION

Procedures recommended by the Manufacturer tor proper ground handling, service and maintenance which must be observed in order to maintain the same performance and dependability of the sailplane as that on of a new sailplane are provided in Maintenance Manual of the L - 13 AC BLANIK (Do-L13AC-1032.3).

8.2 SAILPLANE INSPECTION PERIODS

Inspections and maintenance of the sailplane consist of operational and periodical maintenance.

Operational inspections:

- preflight inspections

- daily inspections (after each flight day)

Operational inspections scope is mentioned in this flight manual , items 4.3 and 4.4.

Periodical inspections intervals and scope - see Maint enance Manual item 2.2.3 - Periodical maintenance

8.3 SAILPLANE ALTERNATIONS OR REPAIRS

Before each sailplane alternation contact appropriate CAA to ensure adequate leve l of operation .

Instruments and aggregates which were recognized as disable for the further operation, can be replaced only by the same type of the instruments {aggregates) and they must be tested before mounting on the sailplane.

Common sailplane repaires are mentioned in the Maintenance Manual in the end of the relevant chapters.

Work procedures which can be done by the operator are mentioned in the Maintenance Manual, chapter 11 - Repairs. It includes repairs of the skin, deformed or broken stringers , parts of th e ribs and frames, small faults of fabric s k in and instrument install ation fai lures.

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8.4 GROUND HANDLING/ ROAD TRANSPORT

a) Towing of sailplane

Carry out the towing of sailplane behind the trolley by means of aerotowing cable. It is necessary to hold the wing tip during the sailp lane towing. The aerotowing cable is modified for the connection to the front attachment and it is secured with the safety pin. Since the aerotowing cable has a considerable lenght, it is possible to shorten it by means of a loop.

b) Parking

The following ground equipment is intended for securing of the sai lplane during the parking:

- blocking fork for controls blocking (optional), blocking is performed in the rear cockpit

- plug of the sensor of compensated pressure

- cockpit cove r

For more details see Maintenance Manual, item 3.1 o.

c) Mooring

If the sailplane is to be parked out of hangar, it is to be moored to prevent its damage in the event of a strong wind.

The following equipment is intended for sailplane mooring:

- 4 mooring eyes (screws), 3 mooring ropes (optional)

- 2 mooring eyes to wing

For more details see Maintenance Manual, item 3.11.

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'

~·~ L - 13 AC BLANIK An Ay.cs Compony

SAILPLANE FLIGHT MANUAL Do -L 13AC.1013.3

3

2

Fig. 8-1

(1) Mooring rope, (2) Mooring eye (screw), (3) Mooring eye on wing

8.5 CLEANING AND CARE

Keep the sailplanes in c leaness. wash the sordid p laces . Give the special attention to the glasses of the cockpit canopy and aft cockpit canopy and to the glases of left and right side windows.

- The cockpit canopy is made of plexiglass , remove the soil (powder, mud etc.) with wet soft cloth or with bucksin, polish the glases with clean flannel rag after cleaning

CAUTION: It is prohibited to use the lacquer thinners, petrol, benzol , alcohol, turpentine, nitrolacquers and the agents containing the silicon oil.

- Wash the soil on the outer painted surface with detergent water and consecutively polish the surface.

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QI'!~ L - 13 AC BLANIK ""-Con"-.. SAILPLANE FLIGHT MANUAL Do - L13AC .1013.3

Section 9

Supplements

Contents

9.1 Introduction

9.2 List of Inserted Supplements

9 .3 Supplements Inserted

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9.1 INTRODUCTION

Section 9 of this Sailplane Flight Manual provides supplemental information for optional equipment which is installed on the sailplane and additionaly it may contain the supplementary information on sailplane operation.

The information contained in this document supplements or superseds the basic Sailp lane Flight Manual where covered in the sections contained herein. For lim itations, procedures and performance not contained in this supplement, consu lt the basic Sailplane Flight Manual.

_..--.._ 9.2 LIST OF INSERTED SUPPLEMENTS

Date of 'Doc. No. Title of inserted supplement insertion

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