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LET L-23 Super Blanik, Flight Manual

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LET L-23 Super Blanik Flight Manual Download Page 34

L 23 SUPER  - BLANIK

686 04 KUNOVICE

CZECH REPUBLIC

SAILPLANE FLIGHT MANUAL

Do  - L 23. 1012.5

4.3.2 BEFORE TAKE-OFF CHECKLIST

Front seat

Before entering the front cockpit, adjust the front seat back-rest to a

position allowing control of the sailplane when fully strapped in.

udder control

The position of the rudder pedals should be adjusted with the pilot fully
strapped in so that both left and right pedals can be moved comfortably
to the full extent of their travel. The position of the rudder pedals in the
front cockpit can be adjusted by means of the crank. In the rear cockpit,
adjustment to one of three possible positions may be obtained by

removing the locking pin.
Note:

This can be done only before the flight.

Control column

Check for full and free movement of the control column in all directions;
move it to the left, to the  right, forwards  and backwards.

Instruments

Set the altimeters to zero or as desired by the baro-set knob. Check the
other instruments and see that vertical speed indicators and airspeed
indicators read zero.

ockpit   canopy

Close and lock.

Safety  belts

Fasten the safety belts.

Trim

Set the elevator trim tab to the neutral position marked  "0"   .

Air brakes

Check for easy movement of air brake control. Confirm air brakes
retracted for take off.

Tow rope release

Check the tow rope release mechanism for proper functioning.

Appr.

Dec   1/93

4 - 8

Summary of Contents for L-23 Super Blanik

Page 1: ...egistered sailplanes in accordance with provision of 14 CFR Part 21 29 and as reguired by FAA Type Certificate Data Sheet No G60EU Approved byTheCivil Aviation Inspectorate ofTheCzech Republic in Prague Signature 7 Authority CAI Prague Stamp Original date of approval December 6 1993 I This Sailplane Flight Manual must be carried in the sailplane at all times This sailplane is to be operated in com...

Page 2: ...e existing pages with revised and effective ones Revised or amended parts of the text will be indicated by a vertical line in the left hand margin and the revision No and the date will be shown on the bottom left hand of the page Rev No 1 Affected Section 0 2 6 7 4 Not affected Affected pages Date 0 l 0 3 2 5 2 10 2 11 6 5 6 6 6 7 7 1 7 4 7 5 Dec 20 95 0 1 0 3 1 1 1 3 1 4 1 5 2 10 2 11 3 1 3 2 3 3...

Page 3: ...SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 Rev Affected Affected pages No Section Date Bulletin No Date of Bulletin approval Date inserted and signature Dec 1 933 0 2 ...

Page 4: ...ied as Appr provide information reguired to be furnished by the Federal Aviation Regulations Section 0 Page Date 1 Jan 13 99 2 Dec 1 93 3 Jan 13 99 4 Jan 13 99 Section 4 Page Appr 15 Appr 16 Appr 17 Appr 18 Appr 19 Appr 20 Appr 21 Appr 22 Date Dec 1 93 Dec 1 93 Dec 1 93 Dec1 93 Dec 1 93 Dec 1 93 Dec 1 93 Dec 1 93 Jan 13 99 0 0 3 ...

Page 5: ...es Performance Weight and balance Sailplane and systems description Sailplane handling care and maintenance I Supplements a non approved section an approved section an approved section an approved section a partly approved section a non approved section a non approved section a non approved section a partly approved section Section 1 2 3 4 5 6 7 8 9 Jan 13 99 0 0 4 ...

Page 6: ...ANE FLIGHT MANUAL Do L 23 1012 5 SECTION 1 General CONTENTS 1 1 Introduction 1 2 Certification basis 1 3 Warnings cautions and notes 1 4 Descriptive data 1 5 1 Three view drawing to ser No xx 8320 1 5 2 Three view drawing from ser No 96 8401 Oct 30 96 0 1 1 ...

Page 7: ...l Aviation Inspectorate of the Czech Republic in accordance with JAR 22 Change 4 issued April 1 1980 including Amendment 22 86 1 Eff Oct 22 1986 and AC 21 17 2 1 3 WARNINGS CAUTIONS AND NOTES The following definitions apply to warnings cautions and notes used in the Flight Manual WARNING MEANS THAT THE NON OBSERVATION OF THE CORRESPONDING PROCEDURE LEADS TO AN IMMEDIATE OR IMPORTANT DEGRADATION OF...

Page 8: ... Basic dimensions Wing span 53 15 ft 16 2 m with the installed wing tip extensions 59 71 ft 18 2 m Note If the wing tip with supporting wheel is installed wing span is 53 35 ft 16 26 m Length 27 89 ft 8 5 m Height 6 23 ft l 9 m Wing area 206 13 sq ft 19 15 sq m with the installed wing tip extensions 215 27 sq ft 20 00sq m Aspect ratio 13 7 with the installed wing tip extensions 16 6 Mean aerodynam...

Page 9: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 I 1 5 1 THREE VIEW DRAWING Dimensions in ft valid to ser No XX 8320 I I I i Oct 30 96 0 1 4 ...

Page 10: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 1 5 2 THREE VIEW DRAWING Dimensions in ft valid from ser No 96 8401 Oct 30 96 0 1 5 ...

Page 11: ...TENTS 2 1 Introduction 2 2 Airspeed 2 3 Airspeed indicator markings 2 4 Weight 2 5 Centre of gravity 2 6 Approved manoeuvres 2 7 Manoeuvring load factors 2 8 Flight crew 2 9 Kinds of operation 2 10 Minimum equipment 2 11 Aerotow and winch launching 2 12 Other limitations 2 13 Limitation placards Appr Dec 1 93 2 1 ...

Page 12: ...6 Do not exceed this speed except in smooth air and then only with caution Examples of rough air are lee wave rotor thunderclouds etc VA Manoeuvring speed 81 Do not make full or abrupt control movement above this speed because under certain conditions the sailplane may be overstressed by full control movement VW Maximum winch 65 Do not exceed this speed during launching speed winch or autotow laun...

Page 13: ... m weight 2 4 WEIGHT LIMITS Maximum take off and landing weight with two occupants 1124 lb with one pilot 925 lb Empty weight with standard equipment 683 lb 2 2 695 lb 2 and the corresponding centre of gravity position 67 30 c 1 MAC 68 30 t 2 MAC Maximum weight of all non lifting parts 778 lb 767 lb Note Refer to weight and Balance Section 6 0 to determine actual empty weight c g as established by...

Page 14: ...t removable ballast of 33 lb when flown solo by a pilot including parachute weighing less than 154 lb in the front cockpit Note Installation of the front seat ballast is described in Section 7 paragraph 7 2 of this Flight Manual maximum pilot s weight solo 242 lb Maximum useful load occupants baggage optional equipment 440 lb 430 lb Maximum baggage compartment load 22 lb Appr Dec 1 93 2 4 ...

Page 15: ...e back The reference datum is located 93 6 in aft of the sailplane nose 2 6 APPROVED MANOEUVRES UTILITY CATEGORY Sailplane is certified in the Utility Category With the installed wing tip extensions all aerobatic manoeuvres are prohibited Manoeuvre Airspeeds KIAS Procedures SOLO DUAL ENTRY RECOVERY Loop 8 6 9 7 x Section 4 4 6 item Stall turn 9 2 9 7 x Section 4 4 6 item 2 Lazy Eight 9 7 9 7 x Sec...

Page 16: ...ont seat and his weight including parachute must be 154 lb at least If the pilot s weight is less than 154 lb it is necessary to use the cushion with 33 lb ballast WARNING THE REAR SEAT MUST BE SECURED AGAINST FOLDING AND SAFETY HARNESSES ON THE REAR SEAT MUST BE CONNECTED DRAWN TOGETHER AND SECURED 2 9 KINDS OF OPERATION The sailplane is approved for Day VFR operations Cloud flying is permitted w...

Page 17: ...WITH INSTALLED WING EXTENSIONS ALL FLIGHT TIME WITH WING EXTENSIONS MUST BE RECORDED IN THE SAILPLANE LOG BOOK TO COMPLY WITH CONTINUED AIRWORTHINESS REQUIREMENTS 5 THE NUMBER OF WINCH AND AEROTOW LAUNCHES MUST BE RECORDED IN THE SAILPLANE LOG BOOK TO COMPLY WITH CONTINUED AIRWORTHINESS REQUIREMENTS 2 1 0 M I N I M U M EQUIPMENT Instruments and minimum equipment must be approved types A Instrument...

Page 18: ...nch launching the maximum cable strength or cable safety device weak link is 1460 lb maximum permissible speed Vw 65 KIAS 2 12 OTHER LIMITATIONS A Maximum crosswind component maximum demonstrated crosswind component for safe approach landing and aerotow launching is 16 kt for angle 90 Maximum demonstrated crosswind component for winch launching E 24 n Q 5 22 kl 20 n 18 h z 18 kt a 14 n c 12 n s v ...

Page 19: ...lowing operating conditions Max 4 83 take offs per 1 flight hour The winch launching aerotow take off ratio is 5 1 Crew 35 double 65 single Elementary training to advanced training and to performance soaring ratio is 40 60 whereby the aerobatics share is 2 of the total operation Sailplane life LB versus operation with wing tip extensions is LB 6000 25 x where x is operation with wing tip extension...

Page 20: ...T FOR SOLO FLIGTS WITHOUT BALLAST 154 LB WITH 33 lb BALLAST 121 LB 1 1 b both front and rear cockpits AIR BRAKES LANDING GEAR E3 CANOPY LIFT OFF From ser No 96 8401 Gx 05 3 8 0 n4 AIR VENT FRONT LIFT OFF para 3 2 1 To ser No xx 8320 JETTISON LIFT OFF REAR SEAT ONLY see para 3 2 1 To ser No xx 8320 FRONT CANOPY JETTISON see para 3 2 1 To ser No xx 8320 p a r a CANOPY JETTISON see para 3 2 2 From se...

Page 21: ...PLIED WITH WHEN OPERATING IN UTILITY CATEGORY OTHER LIMITATIONS ARE CONTAINED IN SAILPLANE FLIGHT MANUAL MAX GROSS WEIGHT 1124 LB APPROVED MANOEUVRES LOOP SPIN STALL TURN CHANDELLE CLIMBING LAZY EIGHT STEEP TURN SOLO FLIGHT FROM FRONT SEAT ONLY 1 U TRIMMER 0 T T RELEASE I MAX WINCH LAUNCHING SPEED 65 KIAS MAX AERO TOWING SPEED 81 KIAS MAX MANOEUVRING SPEED 81 KIAS Valid from ser No 96 8304 OPERATI...

Page 22: ...NUAL Do L 23 1012 5 SECTION 3 Emergency procedures CONTENTS 3 1 Introduction 3 2 1 Canopy jettison valid to ser No XX 8 3 2 0 3 2 2 Canopy jettison valid from ser No 96 8401 3 3 Bailing Out 3 4 Stall recovery 3 5 Spin recovery 3 6 Spiral Dive Recovery Appr Oct30 96 3 1 ...

Page 23: ...lockwise and HOLD FORCE UPWARDS ROTATE canopy jettison levers FIG 3 1 pos 2 in the direction of arrows LIFT rear canopy UP Front canopy not jettisoned RELEASE safety belts Red Front Canopy Jettison Lever ROTATE fully counterclockwise a n d H O L D FORCE Front Canopy UPWARDS ROTATE Rear Canopy Jettison Levers in the Direction of Arrows LIFT rear canopy UP 3 2 2 CANOPY JETTISON SEE FIG 3 2 valid fro...

Page 24: ...l stick slightly CHECK airspeed within normal operation range PUSH control stick to reach subcritical angle of attack ELIMINATE bank by rudder APPLY full deflection opposite to sense of rotation RETURN to neutral when rotation stopped PUSH forward slightly simultaneously as rudder is neutralized after rotation has stopped USE to establish at nose low wings level condition INCREASE gently back pres...

Page 25: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 CANOPY JETTISON DURING FLIGHT valid to ser No XX 8320 FIG 3 1 Appr Oct 30 96 0 3 4 ...

Page 26: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 CANOPY JETTISON DURING FLIGHT valid from ser No 96 8401 FIG 3 2 Appr Oct 30 96 3 5 ...

Page 27: ...2 5 SECTION 4 Normal procedures CONTENTS 4 1 Introduction 4 2 Rigging and de rigging 4 3 Preflight Inspection 4 4 Normal operations and recommended speeds 4 4 1 Take off and climb 4 4 2 Flight 4 4 3 Approach 4 4 4 Landing 4 4 5 Use of air brakes 4 4 6 Basic aerobatics Appr Dec 1 93 4 1 ...

Page 28: ...l movement and sit the wing vertically with the leading edge down on the special handling equipment B Wing installation The process of wing installation is the opposite For easier installation of the centre hinge pins use the centering pin or installation drift pin before inserting the main pins see Fig 8 1 Detail A When slipping wing hinges on fuselage hinges make sure that the globular joint of ...

Page 29: ...BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 A Centering the front hinge pin B Control joint between the wing and the fuselage C Wing main hinges with the main pin Appr Dec 1 93 4 3 ...

Page 30: ...tal stabilizers in front of the leading edge of the vertical stabilizer on its top Rotate the pin handle 180 and pull out the pin Elevate the horizontal stabilizer leading edge about 30 o up slip out the horizontal stabilizers from pins by pulling forward It is recommended that the elevator to be in the neutral position during removal Put the horizontal stabilizers on the special handling equipmen...

Page 31: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 Sequence of the walkaround inspection FIG 4 1 Cont I Appr Oct 30 96 4 5 ...

Page 32: ...e or clogging 2 Cockpit Instruments no damage Altimeters correct setting QFE QNH Radio station if installed proper operation Front ventilation for season Safety belts no damage Landing gear 3 Tire no damage correct inflation 4 L Left wing Wing skin including leading no damage edge Wing tip fairing no damage or loose wing tip extension Aileron skin no damage to fabric cover or trailing edge Aileron...

Page 33: ...pickup in place plug removed Elevator free movement Horizontal stabilizers condition of locking wire on the f r o n t p i n o f t h e h o r i z o n t a l stabilizer in front of the leading edge of the top part of the vertical stabilizer Rudder free movement 7 Tail landing gear Landing gear attachment no damage of attachment 8 Right wing see Item 4 left wing Front fuselage sec tion 9 Pins for canop...

Page 34: ... adjustment to one of three possible positions may be obtained by removing the locking pin Note This can be done only before the flight Control column Check for full and free movement of the control column in all directions move it to the left to the right forwards and backwards Instruments Set the altimeters to zero or as desired by the baro set knob Check the other instruments and see that verti...

Page 35: ... in proportion to the wind speed and to unstick the sailplane at a higher speed The tow rope should be attached to the front hook only Note Before take off close the ventilation in order that dust and impurities do not get into the cockpit The ventilation can be opened during at climb 2 Winch launching WARNING USE EITHER SIDE HOOKS OR LOWER HOOK DEPENDING ON WHICH HOOK IS INSTALLED The winch launc...

Page 36: ... The maximum speed for aerotow is 81 KIAS It is necessary to trim the sailplane to reduce control forces and to decrease pilot fatigue during longer flights on tow It is necessary to realize that control sensitivity increases with flight speed Descending A satisfactory rate of descent 390 590 ft min can be obtained when the towing aircraft maintains an airspeed at least of 54 KIAS Appr Dec 1 93 4 ...

Page 37: ...ing technique of the side slipping is entirely conventional The angle of bank of the sailplane should be between 1 0 and 20 The side slip is not very effective mean of loosing height in this sailplane As the rate of descent may be effectively increased by the use of the air brakes If a constant airspeed is to be maintained during a side slip the angle of pitch must be constant The air speed indica...

Page 38: ...rol stick forward and start the stall recovery CAUTION Before stalling and spinning the following procedures must be done Trim neutral Air brakes retracted and secured Cockpit canopy locked and secured Ventilation shut Rudder pedals properly adjusted to allow full deflections Safety belts fastened and tight Loose objects removed or secured 4 High Altitude Flight Operation above 13 780 feet has not...

Page 39: ... at the flare The sailplane should touch down with the landing gear first and then with the tail wheel if landed correctly to reduce shock to the tail wheel on ground contact Do not flare prematurely in order to prevent the sailplane from droping from a higher height Off field landing It is recommended to land with the landing gear retracted if landing on a soft ground Note In this case extend the...

Page 40: ...t 3 4 kts higher 3 To avoid exceeding the never exceed speed vNE during unusual atti tude recoveries for example during aerobatics It is recommended to use the air brakes in any case when the sailplane starts to increase the speed and the pilot is uncertain of his orientation or how to manage the situation Configuration with I air brakes extended will ensure that VNE is not exceeded Use of air bra...

Page 41: ...d approved aerobatic manoeuvres The rate of acceleration of this sailplane is high so great care must be taken not to exceed limitations given in Sections 2 2 2 6 and 2 7 Instruction guidelines for performing approved acrobatic manoeuvres are given on pages 13 to 19 of this Section WARNING ONLY MANOEUVRES WITH POSITIVE G LOAD FACTORS ARE APPROVED Cont Appr Dec 1 93 4 15 ...

Page 42: ...d maintain this rate of backward stick movement throughout the first half of the loop but do not use more than about 60 of the control stick full deflection The load factor must drop in the inverted position After passing the inverted position the speed will increase and the control stick must be eased forward gradually until the sailplane is flying level again Before and during this manoeuvre rud...

Page 43: ... 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 The ailerons should be used against the direction of turn as necessary to prevent the sailplane rolling to the inverted position As the nose approaches the reciproc...

Page 44: ... smoothly pulling the control stick with simultaneous coordinated use of ailerons and rudder At a speed of 54 KIAS transition the sailplane to a descent and after reaching a speed of 97 KIAS perform the steep turn to the opposite side smoothly pulling the control stick with simultaneous coordinated use of ailerons and rudder The flight path intersects at the lowest point of the manoeuvre 54 KIAS 9...

Page 45: ...m the dive in the usual way The attitude during the spin is 60 to 70 nose down and the loss of height in one turn is aproximately 260 ft when flying solo and 390 ft when flying dual The time of one revolution of the spin is approximately 3 5 secs Caution 1 Before spinning accomplish the procedures given in the Flight Manual Section 4 paragraph 3 2 IAS error The airspeed indications become erroneou...

Page 46: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 43 54 KIAS 81 86 KIAS FIG 4 6 Appr Dec 1 93 ...

Page 47: ...lo or dual Transition the sailplane to a steep climb at an angle of approximately 45 o above the horizon do not increase the angle At a speed of 76 KIAS apply the rudder to the selected side of the turn and by coordinated positive use of the ailerons make a transition to gliding flight in the opposite direction at a minimum speed of 43 KIAS 43 KIAS 97 103 KIAS FIG 4 7 Cont Appr Dec 1 93 4 21 ...

Page 48: ...try speed of 92 KIAS when flying solo or 97 KIAS when flying dual Enter the climb simultaneously with a bank of approx 45 After turning 150 start a transition to a glide angle such that the manoeuvre will be finished in the opposite direction with the speed not decreasing below 43 KIAS 4 3 KIAS 97 KIAS FIG 4 8 SOLO DUAL Appr Dec 1 93 4 22 ...

Page 49: ...CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 SECTION 5 Performance CONTENTS 5 1 Introduction 5 2 Approved data 5 2 1 Airspeed system calibration 5 2 2 Stall speeds 5 3 Additional information 5 3 1 Flight polar Appr Dec 1 93 5 1 ...

Page 50: ...r airspeed calibration and stall speeds Other non approved information is provided 5 2 APPROVED DATA 5 2 1 AIRSPEED INDICATOR SYSTEM CALIBRATION Assumes zero instrument error The diagram is effective for maximum flight weight of 1124 lb 8 0 6 0 f 20 4 0 6 0 8 0 1 0 0 120 140 Indicated Airspeed KIAS FIG 5 1 Appr Dec 1 93 5 2 ...

Page 51: ... SPEEDS unaccelerated The broken line is valid only when using the wing tip extensions Note The stall warning speed is about 5 higher than stall speed for all configurations Stall speed for forward c g position 2 5 air brakes extended J u L I A air brakes retracted FIG 5 2 Weight lb Appr Dec 1 93 5 3 ...

Page 52: ...MATION 5 3 1 FLIGHT POLAR 5 3 1 1 FLIGHT SPEED POLAR Maximum flight weight of 1124 lb The broken line is valid only when using the wing tip extension Airspeed with the angle of descent of 45 124 KIAS 0 20 40 6 0 8 0 1 0 0 600 1200 Airspeed KIAS air brakes retracted landing gear retracted FIG 5 3 Dec 1 93 5 4 ...

Page 53: ...UPER BLANIK SAILPLANE FLIGHT MANUAL Do L 23 1012 5 SECTION 6 Weight and balance CONTENTS 6 1 Introduction 6 2 Weight and balance record 6 3 Basic empty weight and moment 6 4 Balance chart 6 5 Balance record 6 6 Equipment list Dec 1 93 6 1 ...

Page 54: ... the L 23 SUPER BLANIK Sailplane chapter 8 6 3 BASIC EMPTY WEIGHT AND MOMENT Basic empty weight 683 lb t 2 with the installed wing tip extensions 695 lb t 2 Moment to the reference plane 17 923 1 in lb see weight and balance record The reference datum is located 93 6 in aft of the sailplane nose 6 4 BALANCE CHART FIG 6 1 1 Balance chart description The varying load scales are in the upper part of ...

Page 55: ...s in 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 Scale 4 for any changes in the rear instrument panel in the same fashion as i...

Page 56: ... 150 I I I I I I I 100 50 c I I I a Rear Pilot parachute 300 200 100 I I I I I I I I I I I 1 B Front instrument panel changes 30 1 0 1 1 1 I 1 1 I 1 I I 1 a I A C Rear instrument panel changes 1 0 11111111111111111111llllllllllllllllll D Weight l b 23 40 I 800 Baggage c Aft of rear pilot seat no influence E on centre of gravity position EMPTY SAILPLANE CENTER OF GRAVITY RANGE 62 70 1 1 1 23 40 Dec...

Page 57: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 6 5 BALANCE RECORD ...

Page 58: ...eter myp 3 1 75 front instr panel rear instr panel 2 x Airspeed indicator LUN 1106 14 8 0 88 5 83 front instr panel 1 82 Q mhi t rear instr panel ib2 I 3 x Electric LUN 1211 1 0 79 5 83 turn and bank side front instr panel 1 82 indicator rear instr panel 4 x Vertical speed LUN 1141 02 1 06 5 87 indicator t 1000 front instr panel 1 87 ft min rear instr panel o r Vertical speed LUN 1141 04 1 06 5 87...

Page 59: ...rib No 1 ft 7 X Accelerometer AM l 0 front 0 55 5 51 indicator k 6000 Optional 0 Item 7 as applicable is required for pilot s station for cloud flying operations s 0 Subject Type Mass Arm from the Date of lb reference instalation plane rib No 1 ft y y P 1 0 x Fjl N IT 3 Y 11 K 7C f z cj c J G y 1 2 Kf 7 J j c e 3 g Qjb 4 jq 1 3 1 4 1 5 1 6 1 7 1 8 Dec 20 95 6 7 ...

Page 60: ...C SAILPLANE FLIGHT MANUAL Do L23 1012 5 SECTION 7 Sailplane and systems description CONTENTS 7 1 Introduction 7 2 Sailplane description 7 3 Front seat ballast 7 4 1 Front cockpit standard 7 4 2 Front cockpit optional 7 5 Rear cockpit Sep 20 96 0 7 l ...

Page 61: ...ntal stabilizer is fastened by hinges on the top of the vertical stabilizer Elevator and aileron controls are actuated by control push rods and control cables the rudder control is pedal operated also by control push rods and control cables Air brakes are controlled by control levers The elevator trim tab is controlled by the control lever The sailplane is equipped with the main landing gear and t...

Page 62: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L23 1012 5 B Seat removal Removal is carried out in a reverse order to installation FIG 7 1 Dec 1 93 7 3 ...

Page 63: ...Wheel brake 24 Label No smoking 25 Label Tow release 26 Label Max airspeeds 27 ldentification number 28 Label TURN AND BANK INDICATOR 29 Label Maneuvers with wing tip extensions forbidden 30 Label Air vent 31 Label Landing gear extended 32 Label Landing gear retracted 33 Label Adjustment of pedals 34 Label Max pilot weight 35 Label Front cockpit hood emergency release 36 Label Permitted maneuvers ...

Page 64: ...ended 21 Label Airbrakes retracted 22 Label Elevator trim control 23 Label Wheel brake 24 Label No smoking 25 Label Tow release 26 Label Max airspeeds 27 Identlfication number 28 Label TURN AND BANK INDICATOR optionaI 29 Label Manoeuvers with wing tip extensions forbidden 30 Label Air vent 3l Label Landing gear extended 32 Label Landing gear retracted 33 Label Adjustment of pedals 34 Label Max pil...

Page 65: ...g 22 Label Elevator trim control 23 Label Wheel brake 24 Label No smoking 25 Label Tow release 26 Label Max airspeeds 27 ldentification number 28 Label TURN AND 8ANK INDICATOR optional 29 Label Max airspeed with wing tip extensions 30 Label Front cockpit hood emergency release 31 Label Max alowable speed vs altitude 32 Label Operating limitations 33 Label Landing gear extended 34 Label Landing gea...

Page 66: ...3 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 SECTION 8 Sailplane handling care and maintenance CONTENTS 8 1 Introduction 8 2 Sailplane inspection period Dec 1 93 8 1 ...

Page 67: ...g servicing and maintenance which must be followed if the sailplane is to retain new plane performance and dependability are given in the Maintenance Manual of the L 23 SUPER BLANIK Sailplane 8 2 SAILPLANE INSPECTION PERIOD Maintenance and servicing of the sailplane are provided in the L 23 SUPER BLANIK sailplane Maintenance Manual Do L 23 1031 3 see Section 5 Dec 1 93 8 2 ...

Page 68: ... SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 SECTION 9 Supplements CONTENTS 9 1 Introduction 9 2 List of inserted Supplements 9 3 Supplements inserted Jan 13 99 0 9 l ...

Page 69: ...quipment which is installed on the sailplane may contain the supplementary information on The information contained in this document supplements or superseds the basic Sailplane Flight Manual where covered in the sections contained herein For limitations procedures and performance not contained in this supplement consult the basic Sailplane Flight Manual 92 LIST OF INSERTED SUPPLEMENTS Title of in...

Page 70: ...L 23 SUPER BLANIK 686 04 KUNOVICE CZECH REPUBLIC SAILPLANE FLIGHT MANUAL Do L 23 1012 5 Date of Doc No Title of inserted supplement insertion I Jan 13 99 0 9 3 ...

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