Albatros Commercial Airplane L 73 Page: 8 of 17
[16] p. : ill.View a full description of this report.
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.A...A..Arcraft Circular No. 16
3 u Fuselage and furnishings
Fuselage frame
Cabinl (walls, dooi s, windows,
seats, etc.) including toilet and
rear baggage room
Fuselage covering
Pilots' seats, front baggage room,
instruments and steering gear
Total weight of fuselage and furn-
ishings
4. Landing gear
5. Tail skid with rubber
6. Tail group, complete8.12
8.98
1.36
7.3525.81
7.75
0. 54
3.66
100.00The useful load is equal to about 53c of the dead load, the
specially installed instruments being included in the dead load.
For judging the given percentages, the strengths are impor-
tant, which were taken as the basis of the computations. These
strengths, corresponding to present-day views, are considerably
greater than formerly called for by the B.L.V. (construction and
delivery specifications). The computed breaking strengths of the
airplane in the principal flight cases are as follows:
Case A (Pulling out of a dive) 6.0 (According to the B.L.V.
4.0),Case B (Gliding)
Case C (Diving)Case D (Flying upside down)
3..5 (According to the.B.L.V.
2.5),
2.0 (According to the 3.L.V.
1.5),
3.0 (According to the B.L.V.
0.0).
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Rühl, Karl & Wiederhold, Hasso. Albatros Commercial Airplane L 73, report, September 1926; (https://digital.library.unt.edu/ark:/67531/metadc62075/m1/8/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.