STEMME S12, Руководство по обслуживанию

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DOCUMENT NUMBER:
L500-912.820 ISSUE JUL 20, 2016
AMENDMENT: 00
DATE: --
CHAPTER- PAGE D-2
MAINTENANCE MANUAL STEMME S12
THIS PAGE IS INTENTIONALLY LEFT BLANK
Weight and balance report
Document Number
1001-12-S12-2
STEMME S12
Page 1 (of 2)
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 and coolant if necessary. Fixed ballast must be installed, loose ballast must be removed.
1.2. Wing weight must be determined with bolts and 1.4 l / 0.31 imp. gal (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)
900kg
1984 lbs
Right Hand Outer Wing
Maximum Weight of Non-Lifting Parts
NLP
max
(incl. Load in Cockpit)
610kg
1345lbs
Left Hand Outer Wing
Of that: Maximum weight of equipment on
Instrument Panel, without Minimum Equipment
7 kg / 15.4 lbs
11 kg/24.2 lbs
Fuselage
Maximum Load (MTOW - Empty Weight)
Horizontal Tail
Max. Load in Cockpit
(NLP
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 10 kg / 22 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 1000:54,2 (3,1°) on tail
cone, upper edge horizontal