STEMME S10 Technical specifications


Flight Manual STEMME S10Date of Issue Oct. 1, 1990 page: 1
Amendment No.: 8 Date: Jan. 10, 2014
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Deviations from the Basic Flight Manual for the Type:
The aircraft specified below is fitted, in accordance with the entries in the list, with equipment or systems
installed as an alternative to the equipment of the standard version. Resulting additional text has been inclu-
ded in the Flight Manual under the specified revision numbers; the text passages relating to the standard
version have been crossed out. The required modifications to the text are described in further detail in the
associated LBA approved Service Bulletins.
The procedure of amending the Manual in the case of installation of alternative equipment is described in
Section 9.2.
The licensed inspector certifies by his signature that this Flight Manual complies with the data specified in the
following and with the associated aircraft.
Valid for STEMME
S10, serial no.:
Affected Component Am.No.
SB-Number Date Approval


Flight Manual STEMME S10
Date of Issue Oct. 1, 1990 page: 3
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0.2 List of Effective Pages
This record is valid only for the Serial No. specified on the title page.
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Flight Manual STEMME S10 Date of Issue Oct. 1, 1990 page: 4
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0.3 Contents
Section 1 - General 5
Section 2 - Limitations 8
Section 3 - Emergency Procedures 8
Section 4 - Normal Operating Procedures 8
Section 5 - Performance 8
Section 6 - Mass and Balance 8
Section 7 - Description of the powered Glider and its Systems and Equipment 8
Section 8 - Handling, Servicing and Maintenance 8

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Section 1 - General
1.1 Introduction 6
1.2 Certification Basis 6
1.3 Warnings, Cautions and Notes 6
1.4 Description and Technical Data 7
1.5 3-View Plan 8

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1.1 Introduction
This flight manual was compiled to give pilots and instructors all necessary information for a safe, appropriate
and performance- optimized operation of the motor glider.
The manual includes all the data required to be furnished to the pilot by JAR-22. It further contains a number
of other data and operating hints which may be useful to the pilot from the manufacturer's point of view.
For the conversion of technical data the following factors have been used:
1 lb. 0.4536 kg 1 ftlb 0.1356 Nm
1 dr. 1.772 g 1 hp 0.7457 kW
1lbf =1 lb.(wt) 4.45 N 1 kts 1.852 km/h
1in. 25.4 mm 1 mph 1.609 km/h
1ft. 0.3048 m 1 U.S.gal. 3.785 l
1 sqft. 0.0929 m21 p.s.i. 0.06895 bar
100 fpm 0.5081 m/s
1.2 Certification Basis
This powered sailplane with the works reference STEMME S10 has originally been approved by the Luftfahrt-
Bundesamt in accordance with Joint Airworthiness Requirements for Sailplanes and Powered Sailplanes
JAR-22, effective through change 3, including Amendment 22/84/1, effective October 22, 1984.
The Type Certificate No. 846 has been issued on December 31, 1990.
Category of Airworthiness: "Utility".
Noise Certification Basis: according to chapter VI of the "Laermschutzforderungen fuer Luftfahrzeuge (LSL)"
(Noise Protection Requirements for Aircraft) dated Jan.1, 1989, published in the "Bundesanzeiger Jahrgang
41, no. 41a dated Feb. 28, 1989" (Federal Gazette, year 41).
For U.S. import the aircraft has been approved by the FAA in accordance with 14 CFR 21, effective
February 1, 1965, Amendments 21-1 through 21-68, Sections 21.17, 21.29 and 21.50, Advisory Circular
AC 21.17-2, effective July 13, 1989.
The U.S. Type Certificate No. G 58 EU has been issued on July 8, 1992.
1.3 Warnings, Cautions and Notes
Remarks in the manual of particular importance to flight safety and handling have been specially marked by
use of one of the following terms:
"Warning" means that the non-observation of the corresponding procedure leads to an immediate
or important degradation of the flight safety.
"Caution" means that the non-observation of the corresponding procedure leads to a minor or to a more or
less long-term degradation of the flight safety.
"Note" draws attention on any special item not directly related to safety but which is important or
unusual.

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1.4 Description and Technical Data
The STEMME S10 is a two-seat high performance motor glider with an innovative propulsion concept and
highly finished aerodynamic shape. The seats are arranged side-by-side (forward of the wing) and are
equipped with dual controls.
The wing is mounted to the fuselage in the upper third. It consists of an inner wing with flaps and Schempp-
Hirth air brakes and two outer wings with continuous ailerons.
The tailplane is designed as a "T"-type.
The two-wheel main landing gear can be retracted electrically and contains hydraulic brakes.
The engine is mounted in the fuselage in a central steel tubing frame near the aircraft's Center of Gravity.
Engine power is transmitted via a prop shaft made of composites and a reduction gearbox to the jointed
propeller in the fuselage nose. The propeller is folded in during soaring flight and covered by the movable
nose cone (propeller cone).
One fuel tank is placed in each of the two outer sections of the inner wing.
Technical data:
wingspan 75.5 ft 23.00 meters
length of fuselage 27.6 ft 8.42 m
height 5.74 ft 1.75 m
aspect ratio 28.22
wing area 201.64 sqft. 18.74 m
2
max. weight 1874 lb. 850 kg
max. wing loading 9.29 lb./sqft. 45.36 kg/m
2
airfoil HQ 41/14.35 (laminar profile)
mean aerodynamic wing chord 2.86 ft 0.873 m
engine Limbach L2400 EB1.AD
propeller STEMME 10AP-N
gear box ratio i = 1.18

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1.5 3-View Plan

Flight Manual STEMME S10 Date of Issue Oct. 1, 1990 page: 9
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Section 2 - Limitations
2.1 Introduction 8
2.2 Airspeed 8
2.3 Airspeed Indicator Markings 8
2.4 Power-Plant 8
2.5 Power-Plant Instrument Markings 8
2.6 Masses (Weights) 8
2.7 Center of Gravity 8
2.8 Approved maneuvers 8
2.9 Maneuvering Load Factors (Maximum G-loading) 8
2.10 Flight Crew 8
2.11 Kinds of Operation 8
2.12 Minimum Equipment List 8
2.13 Fuel 8
2.14 Other Limitations 8
2.15 Limitations placards 8

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2.1 Introduction
This section includes operating limitations, instrument markings and the information signs which are
necessary for the safe operation of the motorglider, its engine, standard systems and standard equipment.
The operating limitations included in this section and in section 9 have been approved by the LBA.

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2.2 Airspeed
The airspeed limitations and their importance for the use of the aircraft are shown as follows:
Speed IAS Remarks
VNE
Never exceed speed (maximum
permissible airspeed in calm weather) 270 km/h
146 knots
168 mph
This speed must not be exceeded and the control
movement must be not more than 1/3rd.
VRA
Maximum airspeed in rough air 180 km/h
97 knots
112 mph
Do not exceed this speed
except in smooth air and
then only with caution. Examples of rough air are lee-
wave rotors, thunderclouds etc.
VACalculated maneuvering speed 180 km/h
97 knots
112 mph
Above this limit the controls must not be moved fully or
abruptly because the motorgl
ider structure could be
over-stressed under certain conditions.
VFE Permissible maximum airspeed for
operation of flaps
positive position +5 deg., +10 deg.
Landing position L (+16 deg.)
180 km/h
97 knots
112 mph
140 km/h
76 knots
87 mph
These air
speeds may not be exceeded in the flap position
indicated.
VLO
Permissible maximum airspeed for the
operation of the landing gear 140 km/h
76 knots
87 mph
At airspeeds in excess of this airspeed the landing
gear may not be lowered or raised.
2.3 Airspeed Indicator Markings
The following table gives the airspeed indicator markings and the meaning of the colors (AUW = all-up
weight).
Marking (IAS) Value
or Range]
Meaning
White arc 85-180 km/h
46-97 knots
53-112 mph
Positive flap operation range.
(Lower limit is 1.1 VS0
in landing configuration with maximum AUW. Upper limit is the
maximum airspeed with positive flap position.)
Green arc 90-180 km/h
51-97 knots
59-112 mph
Normal operating range.
(Lower limit is speed 1.1VS1 at max. AUW and most forward C.G. position with
flaps neutral; upper limit is rough air speed.
Yellow arc 180-270 km/h
97-146 knots
112-168 mph
Maneuvers must be conducted with caution and only in smooth air.
L 140 km/h
76 knots
87 mph
Max. permissible airspeed with flaps in landing position and for landing gear
operation
Red line 270 km/h
146 knots
168 mph
Max. airspeed for all operations.
Blue line 115 km/h
62 knots
71 mph
Best rate of climb speed VY.
Yellow
triangle 110 km/h
59 knots
68 mph
Approach speed at max. AUW.

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2.4 Power-Plant
engine manufacturer: LIMBACH
engine: L 2400 EB1.AD
take off power: 92.5 hp / 69 kW
max. permissible take-off RPM 5 min: 3400 rpm
max. permissible permanent RPM: 3000 rpm
max. permissible cylinder head temp.: 482 deg. F / 250 deg. C
max. permissible oil temp.: 248 deg. F / 120 deg. C
oil pressure, minimum: 14.5 p.s.i. / 1 bar
max. permissible press.: 101.5 p.s.i. / 7 bar
lubricants and all other engine related data: refer to Operating and Maintenance Manual LIMBACH L2400
and series.
propeller manufacturer: STEMME
propeller type: 10AP-N
2.5 Power-Plant Instrument Markings
The following table shows the markings of the engine instruments and the meaning of the colors used.
Instrument Red Line
Minimum Limit Green Arc
Normal Operating Yellow Arc
Caution Range Red Line
Maximum Limit
Tachometer1) (rpm) - 1200·-·3000 3000·-·3400 3400
Oil temperature2) [deg. C]
[deg. F]
- 50··120
122 - 248
···50
...122
120
248
Cyl. head Temp.2)[Deg. C]
[Deg. F]
- 150·-·250
302 - 482
···150
...302
250
482
Oil pressure3) [bar]
[p.s.i.]
1
14.5
1 -7
14.5 - 101.5
-
-
7
101.5
Fuel quantity gauge: "0" at white line = empty
Red point (beyond "full" mark) means: "no electrical connection"
Notes:
1) reading error ±50rpm
2) display in [°C]
3) display in [bar]

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2.6 Masses (Weights)
maximum permissible take-off weight: 1874 lb. / 850 kg
maximum permissible landing weight: 1874 lb. / 850 kg
maximum mass of all non-lifting parts: 1256.5 lb. / 570 kg
maximum mass in luggage compartment:48.5 lb. / 22 kg
2.7 Center of Gravity
The limits of the in-flight center of gravity are:
•forward limit:10 in / 254 mm aft of reference plane
•rear limit: 16.5 in / 420 mm aft of reference plane
In this the reference plane is the vertical plane which contains the leading edge of the inner wing at given
angle of the longitudinal axis (refer to maintenance manual).
2.8 Approved maneuvers
The motorglider is certificated in the "Utility" category (normal soaring flight).
2.9 Maneuvering Load Factors (Maximum G-loading)
The following maneuvering load factors (g) must not be exceeded:
up to a maneuvering speed of 97 kts / 180 km/h: positive5.3g; negative 2.65 g.
up to maximum air speed 146 kts / 270 km/h: positive 4.0 g; negative 1.5 g.
2.10 Flight Crew
The crew of the S10 consists of 2 persons; the lowest crew number is one person.
(For solo operations): When operated solo, the left seat is for the pilot in charge.
2.11 Kinds of Operation
•Flights according to VFR by day.
•Flights in IFR and/or icing conditions are not permitted
•Aerobatics and cloud flying are not permitted.
•For VFR-Night Flights a additional euipment is required within the provisions of the national law. Required
base for VFR-Night Flights is the accomplishment of the Stemme SB A31-10-072.
Caution: Night flights are limited to the vicinity of active airfields that are approved for night flight operation
(range of glide ratio).

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2.12 Minimum Equipment List
1 airspeed indicator
1 altimeter
1 stall warning system
1 magnetic direction indicator
1 side slip indicator
1 tachometer
1 engine elapsed time indicator
1 oil pressure indicator
1 oil temperature indicator
2 fuel quantity indicators
1 cylinder head temperature indicator
2 four-element straps
1 parachute or back-cushion (1.97 in / 50 mm compressed) per pilot
1 Canopy breakage tool
2.13 Fuel
total capacity of fuel tanks (±5%): 2 times 11.9 U.S. gal / 45.0 l
as special equipment(±5%): 2 times 15.8 U.S. gal / 60.0 l
unusable fuel quantity 2 times 0.4 U.S. gal / 1.5 l
Permissible octane rating and fuel types:
•AVGAS 100 LL, aviation fuel
•MOGAS (or car fuel super grade, min. 96 OCT. (RON)
The engine manufacturer recommends that at temperatures in excess of 68 deg. F / 20 deg. C. only
AVGAS 100LLOCT. used.
When stowing the aircraft for longer than one month it is recommended to drain the tank if MOGAS has been
used. MOGAS or car fuel have varying compositions, and it is not known how this might affect the long term
service life of the tanks.
2.14 Other Limitations
The only permitted colour for the aircraft exterior painting is white due to the necessity of protecting the
structure from high temperatures caused by sunlight (approved up to 129°F). For coloured warning paintings
the areas of the propeller dome and the wing tips or optional installed winglets are to be used.
For the glazing of the canopy the use of material of an accepted type is permitted only. The luminous
transmittance value of these materials may not be less then 70 per cent and colours may not be falsified.
These characteristics may not be reduced by the use of tinted canopies.
The luggage load must not exceed 22 lb. (10 kg) in each of the compartments at the sides of the cabin and
4.4 lb. (2 kg) in the centre compartment. Single pieces weighing more than 1.1 lb. must be fastened securely
and must load the bottom of the luggage compartment on a sufficient area.

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2.15 Limitations placards
This section provides a list of all cockpit placards and their locations required or containing information for the
safe flight operation of the motorglider.
For further placards please refer to the Maintenance Manual (Document No. MM10US).
Instrument panel near radio (provided for Reg. No.)
on center console in the back
on T-grips in the back
(for Landing Gear Emergency Let Down)
on center console; in front and behind the throttle and choke lever
on nose cone operating handle
on left side of center console
on left face of panel near Airspeed Indicator
on right face of panel
on side wall, left, next to the airbrake lever
next to the lower baggage compartments on the left and right
on back wall over baggage compartment in the back
on the wing flap position indicator (center console)
on center console
on center face of panel
on red T-grip for canopy emergency jettison (on instrument panel, center face)
on red T-grip for canopy emergency jettison (on instrument panel, left face)
on covers of canopy operating handles (left and right)

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Section 3 - Emergency Procedures
3.1 Introduction 8
3.2 Canopy jettison 8
3.3 Bailing out 8
3.4 Stall Recovery 8
3.5 Spin Recovery 8
3.6 Spiral Dive Recovery 8
3.7 Engine failure 8
3.8 Fire 8
3.9 Other Emergencies 8
Landing Gear Malfunction and Emergency Deployment: 8
Breakdown of Electrical System: 8
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