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1. Dive forward greater than 90 Table 41 Classification of a paraglider s behaviour in the big ears test Code de champ modifi Measurement and ranges according to Table 40 Classification Entry procedure Dedicated controls Standard technique No dedicated controls and non standard technique Behaviour during big ears Stable flight Unstable flight Deep stall occurs Recovery Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action between a further 3 s to 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 31 prEN 926 2 2012 E 4 4 21 Big ears in accelerated flight This test is only required for paragliders equipped with an accelerator This test manoeuvre is not required if the manufacturer excludes this manoeuvre in the user s manual and the A risers are clearly marked accordingly When tested in accordance with 5 5 4918 21 the glider s behaviour and handling during and exiting big ears when using the accelerator is measured according to Table 42 and classified according to Table 43 Table 42 Measurements and possible ranges in the big ears in accelerated flight test Measurement Ranges Entry proced
2. Mis en forme Titre 4 prEN 926 2 2012 E 2 5 Keys 1 Flight direction 2 Tolerance field Code de champ modifi Figure 2 Marking of the test specimen Mis en forme Retrait Gauche 0 71 cm Sans numerotation ni puces J 5 3 2 2 Marking of the control lines Mmarkings are required en for the control lines travel lt Mis en forme Sans num rotation ni puces zZero and symmetric stall positions shall be marked The zero position mark is placed at the position of the control lines at which the first action on any point of the trailing edge can be observed There shall be a minimum of 5 cm free control lines travel before the zero mark is reached NOTE To mark zero and symmetric stall positions it is recommended that manufacturers attach an Mis en forme Police 10 pt additional reference line to each side of the paraglider running from the B riser to the seat of the harness and incorporating elastic to maintain tension Each reference line should be fitted with 2 adjustable toggles e g tonkasTM Py When moving the controls to a position to be marked the pilot moves both the controls and the appropriate Mis en forme Police 10 pt tonkas toggles down When releasing the controls again he lets go of the tonkas toggles refer to the Mis en forme Police 10 pt procedure ka Mis en forme
3. Width of harness attachment points Table 48 Total weight in flight prEN 926 2 2012 E TWF total weight in flight 80 kg gt 80 kg 100 kg gt 100 kg Width Measurement A on Figure 54 40 40 2 cm 44 2 cm44 48 2 cm48 Tolerance 2 cm Height Measurement B on Figure 65 40 1 cm40 42 1 cm42 44 1 cm44 Telerange dcr 5 5 7 Ballast Figure 6 Height of harness attachment points Any ballast shall be tightly attached to the pilot and positioned as close as possible to the centre of gravity of a pilot sitting in the harness not carrying any ballast When testing in two seater configuration any ballast carried by the passenger shall be attached following the same principles as for the pilot s ballast The use of water ballast is recommended for safety reasons 5 5 8 Sitting position Unless the test procedure states otherwise the test pilot should adopt a normal upright sitting position with his feet perpendicularly below his knees 43 Code de champ modifi Code de champ modifie Code de champ modifi prEN 926 2 2012 E 5 5 9 Controls in hand Unless the test procedure states otherwise the controls are always held in the pilots hands The term releasing the controls means taking all tension off the control lines 5 5 10 Wraps The test pilot shall never need to us
4. 5 5 Procedure 5 5 1 General Two different test pilots of the testing laboratory each carry out one complete programme of the test manoeuvres laid down in 5 5 4918 one at the minimum weight in flight declared by the manufacturer the other one at the maximum weight in flight declared by the manufacturer Where the declared maximum weight in flight exceeds 170 kg then specified tests shall be conducted at a maximum weight in flight of 170 kg The maximum weight in flight declared by the manufacturer shall not exceed the maximum weight in flight up to which the paraglider is in compliance with EN 926 1 39 prEN 926 2 2012 E In the exceptional case that the minimum weight in flight declared by the manufacturer is less than 65 kg and the testing laboratory cannot provide a light enough test pilot then the test programme at the minimum weight in flight is replaced by a test programme flown at the lowest weight in flight which is achievable The manufacturer is then additionally reguired to demonstrate a test programme at the declared minimum weight in flight This demonstration programme shall be witnessed by a test pilot of the testing laboratory and recorded on video Any test weight in flight up to 125 kg shall be achieved using 1 pilot If any test weight in flight exceeds 125 kg this weight can be achieved using 1 or 2 pilots If any test weight in flight exceeds 155 kg this weight shall be achieved using 2 pilots All weights ar
5. of the span of the paraglider s leading edge is affected If more than 50 of the span is affected this is a cascade 5 195 5 18 Details of test manoeuvres to be carried out 5 5 49 45 5 18 1 Inflation take off test The inflation shall take place on a slope between 10 and 33 90 prEN 926 2 2012 E It shall be carried out in headwinds of less than 8 km h measured about 1 5 m above the ground and shall be repeated twice to ensure the genuine behaviour is established The test pilot uses a normal forward launch technigue controls and A risers in the hands the other risers in the elbows A lines just tight constant steady acceleration If a special take off technique is required for a paraglider then this information shall be contained in the user s manual and these instructions shall be followed by the test pilot Camera axis Camera not reguired 5 5 19 25 5 18 2 Landing test The pilot shall make a normal landing straight final glide at trim speed on level ground into a wind of less than 8 km h measured about 1 5 m above the ground using the controls only If a special landing technique is required for a paraglider then this information shall be contained in the user s manual and these instructions shall be followed by the test pilot Camera axis Camera not required 5 5 19 35 5 18 3 Speeds in straight flight test Assess the trim speed in 10 s stabilised straight flight and then the minimum speed in 10 s s
6. p I Paragliding equipment Date 2012 08 03 Assistant Veronique MEYER Direct line 01 41 62 85 04 veronigue meyer afnor org afnor NOR MAL IS A TTC CEN TC 136 WG 06 Doc Number N 0054 Your contact Aisatou DOUCOURE Direct line 01 41 62 80 86 aisatou doucoure afnor org Draft of FprEN 926 2 for submission to formal vote with marking Commentaries Decisions Forow UP This document presents the final version with marking of prEN 926 2 updated with tje following given to CEN enguiry results and comments on during CEN TC 136 WG 6 meeting in Zurich on July 11th 12th 2012 The WG experts agreed to submit the current version of prEN 926 2 standard to CEN TC 212 for formal vote You are invited to considerate changes made during this meeting decisions taken and submit your comments for no later than August 17th 2012 to aisatou doucoure afnor org Then the project will be sent for formal vote approval to CEN TC 136 2012 08 17 Association Fran aise de Normalisation 11 rue Francis de Pressens F 93571 La Plaine Saint Denis Cedex http www afnor fr SIRET 775 724 818 00205 ENCEN TC 136136 CEN Date 20122012 0202 prEN 926 2 2012prEN 926 2 2012 CENGEN TC 136136 Secretariat DINDIN Paragliding eguipment Paragliders Part 2 Reguirements and test me thods for classifying tiani safety characteristics sParagliding equipment Equipement pour le parapente
7. 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Change of course Changing course less than 45 Changing course 45 or more Cascade occurs No Yes 21 Code de champ modifi Code de champ modifie prEN 926 2 2012 E 4 4 12 High angle of attack recovery When tested in accordance with 5 5 1918 12 the glider s recovery from high angles of attack is measured according to Table 24 and classified according to Table 25 Table 24 Measurements and possible ranges in the high angle of attack recovery test Measurement Ranges Recovery Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action in more than a further 3 s Cascade occurs No Yes Table 25 Classification of a paraglider s behaviour in the high angle of attack recovery test Measurement and ranges according to Table 24 Recovery Classification Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action in more than a further 3 s Cascade occurs No Yes 4 4 13 Recovery from a developed full stall When tested in accordance with 5 5 198 13 the glider s behaviour when recovering from a maintained full stall a
8. Anglais Mis en forme Anglais Mis en forme Anglais 6 Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais 7 Users mamua ETT Na Pb 5348 Mis en forme Anglais 8 Manufacturing RECORD ue UE 5550 Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais prEN 926 2 2012 E Mis en forme Anglais Royaume Uni prEN 926 2 2012 E Foreword This document prEN 926 2 2012 has been prepared by Technical Committee CEN TC 136 Sports play ground and other recreational facilities and equipment the secretariat of which is held by DIN This document is currently submitted to the CEN Enquiryformal vote This document will supersede EN 926 2 2005 This document is one of a series of standards on eguipment for paragliding as follows EN 926 1 Paragliding equipment Paragliders Part 1 Requirements and test methods for structural strength EN 926 2 Paragliding equipment Paragliders Part 2 Requirement
9. More than 50 of the symmetric control travel 25 to 50 of the symmetric control travel Less than 25 of the symmetric control travel Table 31 Classification of a paraglider s behaviour in the directional control with a maintained Code de champ modifi asymmetric collapse test Measurement and ranges according to Table 30 Classification Able to keep course Yes A No F 180 turn away from the collapsed side possible in 10 s Yes A No F Amount of control range between turn and stall or spin More than 50 of the symmetric control travel A 25 to 50 of the symmetric control travel C Less than 25 of the symmetric control travel D 4 416 Trim speed spin tendency When tested in accordance with 5 5 1918 16 the glider s tendency to enter a spin from trim speed is measured according to Table 32 and classified according to Table 33 Table 32 Measurements and possible ranges in the trim speed spin tendency test Code de champ modifi Measurement Spin occurs Code de champ modifi Measurement and ranges according to Table 32 Spin occurs 27 prEN 926 2 2012 E 4 417 Low speed spin tendency When tested in accordance with 5 5 1918 17 the glider s tendency to enter a spin from low speed is measured according to Table 34 and classified according to Table 35 Table 34 Measurements and possible ranges in the low speed spin tendency test Code de champ modifi Measurement Ranges Spin
10. Parapentes Partie 2 Exigences et proc dures de test pour classification des caracteristi ues de Secure en vo Parle Exlgences el Mis en forme Couleur de police Bleu Mis en forme Couleur de police Bleu Mis en forme Police 10 pt Non Gras Couleur de police Bleu Mis en forme Police 10 pt Non Gras Couleur de police Bleu Mis en forme Couleur de police Bleu V rifier l orthographe et la grammaire Mis en forme Police 10 pt Non Gras Couleur de police Bleu V rifier l orthographe et la grammaire Mis en forme Police 10 pt Non Gras Couleur de police Bleu V rifier l orthographe et la grammaire Mis en forme Police 10 pt Non Gras Couleur de police Bleu Mis en forme Police 14 pt Couleur de police Bleu V rifier l orthographe et la grammaire Mis en forme Police Italigue Couleur de police Bleu V rifier l orthographe et la grammaire Mis en forme Police Italigue Couleur de police Bleu Fran ais France V rifier l orthographe et la grammaire Code de champ modifi Mis en forme Fran ais France Mis en forme Fran ais France Code de champ modifi Descriptors sports qualification safety accident prevention flight classifications testing conditions markings conditions marking Document type European StandardE
11. Police 10 pt If the position of any of these marks obtained at the minimum weight in flight differs noticeably from the Mis en forme Police 10 pt S position obtained at the maximum weight in flight the manufacturer is required to provide the test specimen with a second set of clearly identified marking s pairofidentical controHines or referencetines one marked for the minimum and or the maximum the other one forthe maximum weight in flight To help visualize the glider trajectory a streamer 1 m long and 5 cm wide shall be attached to on one Mis en forme Retrait Gauche 0 risera suitable lineto help visualise the trajectory cm Suspendu 0 71 cm Sans num rotation ni puces 37 prEN 926 2 2012 E 2 5 Keys Eli 2 Tolerance field Fi 2 Marki fl 5 3 3 FoldingtinesAdditional lines 5 3 3 1 General Mis en forme Titre 4 The test house shall determine if it is possible to test the glider in deliberate collapse manoeuvres without additional lines If it is possible to test the glider without the use of additional lines then the glider shall be tested without additional lines 5 3 3 2 Cross lines Cross lines are allowed in all categories only for the large asymmetric collapse test Test according to
12. Uni Page 2 20 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 21 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 22 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 23 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 24 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 25 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 26 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 27 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 28 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 29 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 30 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 31 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 32 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 33 Mis en forme aid 12 07 2012 08 00 00 Anglais Royaume Uni Page 2 34 Mis en forme aid 12 07 2012 08 00 00 Anglais Royaume Uni Page 2 35 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 36 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 37 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 38 Mis en
13. forme B HB Mis en forme m N Mis en forme 13 Mis en forme 14 Mis en forme 15 Mis en forme 16 Mis en forme 17 Mis en forme 18 Mis en forme 19 Mis en forme 20 Mis en forme 21 Mis en forme 22 Mis en forme 231 Mis en forme 241 Mis en forme 125 Mis en forme 26 Mis en forme 27 Mis en forme 28 Mis en forme 29 Mis en forme 30 Mis en forme 31 Mis en forme 32 Mis en forme 33 UJ Mis en forme Mis en forme 35 Mis en forme 36 Mis en forme 137 Mis en forme 38 Mis en forme 39 Mis en forme 140 Mis en forme 41 Mis en forme 42 Mis en forme 43 Mis en forme 44 Mis en forme 145 Mis en forme 146 Mis en forme 47 Mis en forme 48 Code de champ modifi 49 Mis en forme 50 Code de champ modifi I51 prEN 926 2 2012 E 5 5 6 Harness diMENSiOi Sikatan mas ias adiaka i rras diirai 4137 Mis en forme Fran ais France 5 5 7 Ballast 4338 Code de champ modifie Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme Anglais Mis en forme
14. forme aid 12 07 2012 08 00 00 Anglais Royaume Uni Page 2 39 Mis en forme aid 12 07 2012 08 00 00 Anglais Royaume Uni Page 2 40 Mis en forme aid 12 07 2012 08 00 00 Anglais Royaume Uni Page 2 41 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 42 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 43 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 441 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 45 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 46 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 471 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 48 Mis en forme aid 11 07 2012 12 43 00 Fran ais France Page 2 49 Modifier Unknown Code de champ modifi Page 2 50 Mis en forme aid 11 07 2012 12 43 00 Fran ais France Page 2 51 Modifier Unknown Code de champ modifi
15. the roll angle Then observe the glider s immediate behaviour Camera axis Any axis 5 19 85 5 18 8 Stability in gentle spirals test Stabilise the glider in straight flight at trim speed By use of the controls only direct the paraglider into a gentle spiral between 3 m s and 5 m s sink rate such that the least stable behaviour least tendency to exit the turn is established Maintain this sink rate for one turn Then release the controls over a period of 2 s and observe the paraglider s behaviour If the turn clearly tightens the pilot acts to recover the glider Otherwise the pilot waits for two turns to establish the glider s behaviour The pilot shall not counteract inertia effects on his body at any stage Camera axis Any axis 5 5 19 95 5 18 9 Behaviour exiting a fully developed spiral dive Stabilise the glider in straight flight at trim speed Without weight shift apply a smooth progressive input with one brake until the glider enters a spiral dive For a valid test the glider should enter the spiral dive after a minimum of 5s and a maximum of 1 5 turns without a spin or collapse occurring The pilot then holds the brake position reached while actively maintaining a central and neutral position relative to the risers as if the harness was cross braced The pilot shall hold this position for 720 then release the initiating brake smoothly and progressively in one turn Whilst releasing the brake the pilot no long
16. 1 07 2012 12 43 00 Anglais Royaume Uni Page 2 2 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 3 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 4 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 5 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 6 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 7 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 8 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 9 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 10 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 11 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 12 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 13 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 14 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 15 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 16 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 17 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 18 Mis en forme aid 11 07 2012 12 43 00 Anglais Royaume Uni Page 2 19 Mis en forme aid 12 07 2012 08 00 00 Anglais Royaume
17. 18 1 to 5 5 4918 23 any failure of any part or component occurs the results of any of the tests 5 5 4918 1 to 5 5 4918 23 are not classified A B C or D In the classification tables in 4 4 1 to 4 4 23 the letter F failed is used to identify unacceptable behaviour 4 4 Flight characteristics 4 4 1 When tested in accordance with 5 5 4918 1 it is found out how difficult it is to take off with this glider including Inflation take off checking for undesirable tendencies The behaviour of the paraglider is measured according to Table 2 and classified according to Table 3 12 Code de champ modifi Table 2 Measurements and possible ranges in the inflation take off test Measurement Ranges prEN 926 2 2012 E Rising behaviour Smooth easy and constant rising no pilot correction reguired is reguired Easy rising some pilot correction Overshoots shall be slowed down to avoid a front collapse Hangs back Special take off technigue reguired Table 3 Classification of a paraglider s behaviour in the inflation take off test Measurement and ranges according to Table 2 Rising behaviour Smooth easy and constant rising Easy rising some pilot correction is reguired Overshoots shall be slowed down to avoid a front collapse Hangs back Special take off technique required 4 4 2 Landing When tested in accordance wi
18. 2 E rie EU 1 DR ES tale tanh VD VD nee Ko DNA TES AO A ON ANS Niu Key prEN 926 2 2012 E BB Pitch angle Figure 14 Illustration of a spiral dive 3 4011 spontaneous recovery without any action on the part of the pilot the paraglider returns to normal flight 3 4412 front collapse front collapse is considered to have occurred when the top surface is visible from the underside of the paraglider NOTE Deformation of the leading edge is not considered to be a front collapse 3 4213 cascade transition from one involuntary abnormal flight condition to another involuntary abnormal flight condition 3 1314 minimum speed slowest airspeed maintainable without entering a deep stall or full stall 3 4415 trim speed airspeed of the paraglider in straight flight without activating the controls or the accelerator 3 4516 maximum speed airspeed of the paraglider in straight flight with the controls in the zero position and the accelerator fully activated NOTE Maximum speed is only used when referring to gliders equipped with an accelerator 3 1617 low speed airspeed of the paraglider in straight flight with the controls at 50 of travel between the zero and the symmetric stall position i e 50 of the symmetric control travel 3 1718 weight in flight total weight mass of the pilot and his entire paragliding equipment including the glider
19. 5 4918 22 are tested in accordance with 5 5 4918 23 The glider should behave during and exit any normal flight procedure and or configuration as described in the manual No procedure should require high levels of pilot skill The behaviour of the paraglider is measured according to Table 46 and classified according to Table 47 Table 46 Measurements and possible ranges when testing any other flight procedure and or Code de champ modifi configuration described in the user s manual Measurement Ranges Procedure works as described Procedure suitable for novice pilots Cascade occurs Table 47 Classification of a paraglider s behaviour when testing any other flight procedure and or Code de champ modifie configuration described in the user s manual Measurement and ranges according to Table 48 Procedure works as described Classification Yes No Procedure suitable for novice pilots Yes No Cascade occurs No Yes 34 prEN 926 2 2012 E 5 Flight tests 5 1 General The behaviour of the paraglider in the programme of test manoeuvres laid down in 5 5 19 18 is demonstrated by a manufacturer s pilot in front of a test pilot of the testing laboratory carrying out the flight tests If this demonstration is judged satisfactory by the test pilot the test procedure described in 5 5 of this document is then carried out by two test pilots of
20. 5 5 18 14 3 5 3 3 3 Folding lines Folding lines shall not be used in categories A B and C gliders In category D gliders folding lines are only permitted in symmetric and asymmetric collapse manoeuvres Test according to 5 5 18 10 and 5 5 18 14 3 If folding lines are used The attached riser shall be longer than the original riser such that the folding line has no effect when not in use 38 prEN 926 2 2012 E for safety reasons the test pilot can hold a longer extra brake handle in his hand There has to be no tension visible on the trailing edge this has to be reported in the User Manual with the attachment and the dimensions lengths of the folding lines specified the maximum rearward position is the position of the original A s the maximum forward position is on the lower surface of the paraglider and not further forward than the rear end of the air inlet In no case may it be further forward than 3 of the chord the additional line attachment points on the glider must be supplied with the production glider as well 5 3 4 Control extensions Where desired for test 5 5 1918 10 control extensions may be used to enable the controls to be held in the pilot s hands throughout the manoeuvres 5 4 Test conditions Meteorological conditions wind less than 10 km h within the test perimeter _ no turbulence within the test perimeter disturbing the flight tests
21. 8 11 Exiting deep stall parachutal stall test Slow down the paraglider using the controls to obtain a trajectory as close as possible to the vertical without significantly changing the shape of the wing deep stall If a deep stall cannot be achieved due to a very long control travel the pilot takes wraps to shorten the control lines If a deep stall is achieved maintain it for 3 s Then release the controls smoothly and gradually in about 2 s to the zero position 47 prEN 926 2 2012 E If the glider does not recover in 5 s then intervene in accordance with the user s manual Camera axis Profile 5 5 19 125 5 18 12 High angle of attack recovery test Attain a trajectory as close as possible to the vertical deep stall without activating the controls or the accelerator and with the minimum amount of deformation of the canopy usually by using the minimum necessary pull down of the B risers Maintain this high condition for 3 s Then release the risers very slowly symmetrically and continuously Camera axis Profile 5 5549435 5 18 13 Recovery from a developed full stall test Stabilise the glider in straight flight at minimum speed Fully apply the controls and hold that position until the paraglider is in a maintained full stall If a full stall cannot be achieved due to a very long control travel the pilot takes wraps to shorten the control lines Release the controls slowiy and symmetrically until the canopy has ap
22. 926 2 2012 E 5 2 2 Ground eguipment The ground personnel shall be eguipped with telephoto video camera to review the movements and actions of the pilot and the behaviour of the paraglider radio link with the test pilot to record his comments directly on the video tape 5 3 Test specimen 5 3 1 Selection Select a test specimen complete with the user s manual in a language acceptable to the testing laboratory ready to fly and conforming in all points to the production model 5 3 2 Marking 5 3 2 1 Marking of the wing 5 3 2 The test specimen supplied by the manufacturer shall be clearly marked in the following way A line must be marked from a point at 50 of the trailing edge at a 45 angle to the leading edge Either side of this line at distances of 1 2 5 of the wingspan with a minimum of 50 cm and maximum of 75 cm measured between the inside of the parallel marks parallel marks must be attached indicating the tolerance area Marks must be contrasting and easily recognisable from the video documentation as shown in Figure 2 A line must be marked from a point of 50 of the leading edge at a 45 angle to the trailing edge There is no need to mark a tolerance field for the asymmetric 50 collapse When agreed by the test centre the marks can only be done on one wing side these positions are percentages of the flat i e non inflated span and are determined with the paraglider laid flat 36
23. O gt Greater than 360 without tendency to recover g force not decreasing rate of turn not decreasing Im Collapse on the opposite side occurs No or only a small number of collapsed cells with a spontaneous re inflation Yes no turn reversal Yes causing turn reversal Twist occurs No Yes Cascade occurs No Code de champ modifie Yes MI Folding lines used Mis en forme Retrait Gauche cm Paragraphes solidaires No Yes Mis en forme Retrait Gauche 1 38 cm Paragraphes solidaires Mis en forme Retrait Gauche 1 38 cm 25 prEN 926 2 2012 E 4 4 15 Directional control with a maintained asymmetric collapse When tested in accordance with 5 5 4918 15 the glider s directional controllability whilst affected by an asymmetric collapse the ability to fly straight and to turn away from the collapsed side is measured according to Table 30 and classified according to Table 31 26 prEN 926 2 2012 E f Table 30 Measurements and possible ranges in the directional control with a maintained Sode de champ mocene asymmetric collapse test Measurement Ranges Able to keep course Yes No 180 turn away from the collapsed side possible in Yes 10s No Amount of control range between turn and stall or spin
24. Table 15 Table 14 Measurements and possible ranges in the roll stability and damping test Code de champ modifi Measurement Ranges Oscillations Reducing Not reducing Code de champ modifi Table 15 Classification of a paraglider s behaviour in the roll stability and damping test Measurement and ranges according to Table 14 Classification Oscillations Reducing Not reducing 4 4 8 Stability in gentle spirals When tested in accordance with 5 5 1918 8 the glider s behaviour during and exiting from gentle spirals is measured according to Table 16 and classified according to Table 17 Table 16 Measurements and possible ranges in the stability in gentle spirals test Code de champ modifi Measurement Ranges Tendency to return to straight flight Spontaneous exit Turn remains constant Turn tightens Code de champ modifi Table 17 Classification of a paraglider s behaviour in the stability in gentle spirals test Measurement and ranges according to Table 16 Classification Tendency to return to straight flight Spontaneous exit Turn remains constant Turn tightens 4 49 Behaviour exiting a fully developed spiral dive When tested in accordance with 5 5 189 9 the glider s behaviour during and exiting from steep spirals is measured according to Table 18 and classified according to Table 19 The G force and or the rate of turn are recorded for documentati
25. all components essential for operation 53 prEN 926 2 2012 E d 54 2 wing span laid flat including stabilisers manufacturer s information 3 projected area manufacturer s information 4 number of cells 5 number of risers 6 trimmers with travel in centimetres If no trimmers are present this fact has to be clearly specified 7 accelerator with travel in centimetres If no accelerator is present this fact has to be clearly specified 8 any other adjustable or removable or variable device with information on adjustment limits if applicable If no such device is present this fact shall be clearly specified 9 dimensioned drawings of all suspension lines including the control lines 10 dimensions shall include both individual section lengths and the overall lengths measured from the lower surface of the canopy to the inside edge of the maillon connecting them to the risers see Annex A 11 line lengths shall be specified when measured under a tension of 50 N this tension being slowly and gradually applied before taking the measurement 12 dimensioned drawings of the risers 13 compliance of the test samples suspension lines control lines and risers with the dimensions given in the user s manual shall be checked by the testing laboratory after the test flights have been completed 14 overall line lengths actually measured shall not differ more than 10 mm from the lengths laid down in the use
26. ay be kept in the hands if the front collapse is achievable without significantly affecting the trailing edge Then by abruptly pulling the appropriate lines or risers induce a symmetric front collapse over the entire leading edge with at least 50 of the centre chord affected As soon as the collapse is achieved let go of the lines risers If the paraglider has not recovered spontaneously after 5 s or after 180 of turn which ever happens first the pilot acts on the controls to recover normal flight without inducing a deliberate stall 5 5 19 10 35 5 18 10 3 Test 3 Accelerated collapse If the paraglider is eguipped with an accelerator then the following additional test is required Stabilise the glider in straight flight at maximum speed Release the controls and attach them to the risers however for safety reasons the controls may be kept in the hands if the front collapse is achievable without significantly affecting the trailing edge Then by abruptly pulling the appropriate lines or risers induce a symmetric front collapse over the entire leading edge with at least 50 of the centre chord affected As soon as the collapse is achieved let go of the accelerator and the lines risers If the paraglider has not recovered spontaneously after 5 s or after 180 of turn which ever happens first the pilot acts on the controls to recover normal flight without inducing a deliberate stall Camera axis Profile 5 5 19 115 5 1
27. be performed without special knowledge or special machinery list of spare parts and information how to obtain them 8 Manufacturing record The manufacturing record supplied by the manufacturer shall contain the following information a name and address of manufacturer b name and address of person or company presenting the paraglider for testing if different from manufacturer c name of model d year four digits and month of manufacture of the sample tested e minimum and maximum total weight in flight f users manual with date of issue and version number g dimensioned and toleranced drawings The drawings are provided in an annex to the manufacturing record They permit the suspension lines to be clearly seen and also give a plan view of all the components of the paraglider If folding lines have been provided for the flight tests their locations must be detailed on the drawings It is possible to provide these drawings on binary media as long as their format is readable with standard office software but the suspension lines and plan view drawings shall necessarily be on paper h list of components and materials All the materials used shall be listed with 1 2 3 4 name of the material name and references of the manufacturer its specific use in the paraglider characteristics and tests carried out on this material by the supplier or manufacturer 55 prEN 926 2 2012 E 9 The
28. chutal stall When tested in accordance with 5 5 1918 11 it is found out how difficult it is to exit a deep stall with this glider including checking for undesirable tendencies The behaviour of the paraglider is measured according to Table 22 and classified according to Table 23 20 Table 21 Classification of a paraglider s behaviour in the symmetric front collapse test Measurement and ranges according to Table 20 Entry Classification Rocking back less than 45 Rocking back greater than 45 Recovery Spontaneous in less than 3 s Spontaneous in 3 sto 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action in more than a further 5 3 s T O O m Dive forward angle on exit Change of course Dive forward 0 to 30 Keeping course Dive forward 0 to 30 Entering a turn of less than 90 Dive forward 0 to 30 Entering a turn of 90 to 180 Dive forward 30 to 60 Keeping course Dive forward 30 to 60 Entering a turn of less than 90 Dive forward 30 to 60 Entering a turn of 90 to 180 Dive forward 60 to 90 Keeping course Dive forward 60 to 90 Entering a turn of less than 90 Dive forward 60 to 90 Entering a turn of 90 to 180 Dive forward greater than 90 Keeping course Dive forward greater than 90 Ente
29. collapse is measured according to Table 28 and classified according to Table 29 If the paraglider is eguipped with an accelerator its behaviour in the asymmetric collapse test shall be classified both with and without its use Table 28 Measurements and possible ranges in the asymmetric collapse test Measurement Ranges Change of course until re inflation Less than 90 90 to 180 180 to 360 Greater than 360 Maximum dive forward or roll angle Dive or roll angle 0 to 15 Dive or roll angle 15 to 45 Dive or roll angle 45 to 60 Dive or roll angle 60 to 90 Dive or roll angle greater than 90 Re inflation behaviour Spontaneous re inflation Inflates in less than 3 s from start of pilot action Inflates in 3 s to 5 s from start of pilot action No re inflation within a further 5 s Total change of course Less than 360 Greater than 360 Collapse on the opposite side occurs No or only a small number of collapsed cells with a spontaneous re inflation Yes no turn reversal Yes causing turn reversal Twist occurs No Yes Cascade occurs No Yes Folding lines used 24 Code de champ modifi i Tableau mis en forme Mis en forme Retrait Gauche 0 2 cm prEN 926 2 2012 E f Table 29 Classification of a paraglider s behaviour in th
30. conformity of the paraglider to the reguirements of this document shall be stated on a stamp or label Marking permanently fixed to the canopy which shall include the following information a 56 manufacturer s name name of person or company having presented the paraglider for testing if different from manufacturer paraglider model name class of the paraglider harness chest strap dimensions distance between center of base of connectors number of this document i e EN 926 2 and issue date references to any other standards the paraglider is in compliance with year four digits and month of manufacture serial number minimum and maximum total weight in flight kg paraglider weight wing lines risers kg projected area m3 number of risers accelerator yes or no trimmer yes or no inspections whichever is earlier 1 number of months 2 number of hours flying time conformity tests carried out by name and address of the testing laboratory unigue identifying test reference number warning Before use refer to the user s manual prEN 926 2 2012 E Annex A norm ative Code de champ modifi Code de champ modifi Measuring suspension line lengths Code de champ modifi Key A Overall suspension line length B Suspension line section length Figure A A 1 Measuring suspension line lengths 57 Page 2 1 Mis en forme aid 1
31. d recommended in the user s manual without affecting the primary controls and perform a 180 turn Wait for 20 s or until the turn is completed Camera axis Any axis 5 49 235 5 18 23 Testing any other flight procedure and or configuration described in the user s manual Check whether every other flight procedure and or configuration described in the user s manual can be flown safely This requirement may be satisfied by the manufacturer producing suitable and acceptable evidence e g video Camera axis Camera not required 6 Test files 6 1 Test file information The test files shall include a version of the current EN 926 2 standard a9b name and address of the manufacturer b c name and address of the person or company presenting the paraglider for testing if different from manufacturer d model and reference of the paraglider tested d e model size dimensions of harness es used during the test e f class of the paraglider tested Pa results of each test programme according to 4 4 1 to 4 4 23 this should include a note detailing whether this test was performed with the use of folding lines or using any other special procedure permitted in the details of test manoeuvres described in 5 5 1918 52 Mis en forme prEN 926 2 2012 E g h name and address of the testing laboratory Hi names of the test pilots dj unique identifying test reference number 6 2 Items accompanying the t
32. e asymmetric collapse test l Measurement and ranges according to Table 28 Classification Change of course until re inflation Maximum dive forward or roll angle Less than 90 Dive or roll angle 0 to 15 Dive or roll angle 15 to 45 Dive or roll angle 45 to 60 Dive or roll angle 60 to 90 Dive or roll angle greater than 90 90 to 180 Dive or roll angle 0 to 15 Dive or roll angle 15 to 45 Dive or roll angle 45 to 60 Dive or roll angle 60 to 90 Dive or roll angle greater than 90 180 to 360 Dive or roll angle 0 to 15 Dive or roll angle 15 to 45 Dive or roll angle 45 to 60 Dive or roll angle 60 to 90 Dive or roll angle greater than 90 Greater than 360 Dive or roll angle 0 to 15 Dive or roll angle 15 to 45 Dive or roll angle 45 to 60 Dive or roll angle 60 to 90 Dive or roll angle greater than 90 In niglolololniololo gt 8l8 olw 9 8 lol Re inflation behaviour Spontaneous re inflation Inflates in less than 3 s from start of pilot action Inflates in 3 s to 5 s from start of pilot action No re inflation within a further 5 s nO OI gt Total change of course Less than 360 Greater than 360 with tendency to recover g force decreasing rate of turn decreasing l
33. e subject to an acceptable tolerance of 2 kg All speeds are subject to an acceptable tolerance of 2 km h If a test manoeuvre has not been performed in precise accordance with its procedure in 5 5 4918 the manoeuvre shall be repeated This may be due to an error of the test pilot or due to meteorological influences If the outcome of any test manoeuvre appears open to doubt the manoeuvre shall be repeated 5 5 2 Trimmers If trimmers are fitted to a paraglider then the complete test programme is repeated with the trimmers set both to the slowest and to the fastest position 5 5 3 Other adjustable or removable devices If the paraglider is equipped with other adjustable or removable devices which are not covered explicitly in this clause and which may influence its flight characteristics or its control the paraglider shall be tested in the least favourable symmetric configuration 5 5 4 Video documentation All the tests shall be filmed on video If required explicitly by the procedures 5 5 1918 1 to 5 5 4918 23 the test pilot maintains a defined course relative to the camera axis when starting the test manoeuvre 1n 5 5 19 1 te 5 5 19 23 tThe following terms configurations are shall be used Camera axis Profile The pilot maintains a course at a right angle to the horizontal projection of the camera axis Camera axis Face on The pilot is approaching the camera along the horizontal projection of the camera axi
34. e the total weight in flight exceeds 170 kg the maximum weight test will be conducted at a total weight in flight of 170 kg Camera axis Any axis 5 5 19 195 5 18 19 B line stall test Stabilise the glider in straight flight at trim speed Quickly pull down the B riser maillons symmetrically until the maillons reach the main connectors or until a mechanical limit e g interference with the accelerator or other risers is reached Wait 5 s then quickly and symmetrically fully release the risers in a period of not more than 1 s If a special technique for entry is required then this information shall be contained in the users manual and these instructions shall be followed by the test pilot Where the total weight in flight exceeds 170 kg the maximum weight test will be conducted at a total weight in flight of 170 kg Camera axis Profile 5 5 19 205 5 18 20 Big ears test Stabilise the glider in straight flight at trim speed Collapse approximately 30 of the span at each tip by twisting down the appropriate lines simultaneously Note the glider s behaviour After at least 10 s let go of both ears simultaneously The pilot shall take no further action and remains passive until the glider either recovers or 5 s elapses If the glider has not recovered the pilot acts to recover the glider If the glider is eguipped with special big ears handles or if special entry or exit technigues are reguired then this information shall be c
35. e wraps unless the test procedure requires this 5 8 425 5 11 Timing when starting test measurements In tests 5 5 19 11 5 5 19 12 5 5 19 14 5 5 19 20 5 5 19 21 timing starts from the instant that the controls reach the zero position after the pilot releases them 5 5435 5 12 Timing when exiting stalled flight conditions The glider is considered to have exited tests 5 5 19 11 5 5 19 12 and 5 5 19 19 when it reaches its furthest forward pitching point If there is no noticeable pitching the glider is considered to have exited any of these tests when the streamer on the riser reaches 45 to the horizon 5 5 145 5 13 Exiting developed spin rotation The glider is considered to have exited a developed spin when the airflow is reattached over the full span 5 155 5 14 Pitch angles Measurement is of the change of angle A straight line taken from the leading edge at the centre of the canopy to the pilot s buttocks is compared to the horizon before and after the manoeuvre 5 5 165 5 15 Keep course The paraglider is considered to have kept its course throughout a test if it stays within 15 either side of its original course 5 5175 5 16 Twist In test 5 5 19 14 a twist has occurred when after 5 s or after a turn of 360 the pilot s position still is rotated more than 180 relative to the glider 5 5 185 5 17 Collapse on the opposite side In test 5 5 19 14 a collapse on the opposite side has occurred when less than 50
36. er actively maintains a central and neutral position and allows his body to follow the inertial effects If the turn clearly tightens significantly the pilot shall act to recover the glider Otherwise the pilot waits up to four turns to establish the glider s behaviour The measurements ranges start when the pilot begins to release the control Camera axis any axis 46 prEN 926 2 2012 E 5 5 49 495 5 18 10 Symmetric front collapse test 5 5 19 10 15 5 18 10 1 Test 1 Unaccelerated collapse approximately 30 chord Stabilise the glider in straight flight at trim speed Release the controls and attach them to the risers however for safety reasons the controls may be kept in the hands if the front collapse is achievable without significantly affecting the trailing edge Then by abruptly pulling the appropriate lines or risers induce a symmetric front collapse over the entire leading edge with approximately 30 of the centre chord affected As soon as the collapse is achieved let go of the lines risers If the paraglider has not recovered spontaneously after 5 s or after 180 of turn which ever happens first the pilot acts on the controls to recover normal flight without inducing a deliberate stall 5 5 19 10 25 5 18 10 2 Test 2 Unaccelerated collapse at least 50 chord Stabilise the glider in straight flight at trim speed Release the controls and attach them to the risers however for safety reasons the controls m
37. eristics Gliders with some resistance to departures from normal flight Designed for all pilots and may be suitable for pilots under training if recommended by the manufacturer Paragliders with moderate passive safety and with potentially dynamic reactions to turbulence and pilot errors Recovery to normal flight may reguire precise pilot input Designed for pilots familiar with recovery techniques who fly actively and regularly and understand the implications of flying a glider with reduced passive safety Paragliders with demanding flying characteristics and potentially violent reactions to turbulence and pilot errors Recovery to normal flight requires precise pilot input 4 2 Classification of flight characteristics When testing in accordance with the procedures 5 5 1918 1 to 5 5 4918 23 various aspects of the paraglider s Designed for pilots well practised in recovery techniques who fly very actively have significant experience of flying in turbulent conditions and who accept the implications of flying such a wing behaviour are measured These measurements are classified according to 4 4 1 to 4 4 23 The class of a paraglider according to this document is determined by the highest classification obtained i e by the highest level of pilot skill required see Table 1 4 3 Failure The glider has failed the test procedure if either a b NOTE as a consequence of tests 5 5 19
38. est files The following items shall accompany the test files and be filed by the testing laboratory a video recording of the tests b manufacturing record c user s manual d paraglider that has undergone testing e This documentation shall be archived for a minimum of 15 years and the tested paraglider for a minimum of 5 years 7 User s manual The user s manual should be supplied in English and in the majority language s of any country in which the paraglider is intended to be sold It shall always accompany the paraglider and shall include and specify the following elements that shall be checked by test laboratory a General information 1 paraglider model name 2 name and address of the manufacturer 3 name and address of person or company having presented the paraglider for testing if different from manufacturer 4 minimum and maximum total weight in flight 5 maximum symmetric control travel at maximum weight in flight 6 introduction to the intended use of the paraglider 7 class of the paraglider according to this document 8 harness dimensions used during testing 9 version and date of issue of the user s manual b Manufacturer s recommendations on the levels of pilot skills required for safe operation the paraglider shall not be recommended for less experienced pilots than laid down for its class in Table 1 c Dimensions illustrations and characteristics 1 overall illustration identifying
39. glider s behaviour and recovery from a B line stall is measured according to Table 38 and classified according to Table 39 Table 38 Measurements and possible ranges in the B line stall test Code de champ modifi Measurement Ranges Change of course before release Changing course less than 45 Changing course more than 45 Behaviour before release Remains stable with straight span Remains stable without straight span Unstable Recovery Spontaneous in less than 3 s Spontaneous in 3 sto 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action between a further 3 sto 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Cascade occurs No Yes 29 prEN 926 2 2012 E Table 39 Classification of a paraglider s behaviour in the B line stall test Measurement and ranges according to Table 38 Classification Change of course before release Changing course less than 45 Changing course more than 45 Behaviour before release Remains stable with straight span Remains stable without straight span Unstable Recovery Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a fu
40. he total weight in flight exceeds 170 kg the maximum weight test will be conducted at a total weight in flight of 170 kg Camera axis Face on 5 5 19 165 5 18 16 Trim speed spin tendency test Stabilise the glider in straight flight at trim speed Then over a period of 2 s activate one control to 25 of the symmetric control range Wait 20 s or until the glider has turned 360 then over a period of 2 s further activate the same control to 50 of the remaining range and wait 20 s or until the glider has turned another 360 or the glider has obviously entered a spin Camera axis Camera not reguired 5 5 19 175 5 18 17 Low speed spin tendency test Stabilise the glider in straight flight at low speed Then over a period of 2 s further activate one control to 50 of the remaining range i e to 75 of the symmetric control travel without releasing the other and wait for 60 s or until the glider has turned 360 or the glider has obviously entered a spin Camera axis Any axis 5 5 19 185 5 18 18 Recovery from a developed spin test Stabilise the glider in straight flight at low speed Induce a spin with as little pitch and roll as possible by rapidly lowering one control to its maximum range whilst releasing the other Release the inside control while the glider is above the pilot after about one turn of spin rotation inducing as little pitch and roll as possible Assess the behaviour 50 prEN 926 2 2012 E Wher
41. hrough pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Behaviour immediately after releasing the accelerator while maintaining big ears Stable flight Unstable flight Deep stall occurs 4 4 22 Alternative means of directional control When tested in accordance with 5 5 1918 23 it is checked whether the glider may be steered in case of a failure of the primary controls The glider s behaviour when applying alternative means of directional control is measured according to Table 44 and classified according to Table 45 Code de champ modifie Table 44 Measurements and possible ranges in the alternative means of directional control test Measurement 180 turn achievable in 20 s Stall or spin occurs 33 prEN 926 2 2012 E Table 45 Classification of a paraglider s behaviour in the alternative means of directional control test Measurement and ranges according to Table 46 180 turn achievable in 20 s Code de champ modifi Classification Yes No Stall or spin occurs No Yes 4 4 23 Any other flight procedure and or configuration described in the user s manual Any other flight procedure and or configuration described in the user s manual not covered through the tests 5 5 1918 1 to 5
42. ider s behaviour in the speeds in straight flight test Measurement and ranges according to Table 6 Classification Trim speed more than 30 km h Yes A No F Speed range using the controls larger than 10 km h Yes A No F Minimum speed Less than 25 km h 25 km h to 30 km h B Greater than 30 km h 44 4 Control movement The paraglider shall have acceptable control force and control travel When tested in accordance with 5 5 1918 4 the glider s control force and control travel are measured according to Table 8 and classified according to Table 9 14 Code de champ modifi Code de champ modifie prEN 926 2 2012 E Table 8 Measurements and possible ranges in the control movement test Measurement Ranges Symmetric control pressure Increasing Approximately constant Decreasing Symmetric control travel cm Ranges max weight in flight up to 80 kg Ranges max weight in flight 80 kg to 100 kg Ranges max weight in flight greater than 100 kg Greater than 55 em Greater than 60 em Greater than 65 em 40 cm to 55 em 45 cm to 60 cm 50 em to 65 em 35 cm to 40 cm 35 em to 45 cm 35 cm to 50 cm Less than 35 sm Less than 35 cm Less than 35 cm Code de champ modifie Code de champ modifi Table 9 Classification of a paraglider s behaviour in the control movement test C
43. l flight Less than 720 spontaneous recovery 720 to 1 080 spontaneous recovery 1080 to More than 1 0801440 spontaneous recovery With pilot action 18 prEN 926 2 2012 E 4 410 Symmetric front collapse When tested in accordance with 5 5 4918 10 the glider s behaviour and recovery from a front collapse is measured according to Table 20 and classified according to Table 21 If the paraglider is equipped with an accelerator its behaviour in the symmetric front collapse test shall be classified both with and without its use Table 20 Measurements and possible ranges in the symmetric front collapse test Measurement Ranges Entry Rocking back less than 45 Rocking back greater than 45 Recovery Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action in more than a further 5 3 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Change of course Keeping course Entering a turn of less than 90 Entering a turn of 90 to 180 Cascade occurs No Yes Folding lines used No Yes 19 Code de champ modifi Mis en forme Retrait Gauche cm 0 2 prEN 926 2 2012 E 4 4 11 Exiting deep stall para
44. lassifi cation Measurement and ranges according to Table 8 Symmetric control pressure Symmetric control travel cm Max weight in flight up to 80 kg Max weight in flight 80 kg to 100 kg Greater than 60 em Max weight in flight greater than 100 kg Increasing Greater than 55 em Greater than 65 em Increasing 40 erto 55 em 45 em to 60 em 50 em to 65 em Increasing 35 em to 40 em 35 em to 45 em 35 cm to 50 em Increasing Less than 35 em Less than 35 em Less than 35 em Approximately constant Greaterthan 55 em Greaterthan 60 cm Greater than 65 em Approximately constant 40 cm to 55 em 45 em to 60 em 50 em to 65 em Approximately constant 35 em to 40 cm 35 em to 45 em 35 cm to 50 em Less than 35 cm Less than 35 em Less than 35 cm Approximately constant njnlin oloni olol Decreasing any any any 4 4 5 Pitch stability exiting accelerated flight This test is only required for paragliders equipped with an accelerator When tested in accordance with 5 5 4918 5 it is checked that the paraglider returns to normal flight when the accelerator is quickly released The behaviour of the paraglider is measured according to Table 10 and classified according to Table 11 15 prEN 926 2 2012 E Table 10 Measurements and possible ranges in the pitch stability exiting accelerated flight test Measurement Ranges Dive forward angle on exit Dive forward less
45. ls which are designated as such by the manufacturer Mis en forme Note Pas de paragraphes solidaires prEN 926 2 2012 E 3 5 trimmer lockable pitch adjustment system i e action by the pilot is required to return it to the initial position 3 6 accelerator secondary pitch control mechanism operated by the feet generally which automatically returns to the initial position when the action of the pilot stops 3 7 accelerator fully activated when the mechanical limits of the glider are reached and further action on the accelerator does not result in a further decrease of the angle of attack Mis en forme Police Non Gras A 3 78 action of the pilot any transfer of weight action on the controls the accelerator or on the trimmer 3 89 normal flight flight condition in which the paraglider is fully inflated and is following a trajectory close to straight flight at a speed close to trim speed without any action on the part of the pilot A small number of cells may still be collapsed 3 910 spiral dive flight condition in which the paraglider is fully inflated and is following a circling steep nose down trajectory pitch angle of more than 70 and the angle of the span relative to the horizontal between 0 and 40 as illustrated in figure 1 Mis en forme Police Non Gras Mis en forme Term s Mis en forme Normal prEN 926 2 201
46. nd in particular its dive forward behaviour is measured according to Table 26 and classified according to Table 27 22 Code de champ modifi Code de champ modifi prEN 926 2 2012 E Code de champ modifi Table 26 Measurements and possible ranges in the full stall test Measurement Ranges Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Collapse No collapse Symmetric collapse Cascade occurs other than collapses No Yes Rocking back Less than 45 Greater than 45 Line tension Most lines tight Many visibly slack lines Table 27 Classification of a paraglider s behaviour in the full stall test Code de champ modifi Measurement and ranges according to Table 26 Classification Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Collapse No collapse Symmetric collapse Cascade occurs other than collapses No Yes Rocking back Less than 45 Greater than 45 Line tension Most lines tight Many visibly slack lines 23 prEN 926 2 2012 E 4 414 Asymmetric collapse When tested in accordance with 5 5 1918 14 the glider s behaviour and recovery from an asymmetric
47. occurs No Yes Table 35 Classification of a paraglider s behaviour in the low speed spin tendency test Code dechampimodin Measurement and ranges according to Table 34 Classification Spin occurs 4 4 18 Recovery from a developed spin When tested in accordance with 5 5 4918 18 the glider s behaviour and recovery from a fully developed spin is measured according to Table 36 and classified according to Table 37 Table 36 Measurements and possible ranges in the recovery from a developed spin test Code de champ modifi Measurement Ranges Spin rotation angle after release Stops spinning in less than 90 Stops spinning in 90 to 180 Stops spinning in 180 to 360 Does not stop spinning within 360 Cascade occurs No Yes 28 prEN 926 2 2012 E Table 37 Classification of a paraglider s behaviour in the recovery from a developed spin test Cade Ue chan modne Measurement and ranges according to Table 36 Classification Spin rotation angle after release Stops spinning in less than 90 Stops spinning in 90 to 180 Stops spinning in 180 to 360 Does not stop spinning within 360 Cascade occurs 4 419 B line stall This test manoeuvre is not required if the manufacturer excludes this manoeuvre in the user s manual and the B risers are clearly marked accordingly When tested in accordance with 5 5 4918 19 the
48. on and information purposes 17 prEN 926 2 2012 E Table 18 Measurements and possible ranges in the behaviour exiting a fully developed spiral dive Table 19 Classification of a paraglider s behaviour in the behaviour exiting a fully developed spiral Code de champ modifie Measurement Ranges Initial response of glider first 180 Immediate reduction of rate of turn No immediate reaction Immediate increase in rate of turn Tendency to return to straight flight Spontaneous exit g force decreasing rate of turn decreasing Turn remains constant g force constant rate of turn constant Turn tightens g force increasing rate of turn increasing Turn angle to recover normal flight Less than 720 spontaneous recovery 720 to 1 080 spontaneous recovery More than 1 080 to 1440 spontaneous recovery With pilot action Code de champ modifi dive Measurement and ranges according to Table 18 Classification Initial response of glider first 180 Immediate reduction of rate of turn No immediate reaction Immediate increase in rate of turn Tendency to return to straight flight Spontaneous exit g force decreasing rate of turn decreasing Turn remains constant g force constant rate of turn constant Turn tightens g force increasing rate of turn increasing Turn angle to recover norma
49. ontained in the users manual and these instructions shall be followed by the test pilot Camera axis Profile 5 5 19 215 5 18 21 Big ears in accelerated flight test Stabilise the glider in straight flight at trim speed Collapse approximately 30 of the span at each tip by twisting down the appropriate lines simultaneously Fully apply the accelerator and note the glider s behaviour After at least 10 s release the accelerator guickly and immediately let go both ears simultaneously The pilot shall take no further action and remains passive until the glider either recovers or 5 s elapses If the glider has not recovered the pilot acts to recover the glider To evaluate the behaviour of the glider when releasing the accelerator while maintaining big ears collapse approximately 30 of the span at each tip by twisting down the appropriate lines simultaneously 51 prEN 926 2 2012 E Fully apply the accelerator After at least 10 s release the accelerator quickly and note the glider s behaviour while maintaining the big ears If the glider is eguipped with special big ears handles or if special entry or exit technigues are reguired then this information shall be contained in the user s manual and these instructions shall be followed by the test pilot Camera axis Profile 5 49 225 5 18 22 Alternative means of directional control Stabilise the glider in straight flight at trim speed Apply the alternative control metho
50. own the appropriate lines on one side as fast as possible to collapse the canopy asymmetrically at 45 to 50 of the span at an angle of approximately 45 relative to the longitudinal axis and hold the collapse 49 prEN 926 2 2012 E Then the pilot attempts to keep course for a period of 3 s using the control on the inflated side if necessary From straight flight the pilot further uses this control to turn 180 to the inflated side in a period of 10 s without involuntarily entering an abnormal flight condition The pilot assesses the position of the control relative to the symmetric stall position mark Stabilise the glider in straight flight at trim speed Release the control handle on the side to be collapsed and attach it to the riser Pull down the appropriate lines on one side as fast as possible to collapse the canopy asymmetrically at 45 to 50 of the span at an angle of approximately 45 relative to the longitudinal axis and hold the collapse Then the pilot attempts to keep course for a period of 3 s using the control on the inflated side if necessary From straight flight the pilot further uses this control to establish the minimum amount of control input required to induce a stall or spin This amount of control shall be applied in a period of 1 s The pilot assesses the position of the control relative to the symmetric stall position mark The pilot shall not counteract inertia effects on his body at any stage Where t
51. proximately regained its inflated span Then guickly and symmetrically fully release the controls in a period of 1 s If an asymmetric collapse occurs it is assumed that the release has not been sufficiently symmetrical and the test manoeuvre should be repeated If any pitch oscillations don t die out the controls are to be fully released when the canopy rocking forward arrives above the pilot Where the total weight in flight exceeds 170 kg the maximum weight test will be conducted at a total weight in flight of 170 kg Camera axis Profile 5549445 5 18 14 Asymmetric collapse test 9 49 44 45 5 18 14 1 General If the paraglider is equipped with an accelerator the two tests below shall be repeated with the accelerator fully activated The accelerator shall be released at the same time as the lines are released Camera axis Face on and behind this may be with two cameras or by a repeated test 5 49 44 25 5 18 14 2 Small asymmetric collapse Stabilise the glider in straight flight at trim speed Release the control handle on the side to be collapsed and attach it to the riser Pull down the appropriate lines on one side as fast as possible to collapse the canopy asymmetrically at approximately 50 of the leading edge along the marked line As soon as the collapse is achieved release the lines quickly 48 prEN 926 2 2012 E The pilot shall take no further action and remains passive until the glider either recove
52. r s manual 15 riser lengths actually measured shall not differ more than 5 mm from the lengths laid down in the user s manual the manufacturer s recommendations on all necessary piloting techniques in particular these recommendations shall describe and specify 1 harness dimension used during testing 2 pre flight inspection procedure 3 normal piloting techniques including the procedure for laying out the wing before inflation take off 4 use of trimmers accelerator and any other devices 5 recovery from involuntary abnormal flight conditions deep stall asymmetric collapse etc 6 rapid descent procedure s 7 procedure for steering in case of failure of the primary controls 8 any other special flying procedure and or configuration the manufacturer suggests to apply prEN 926 2 2012 E e Repair and maintenance instructions in particular these instructions shall describe and specify 1 2 3 4 5 general information on maintaining and repairing the paraglider recommended freguency of inspections in months from purchase or accumulated hours flying time whichever comes first a thorough inspection of all components including checking suspension line strength line geometry riser geometry and permeability of the canopy material shall be recommended at least every 36 months or 150 hours flying time whichever comes first detailed instructions on any repair and maintenance procedures that can
53. ready to fly NOTE for the purposes of this document masses are indicated in kg rounded to the nearest integer value 3 19 additional lines cross lines or folding lines used to help the test pilot achieving specified manoeuvres 3 20 cross line single line going from one riser to any position on an opposite A line or A line attachment point 3 21 folding lines copy of the complete geometry of the A lines angle cascade length used to help the test pilot achieving specified manoeuvres 10 Mis en forme Police Non Italigue Code de champ modifi Code de champ modifie Mis en forme Note Mis en forme Note Mis en forme Term s prEN 926 2 2012 E Gi Mis en forme Normal 4 Requirements 41 Paraglider classes The class of a paraglider is determined according to 4 2 The class is intended to give pilots a guideline whether a paraglider is suitable for their levels of skills see Table 1 ti prEN 926 2 2012 E Table 1 Description of the paraglider classes Description of flight characteristics Paragliders with maximum passive safety and extremely forgiving flying characteristics Gliders with good resistance to departures from normal flight Description of pilot skills reguired Designed for all pilots including pilots under all levels of training Paragliders with good passive safety and forgiving flying charact
54. ring a turn of less than 90 Dive forward greater than 90 Entering a turn of 90 to 180 nn MODO O m m O P D Cascade occurs No Yes Folding lines used Code de champ modifi Tableau mis en forme Mis en forme Retrait Gauche 0 2 cm J prEN 926 2 2012 E Table 22 Measurements and possible ranges in the exiting deep stall parachutal stall test Measurement Ranges Deep stall achieved Yes No Recovery Spontaneous in less than 3 s Spontaneous in 3 sto 5 s Recovery through pilot action in less than a further 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Change of course Changing course less than 45 Changing course 45 or more Cascade occurs No Yes Table 23 Classification of a paraglider s behaviour in the exiting deep stall parachutal stall test Measurement and ranges according to Table 22 Classification Deep stall achieved Yes No Recovery Spontaneous in less than 3 s Spontaneous in 3 sto 5 s Recovery through pilot action in less than a further 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to
55. rs or changes course by more than 360 or 5 s elapses If the glider has not recovered the pilot acts to recover the glider 5 5 19 14 35 5 18 14 3 Large asymmetric collapse Stabilise the glider in straight flight at trim speed Release the control handle on the side to be collapsed and attach it to the riser Pull down the appropriate lines on one side as fast as possible to collapse the canopy asymmetrically inside the tolerance field in accordance with 5 3 2 In the status of the maximum shape of the collapse the bend line has to be completely right through to the trailing edge inside the marked tolerance field as shown in Figure 7 As soon as the collapse is achieved release the lines quickly Mis en forme J ustifi The pilot shall take no further action and remains passive until the glider either recovers or changes course by more than 360 or 5 s elapses If the glider has not recovered the pilot acts to recover the glider Where the total weight in flight exceeds 170 kg the maximum weight test will be conducted at a total weight in flight of 170 kg 24 Code de champ modifi Figure 7 Asymmetric collapse overlap 5 5 19 155 5 18 15 Directional control with a maintained asymmetric collapse test Stabilise the glider in straight flight at trim speed Release the control handle on the side to be collapsed and attach it to the riser Pull d
56. rther 3 s Recovery through pilot action between a further 3 s to 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Cascade occurs 4 4 20 Big ears This test manoeuvre is not required if the manufacturer excludes this manoeuvre in the user s manual and the A risers are clearly marked accordingly When tested in accordance with 5 5 1918 20 the glider s behaviour and handling during and exiting big ears is measured according to Table 40 and classified according to Table 41 30 Code de champ modifi prEN 926 2 2012 E Code de champ modifi Table 40 Measurements and possible ranges in the big ears test Measurement Ranges Entry procedure Dedicated controls Standard technique No dedicated controls and non standard technique Behaviour during big ears Stable flight Unstable flight Deep stall occurs Recovery Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action between a further 3 s to 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90
57. s Camera axis From behind The pilot is flying away from the camera along the horizontal projection of the camera axis 40 prEN 926 2 2012 E 5 5 5 Radio documentation Any comments of the pilot in flight shall be recorded on the video Using the radio connection to the camera the test pilot shall announce which manoeuvre is about to follow add any comment helping to evaluate the glider s behaviour optional announce if he is sure any manoeuvre just performed was not valid for some reason 5 5 6 Harness dimensions The test pilot and the passenger when testing in two seater configuration shall use a harness with a perpendicular distance from the harness attachment points bottom of the carabiners as shown in Figure 3s 3 and4 measured from connector centrelines to the seat board top surface as shown in figure 4 depending on the total weight in flight as shown in Table 48 The horizontal distance between the harness attachment points measured between connector centrelines shall be set depending on the total weight in flight as shown in Figure 3 5 and Table 48 When testing in two seater configuration the horizontal dimension of the passenger s harness is set to the same width as the pilot s harness 41 prEN 926 2 2012 E Code de champ modifie Code de champ modifi Code de champ modifi Code de champ modifie 42 Figure 5
58. s and test methods for classifying flight safety characteristics EN 1651 Paragliding equipment Harnesses Safety requirements and strength tests EN 12491 Paragliding equipment Emergency parachutes Safety requirements and test methods In comparison with the previous edition EN 926 2 2005 the following significant changes have been made _ Mis en forme Anglais o ic Mis en forme Anglais a editorial revision b introduction of new definitions Mis en forme Anglais c modification of paraglider s classification Mis en forme Anglais d update of marking e introduction of additional lines paragraph f harness dimension have been modified g tests method for asymmetric and symmetric collapse have been improved h update of test method for behaviour exiting a fully developed spiral dive 3 Mis en forme Gauche Espace Apr s 0 pt Interligne simple Ne pas ajuster l espace entre le texte latin et asiatique Ne pas ajuster l espace entre le texte et les nombres asiatiques prEN 926 2 2012 E 1 Scope This document specifies reguirements and test methods for classifying the flight safety characteristics of paragliders in terms of the demands on pilot flying skills This document is intended for the use of independent testing laboratories gualified for flight testing paragliders 2 Normative references The following referenced document
59. s are indispensable for the application of this document For dated references only the edition cited applies For undated references the latest edition of the referenced document including any amendments applies EN 926 1 Paragliding eguipment Paragliders Part 1 Reguirements and test methods for structural strength EN 966 Helmets for airborne sports EN 1651 4999 Paragliding equipment Harnesses Safety requirements and strength tests EN 12491 2001 Paragliding eguipment Emergency parachutes Safety reguirements and test methods 3 Terms and definitions For the purposes of this document the following terms and definitions apply 3 1 paraglider ultralight glider with no primary rigid structure for which take off and landing are on foot with the pilot and potentially one passenger carried in a harness or harnesses connected to the wing 3 2 harness assembly composed of straps and fabric for supporting the pilot in the seated or semi recumbent or standing position NOTE The harness is attached to the wing via two connectors it can also be integral with the wing via risers EN 1651 4999 3 3 emergency parachute emergency device intended to slow the descent of a paraglider pilot in the event of an incident in flight which is deployed by the pilot by an intentional manual action NOTE This may be unsteered or steerable EN 12491 2004 3 4 controls primary steering and speed contro
60. tabilised straight flight Camera axis Camera not required 5 19 45 5 18 4 Control movement test Check the zero position and the symmetric stall position reference marks The symmetric stall position is checked by stabilising the paraglider in straight flight at trim speed Over a period of 5 s gradually lower both controls to the symmetric stall position marks being careful not to induce pitch oscillations Hold this position until the paraglider rocks back entering a full stall Assess the control forces throughout the procedure Camera axis Camera not required 5 19 55 5 18 5 Pitch stability exiting accelerated flight test Stabilise the paraglider in straight flight at maximum speed Then abruptly release the accelerator and assess the behaviour Camera axis Profile 5 5 19 65 5 18 6 Pitch stability operating controls during accelerated flight test Stabilise the paraglider in straight flight at maximum speed Activate both controls symmetrically to 25 of the symmetric control range within 2 s 45 prEN 926 2 2012 E Hold that position for 2 s Then slowly release both controls Camera axis Any axis 5 5 19 75 5 18 7 Roll stability and damping test Induce the maximum possible roll angle achievable by guickly activating and releasing each control in turn to the symmetric stall position marks once without inducing a stall spin or collapse The timing of the control inputs is selected by the test pilot to maximise
61. th 5 5 4918 2 it is found out how difficult it is to flare and land this glider including checking for undesirable tendencies The behaviour of the paraglider is measured according to Table 4 and classified according to Table 5 Table 4 Measurements and possible ranges in the landing test L Measurement Special landing technique required Table 5 Classification of a paraglider s behaviour in the landing test Measurement and ranges according to Table 4 Special landing technique required Code de champ modifie Code de champ modifi Classification Code de champ modifi Ranges Code de champ modifi Classification No Yes 13 prEN 926 2 2012 E 4 4 3 Speeds in straight flight When tested in accordance with 5 5 4918 3 it is made sure that the paraglider is not too slow hands up and an adeguate speed range is achievable using the controls only not activating the accelerator The behaviour of the paraglider is measured according to Table 6 and classified according to Table 7 The speeds recorded in this test are not to be published Table 6 Measurements and possible ranges in the speeds in straight flight test Measurement Trim speed more than 30 km h Yes No Speed range using the controls larger Yes than 10 km h No Minimum speed Less than 25 km h 25 km h to 30 km h Greater than 30 km h Table 7 Classification of a paragl
62. than 30 Dive forward 30 to 60 Dive forward more than 60 Table 11 Classification of a paraglider s behaviour in the pitch stability exiting accelerated flight test vomemon 4 4 6 Pitch stability operating controls during accelerated flight This test is only required for paragliders equipped with an accelerator When tested in accordance with 5 5 1918 6 the behaviour of the paraglider after activating the controls in accelerated flight is checked The behaviour of the paraglider is measured according to Table 12 and classified according to Table 13 Table 12 Measurements and possible ranges in the pitch stability operating controls during accelerated flight test Measurement Ranges No Collapse occurs Yes Table 13 Classification of a paraglider s behaviour in the pitch stability operating controls during accelerated flight test Measurement and ranges according to Table 12 Classification Collapse occurs No Yes 16 Code de champ modifi Code de champ modifi Code de champ modifi Code de champ modifie prEN 926 2 2012 E 4 4 7 Roll stability and damping When tested in accordance with 5 5 1918 7 it is checked that the paraglider returns to normal flight from large control input and that roll oscillations are damped The behaviour of the paraglider is measured according to Table 14 and classified according to
63. the testing laboratory It is highly recommended that all test manoeuvres are carried out over water and that appropriate safety measures are taken to pick up the pilot quickly in case of an emergency landing in the water 5 2 Apparatus 5 2 1 Test pilot equipment The test pilot shall be equipped with helmet in accordance with EN 966 radio communication system for announcing manoeuvres and comments in flight _ airspeed indicator _variometer lifejacket if the flight tests are carried out over water ballast system for adjusting the load in accordance with the manufacturer s requirements if required emergency parachute which complies with EN 12491 Harness in accordance with EN 1651 A G meter may optionally be used If the paraglider is tested in two seater configuration the passenger shall be equipped with helmet in accordance with EN 966 lifejacket if the flight tests are carried out over water Harness in accordance with EN 1651 ballast system for adjusting the load in accordance with the manufacturer s requirements if required The total weight of the ballast shall not exceed 15 kg or 20 of the pilot s weight whichever is larger If the paraglider is tested in two seater configuration the total weight of the ballast shall not exceed 30 kg or 20 of the total weight of pilot plus passenger and should be distributed proportionally to each see 5 5 7 35 prEN
64. ure Dedicated controls Standard technique No dedicated controls and non standard technique Behaviour during big ears Stable flight Unstable flight Deep stall occurs Recovery Spontaneous in less than 3 s Spontaneous in 3 s to 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action between a further 3 s to 5 s Recovery through pilot action in more than a further 5 s Dive forward angle on exit Dive forward 0 to 30 Dive forward 30 to 60 Dive forward 60 to 90 Dive forward greater than 90 Behaviour immediately after releasing the accelerator while maintaining big ears 32 Stable flight Unstable flight Deep stall occurs Code de champ modifie prEN 926 2 2012 E f Code de champ modifi Table 43 Classification of a paraglider s behaviour in the big ears in accelerated flight test Measurement and ranges according to Table 42 Classification Entry procedure Dedicated controls Standard technique No dedicated controls and non standard technique Behaviour during big ears Stable flight Unstable flight Deep stall occurs Recovery Spontaneous in less than 3 s Spontaneous in 3 sto 5 s Recovery through pilot action in less than a further 3 s Recovery through pilot action between a further 3 s to 5 s Recovery t
65. urepean Standard Document subtype Document stage CEN EnquiryCEN Enquiry Document language EE M dms dsmc domD697 TC 136 Ex domD673 Parapenies S52SNCEN TC 136 WG SISECRETARIAT depuis JE 136 WG _6 N 53 Draft ol FprEN 926 2 for submission formal vote docY Q STD Ne a ea 24a Mis en forme Couleur de police Bleu V rifier l orthographe et la grammaire Mis en forme Fran ais France V rifier l orthographe et la grammaire Code de champ modifi Mis en forme Fran ais France V rifier l orthographe et la grammaire Mis en forme Fran ais France V rifier l orthographe et la grammaire Mis en forme Allemand Allemagne V rifier l orthographe et la grammaire prEN 926 2 2012 E Contents Page 5 3 4 Control extensions 3935 5 4 Test conditions 5 5 Procedure 3935 5 51 General D Trimmers 4036 5 5 3 Other adjustable or removable devices ss nnnnennennee 4036 5 94 Video dOcuMeNtAtiOn ss ssssencemensanenseseensanssranresssansenenenenensunsnes 4036 595 Radio DOCUMENIATION naa ia bea aan akan Sian BnR 4137 Mis en forme Mis en forme Mis en forme Mis en forme Mis en forme Mis en forme Mis en forme Mis en forme Mis en forme lo Ja lalu Is jw in je Mis en forme o Mis en

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