STEMME S6 Maintenance Manual

MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
Report of Empty Mass and CG-Location
(continuous report of changes to the aircraft structure and/or equipment)
Registration Nr.:
Serial-Nr.:
.................
Sheet
Nr.:
STEMME S6
Current Empty-Mass
Cleared by
Authorized
Personnel
Con.
Nr
Date
Description of
Action taken
Mass [kg]
Lever to
RP [m]
Moment
[kgm]
... .......
1. Weighing at
delivery
............
..........
...........
......................
Logsheet Sample
Figure 202
08-10-00
Page 204
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 c ompartment 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 3 l / 0.66 imp. gal. fuel / 0.8 us gal. Þ 6.7 lbs. (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]***
Massegrenzen
[kg]
[lbs]***
Central Wing
Maximum All Up Weight (incl. Fuel) 850 / 1874
Right Hand Outer Wing
Maximum Weight of Non-Lifting Parts
GNT
ma x
(incl. Load in Cockpit)
620 / 1367
Winglet right
Left Hand Outer Wing
Of that: Maximum Weight of Equipment on
Instrument Panel, without engine instruments
14 / 30.9
Winglet left
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 10 kg / 22 lbs
less than maximum load!
Component Weight Sum
Empty
Weight*
LNT**
* cross-check: compare wit h 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 ***:
Main wheel RH m
r
kg / lbs
Main wheel LH m
l
kg / lbs
Nose wheel m
f
kg / lbs
S=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 1000:44 ( 2°26` ) on
tail cone, upper edge horizontal
08-10-00
Page 205
Weight and Balance Report
Nov 18/11
Nov 18/11
EFFECTIVITY
Model S6
EFFECTIVITY
Model S6

STEMME S6 Specifications

General

Brand	STEMME
Model	S6
Category	Aircrafts
Language	English