STEMME S10, Maintenance Manual

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Maintenance Manual STEMME S10
Date of Issue: Oct. 01, 1990 page: 31
Amendment No.: - Date: -
A4010021_B19.doc
Doc.No.: A40-10-021
6. Maintenance Instructions, Tolerances, Adjustment Data for the Aircraft
6.1 General Information
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6.2 Ground Towing, Supporting Points, and Lifting of Aircraft
Ground towing of the aircraft by automobile may be made only in flight direction, since the tail wheel runs in a
castering fork the lateral deflection of which is limited to 30° in both directions.
For ground towing, two ropes of textile material of at least 33 ft. (10 m) each are needed. They are to be
attached to the front struts of the main landing gear at the lowest possible points (mind the brake system
tubes!). The cockpit is to be manned with an instructed person. The aircraft is to be towed at walking pace.
For manouevring on the ground, the manufacturer offers a tail wheel dolly. In exceptional cases, the aircraft
may be pushed backwards over a short distance without a tail wheel dolly, if the rudder is directed.
The supporting points to lift the whole aircraft are situated on the wing lower sides under the wing spar at a
distance of approximately 3.3 ft. (1 m) from the fuselage (the position of the wing spar is to be determined by
slight tapping). Supported at the tail wheel, the fuselage rear end is to be lifted by approximately 1.6 ft.
(0.5 m).
The wing is to be supported over an area of at least 8 in. x 12 in. (200 x 300 mm) (the longer side in wing
span direction). A plywood sheet of 2 in. (50 mm) thickness with a felt layer of .6 to .8 in. (15 to 20 mm)
thickness or something adequate is to be used. The support under the plywood sheet center must be flexible
so that the wing rests evenly upon the plywood sheet.
The stands must be capable of reliably carriing the aircraft mass and be sufficiently stable. The slabs to
support the wing must be non-skid.
Warning: Ensure that the wing stands are evenly lifted and correctly positioned, since otherwise the wing
shell and spar will be deformed or even destroyed.
Letting down of the aircraft must also be done evenly; during both lifting and letting down, the profile chord
shall always remain in a nearly horizontal position.
The fuselage with the wing removed may be supported as follows:
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either in a felt-lined, fitted rigid tray of a width of 40 in. (1 m) and a length of 16 in. (.4 m). directly in front of
the landing gear doors
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or remove the front wing attachment bolts and replace them by round bars of St 37 (soft steel) or
something similar, Ø .78 ±.004 in. (19.8 ± 0.1mm), length 12 in. (300 mm). The bars are to be pushed in
by 6 in. (150 mm) and to be locked against displacement. By means of these bars, the fuselage may be
suspended or supported.
6.3 Determination of the Empty Mass and Corresponding Center of Gravity; Information on
Mass Limits
In the following paragraphs, the determination of single masses, of mass limits and of the empty mass and
corresponding center of gravity is described. Please refer to the "Mass and Balance" Sheet, fig. 6.3.a, and the
table "Empty Masses and Allowable Center of Gravity Positions as a Function of Empty Masses" fig. 6.3.b.
The Equipment List required for weighing is always part of the latest valid inspection records.