STEMME S10, Maintenance Manual

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Maintenance Manual STEMME S 10
Date of Issue Oct. 01, 1990 fig. 6.3.a-1
Amendment No.: 12 Date: Nov. 30. 2007
Fig. 6.3.a
Mass and Balance Sheet
(Pattern; the complete form can be obtained from the
manufacturer)
A4010021_B19.doc-0/27.01.14/2:18 PM
Serial Number:
-
Registration:
-
Relevant Equipment List: Order No.:
This Weight and Balance Report was drawn up without weighing. Any weighing data have been taken from the
Weight and Balance Report dated and if need be corrected according to point 4.2.
Drawing Up Reason: Conformity Inspection
Changes of Equipment
Repair. Date of Findings Report:
Other:
1. Preparation and Conditions
1.1 The fuselage weight must be determined including rudder, back rests with cushions or equivalent upholstery, seat cushions,
canopy, standard tool kit in baggage compartment behind backrest, Logbook and Flight Manual. Replenish oil if necessary.
Fixed ballast must be installed, loose ballast must be removed.
1.2 Wing weight must be determined with bolts and 3 l / 0.66 imp. gal. fuel (unusable volume).
1.3 Fixed supplementary equipment must be installed.
1.4 Points 1.2 through 1.4 must be observed if an overall weighing of the powered glider is performed. The canopy has to be
closed during weighing.
1.5 If weight and moment arm of additionally installed or removed items is known exactly, the new CG may be determined
numerically (see point 4.2)
2. Overview of Component Weights and Weight Limits
Component Weights from Separate
Weighing [kg]
[lbs] *** [kg]
[lbs] *** Weight Limits [kg]
[lbs] ***
Central Wing Maximum All Up Weight (incl. Fuel) 850 (1874)
Right Hand Outer Wing
Maximum Weight of Non-Lifting Parts
GNT
max
(incl. Load in Cockpit)
570 (1257)
Left Hand Outer Wing
Of that: Maximum Weight of Equipment on
Instrument Panel, without engine instruments 10
(22)
Fuselage Maximum Load (Max AUW - Empty Weight)
Horizontal Tail Max. Load in Cockpit
(GNT
max
- LNT**; maximum 202 kg / 445 lbs,
of that max. 180 kg / 397 lbs in seats, max.
110 kg / 243 lbs in each seat and max. 22 kg
/ 48.5 lbs in baggage compartments)
Cockpit load must be at least 7 kg / 15,43
lbs less than maximum load!
Component Weight Sum
Empty
Weight*
LNT**
* cross-check: compare with empty weight from 3.; Divergence of 2 kg / 4.4 lbs due to measure error is allowable.
** LNT: Empty weight of "Non Lifting Parts"
*** Units: cross out if not applicable
3. Determining of Empty Weight and Moment Arms
Weights and Moment Arms ***:
forward RH m
r
kg / lbs
forward LH m
l
kg / lbs
Tail Wheel m
s
kg / lbs
Σ
=Empty Weight m
e
kg / lbs
Moment Arm a mm / in.
Moment Arm b mm / in.
Datum level: Leading Edge of
Central wing, vertical plane
Pitch: wedge 1000:84 (4°50') on tail
cone, upper edge horizontal