SZD-56-2 "Diana
Contents
1. BIURO PROJEKTOWE SB gt s ath Gole _ BOGUMI BERE _ z 811 33 ae 4 136 43 308 Bielsko Bia a tel fax x 63 81 FLIGHT MANUAL FOR A SAILPLANE Model SZD 56 2 Diana 2 Serial No 060000000 Registration Issue I March 2006 Pages identified by Appr are approved by On behalf of President of Civil Aviation Office Signature Stamp Original date of approval March 1 2006 This sailplane is to be operated in compliance with information and limitations contained herein This manual should be always stored onboard This is translation of the original Polish document agreed with airworthiness Authority Translated by Tadeusz Zbos Biuro Projektowe B Bogumit Beres SZD 56 2 Diana 2 0 ISSUANCES 0 1 Record of revisions 0 2 List of effective pages 0 3 Table of contents 0 4 Table of figures Revision No Issued March 1 2006 FLIGHT MANUAL SECTION 0 0 2 0 3 0 4 0 5 SECTION 0 ISSUANCES page 0 1 Biuro Projektowe B SEC TIONG FLIGHT MANUAL Bogumi Bere ISSUANCES SZD 56 2 Diana 2 0 1 Record of revisions Any revision of the present Manual except actual weighing data must be recorded in the following table and in case of approved Section endorsed by the responsible airworthiness Authority The new or amended text in the revised page will be indicated by a black vertical line in the left hand margin and the Revision N2. 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 page 0 3 Biuro Projektowe B SEC TIONG FLIGHT MANUAL Bogumi Bere ISSUANCES SZD 56 2 Diana 2 0 3 Table of contents 0 ISSUANCES a non approved section l GENERAL a non approved section Ze LIMITATIONS an approved section 3 EMERGENCY PROCEDURES an approved section 4 NORMAL PROCEDURES an approved section 5 PERFORMANCES a partly approved section 6 WEIGHT AND BALANCE a non approved section Le SAILPLANE AND SYSTEMS DESCRIPTION a non approved section 8 SAILPLANE HANDLING CARE AND MAINTENANCE a non approved section 9 SUPPLEMENTS Revision No 4 page 0 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECON SZD 56 2 Diana 2 ISSUANCES 0 4 Fig Fig Fig Fig Fig Fig Fig Fig Fig Fig Revision No Issued Table of figures 1 1 Three view drawing culinaria Ea GA 1 5 2 1 Airspeed indicator matkin g deene naien A OARE AR 2 5 2 2 Allowed C G range at different empty WelghtS ooonoococnnnccconncccnoncnononcnnnnnnnnnn 2 6 AN Wing REDOM neen a e E WEW RLN A 4 3 4 2 Vall Plame TIOS lisa 4 4 SI IAS Cabras dilo E ESR 5 2 5 2 Polar speed calculated iniisa ROSA RAA O AA 5 5
3. 4 1 Introduction 4 2 4 2 Sailplane rigging and de rigging 4 2 4 2 1 Wing rigging 4 2 4 2 2 Tailplane rigging 4 4 4 3 Daily inspection 4 5 4 4 Pre flight inspection 4 6 4 5 Normal procedures and recommended speeds 4 7 4 5 1 Aerotowed take off and climb 4 7 4 5 2 Free flight 4 9 4 5 3 Approach 4 10 4 5 4 Landing 4 10 4 5 5 Flight with water ballast 4 10 4 5 6 High altitude flight 4 13 4 5 7 Flight in rain 4 13 Revision No Issued March 1 2006 page 4 1 Biuro Projektowe B SECTION 4 i FLIGHT MANUAL Bogumit Beres NORMAL PROCEDURES SZD 56 2 Diana 2 4 1 Introduction Section 4 provides checklist and amplified procedures for the conduct of normal operation 4 2 Sailplane rigging and de rigging Three persons are necessary for sailplane rigging and de rigging with available wing supports two persons Before rigging all mating surfaces of rigged components should be cleaned with a rag and greased 4 2 1 Wing rigging The following description together with Fig 4 1 define the procedure of wings rigging Sequence of operations in rigging 1 Put the air brake hand grip in a cockpit in its front position do not lock this and the hand grip of water ballast tank valve in a closed position 2 Retract the air brake in the wing 3 Shove the main fitting socket 1 of one wing panel on the corresponding fuselage spar 2 While shoving keep the planes of wing and fuselage enclosing
4. 2 6 2 Weight and balance record permitted payload range 6 2 6 3 Tail ballast limitations 6 4 Revision No Issued March 1 2006 page 6 1 Biuro Projektowe B SECTION 6 Kwea FLIGHT MANUAL Bogumi Bere WEIGHT AND BALANCE SZD 56 2 Diana 2 6 1 Introduction This Section contains the payload range within which the sailplane may be safely operated Procedures for weighing the sailplane and the calculation method for establishing the permitted payload range as well as the list of equipment available for this sailplane and equipment installed in the weighed sailplane are contained in the Technical Service Manual Sections 4 and 6 6 2 Weight and balance record permitted payload range The entries in the following tables are valid only for the sailplane the Fact No of which is shown on the head page of this Flight Manual The loading plan is to be calculated basing on the last weighing Valid for Serial No Permitted weight of Approved pilot amp parachute PP C G with water without water Issued March 1 2006 Revision No Biuro Projektowe B SECTION 6 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 WEIGHT AND BALANCE For calculation of the permitted max and min pilot weight refer to Technical Service Manual Section 4 To verify the correctness of sailplane loading condition refer to Technical Service Manual Section 4 The following table allows to determine the pe
5. 4 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL PI SZD 56 2 Diana 2 1 5 Three view drawing Fig 1 1 Three view drawing Revision No 13 Issued March 1 2006 page Biuro Projektowe B SECTION 1 FLIGHT MANUAL Bogumit Beres GENERAL SZD 56 2 Diana 2 Intentionally left blank Revision No 1 6 page Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL ore Hane SZD 56 2 Diana 2 SECTION 2 2 LIMITATIONS 2 1 Introduction 2 2 2 2 Airspeed 2 3 2 3 Airspeed indicator markings 2 4 2 4 Weight 2 6 2 5 Centre of gravity 2 6 2 6 Approved manoeuvres 2 8 2 7 Manoeuvring load factors 2 8 2 8 Flight crew 2 8 2 9 Kinds of operation 2 9 2 10 Minimum equipment 2 9 2 11 Aerotow 2 9 2 12 Other limitations 2 9 2 13 Limitations placard 2 10 Revision No 2 1 Issued March 1 2006 page Biuro Projektowe B SECTION FLIGHT MANUAL Bogumit Beres LIMITATIONS SZD 56 2 Diana 2 2 1 Introduction Section 2 includes operating limitations instrument markings and basic placards necessary for the safe operation of the sailplane its standard systems and standard equipment The limitations included in this Section and in Section 9 have been approved by the Civil Aircraft Inspection Board Revision No page 2 2 Issued March 1 2006 Biur
6. 5 3 Data on optimum use of wing flap coococnnococnnncccnoancnnoncnononanononanonnnnnnnnnanonnncnnns 5 7 7 1 Scheme of board instrument system sessssseesseesseesseeseeesssetssrtsseesseeessresssees 71 3 M2AOCEPU VE A A A A A a a a e R 7 4 March 1 2006 page 0 5 Biuro Projektowe B SEC HONG FLIGHT MANUAL Bogumi Bere ISSUANCES SZD 56 2 Diana 2 Intentionally left blank Revision No page 0 6 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECON SZD 56 2 Diana 2 GENERAL SECTION 1 1 GENERAL 1 1 Introduction 1 2 1 2 Certification basis 1 2 1 3 Warnings cautions and notes 1 2 1 4 Descriptive and technical data 1 3 1 5 Three view drawing 1 5 Revision No 1 1 Issued March 1 2006 page Biuro Projektowe B SECTION 1 FLIGHT MANUAL Bogumit Beres GENERAL SZD 56 2 Diana 2 1 1 Introduction The sailplane Flight Manual has been prepared to provide pilots and instructors with information for safe and efficient operation of the SZD 56 2 Diana 2 sailplane This manual includes the information required to be furnished to the pilot by JAR 22 requirements It also contains supplemental data supplied by the sailplane manufacturer 1 2 Certification basis This type of sailplane designated SZD 56 2 Diana 2 has been approved for operation by the Polish airworthiness Authority Civil Aircraft Inspection Board in accordance wit
7. push the control stick forward with simultaneous rudder deflection opposite to possible rotation Revision No Issued March 1 2006 Biuro Projektowe B SECTION 4 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 NORMAL PROCEDURES 4 5 2 Free flight Making use of wing flaps Adjustment of wing flap setting allows better adoption of the sailplane to actual flight condition Flap settings 8 through 2 are suitable for straight flight and over the range of corresponding airspeeds these are optimum settings Flap settings 14 through 21 are aimed for use while circling The 14 setting is normally used for centering into thermals as well as for leaving the turbulent lift zones Settings 14 and 21 are used when the thermal has been centered which allows for tight amp steady circling in its core The 28 setting is used for landing only Optimum flap setting at various airspeed range depend strongly on wing surface loading In a diagram under item 5 3 3 the optimum wing flap setting is given versus sailplane weight and airspeed WARNING In case of instantaneous or sudden wing flap displacements the wing lift changes abruptly which may result in abrupt alterations of flight altitude Thus care must be exercised in this respect while flying close to the ground surface or near to other sailplanes gaggle flying Low speed flight and stall characteristics In flight at a low airspeed down t
8. ribs parallel 4 In continued motion the fuselage spar pivot 3 should mate with the ball nest inside the socket 5 Moving at wing tip align the main 1 and rear 6 fitting openings with corresponding openings in fuselage spar 7 and with these of fuselage rear fitting 8 The torque tubes of automatic coupling in air brake 4 and wing ballast valves 5 control system are to be shifted towards the assembled wing panel 6 Having juxtaposed the wing with fuselage as above insert the main bolt 9 and next rotate this which should result in catching the bolt notch at angle bar 13 on fuselage rib and the pin 10 at the spring clamp 11 7 Repeat the operations under items 3 through 6 on opposite wing 8 Having rigged both wings connect the wing push rods 12 of flaperon control system with appropriate push rods in a fuselage 9 Secure the spring clamps with safety pins to prevent the main bolt pin sliding off Wing de rigging requires the reverse sequence of operation NOTE When rigging or de rigging do not catch wings at trailing edge as this may result in damage to control surfaces Revision No page 4 2 Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL SECTION 4 SZD 56 2 Diana 2 NORMAL PROCEDURES Fig 4 1 Wing rigging Revision No page 4 3 Issued March 1 2006 Biuro Projektowe B INS FLIGHT MANUAL Bogumit Beres SZD 56 2 Diana 2 NORMAL
9. taken early enough At an altitude of 100 m 330 ft above the landing site at the very least flaps should be set to 14 through 28 and landing gear extended Additionally for flight path control in approach the air brake should be used Approach should be done at approx 95 km h 51 kt speed while in turbulence approx 10 km h 5 kt above this value 4 5 4 Landing Prior to landing the water ballast should be jettisoned NOTE Landing with full or in part jettisoned water ballast allowed only in necessary instances and then on airfield only WARNING Wing flap manoeuvring close to the ground is not recommended since this may result in dangerous alterations to flight altitude In a landing ground roll pull the elevator control back to facilitate maintaining the directional stability and to avoid the nose touch down when braking on the wheel 4 5 5 Flight with water ballast Wing tank water ballast allows to adopt the optimum value of wing surface loading to the anticipated in flight weather conditions Tail water ballast allows to obtain the more aft in flight C G position when flying with water ballast better performances Capacities of water ballast tanks are as follows front tank in a wing 2 x 81 4 litre 2 x 21 5 gal rear tank in a wing 2 x 42 5 litre 2 x 11 2 gal tail tank 5 6 litre 1 48 gal NOTE This is to remember that in line with increasing surface loading both the min
10. the airfoil family from KL 002 128F 17 at the root onto KL 002 122F 17 at the tip Detachable winglets based on the distinct airfoil family Wing structure in multicell monocoque torque box layout Air brake extending on wing top surface only Flaperon of 0 17 chord ratio over the whole wing span On flaperon bottom surface the pneumatic turbulizers are provided supplied from NACA air intakes Each wing panel contains two integral ballast tanks with independent jettison valves Total capacity of wing tanks ranges 248 litre 65 5 gal Wing fuselage connection is accomplished by shoving the wing panels on the fuselage spar ends and locking these with two bolts parallel to wing chord The air brake control systems and water tank valves actuation connected automatically at wing rigging while coupling in flaperon control system by means of joint secured with sleeve Horizontal tailplane in T arrangement mounted on a fin with horizontal mechanically locked bolt Elevator control coupling by means of joint with locking sleeve In a fin the antenna for board transceiver is provided At fin root a water ballast tank of 5 6 litre 1 48 gal capacity is installed The sprung retractable landing gear equipped with the TOST AERO 4 00 x 4 300mm diameter wheel and drum brake Tail wheel of 100mm diameter with polyurethane tread Tow release installed on a fuselage bottom front part One piece front hinged upwards opening cockpit canop
11. 0 150 200 250 300 350 400 450 500 550 600 uiu m Fig 5 2 Polar speed calculated Revision No Issued March 1 2006 page 5 5 SECTION 5 PERFORMANCES FLIGHT MANUAL 5 3 3 Data on optimum use of wing flap DIANA 2 SPEED FLAPS POSITION RECOMMENDED COMPUTATIONAL o u O LO 1 lt lt cm 54 SSYW page 5 6 Biuro Projektowe B Bogumi Bere SZD 56 2 Diana 2 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 o re c N N Revision No Issued March 1 2006 V km h Biuro Projektowe B Bogumit Beres FLIGHT MANUAL RZN SZD 56 2 Diana 2 RFORMAN 140 af 130 20 0 3 3 8 B 8 414 a 14 421 21 28 e 28 Vmin 4 2 Vmax 50 60 70 80 90 100 110 120 SPEED knots DIANA 2 SPEED FLAPS POSITION RECOMMENDED COMPUTATIONAL 40 30 1200 1100 1000 900 800 700 600 500 qi SSY Fig 5 3 Data on optimum use of wing flap Revision No Issued March 1 2006 page 5 7 Biuro Projektowe B URN gt FLIGHT MANUAL Bogumi Bere ERFORMANCES SZD 56 2 Diana 2 Intentionally left blank Revision No page 5 8 Issued March 1 2006 Biuro Projektowe B Bogumi Bere FLIGHT MANUAL SECTION 6 SZD 56 2 Diana 2 WEIGHT ANDBALANCE SECTION 6 6 WEIGHT AND BALANCE 6 1 Introduction 6
12. 56 2 Diana 2 EMERGENCY PROCEDURES 3 7 6 Break or inadvertent release of towing rope In case of break or inadvertent release of towing rope at a low altitude proceed as follows pull the tow release if the rope remained attached to the glider extend the undercarriage tighten the shoulder belts select a landing site land off field or if possible on the airfield In case of unavoidable collision with the terrain obstacles off the airfield DO NOT ALLOW THE HEAD ON CRASH 3 7 7 Water jettison at temperatures below 0 C Till reducing the flight altitude and entering the air of temperature above 0 C 32 F the icing of wing flaps in the area of water discharge valves as well as this of fuselage tail with rudder must be taken into account This may result in blocking the a m control surfaces as well as in shifting the C G position further aft To prevent the locking of control surfaces deflect these more often than usual and pay also attention to any abnormalities in longitudinal balance of sailplane Revision No a Issued March 1 2006 page 3 Biuro Projektowe B SECTION FLIGHT MANUAL Bogumit Beres EMERGENCY PROCEDURES SZD 56 2 Diana 2 Intentionally left blank Revision No page 3 8 Issued March 1 2006 Biuro Projektowe B SECTION 4 Bogumi Bere FLIGHT MANUAL SZD 56 2 Diana 2 NORMAL PROCEDURES SECTION 4 4 NORMAL PROCEDURES
13. Diana 2 sailplane 8 3 Sailplane alterations or repairs Repairs and alterations are referred to in the Repair Manual for SZD 56 2 Diana 2 sailplane It is essential that the responsible airworthiness Authority be notified prior to any alterations on the sailplane to ensure that the airworthiness of the sailplane is not compromised 8 4 Ground handling road transport 8 4 1 Ground handling With respect to ground handling i e securing against wind towing rope connection anchoring proceeding with a wet glider draining of the instrument pneumatic system the generally known rules for performance gliders should be observed Sailplane is to be anchored using towing hook clamps for wing transport wheels as well as with wide strap at the fuselage fin transition NOTE Leaving the glider outside without protection against environmental conditions and sunlight will harmfully affect durability of the lacquer coat In case of prolonged pause in operation sailplane de rigging is recommended If the sailplane is to be stored in rigged condition the wings should be supported at tips The metal fittings and elements should be greased Revision No page 8 2 Issued March 1 2006 Biuro Projektowe B SECTION 8 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 AE Put the individual covers on the sailplane main sets NOTE Do not hangar in wet covers The hangared sailplane should not be exposed to environmental
14. E DESCRIPTION SZD 56 2 Diana 2 7 1 Introduction This Section contains description of sailplane and its systems and provides information on operation of these Refer to Section 9 for details of optional systems and equipment 7 2 Cockpit controls 7 2 1 Aileron amp elevator control Ailerons and elevator are controlled with control stick located on right hand cockpit side The transceiver push to talk button is installed on the control stick 7 2 2 Rudder Rudder pedals are in flight adjustable 9 settings Grip of pedal adjustment is located in the lower part of instrument panel column 7 2 3 Wing flaps Wing flaps are operated by means of a handle located on a cockpit left hand side Flaps control handle can be locked at 7 various settings To facilitate access to and egress from a cockpit the flap control handle is folded up 7 2 4 Longitudinal trim Trim device is controlled by means of a lever on control stick Pressure on a lever disconnects the elevator control from trimming spring On releasing the lever the spring supports retaining the control stick in selected position Indicator of trimming device position is located on the right hand cockpit side With the lever on control stick held pressed the trimming device may be precisely set with an indicator 7 2 5 Tow release The yellow grip is installed on a column of instrument panel on the left hand side The hook is released on pulling at
15. PROCEDURES 4 2 2 Tailplane rigging Sequence of operations in tailplane rigging see Fig 4 2 Disassemble the fairing 1 removing first the screw 5 Put the horizontal tailplane on the fin inserting the protruding from stabilizer T shape arm 7 of main fitting into a socket 10 3 Connect the front 4 and main 7 fittings of horizontal and vertical tailplanes with bolt 6 Insert the pin 9 in the opening in fin rib and secure this with a safety pin 4 Connect the elevator control system by coupling the push rod 3 with the top lever 2 5 Put the fairing 1 on and secure this with screw 5 N Tailplane de rigging requires the reverse sequence of operation pana won iR z E AS o ll E TE TAO Fig 4 2 Tailplane rigging Revision No page 4 4 Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL SECTION 4 SZD 56 2 Diana 2 NORMAL PROCEDURES 4 3 Daily inspection O ae Ge 10 11 12 13 14 Before flying the glider should be inspected carefully This concerns also the gliders stored in hangar since as learnt by experience these are exposed to damage during manoeuvring or when in rest e g rodents During the inspection the followings should be checked Glider documents validity of Inspection Certificate complete the records Condition of the fuselage wing and tailplane structure and skin visual ins
16. approved further values and data The data in a charts have been computed from flight tests with the sailplane in good condition and using average piloting techniques 5 2 Approved data 5 2 1 Airspeed indicator system calibration NOTE page 5 2 CAS km h IAS kt 30 40 50 60 70 80 90 100 110 120 130 140 150 280 260 240 220 N o o k o _ O o 4 R 120 100 00 o o 150 140 130 120 110 100 CAS kt PEETA ETETA FETT aa di tari pt iti iti ii vot Ja paar fives titi Aa ad PEENE ETET ETET uul ULU LELAS LULU ELU LULU ELU LLU LS O A FA TS US LS OS O LELEN 60 80 100 120 140 160 180 200 220 240 260 280 IAS km h Fig 5 1 IAS Calibration The above diagram presents CAS versus IAS CAS Calibrated Airspeed instrument value airspeed indicator reading corrected for instrument error and aerodynamic calibration error IAS Indicated Airspeed instrument reading corrected for instrument error only IAS values presented in this Manual are given assuming zero instrument error Revision No Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL ES SZD 56 2 Diana 2 RFORMAN 5 2 2 Stall speeds In the following table the IAS stall speeds values airspeed indicator readings are g
17. been certified in Utility Category with no aerobatic manoeuvres allowed 2 7 Manoeuvring load factors The allowed manoeuvring load factors are as follows at Va 198 km h at Vne 277 km h 107 kt 149 kt maximum positive load factor 5 3 4 0 maximum negative load factor 1 5 NOTE The above refers to the configuration with air brake retracted and wing flap setting not exceeding 8 With air brake extended the positive limit manoeuvring load factor is 3 5 over the whole range of operating airspeed With wing flaps deflected down by more than 8 the positive limit manoeuvring load factor is 4 0 over the airspeed range up to Vre 224 km h 121 kt 2 8 Flight crew The pilot parachute weight must be contained within the following limits minimum 55 kg 121 Ib maximum 110 kg 242 Ib Revision No page 2 8 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL ore Hane SZD 56 2 Diana 2 2 9 Kinds of operation This sailplane has been certified in Utility Category and is intended for normal soaring flight in accordance with VFR rules by day WARNING The following are forbidden night flying cloud flying aerobatics 2 10 Minimum equipment The minimum equipment required according to JAR 22 standards comprises airspeed indicator altimeter pilot safety harness 4 point Sailplane standard eq
18. ccessible in front of the instrument panel 6 The instrument panel is mounted to a column with a screw 5 Revision No Issued March 1 2006 page 7 5 Biuro Projektowe B SECTION FLIGHT MANUAL Bogumi Bere SAILPLANE DESCRIPTION SZD 56 2 Diana 2 7 7 Air brake Air brake control is actuated conventionally with a slider located on the cockpit left hand side On the slider a lever is provided used to lock the air brake in its retracted position and also to brake the landing gear wheel 7 8 Baggage compartment A baggage compartment is located above the fuselage spar accessible from the cockpit Baggage is fastened with straps to the lugs provided in baggage compartment Maximum weight of luggage in baggage compartment 5 kg 11 1b Carriage of dangerous or flammable materials in baggage compartment forbidden 7 9 Water ballast system Jettison of water ballast is controlled with levers located on the cockpit right hand side see item 4 5 5 7 10 Miscellaneous equipment 7 10 1 Transceiver Sailplane is adapted for transceiver installation As a standard the tubular antenna is installed in the fin nose with a cable led to the instrument panel 7 10 2 Ventilation The cockpit is ventilated by means of a side window with deflectable ventilation tab Moreover an adjustable air blow on the canopy portion above the instrument panel is provided controlled with a black slider on th
19. colour at the bottom of instrument panel resolutely push the canopy up NOTE If the canopy cannot be jettisoned break the perspex starting at the window Use the leg force if necessary Revision No page 3 2 Issued March 1 2006 Biuro Projektowe B SECTION 3 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 EMERGENCY PROCEDURES 3 3 Bailing out Bailing out is the last resort mandatory emergency action if it is not possible to control the glider into the safe landing To bail out jettison the canopy acc to item 3 2 release the safety belts pull up the legs and bail out if the glider is rotating e g spinning bail out towards rotation centre open the parachute with a delay depending on circumstances acc to its operation instruction NOTE If bailing out takes place below 200 m 656 ft of altitude the parachute should be opened immediately after leaving the cockpit avoiding as far as possible collision with the glider 3 4 Stall recovery The stalled glider pitches nose down symmetrically or with a tendency to bank The recovery is troubleless and reliable by releasing the stick forwards 3 5 Spin recovery This sailplane is not allowed for spinning Recovery from an inadvertent spin this concerns also sailplane with water ballast should be accomplished as follow ailerons neutral wing flaps neutral rudder opposite to rotat
20. conditions or humidity Put the fuselage on the belly supports placed in front of the undercarriage house and under the fin Set the wings chord vertical and shore the wings with band supports at the leading edge Release pressure in the tyre For sailplane ground rolling the tail forwards attitude is recommended Pulling the sailplane at wing tips not recommended For motor car transportation in nose forwards attitude the tow release should be used and a towing rope with connection link Immobilize the control stick with safety belts 8 4 2 Road transport Standard procedure for transport of de rigged sailplane on a trailer involves the special composite sleeves shoved on the fuselage spar on which the wing clamps are installed The outboard sleeve portions inserted in the cut out in side boards of sailplane standard trailer are used to immobilise the transported sailplane In case of glider transport in a trailer without composite special clamps the assemblies may be fastened at their external surfaces with the wide clamps upholstered with a soft padding or with bands supports Fasten the wings at the fittings close to the root ribs and support under the leading edge at semispan wing chord vertical The fuselage should be fastened at the undercarriage wheels and at the fuselage spar The tailplane to be fixed in clamps For transportation protect the mating surfaces of the fittings access openings and bearings agai
21. e left hand side and the adjustable nozzle on the right hand side in front of the control stick Pressing the nozzle home stops air blow weng Revision No page Issued March 1 2006 Biuro Projektowe B SECTION 8 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 SAILPLANE MAINTENANCE SECTION 8 8 SAILPLANE HANDLING CARE AND MAINTENANCE 8 1 Introduction 8 2 8 2 Sailplane periodic inspections 8 2 8 3 Sailplane alterations or repairs 8 2 8 4 Ground handling road transport 8 2 8 4 1 Ground handling 8 2 8 4 2 Road transport 8 3 8 5 Cleaning and care 8 3 Revision No Issued March 1 2006 page 8 1 Biuro Projektowe B SECTIONS FLIGHT MANUAL Bogumi Bere SAILPLANE MAINTENANCE SZD 56 2 Diana 2 8 1 Introduction This Section contains manufacturer s recommended procedures for proper ground handling and servicing of the sailplane In this connection certain inspection and maintenance requirements are identified which must be followed if the sailplane is to retain the new plane performance and dependability It is wise to follow a planned schedule of lubrication and maintenance based on the specific climatic and operating conditions encountered 8 2 Sailplane periodic inspections The sailplane inspection should be performed at the beginning of every flying season The scope and time periods of all inspections are contained in the Technical Service Manual for SZD 56 2
22. edals Balancing weight Instrument panel Cockpit canopy emergency jettison grip Longitudinal trim lever Control stick Water ballast jettison levers Trim indicator Safety belts Seat cushion Back rest or head rest Revision No Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECTION 7 SZD 56 2 Diana 2 SAILPLANE DESCRIPTION 7 4 Landing gear The retraction mechanism of landing gear is controlled with a slider on a left hand cockpit side With slider in a front position the landing gear is retracted and in a rear position extended A locking lever is provided on a slider grip The landing gear is extended by shifting the slider grip 8 inboard and backward not touching the lever 7 The extended landing gear is correctly locked when after pushing the slider home to its extreme position a characteristic knock can be heard and slider can not be moved Unlocking of landing gear mechanism is achieved by pressing the lever When retracting it is recommended to pull first the slider grip slightly back unlock the mechanism at this position and next to push the slider forwards not touching the lever 7 On pushing the slider home forwards lock the landing gear by re setting the slider grip to the left towards the cockpit side board outboard The doors of landing gear house are closed automatically with aid of loading spring NOTE Pressing the locking lever while on ground may
23. g water icing valve malfunction or tension member break If after discharge of water ballast a sailplane longitudinal balance has changed distinctly to tail heavy the following procedure should be employed re set several times the valves control handle between the front and aft positions leave the control handle in aft position all valves open continue flight avoiding sailplane stall and spin WARNING Pilot below 70 kg 154 Ib should land on the nearest airfield 3 7 4 Landing with main wheel retracted Landing with undercarriage retracted is allowed only if correct extending and locking it is impossible Prior to landing the water ballast must be jettisoned During landing with undercarriage retracted select the possibly smooth grass surface or a soft ploughed field land against the wind touch down with care avoid heavy or pancake landing 3 7 5 Landing with ground loop If it is unavoidably necessary in landing to shorten the ground run e g to avoid collision with an obstacle a controlled ground loop should be made as follows bank the glider towards a wing opposite to an obstacle and in case of cross wind component against the wind if at all possible in line with turning release the stick forward and deflect the rudder opposite to the turn Revision No page 3 6 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECTION 3 SZD
24. h Joint Airworthiness Requirements for Sailplanes and Powered Sailplanes JAR 22 Amendment 7 of 1 September 2003 and gained Type Certificate No BG 203 1 Category of Airworthiness Utility 1 3 Warnings cautions and notes The warnings cautions and notes used in the Flight Manual are defined as follows WARNING means that non observation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION means that non observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight safety NOTE draws the attention on any special item not directly related to safety but which is important or unusual Revision No page 1 2 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECTION SZD 56 2 Diana 2 GENERAL 1 4 Descriptive and technical data SZD 56 2 Diana 2 is a single seat high performance sailplane intended for FAI 15 meter Class Thanks to its high performances Diana 2 is especially suitable for competition flying Sailplane constructed of carbon aramide epoxy composites with sandwich structures employing hard PVC foam core Monocoque structure fuselage of characteristic silhouette aft of the cockpit area passing in a small diameter tube Over the wing portion the fuselage spar ends are protruding out from the fuselage Two panel wing of multi tapered outline employs
25. iana 2 WEIGHT AND BALANCE TAIL BALLAST f WING BALLAST with back rest tail ballast Ib 0 50 100 150 200 250 300 350 400 450 500 550 wing ballast Ib TAIL BALLAST f WING BALLAST without back rest head rest only 14 00 12 00 10 00 Cc 8 00 6 00 tail ballast Ib 0 50 100 150 200 250 300 350 4004 450 500 550 wing ballast Ib Revision No Issued March 1 2006 page 6 5 Biuro Projektowe B SECTION 6 Ruwe FLIGHT MANUAL Bogumit Bere WEIGHT AND BALANCE SZD 56 2 Diana 2 Intentionally left blank Revision No page 6 6 Issued March 1 2006 Biuro Projektowe B SECTION 7 Bogumit Beres FLIGHT MANUAL AILPLANE CRIPTI SZD 56 2 Diana 2 S DER ON SECTION 7 7 SAILPLANE AND SYSTEMS DESCRIPTION 7 1 Introduction 7 2 7 2 Cockpit controls 7 2 7 2 1 Aileron amp elevator control 7 2 7 2 2 Rudder 7 2 7 2 3 Wing flaps 7 2 7 2 4 Longitudinal trim 7 2 7 2 5 Tow release 7 2 7 3 Instrument panel 7 3 7 4 Landing gear 7 5 7 5 Cockpit canopy seat and safety belts 7 5 7 6 Board instrument system 7 5 7 7 Air brake 7 6 7 8 Baggage compartment 7 6 7 9 Water ballast system 7 6 7 10 Miscellaneous equipment 7 6 7 10 1 Transceiver 7 6 7 10 2 Ventilation 7 6 Revision No 7 1 Issued March 1 2006 page Biuro Projektowe B SECTION FLIGHT MANUAL Bogumi Bere SAILPLAN
26. imum speed and the take off run distance are rising as well General guidelines on water ballast application Taking the decision on using water ballast it is to remember that the maximum allowed sailplane weight as well as the range of permissible C G position may not be exceeded when filling the tanks in wing and in tail Revision No page 4 10 Issued March 1 2006 Biuro Projektowe B SECTION 4 Bogumi Bere FLIGHT MANUAL SZD 56 2 Diana 2 NORMAL PROCEDURES Tables and formulas allowing to select the correct amount of water ballast are given in Section 6 of this Manual as well as in Section 4 of Technical Service Manual Only plain filtered water should be used when filling the tanks Flying with water ballast allowed only at temperatures above 0 C 32 FJ WARNING Water freezing may result in a serious damage to sailplane internal structure getting flooded incorrect C G position water valves blocking etc The following table located on a right hand cockpit side wall allows to find the limit altitudes for flight with water ballast in the absence of board thermometer MAX FLIGHT ALTITUDE WITH WATER BALLAST Wa FLIGHT ALTITUDE WITA WATER BALLAST un eneee ongona ses ses 61 oo os A A A Filling the wing tanks Tanks in the right and left hand wing panels are independent valves opening and closing symmetrically mechanical interconnection Start filling with the fron
27. ion release stick forwards until the rotation ceases center the rudder with simultaneous pulling out of ensuing dive The recovery ensues without significant delay Revision No Issued March 1 2006 page 3 3 Biuro Projektowe B SECTION FLIGHT MANUAL Bogumit Beres EMERGENCY PROCEDURES SZD 56 2 Diana 2 3 6 Recovery from spiral dive Depending on aileron and wing flap position in a spin sailplane can pass into spiral dive Recovery from this flight condition should be accomplished as follows wing flaps neutral ailerons neutral rudder neutral release the stick slightly forwards and gently pull out of dive controlling the airspeed 3 7 Other emergencies 3 7 1 Landing with water ballast For the sake of landing gear loads landing with water ballast should be restricted to the indispensable cases e g balked take off malfunction of ballast tanks valve control unsuccessful take off for competition task Approach at speed raised by 10 20 km h 5 11 kt Touch down with care preferably on a paved runway Cross wind heavy and pancake landing should be avoided 3 7 2 Flight and landing with asymmetric water ballast For the sake of design characteristics appearance of asymmetric water ballast in a normal operation carried in accordance with sailplane manuals is not much probable Slight asymmetry to wing ballast distribution remains in general imperce
28. ith loading plan given in Section 6 of this Manual Check the C G position see TECHNICAL SERVICE MANUAL Section 4 4 Correct filling of water ballast tanks 5 Transportation tail wheel removed 6 Back rest correctly mounted and secured 7 Parachute condition Procedures before take off The list of inspection procedures to be followed immediately before take off has been enclosed at the base of instrument panel PRE FLIGHT CHECKLIST 1 Ballast ventilation CHECK lateral balance CHECK 2 Transport tail wheel removed CHECK 3 No loose items in a cockpit CHECK 4 Parachute PUT ON 5 Safety belts FASTEN 6 Landing gear locking CHECK 7 Controls full deflection CHECK 8 Air brake RETRACT 9 Trimming device for take off SET 10 Wing flaps for take off SET 11 Altimeter setting CHECK 12 Cockpit canopy CLOSE 13 Transceiver CHECK 14 Towing rope connection CHECK page 4 6 Revision No Issued March 1 2006 Biuro Projektowe B SECTION 4 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 NORMAL PROCEDURES 4 5 Normal procedures and recommended speeds 4 5 1 Aerotowed take off and climb In aerotowed take off with water ballast recommended tug airplane with possibly high thrust ensuring high acceleration over the first phase of ground roll avoid take off from high grass especially with cross wind take off against the wind in case of cross wind take off allowed with cross wind com
29. iven for particular wing flap settings both in straight flight and in circling flap 283 kg 624 1b 500 kg 1102 Ib setting straight flight circling 4 45 straight flight circling 459 km h kt km h km h km h kt 44 49 2 e os Landing gear extending does not affect the stall speeds value Altitude loss during recovery from stall depends on the actual glider loading and is contained within the range up to 90 m 300 ft approx 5 3 Additional non approved information 5 3 1 Demonstrated cross wind performance The correct sailplane behaviours in take off and landing have been demonstrated at cross wind component of in aerotowed take OfF 1 2111111 17 km h 9 kt MO to 17 km h 9 kt Revision No Issued March 1 2006 page 5 3 Biuro Projektowe B SECTIONS FLIGHT MANUAL Bogumit Beres PERFORMANCES SZD 56 2 Diana 2 5 3 2 Polar speed calculated 36 0 kg m 2 312 kg 57 7 kg 28 0 kg m 2 242 kg m S m S m S DIANA 2 CALCULATED SPEED POLARS V km h s w m Revision No page 5 4 Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL RZN SZD 56 2 Diana 2 RFORMAN 140 130 534 Ib 687 lb 120 110 5 73 Ib ft 2 7 38 Ib ft 2 m S 11 81 Ib ft 2 1102 lb DIANA 2 CALCULATED SPEED POLARS 60 70 80 90 100 V knots 50 40 30 10
30. k pushed completely forward until raising a tail before lifting the tail the ground roll direction is to be corrected with resolute full deflections of rudder in most cases however this is not necessary since soon after ground roll start the sailplane is lifting the tail and becomes laterally and directionally more stable In case of change to direction in ground roll by more than 20 30 or touching ground with a wing right after starting the ground roll take the following action without delay o release the towing rope maintain the control stick pushed forwards onto stop o apply aileron opposite to bank o use the wheel brake after lifting the tail control the ground roll direction with gentle rudder deflections after lifting the tail if wings are maintained level no distinct bank sailplane response to control deflection is positive and with no delay on lifting off and gaining safe altitude above ground the wing flap deflection may be reduced so to reduce the aileron control force maintaining at the same time a good visibility of tug plane at an altitude of approx 150 m 330 ft retract the landing gear and correct the longitudinal trim Recommended aerotow speed is without ballast 110 120 km h 59 65 kt with ballast 120 130 km h 65 70 kt NOTE In case of touching ground with a wing and change to the direction by page 4 8 more than 15 release the towing rope immediately and
31. l piloting skill The sailplane maintained in correct attitude behind a tug airplane is directionally and laterally stable on lifting off and gaining safe altitude above ground the wing flap deflection may be reduced so to reduce the aileron control force maintaining at the same time a good tug plane visibility setting the climbing flight parameters it is recommended to continue the flight at 10 through 12 flap setting over the whole take off run from ground roll start until gaining safe altitude it is not recommended to take any action different from these indispensable to conduct take off Do not retract landing gear change wing flap position etc Revision No Issued March 1 2006 pace as Biuro Projektowe B SECTION 4 RMAL PROCEDURES FLIGHT MANUAL Bogumit Beres O e SZD 56 2 Diana 2 In aerotowed take off without water ballast position the sailplane into a wind as far as possible for take off ground roll select a dry hard and flat terrain set the wing flaps at no more than 14 the optimum range however is 8 through 3 set the trimming device for take off To do so press the trim lever on control stick set control stick at 30 per cent of full deflection range from its foremost position and release the trim lever set the stick to aileron neutral position check visually on a wing keep your left hand close to release hand grip ground roll to be initiated with the control stic
32. mount through the funnel inserted into the filler An eventual excess of water flows out through the venting opening Jettison of ballast water Discharge of ballast water is controlled by means of lever located on the cockpit right hand side Rotating the short lever backwards results in opening of discharge valves of wing rear tanks Rotating the long lever backwards results in opening the discharge valves of wing front and rear tanks together with the tail tank valve Water outflow can be stopped 1 e the discharge valves of wing and tail tanks closed by rotating the appropriate lever of water discharge control forwards It is not possible to discharge the water from wing front tanks without discharging first the water from wing rear tanks Water from wing tanks flows partially on the wing bottom surfaces and fuselage Water outflow remains imperceptible from the cockpit Time of water complete jettison depends on the amount of water With wing tanks full it takes approx 3 minutes jettison of water from tail tank is accomplished in shorter time Revision No page 4 12 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECTION 4 SZD 56 2 Diana 2 NORMAL PROCEDURES 4 5 6 High altitude flight One should keep in mind that in line with increasing flight altitude the true airspeed is higher than this indicated one Therefore the maximum allowed airspeed Vue must be reduced according
33. nce White arc 92 224 50 121 Positive flap operating range Lower limit is 1 1Vso in landing configuration at maximum weight upper limit is maximum speed permissible with flaps extended positive Green arc 111 198 60 107 Normal operating range Lower limitis 1 1Vs at maximum weight and most forward C G with flaps neutral upper limit is rough air speed Yellow arc 198 277 107 149 Manoeuvres must be conducted with caution and only in smooth air radial Red 277 149 Maximum speed for all operations line Yellow 94 51 Approach speed at maximum weight triangle without water ballast Vsi glider stalling speed in a given flight configuration Vso Stalling speed in a landing configuration at maximum weight and most forward C G position Revision No page 2 4 Issued March 1 2006 Biuro Projektowe B Bogumil Beres FLIGHT MANUAL SECTION SZD 56 2 Diana 2 LIMITATIONS ES knots 60 winter Fig 2 1 Airspeed indicator marking Revision No Issued March 1 2006 page 2 5 Biu
34. ned water outflow from one of wing tanks during water ballast discharge When an increasing tendency to bank appears after opening the valves the following should be observed retard landing if at all possible resign the accelerated descent with air brake extended or even make use of ascending air current to climb maintain the forced bank towards the light wing avoid sailplane stall especially in turns towards the heavy wing if after approx 10 minutes the asymmetry ceases gradually flight task can be continued acc to the program if after approx 10 minutes the asymmetry remains unchanged or is increasing further turn to the nearest airfield and report necessity of emergency landing Touch down to be accomplished with sailplane bank towards the light wing at raised speed and at a safe distance from obstacles on a heavy wing side If in ground roll sailplane will bank towards the heavy wing immediately deflect the rudder to the opposite side and release the stick forwards Braking on the main wheel facilitates maintaining the direction in ground roll Even with ventilation holes choked entirely the time for water ballast discharge does not exceed 10 minutes Revision No Issued March 1 2006 page 3 5 Biuro Projektowe B EN SZD 56 2 Diana 2 3 7 3 Flying and landing with tail water ballast The tail ballast tank can remain not drained due to e
35. nst dust and dirt Immobilize the control surfaces Protect the canopy with a flannel cover In case the open trailer is used the external surfaces of sailplane main components should be protected with individual covers and in case of rain with a plastic foil 8 5 Cleaning and care Moisture and direct sunlight have a harmful effect on composite material and lacquer coat therefore for modern sailplanes the proper maintenance and care are necessary Revision No Issued March 1 2006 page 8 3 Biuro Projektowe B SECTIONS ANCE FLIGHT MANUAL Bogumit Beres SAILPLANE MAINTEN SZD 56 2 Diana 2 In particular high moisture combined with high temperature should be avoided e g poorly ventilated trailer with accumulated moisture exposed to sun rays If the moisture penetrates into the hardly accessible structure areas the glider should be de rigged and its wet components stored in a dry room to get dried In case of soiling the external surfaces e g with insects it is recommended to wash these with a clear water with a gentle detergent without an abrasive agent Wipe the washed area with a flannel rag or shammy Dry the wet sailplane interior air brake boxes make sure the drainage openings are free The lifting surfaces should be polished time to time with a polishing paste chord wise direction movement mechanically or manually with a special slat NOTE For lifting surfaces polishing only the non silice
36. o Projektowe B Bogumil Beres FLIGHT MANUAL SECTION SZD 56 2 Diana 2 LIMITATIONS 2 2 Airspeed Airspeed limitations and their operational significance are shown below Do not exceed this speed in any operation and do not use more than 277 149 1 3 of control deflection 198 107 Do not exceed this speed except in smooth air and then only with caution Examples of rough air are lee wave rotor thunderclouds etc Manoeuvring speed 198 107 Do not make full or abrupt control movement above this speed because under certain conditions the sailplane may be overstressed by full control movement Ver Maximum Do not exceed these speeds with the flap extended speed given flap setting 2 0 8 Do not exceed this speed during aerotowing Vr Maximum 139 75 aerotowing speed Vio Maximum landing 200 108 Do not extend or retract the landing gear operating speed gear above this speed Revision No 53 Issued March 1 2006 page lt Biuro Projektowe B RAA xa FLIGHT MANUAL Bogumi Bere SZD 56 2 Diana 2 In the following table the allowed Vye values for various flight altitudes are given U Absolute flight altitude 0 2 S Absolute eas altitude 13 1 16 4 19 7 26 2 soar oe oof fm 2 3 Airspeed indicator markings Airspeed indicator markings and their colour code significance are shown below IAS value or range Marking km h kt Significa
37. o and the date will be shown on the bottom left hand of the page Rev Affected Affected Date of nal Date of Date of Sienie No Section Page Issue PP Approval Insertion E Revision No page 0 2 Issued March 1 2006 Biuro Projektowe B Bogumit Beres SZD 56 2 Diana 2 0 2 List of effective pages Pa Te oe se ne To Revision No Issued rs 0 3 0 4 0 5 0 6 1 1 1 2 1 3 1 4 1 5 1 6 2 1 Appr 2 2 Appr 2 3 Appr 2 4 Appr 2 5 Appr 2 6 Appr 2 7 Appr 2 8 Appr 2 9 Appr 2 10 3 1 Appr 3 2 Appr 3 3 Appr 3 4 Appr 3 5 Appr 3 6 Appr 3 7 Appr 3 8 4 1 Appr 4 2 Appr 4 3 Appr 4 4 Appr 4 5 Appr 4 6 Appr 4 7 Appr 4 8 Appr 4 9 Appr 4 10 Appr 4 11 March 1 2006 FLIGHT MANUAL 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 Appr 4 12 Appr 4 13 4 14 5 1 Appr 5 2 Appr 5 3 5 4 5 5 5 6 6 1 6 2 SECTION 0 ISSUANCES 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006 01 03 2006
38. o stall Diana 2 behaves normally in a way representative for most sailplanes When stalled the sailplane falls symmetrically or with a tendency to drop the wing The stall warning is present in the whole range of C G positions the clear stall warning buffeting occurs at airspeeds higher by approx 5 km h 3 kt than the values given in the table item 5 2 2 Side slip This sailplane performs a very flat inefficient side slip Side slip in a landing configuration air brake and undercarriage extended flaps at 28 setting is inefficient as a manoeuvre aimed to increase sink speed This may be safely performed within the airspeed range from the recommended approach speed up to the Vre 224 km h 121 kt value In a steep dynamic slip a reversal of rudder control force will appear The pulling force is low and does not hinder piloting In steady flight conditions force reversal does not appear Releasing the controls in a slip results in sailplane transition to symmetrical flight Partial or full water ballast does not affect the sailplane slip characteristics The readings of airspeed indicator in a slip are approx 5 through 20 km h 3 through 11 kt below the real values Revision No Issued March 1 2006 page 4 9 Biuro Projektowe B SECTION 4 i FLIGHT MANUAL Bogumit Beres NORMAL PROCEDURES SZD 56 2 Diana 2 4 5 3 Approach Decision on landing despite sailplane high glide ratio should be
39. ous agents are allowed The remnants of adhesive tape should be cleaned with extraction gasoline Canopy perspex should be cleaned with a special care agent or with a large amount of clear water In no case the dry rag or similar can be used for removal of dust and dirt Protect the canopy glassing against dust or sun with a flannel cover The safety belts should be regularly inspected against tear or wear evidence corroded fittings etc Check from time to time the correct functioning of belts fastener Revision No page 8 4 Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL NE 9 SZD 56 2 Diana 2 UPPLEMENTS SECTION 9 9 SUPPLEMENTS 9 1 Introduction 9 2 9 2 List of inserted supplements 9 2 9 3 Supplements inserted 9 2 Revision No Issued March 1 2006 page 9 1 Biuro Projektowe B EM FLIGHT MANUAL Bogumi Bere SUPPLEMENTS SZD 56 2 Diana 2 9 1 Introduction This Section contains the supplements necessary to safely and efficiently operate the sailplane when equipped with various optional systems and equipment not provided with the standard sailplane 9 2 List of inserted supplements Date of insertion Doc No Title of the inserted supplement 9 3 Supplements inserted Revision No page 9 2 Issued March 1 2006
40. pection Reliable securing of the wing and tailplane bolts Reliable securing of the flaperon through the fuselage top access hole and elevator controls Condition of canopy correct closing and opening and condition of its emergency jettison system Cockpit interior position of pedals back rest locking safety belts lack of loose items Unrestricted deflections and plays in control systems of flaperon rudder stabilizer and air brake Correct operation of longitudinal trim system Undercarriage condition wheel rollability wheel tyre pressure by eye cleanness of the undercarriage well deflection of shock absorber Operation and efficiency of wheel brake Condition and operation of tow release Water ballast system symmetric operation i e opening and closing of discharge valves correct tanks filling valves and fillers leak proof venting openings clear Instruments pressure ports battery connection Transceiver make a communication test Revision No Issued March 1 2006 page 4 5 Biuro Projektowe B SECTION 4 Ruwe FLIGHT MANUAL Bogumit Bere NORMAL PROCEDURES SZD 56 2 Diana 2 4 4 Pre flight inspection Inspection before flight Prior to flying check what follows 1 Locking of assembly bolts connection and in control systems 2 Unrestricted deflection of control surfaces over the full range of deflection angles and control forces 3 Check if sailplane loading conforms w
41. ponent not exceeding 5 m s 10 kt prior to take off with water ballast a lateral balance of sailplane should be checked with wings level position the sailplane exactly into a wind for take off ground roll select a dry hard and flat terrain set the wing flaps at no more than 21 in case of lower amount of water ballast 14 or 8 for aerotow employ the towing rope of 30 m 98 ft length at minimum ground roll should be initiated with stick pushed completely fore until rising the tail before lifting the tail control the ground roll direction with resolute full deflections of rudder if this does not inadvertently affect the ground roll raising the tail may be agitated by delicate braking on main wheel In case of change to direction in ground roll by more than 15 20 or touching ground with a wing right after starting the ground roll take the following action without delay o release the towing rope maintain the control stick pushed forwards onto stop o aileron opposite to bank may be used but due to high lateral inertia of wing with water ballast efficiency of this manoeuvre is limited o use the wheel brake after lifting the tail control the ground roll direction with gentle rudder deflections after lifting the tail if wings are maintained level no distinct bank sailplane response to control deflection is positive and with no delay Maintaining the attitude does not require an exceptiona
42. ptible to a pilot and does not significantly affect the flight or landing safety Higher degree of asymmetry results in a distinct sailplane tendency to bank This tendency depends on wing flaps setting and airspeed With ballast tank full in one wing panel and empty in the second the aileron opposite full deflection is necessary when approaching the stall speed At stall speed there is a tendency to bank towards heavy wing The correct controls action will result in regaining the level flight Turns towards the light wing are recommended Revision No page 3 4 Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL SECTION 3 SZD 56 2 Diana 2 EMERGENCY PROCEDURES Asymmetry can appear due to 1 Water outflow on one side through the leaky valve in one wing The asymmetry can increase gradually until reaching the full empty configuration of corresponding front or rear wing tanks In case of increasing sailplane tendency to bank the following procedure should be employed open all discharge valves maintain the forced slight bank of sailplane towards the light wing avoid sailplane stall especially in turns towards the heavy wing change to lateral balance must be observed on regaining the correct lateral balance discharging of the water ballast can be stopped and the flight task can be continued acc to the program 2 The lack of or restrai
43. result in landing gear retraction and damage to the doors of landing gear house The brake of main wheel is activated with a lever located on the air brake slider This lever is used also to lock the air brake in its retracted position 7 5 Cockpit canopy seat and safety belts Canopy opening fore upwards is enabled after shifting the lock levers white up The canopy is retained in opened position by means of a gas spring The cockpit provides space for pilots up to 185 cm 6 ft in height with a back parachute The thickness of parachute or back cushion may not be less than 12 cm 4 7 in Cockpit adjustment to the pilot s height can be obtained on the way of pedals adjustment paragraph 7 2 2 and adequate adjustment of back rest on ground only The mounting bolts of back rest must be arranged symmetrically and correctly mate with the openings The adjustable head rest is provided on a back rest The four point safety belts are included in sailplane standard equipment 7 6 Board instrument system The board instrument system contains see drawing item 7 3 instrument panel 1 compensating bottles 9 two Static pressure ports in fuselage front part 11 total pressure port in fuselage nose 12 additional pressure port nest for special instruments 13 hose joint 7 enabling disconnection of the instrument panel from sailplane drainage units of the total and static pressure ducts a
44. rmissible water ballast in a wing MAX WATER BALLAST IN WING kg cockpit useful load kg kg 55 60 65 70 75 so 85 90 95 100 105 110 115 248 220 Revision No Issued March 1 2006 page 6 3 Biuro Projektowe B SECTION 6 WEI AND BALAN FLIGHT MANUAL Bogumit Beres our p CE SZD 56 2 Diana 2 6 3 Tail ballast limitations NOTE Using the higher amount of tail ballast than resulting from the following diagrams is forbidden this involves a risk of exceeding the approved rearmost CG position thus operating the sailplane beyond the verified and approved operating limitations range Procedure to determine the tail ballast basing on the following diagram e from point A corresponding to the actual amount of wing ballast draw a vertical line to intersection with curve corresponding to the cockpit load point B e on a vertical axis find the maximum permissible amount of tail ballast for the actual loading condition point C TAIL BALLAST f WING BALLAST with back rest tail ballast kg 0 50 100 150 00 250 wing ballast kg TAIL BALLAST f WING BALLAST without back rest head rest only tail ballast kg 0 50 100 150 200 250 wing ballast kg page 6 4 Revision No Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL SECTION 6 SZD 56 2 D
45. ro Projektowe B I s FLIGHT MANUAL Bogumi Bere N SZD 56 2 Diana 2 2 4 Weight kg Ib Maximum take off weight without water ballast 297 655 with water ballast 500 1102 Maximum landing weight 500 1102 Maximum weight of all non lifting parts 90 198 Maximum water ballast in wing tanks 248 547 Maximum water ballast in tail tank 5 6 12 3 Maximum weight in baggage compartment 5 0 11 2 5 Centre of gravity The limits of in flight permissible C G position have been defined as follows front limit 0 2017 m 7 94 in aft of DP corresponding to 19 per cent of MSC rear limit 0 3618 m 14 24 in aft of DP corresponding to 45 per cent of MSC Datum Point stands for Datum Point wing leading edge at root rib MSC stands for Mean Standard Chord page 2 6 Revision No Issued March 1 2006 SECTION 2 LIMITATIONS FLIGHT MANUAL Biuro Projektowe B Bogumit Beres SZD 56 2 Diana 2 195 175 mu kg 425 415 405 395 385 my Ib Fig 2 2 Allowed C G range at different empty weights X empty sailplane C G my empty weight Example of C G position calculation is given in Section 4 Technical Service Manual of 56 2 Diana 2 SZD Revision No Issued page 2 7 March 1 2006 Biuro Projektowe B I E FLIGHT MANUAL Bogumit Beres N SZD 56 2 Diana 2 2 6 Approved manoeuvres This sailplane has
46. roduction 3 2 3 2 Canopy jettison 3 2 3 3 Bailing out 3 3 3 4 Stall recovery 3 3 3 5 Spin recovery 3 3 3 6 Spiral dive recovery 3 4 3 7 Other emergencies 3 4 3 7 1 Landing with water ballast 3 4 3 7 2 Flying and landing with asymmetric water ballast 3 4 3 7 3 Flying and landing with tail water ballast 3 6 3 7 4 Landing with main wheel retracted 3 6 3 7 5 Landing with ground loop 3 6 3 7 6 Break or inadvertent release of towing ropee 3 7 3 7 7 Water jettison at temperatures below 0 C 3 7 Revision No 1 Issued March 1 2006 page 3 Biuro Projektowe B SECTION FLIGHT MANUAL Bogumit Beres EMERGENCY PROCEDURES SZD 56 2 Diana 2 3 1 Introduction Section 3 provides checklist and amplified procedures for coping with emergencies that may occur CHECKLIST EMERGENCY PROCEDURES 1 CANOPY JETTISON Open canopy locks pull the emergency jettison grip onto stop push the canopy upwards 2 BAILING OUT jettison the canopy release the safety belts pull up the legs and exit cockpit watch the wings and tail surfaces Open a parachute 3 SPINNING wing flaps neutral allerons neutral rudder opposite to rotation release stick forwards until rotation ceases center rudder pull out of dive 3 2 Canopy jettison To jettison the canopy in an emergency open canopy locks white colour on canopy frame pull onto stop the emergency jettison grip red
47. t tanks in a wing If the predicted amount of wing water ballast exceeds 162 8 litre 43 0 gal the wing rear tanks are to be filled as well The total capacity of wing tanks ranges 248 litre 65 5 gal The sequence of operations in filling wing tanks is the same for the front and for the rear ones When filling the wing tanks set the sailplane level with no bank support the wing with a brace or by hand close the discharge valves insert a funnel into filler choke the rear tank inlet in a funnel with a plug open the venting orifice located in safety valves Revision No Issued March 1 2006 page 4 11 Biuro Projektowe B SECTION 4 i FLIGHT MANUAL Bogumit Beres NORMAL PROCEDURES SZD 56 2 Diana 2 pour the water in measured amount or brim full until obtaining the continuous outflow from the filler repeat this procedure for filling the wing rear tanks WARNING Never fill the tanks with water supply hose inserted directly into tank filler having filled the tanks remove funnels and close valves Filling the tail ballast tank Tail tank is installed at the base of the fin filler on the right hand fin surface The discharge valve of tail ballast tank is opened every time the valves of wing front tanks are being opened controls interconnection NOTE Tail ballast tank should be filled as a rule after filling the wing tanks Pour water in the measured a
48. the grip To connect the rope pull on the yellow grip insert a rope link and release the grip Next check the correct connection of rope Revision No page 7 2 Issued March 1 2006 Biuro Projektowe B SECTION 7 Bogumit Beres FLIGHT MANUAL AILPLANE CRIPTI SZD 56 2 Diana 2 S P gt EN 7 3 Instrument panel The instrument panel 1 with standard equipment comprises the following set of board instruments see drawing altimeter 60 mm diameter 2 airspeed indicator 60 mm dia 3 variometer 10 m s 2000 ft mint 4 compass KI 13A 10 compensator of total energy variometer KWEC 2 8 8 4 3 N 2 lt A 2 ee we Fig 7 1 Scheme of board instrument system Revision No Issued March 1 2006 page 7 3 SECTION 7 SAILPLANE DESCRIPTION PORADA PONAR NO 101 A O FLIGHT MANUAL Biuro Projektowe B Bogumit Beres SZD 56 2 Diana 2 12 13 14 15 16 17 N 18 19 20 Fig 7 2 Cockpit view Canopy Canopy hinge Wing flap control handle Wheel brake handle Air brake control lever Tow release grip Landing gear locking lever Landing gear extension retraction slider Pedal adjustment grip Head rest adjustment Head rest page 7 4 12 13 14 15 16 17 18 19 20 21 22 P
49. to the table item 2 2 of this Manual 4 5 7 Flight in rain When flying in rain a degradation to sailplane performances should be taken into account In circling and in approach increase airspeed by approx 10 km h 5 4 kt In poor visibility or with foggy canopy glassing open the side window and cockpit ventilation valve It is recommended to remove the rain drops and dry the sailplane prior to take off Do not enter the icing condition zones with a wet glider Revision No 4 1 Issued March 1 2006 page 4 13 Biuro Projektowe B SECTION 4 jektowe FLIGHT MANUAL Bogumi Bere NORMAL PROCEDURES SZD 56 2 Diana 2 Intentionally left blank Revision No 4 14 page Issued March 1 2006 Biuro Projektowe B Bogumit Beres FLIGHT MANUAL IS SZD 56 2 Diana 2 RFORMAN SECTION 5 5 PERFORMANCES 5 1 Introduction 5 2 5 2 Approved data 5 2 5 2 1 Airspeed indicator system calibration 5 2 5 2 2 Stall speeds 5 3 5 3 Additional non approved information 5 3 5 3 1 Demonstrated cross wind performance 5 3 5 3 2 Flight polar calculated 5 4 5 3 3 Data on optimum use of wing flap 5 6 Revision No Issued March 1 2006 page 5 1 SECTION 5 Biuro Projektowe B FLIGHT MANUAL Bogumit Beres PERFORMANCES SZD 56 2 Diana 2 5 1 Introduction Section 5 provides approved data for airspeed indicator system calibration and stall speeds This contains also non
50. uipment apart from the listed above contains variometer 5 m s 10 kt compensator of total energy variometer compass first aid kit 2 11 Aerotow The maximum allowed aerotowing speed is as follows Vqr 139 km h 75 kt The towing rope shall be equipped with the weak link of rated strength 690 kg 10 1520 Ib 10 For aerotow the length of tow rope must be at least 30 m 98 ft 2 12 Other limitations WARNING This sailplane is not adapted for winch launched take off WARNING Flying with water ballast at ambient temperature below 0 C forbidden Revision No 2 Issued March 1 2006 page 2 9 Biuro Projektowe B SECTION 2 E FLIGHT MANUAL Bogumit Beres LIMITATIONS SZD 56 2 Diana 2 2 13 Limitations placard This placard is located on the right hand cockpit wall Weight Wal Airspeed AS ion Maximum in flight weight with water ballast 500 without water ballast 297 Cockpit load maximum 115 minimum 55 Weight mer Arepeed TAS a Maximum in flight weight with water ballast 1102 without water ballast 655 Cockpit load 108 maximum 253 minimum 121 Vre 80 20 150 NOTE Further placards see Technical Service Manual Revision No page 2 10 Issued March 1 2006 Biuro Projektowe B SECTION 3 Bogumit Beres FLIGHT MANUAL SZD 56 2 Diana 2 EMERGENT Oe SECTION 3 3 EMERGENCY PROCEDURES 3 1 Int
51. y closed with two grips on canopy frame Emergency jettison accomplished by opening the canopy locks and pulling onto stop the red grip at the base of instrument panel followed by pushing the canopy upwards Control stick on the right hand cockpit side Mushroom type instrument panel The correct pilot s attitude in a cockpit set by means of the on ground adjustable back rest with adjustable head rest or head rest only supplemented with the in flight adjustable pedals Due to cockpit arrangement a pilot higher than 180 cm may find the position in a cockpit with removed back rest more comfortable In such case pilot leans his back against wheel house wall and the head against head rest this latter constituting optional equipment of the sailplane Revision No Issued March 1 2006 page 1 3 Biuro Projektowe B SECTION 1 FLIGHT MANUAL Bogumit Beres GENERAL SZD 56 2 Diana 2 Effective cockpit ventilation is ensured by the nose air intake with control valve side blow with air stream direction and intensity control as well as by the side slide window with deflectable ventilation tab Control systems of elevator rudder flaperon and air brake push rod type Longitudinal trim control spring type Tow release and wheel brake control cable type TECHNICAL DATA Wing profile KL 002 128F 17 at wing root through KL 002 122F 17 at tip ee 7 Dass Jee 2 pa 2 ja Revision No page 1
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