canopy - Schempp-Hirth Flugzeugbau GmbH

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SCHEMPP-HIRTH FLUGZEUGBAU <strong>GmbH</strong>., KIRCHHEIM/TECK Duo Discus MAINTENANCE MANUAL Datum plane: Aircraft attitude: Wing leading edge at root rib Tail jacked up such that a wedge-shaped block, 100 : 4.5, placed on the rear top fuselage, is horizontal along its upper edge. Distance main wheel: a = 8 mm (0.31 in.) Distance tail wheel: Distance skid: b = 5322 mm (209.53 in.) b = 5357 mm (210.91 in.) Empty mass c/g position: x = W 2 x b W + a C/G position in flight: (just given for the case that the “c/g position in flight” is to be determined by weighing rather than by computing it on the basis of the empty mass c/g position) The aircraft is to be weighed fully equipped (crew with parachutes and complete outfit incl. barograph, cushions, cameras etc.) Seat back and rudder pedals should be correctly adjusted for this purpose. x = W 2 loaded x b W empty + W disposable + a February 2008 MB-No. 396-15 resp. MB-No. 396-16 Revision 20 TN-No. 396-16 (x / xL) 6.2.2
SCHEMPP-HIRTH FLUGZEUGBAU <strong>GmbH</strong>., KIRCHHEIM/TECK Duo Discus MAINTENANCE MANUAL Forward c/g limits: With a maximum seat load of 110 kg (242.5 lb) on either seat and with maximum permitted water ballast Rearward c/g limits: With various minimum loads on the front seat (allowance for 5.0 kg / 11.02 lb baggage already made) To facilitate the checking of the empty mass center of gravity, the table below shows – at different empty mass values – the maximum permissible load on the tail wheel, with various loads on the front seat and in relation to the most rearward c/g position. The actual load on the tail wheel is determined with the aircraft in weighing attitude, i.e. main wheel on the ground and tail jacked up as described on page 6.2.1. If the load on the tail wheel does not exceed the corresponding value in the table, the center of gravity is within the permitted range. Empty mass Load on tail wheel (or skid) with a minimum seat load of: 70 154 75 165 80 176 85 187 90 198 kg lb kg lb kg lb kg lb kg lb kg lb 410 904 39.7 87.5 41.2 90.8 42.8 94.4 44.3 97.7 45.9 101.2 420 926 40.1 88.4 41.7 91.9 43.2 95.3 44.8 98.8 46.3 102.1 430 948 40.6 89.5 42.1 92.8 43.7 96.4 45.2 99.7 46.8 103.2 440 970 41.1 90.6 42.6 93.9 44.2 97.5 45.7 100.8 47.3 104.3 450 992 41.5 91.5 43.1 95.0 44.6 98.3 46.2 101.9 47.7 105.2 460 1014 42.0 92.6 43.5 95.9 45.1 99.4 46.6 102.8 48.2 106.3 470 1036 42.4 93.5 44.0 97.0 45.5 100.3 47.1 103.9 48.6 107.2 480 1058 42.9 94.6 44.4 97.9 46.0 101.4 47.5 104.7 49.1 108.3 490 1080 43.3 95.5 44.9 99.0 46.4 102.3 48.0 105.8 49.5 109.1 500 1103 43.8 96.6 45.3 99.9 46.9 103.4 48.4 106.7 50.0 110.3 Note: Should a tail skid be fitted (instead of a tail wheel), the above values are to be multiplied by a factor of 0.993). February 2008 MB-No. 396-15 Revision 20 TN-No. 396-16 (x) 6.4.2
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canopy - Schempp-Hirth Flugzeugbau GmbH

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