Maintenance Manual STEMME S10-V Date of Issue ... - Stemme AG

Maintenance Manual STEMME S10-V Date of Issue: Sept. 06, 1994 page: iii-2 

Amendment No: 13 Date: May 25. 2005 

Am. 

No. removed Pages included Pages 

Amendment 

Date 

Date of 

inclusion Signature 

11 iii; iv; 4-1; 4-2; 4-3 iii-1; iii-2; iv; 4-1; 4-2; 4-3 09.09.2003 

12 iii-2; iv; 4-1; 4-2; 4-3 iii-2; iv; 4-1; 4-2; 4-3 16.03.2005 

13 

iii-2, iv, v, vi, 3-9, 4-1..4-3, 5-4, 

5-6, 7-2, 7-8, 9-1, 9-2, 9-3 

iii-2, iv, v, vi, 3-9, 4-1..4-3, 5-4, 

5-6, 7-2, 7-8, 9-1, 9-2, 9-3, 9-4, 

9-5 

May 25. 2005 

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Maintenance Manual STEMME S10-V Date of Issue: Sept. 06, 1994 page: iv 

Amendment No:13 Date: May 25, 2005 

0.3 List of Effective Pages 

This record is valid for the Serial No. specified on the title page. Changes on the Maintenance Manual are 

included ex works if dated before production inspection. Amendments concerning alternative equipment is 

provided only if mentioned on page 1. Following amendments must be added by hand. 

page am. no. date 

i 9 Dec. 12,2001 

ii - 

iii-1 11 Sep. 09,2003 

iii-2 13 May 25,2005 

iv 13 May 25,2005 

v 13 May 25,2005 

vi 13 May 25,2005 

1-1 - 

2-1 - 

2-2 7 Nov. 11,1999 

3-1 - 

3-2 5 Feb. 22,1999 

3-3 5 Feb. 22,1999 

3-4 - 

3-5 7 Nov. 11,1999 

3-6 9 Dec. 12,2001 

3-7 7 Nov. 11,1999 

3-8 - 

3-9 13 May 25,2005 

3-10 7 Nov. 11,1999 

4-1 13 May 25,2005 

4-2 13 May 25,2005 

4-3 13 May 25,2005 

5-1 5 Feb. 22,1999 

5-2 5 Feb. 22,1999 

5-3 5 Feb. 22,1999 

5-4 13 May 25,2005 

5-5 4 Aug. 08,1996 

5-6 13 May 25,2005 

5-7 7 Nov. 11,1999 

6-1 - 

6-2 - 

6-3 - 

6-4 - 

6-5 7 Nov. 11,1999 

6-6 7 Nov. 11,1999 

7-1 7 Nov. 11,1999 

7-2 13 May 25,2005 

7-3 - 


7-4 7 Nov. 11,1999 

7-5.1 7 Nov. 11,1999 

7-5.2 7 Nov. 11,1999 

7-6 7 Nov. 11,1999 

7-7.1 7 Nov. 11,1999 

7-7.2 7 Nov. 11,1999 

7-8 13 May 25,2005 

7-9 7 Nov. 11,1999 

7-10 - 

7-11 5 Feb. 22,1999 

8-1 3 Oct. 25,1995 

8-2 3 Oct. 25,1995 

8-3 - 

8-4 5 Feb. 22,1999 

8-5 - 

8-6 3 Oct. 25,1995 

8-7 - 

8-8 

8-9 

5 Feb. 22,1999 

9-1 13 May 25,2005 

9-2 13 May 25,2005 

9-3 13 May 25,2005 

9-4 13 May 25,2005 

9-5 13 May 25,2005 

10-1 1 Dec. 10,1994 

11-1 7 Nov. 11,1999 

12-1 - 

12-2 - 

12-3.1 5 Feb. 22,1999 

12-3.2 5 Feb. 22,1999 

12-4.1 5 Feb. 22,1999 

12-4.2 5 Feb. 22,1999 

12-5.1 5 Feb. 22,1999 

12-5.2 5 Feb. 22,1999 

12-6.1 5 Feb. 22,1999 

12-6.2 5 Feb. 22,1999 

12-7.1 5 Feb. 22,1999 

12-7.2 5 Feb. 22,1999 


12-8.1 5 Feb. 22,1999 

12-8.2 5 Feb. 22,1999 

12-9.1 9 Dec. 12,2001 

12-9.2 5 Feb. 22,1999 

12-10 7 Nov. 11,1999 

12-11 - 

12-12 3 Oct. 25,1995 

12-13.1 7 Nov. 11,1999 

12-13.2 7 Nov. 11,1999 

12-13.3 7 Nov. 11,1999 

12-14 - 

12-15 - 

12-16 - 

12-17 - 

12-18 - 

12-19 3 Oct. 25,1995 

12-20 - 

12-21 - 

12-22 - 

12-23 9 Dec. 12,2001 

12-24 - 

12-25 - 

12-26 - 

12-27 - 

12-28 - 

12-29 - 

12-30 - 

title page 

Annex A 

title page 

Annex B 

title page 

Annex C 

7 Nov. 11,1999 

7 Nov. 11,1999 

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-

Maintenance Manual STEMME S10-V Date of Issue: Sept. 06, 1994 page: v 

Amendment No.: 13 Date: May 25, 2005 

0.4 Contents 

0.1 Deviations from the Basic Maintenance Manual for the Model: ii 

0.2 Record of Amendments iii 

0.3 List of Effective Pages iv 

0.4 Contents v 

1. General Remarks on Maintenance 1-1 

2. Brief Description and Technical Data 2-1 

3. Description of Assemblies 3-1 

3.1 Cell, Primary and Secondary Structures 3-1 

3.1.1 Wing 3-1 

3.1.2 Fuselage and Cockpit 3-1 

3.1.3 Tail Unit 3-3 

3.2 Control System 3-3 

3.3 Power Plant (figure 3.3) 3-5 

3.3.1 Engine 3-5 

3.3.2 Fuel system (fig. 3.3.2.a) 3-5 

3.3.3 Lubrication System 3-6 

3.3.4 Cooling System 3-6 

3.3.5 Induction System 3-6 

3.3.6 Exhaust System 3-6 

3.3.7 Power-Plant Controls and Instruments 3-6 

3.3.8 Fire Protection 3-7 

3.3.9 Engine Cowlings 3-7 

3.3.10 Propeller 3-7 

3.3.11 Drivetrain System 3-9 

3.4 Landing Gear 3-9 

3.4.1 Main Landing Gear (figure 3.4.1) 3-9 

3.4.2 Tail Wheel 3-10 

3.5 Flight Instruments, Pressure System (figure 3.5.a) 3-10 

3.6 Electrical System (figures 3.6.a, b, c, d, e and 3.6.f) 3-10 

3.7 Communication and Navigation Equipment 3-12 

3.8 Oxygen Equipment 3-12 

4. Airworthiness Limitations Section 4-1 

5. Checks 5-1 

5.1 Pre-Flight Checks 5-1 

5.2 Periodical Checks, Inspection Lists 5-1 

5.3 Check Lists for Periodical Inspections 5-1 

5.3.1 Wing 5-1 

5.3.2 Fuselage Front Section 5-2 

5.3.3 Cockpit 5-2 

5.3.4 Center Section of Fuselage 5-3 

5.3.5 Tail Boom 5-3 

5.3.6 Empennage 5-3 

5.3.7 Powerplant - except Propeller and Drivetrain System 5-4 



5.3.10 Main Landing Gear 5-6 


5.3.12 Flight Instruments and Pressure System 5-6 

5.3.13 Electrical System 5-6 

5.3.14 Radio and Navigation Equipment 5-6 

5.3.15 Oxygen System 5-7 

5.3.16 Completition works 5-7 

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Maintenance Manual STEMME S10-V Date of Issue: Sept. 06, 1994 page: vi 


5.4 Special Inspections 5-7 

5.4.1 Inspection following an Impact Landing or a Wing Tip Landing 5-7 

5.4.2 Inspection following an Impact to the rotating Propeller 5-7 

6. Maintenance Instructions, Tolerances, Adjustment Data for the Aircraft 6-1 

6.1 General Information 6-1 

6.2 Ground Towing, Supporting Points, and Lifting of Aircraft 

6.3 Determination of the Empty Weight and Corresponding Center of Gravity; Information on Weight 

6-1 

Limits 6-1 


6.4.1 Deflection of Control Surfaces, Control System Friction, and Pilot Forces 6-4 

6.4.2 Masses and Moments of the Control Surfaces 6-4 

6.4.3 Slackness of Control System Bearings 6-5 

6.5 Lubrication Chart 6-5 

6.6 Tightening Moments for Screw Joints 

7. Maintenance Instructions, Tolerances, Adjustment Data for Assemblies / 

6-5 

Equipment 7-1 

7.1 Airframe 7-1 

7.1.1 Wing 7-1 

7.1.2 Fuselage and Cockpit 7-1 

7.1.3 Tail Unit 7-2 


7.3 Powerplant 7-2 

7.3.1 Engine 7-2 

7.3.2 Fuel System 7-2 

7.3.3 Oil System 7-3 

7.3.4 Cooling System 7-3 

7.3.5 Induction System 7-3 

7.3.6 Controls/Instruments 7-3 

7.3.7 Fire Protection 7-3 

7.3.8 Engine Cowlings 7-3 



7.4 Landing Gear 7-8 

7.4.1 Main Landing Gear 7-8 


7.5 Flight Control Instruments and Pitot and Static Pressure System 7-10 

7.6 Electrical System 7-10 

7.7 Radio and Navigation Equipment 7-11 

7.8 Oxygen Equipment 7-11 

8. List of cockpit placards and their position 8-1 

9. Equipment 9-1 

9.1 Minimum Equipment List 9-1 

9.2 Supplemental Equipment 9-2 

9.3 Additional Equipment and Systems 9-2 

9.3.1 Alternative Equipment 9-2 

9.3.2 Additional Equipment 9-3 

9.3.3 Optional Equipment 9-5 

10. List of Special Tools 10-1 

11. List of Maintenance Documents for Parts Approved Independently from the 

Aircraft 11-1 

12. Figures referring to the previous Sections 12-1 

Annex A: Supplementary Instructions for Maintenance and Care, Maintenance Instructions 

Annex B: Service Bulletins, Airworthiness Directives 

Annex C: Documents (Inspection and Operation Reports) 

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Maintenance Manual STEMME S10-V Date of Issue. Sept. 06, 1994 page: 3-9 


Starter: Push-button for the electric starter. This switch is locked if the ignition is turned on 

before the starter is activated. After each unsuccessful attempt to start the engine, 

the ignition must be switched off first, before the starter can be re-activated. 

Ignition: ON / OFF. 

The ignition switch connects the Aircraft electrical ground with the magnetos. This 

is independent of the Master Switch or the Engine Master Switch. When the ignition 

is switched ON, the starter solenoid circuit is disconnected by a secondary switch 

level in order to prevent damage to the engine and propeller in the event of 

incorrect starting procedures. 

Propeller Variable Pitch: TAKE OFF / CRUISE 

The cruise setting leads to variable power consumption. The propeller is 

disconnected from the electric power source in the TAKE OFF setting of when the 

landing gear is not retracted, the propeller blades then rotate in the take-off setting. 

The take-off setting of the propeller blades (not the switch position!) is indicated by 

a green light under the switch as soon as the Master Switch and the Engine Master 

Switches are ON. 

Avionics: to switch "ON" / "OFF" all flight and navigation instruments electrically energized. 

During operation of the starter, the avionics are switched off or switched over to the 

auxiliary battery (if installed). 

Avionics supply: Connects the avionics bus to the auxiliary battery instead of the main battery. The 

following settings are recommended: 

-Powered flight: setting: Main battery 

-Soaring flight: setting: Auxiliary battery 

Landing gear switch: Upper position: gear up 

Lower position: gear down 

Center position: Circuit disconnected from electrical system. 

ACL (optional): ON / OFF - only active when the Engine Master Switch is positioned ON 

(Anti-Collision Light, ACL). 

Position lights (optional): ON / OFF - only active when the Engine Master Switch is positioned ON. 

Auxiliary Battery (optional) 

Location: In the upper part of the vertical fin or in the left-hand foot-well. 

Utilization: Preferably during soaring flight to avoid inadvertently depleting the main battery while 

soaring and to ensure sufficient capacity of the main battery to re-start the engine. 

Switch Positions: The switch AVIONICS SUPPLY switches from the Main to the Auxiliary battery. 

Alternatively, automatic switch-over during starter operation or when the main circuit 

breaker triggers. 

Charging: By the generator during powered flight. Charging via the external plug only charges the 

main battery; the auxiliary battery must be charged separately via a direct charger 

connection (max. charge voltage is 14.7V). 

CAUTION: If the auxiliary battery is removed (but registered in the Equipment List), airworthiness is 

lost due to changes in Weight and Balance. The Aircraft cannot be operated until the 

Equipment List and Weight and Balance have been corrected. 

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Amendment No.: 13 

LBA-approved 

Date: May 25, 2005 

4. Airworthiness Limitations Section 

This section is FAA-approved for U.S. registered powered sailplanes in accordance with the provisions of 

14 CFR Section 21.29. In addition, this section is required by FAA Type Certificate No. G 58 EU and it 

specifies maintenance required under 14 CFR Sections 43.16 and 91.163 unless an alternative program has 

been FAA-approved. 

The permissible operating times of all parts, components and assemblies assigned for installation - in series 

or optional - in the powered sailplane STEMME S10-V and subject to service life limitations, are notified by 

the Service Bulletin no. A31-10-001. When the limitation of at least one item changes, this SB will be reissued 

in a revised version. The document no. will be maintained in this case, the amendment no. will be advanced 

(the letter in the amendment index is for internal use only). 

The pages of this section are printed on yellow paper for better discernment. They may not be revised without 

FAA engineering approval. Regulations upon keeping of service records must be observed. 

Excerpt of Service Bulletin A31-10-001 Amendment-No: 11.a: Review of permissible operating times: 

No. 

S10 

Model Permissible op. time by 

S10-V 

S10-VT 

Part/Assembly/ 

Equipment 

1 X X X Airframe 

(Composite structure) 

2 X X Limbach Engine 

Manufacturer, 

Type 

Part No. 

(STEMME) 

Overhaul 

(TBO) 

Replaceme 

nt 

NOTES 

STEMME sundry 6000 h 6000 h (1) 

Limbach 

L 2400 EB 1.D 

L 2400 EB 1.AD 

10AM-MOL (2) 

3 X X Magneto for Limbach Slick 4230 (from Limbach) (2) 

4 X Rotax Engine 

5 X 

Propeller 

(fixed pitch) 

ROTAX 914 

F2/S1 

11AM-M 

1000 h 

(10 years) 

STEMME 10AP-N 400 h (3)(4) 

6 X Lateral parts STEMME 

10AP-N01 

10AP-N11 

1000h (4) 

7 X Fix-Pitch Propeller STEMME 10AP-F 400 h (3) (4) 

8 X Centre Part STEMME 10AP-F01 2000 h (4) 

9 X Variable pitch propeller STEMME 10AP-V 

200 h 

(5 years) 

(3)(4)(10) 

10 X Variable pitch propeller STEMME 11AP-V 

200 h 

(5 years) 

(3)(4)(10) 

11 X X Propeller hub STEMME 10AP-V01 2000h (4) 

12 X 

Propeller fork and 

X 

its fastening 

STEMME 

10AP-V88, 

-V77, -V78, -VU 

400h (3)(4) 

13 X X 

Reduction Gear 

(vee-belts) 

STEMME 10AG 400 h (3)(4) 

14 

Reduction Gear 

X 

(cog wheels) 

STEMME 11AG 1000 h (3)(4) 

15 X Gear suspension STEMME 10AA 1000 h 12 years (4) 



18 X X 

Flywheel clutch 

(2 flyweights) 

STEMME 10AK 400 h (3)(4) 

19 

Flywheel clutch 

X 

(3 flyweights) 

STEMME 11AK 400 h (3)(4) 

20 X X Driveshaft 

Ciba-Geigy 

(without P/N ref.) 

10AS-07 400 h (3)(4)(9) 

21 X X X Driveshaft 

Glaenzer-Spicer 

19.01.01.xxx 

10AS-07 400 h (3)(4)(9) 

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(8)


Amendment No.: 13 

LBA-approved 

Date: May 25, 2005 

Model Permissible op. time by 

No. 

S10 

S10-V 

S10-VT 

Part/Assembly/ 

Equipment 

Manufacturer, 

Type 

Part No. 

(STEMME) 

Overhaul 

(TBO) 

Replaceme 

nt 

NOTES 

22 X X X Driveshaft 

MAN Techn. AG 

95.0700.00.000 

10AS-W 400 h (3)(4)(9) 

23 X X X Driveshaft STEMME 10AS-F 400 h (3)(4)(9) 

24 

rubber parts of the 

X 

engine 

Rotax sundry 5 years (7) 

25 

Differential fuel 

X 

pressure sensor 

STEMME 11AB-K01 5 years 

26 X X 

Rubber parts of the 

X 

gear suspension 

STEMME sundry 12 years 

27 X X 

Rubber parts of the 

clutch 

STEMME 

10AK-43 

10AK-48 

12 years 

28 X X 

flexible disk of the drive 

shaft system 

STEMME 10AS-09 12 years 

29 

flexible disk of the drive 

X 

shaft system 

STEMME 11AS-09 12 years 

30 X X Fuel Hoses STEMME 10AB-... - 5 years 

31 X X Fuel Hoses STEMME HZ-KSL 014 - 5 years 

32 X X X Fuel Hoses STEMME HZ-KSL010 - 5 years 

33 X X Lubrication Hoses STEMME 10AM-KÖS / ~T - 5 years 

34 X Lubrication Hoses STEMME 11AM-O... - 5 years 

35 X Coolant Hoses STEMME 11AM-W... - 5 years 

36 X X X Brake Hoses sundry 10FO-B06 - 10 years 

37 X X X Safety Harnesses sundry 10C-08/-09 - 12 years (6) 

38 X X 

Control Rod 

X 

Connectors 

L'Hotellier 10M-098/-099 (2) 

On expiry of a part’s permissible operating times the affected part has to be sent to the manufacturer for 

inspection. The manufacturer has to decide if further use is possible after the inspection, or if an replacement 

or overhaul or repair is necessary. 

If the limitation is given in operating hours and in a calendar period (year), the first occurring case applies. 

If further equipment subject to service life limitations is installed, the overhaul intervals and service life limits 

prescribed by the respective manufacturer must be observed. The item has to be entered in the form Review 

of Operating times. 

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Maintenance Manual STEMME S10-V Date of Issue: Sept. 06, 1994 page: 5-4 


Type and Subject of Inspection first 

25 

7. Inspect Horizontal Stabilizer rear fitting for wear of pins/bushings, fatigue 

cracks (especially in the vicinity of welding and cutouts in the fixing plates), 

axial and radial clearance, corrosion. 

Inspection after [h] 

every 

50 

every 

100 

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AI 

X X X 

8. Check tight fit of all bolt connections of both HS fittings. X X X 

9. Check bolt connection of elevator push-pull rod to rear HS fitting. X X X 

10. Check HS fittings for slackness after attaching the HS (section 7.1.3). X X X 

11. Inspect HS and elevator for damage and cracks, look out for signs of hidden 

structural damage. Check drain outlets. 

12. Check deflection of rudder and elevator (for Control Surface adjustment data, 

see section 12) 

X X 

X X 

5.3.7 Powerplant – except Propeller and Drivetrain System 

The hours given in this list are engine operating hours. 

Caution: In excess of the inspections listed below, the instructions of the engine manufacturer 

given in the Engine Operating and Maintenance Manual are mandatory. LIMBACH 

prescribes an additional periodical engine check after every 25 operating hours. 

1. Check engine mounting X X 

2. Check fuel lines and fittings for leak tightness (fuel leakage) X X X 

3. Check conditions of fuel lines (in particular cracks in the outer surface) X X X 

4. Check function of the electric fuel pumps. X X 

5. Exchange fine filters, clean coarse filters (in tank connector at the wing root; 

open clamp on wing side and remove finger strainer) 

X X 

6. Inspect oil lines, fire protection hose and fittings to oil cooler and engine for 

leaks, improper condition (consider service life limit) and looseness. Check 

sealing cuff at the left cowling to the oil cooler for proper sealing. 

7. Check proper function and settings of air inlet flaps, controlled via cowl flap 

lever. Settings approx. 2, 2.8, 3.5 in. (5, 7, 9 cm). The flaps must not jam and 

fully opened position must be reached safely. Sealing cuff of the cooling air 

ducts in the side cowling must be in contact with the cooling air box of the 

engine 

8. Inspect flexible hose between the air filters and the carburetors for proper 

condition and tight fit. 

X X X 

X X X X 

X X X 

9. Check the exhaust system for sealing, cracks and correct attachment X X X 

10. Throttle/choke control: make sure that the extreme positions in the carburetors 

are achieved. Check attachment of control cables and bowden cable casings. 

Check condition of return springs on the carburetors. 

X X X 

11. Functional check of engine instruments X X X 

12. Check fire wall steel sheets for proper condition and tight fit. X X X



Inspection after [h] 

Type and Subject of Inspection first 

25 

5.3.10 Main Landing Gear 

1. Inspect the main landing gear legs and trailing arms for deformation and 

possible cracks as an result of overloads 

every 

50 

every 

100 

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AI 

X X X X 

2. Check the linear actuators for external damages. X X X 

3. Inspect the screw joint of the complete landing gear X X X 

4. Check main landing gear tires for poor condition and creep markings. Tire 

pressure: [45 - 48 p.s.i. (3.1 - 3.3 bar)] 5s [36 - 39 p.s.i. (2.5 - 2.7 bar), if optional 

wide tires installed] 5a 

X X X X 

5. Functional check of trailing arm spring suspension. X X X 

6. Wheel bearings: check for ease of operation and play. X X X 

7. Inspect brake master and wheel cylinders. Check hoses and tubes for proper 

guidance, chafe marks and leakage. 

X X X 

8. Inspect brake discs and brake linings (at least 0.06 in. / 1.5 mm). X X 

9. Check brake fluid level (replace fluid once in two years). X X X 

10. Check efficiency of brakes, adjust brake or vent brake system if required. X X X X 

11. Clean and grease hinges of landing gear doors. X X 

12. Functional check of the landing gear (support the Aircraft on trestles); check 

stop switches, fit of gear doors, bowden cables for emergency release and the 

release mechanism on the brace strut. 

13. Inspect the operating mechanism of the LH landing gear door, including 

bowden cable, for improper operation and poor condition. 

X X X 

X X X 

14. Check landing gear position indicator and warning system X X X X 

15. Functional check of landing gear Emergency Extension Mechanism X X 

5.3.11 Tail Wheel 

1. Check tail wheel unit for ease of operation and play. X X X 

2. Check condition of tire, pressure (40.6±2.9 p.s.i. / 2.8±0.2 bar) and creep 

markings. 

X X X X 

3. Inspect wheel fork, including bearing. X X X 

4. Check spring coupling between tail wheel and rudder. X X X 

5.3.12 Flight Instruments and Pressure System 

1. Check condition and function - if applicable service life limits - of the flight 

control instruments (see Equipment List) 

X X 

2. Check adjustment of the stall warning (every second AI) X X 

5.3.13 Electrical System 

1. Inspect wiring and conduits for improper routing, insecure mounting and 

obvious defects of electric components. 

2. Inspect condition of main battery (among others voltage drop during starter 

operation). 

5.3.14 Radio and Navigation Equipment 

1. Inspect radio and navigation equipment for improper installation and insecure 

mounting (observe equipment list). Check service life limits if applicable. 

X X 

X X 

X X 

2. Check each antenna installed X


Amendment No.: 13 Date: May 25. 2005 

7.1.3 Tail Unit 

During inspection of the horizontal tail mountings, check the backlash of the horizontal tail attachment by the 

following procedure: 

• move horizontal tail tip forward and aft and up and down 

• take hold of the mid section of the horizontal tail fin, push up and down 

If excessive backlash is found, the bolts and fittings must be measured. Maximum allowable backlash of 

horizontal tail fittings: 

forward fitting: vertically 0.006 in. (0.15 mm) horizontally 0.004 in. (0.1 mm) 

rear fitting vertically 0.006 in. (0.15 mm) horizontally 0.006 in. (0.15 mm) 

7.2 Control System 

Position of stops of the control systems: see description in section 3.2 

Adjustment data: see fig. 6.4.1. 

7.3 Powerplant 

7.3.1 Engine 

Maintenance of the engine in accordance with the instructions of the Operating and Maintenance Manual for 

Flight Engines "Limbach L 2400 and Series". 

Adjustment of the carburetors: For access from the top, remove cover in the upper fire wall. 

Access to the fuel pump: Remove cover in the upper fire wall. 

Access to the mounting attachment of accessories (generator, magneto): remove lateral and lower engine 

cowlings. 

Removal of Engine: 

• disconnect battery 

• remove front and rear fire wall sheets 

• remove V-supports of the frame below the engine 

• loosen clutch on engine side and push it forward on the sliding joint (attention: do not lose bushes of 

screw joints). 

• remove muffler 

• disconnect electrical wiring, fuel hoses above the firewall, bowden cables, oil hoses on the engine and air 

induction hoses 

• support the engine. Then loosen front engine mount at the attachment to the frame, loosen rear engine 

support (attention: mark the distance bushes left/right for reinstallation) 

• lower down engine 

Installation of Engine: 

In the opposite order as removal. 

7.3.2 Fuel System 

Check all fuel lines in the fuel system for tight fit and leak tightness. Check the fuel lines for conditions. A 

indication for high wear and the necessary replacement are cracks in the outer surface. 

For replacement of the fuel hoses after expiration of the allowable time in service, remove or lift the upper 

parts of the fire wall. 

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Amendment No.: 13 Date: May 25. 2005 

7.4 Landing Gear 

7.4.1 Main Landing Gear 

Check the main landing gear legs and the trailing arms for deformations and possible cracks as an result of 

overloads. 

Adjustment Data: see fig. 3.4.1.a 

Functional Check: 

Support the Aircraft (clearance between the main wheels and the ground must be approximately 1.6 in. / 

40 mm), remove upper cowling of the central fuselage. 

Checking procedure: 

• Inspect screw joints (torque paint); 

• check wheels for smooth turning; 

• joint heads of the operating arms should not be jammed; 

• the articulations of the spindles and the operating arms must have play; 

• installation of the landing gear emergency release system without kinks/collisions; 

• landing gear stop switches on the operating arms: check for halfway position and proper functioning, 

inspect wiring / connection; 

• retraction of left landing gear leg: 

Check if the landing gear contacts surrounding components, 

Brake tube must have regular bends, must not jam. 

Stop switch adjustment: 0.08 to 0.2 in. (2 - 5 mm) clearance between the landing gear leg and the shaft 

housing. 

The stop switch must be positioned in the middle of the landing gear strut. 

Joint heads of the operating arm must not be jammed 

Articulation between the spindle and the operating arm must not jam 

• extension of left landing gear leg: 

check if the operating arm returns to its correct over-center-locked position, if necessary adjust the switch. 

• retraction of right landing gear leg: 

(separated from the left side - for this purpose, actuate left stop switch "retracted") 

Check if the leg contacts surrounding components. 

Brake tube must have regular bends, must not jam. 

The stop switch must be positioned in the middle of the landing gear strut. 

Joint heads of the operating arm must not be jammed. 

Articulation between the spindle and the operating arm must not jam. 

• extension of right landing gear leg: 

check for correctly over-center-locked position of the operating arm. 

• retraction of both landing gear legs: 

Collision check. 

Align stop switch on the right landing gear leg for a clearance of 0.08 to 0.12 in. (2 - 3 mm) between both 

gear legs; 

• check of landing gear doors: 

Smooth operation of gear doors 

Fit of gear doors 

Clearance between gear doors and wheels 0.4 to 0.6 in. (10 - 15 mm). 

• retract landing gear with the upper cowling of the central fuselage mounted: 

Check clearance between the drive spindles and the cowling 

the bowden cables of the emergency release system may not be buckled or get stuck 

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9. Equipment 

9.1 Minimum Equipment List 

Subject Manufacturer Type TC No., Specification 

No. 

Range 

Airspeed Indicator Winter 6FMS4 TS10.210/15 up to 300 km/h 

up to 180 mph 

up to 160 kts 

Winter 6FMS5 TS10.210/16 up to 300 km/h 

up to 180 mph 

up to 160 kts 


up to 180 mph 

up to 160 kts 


up to 180 mph 

up to 160 kts 

Altimeter Winter 4FGH10 TS10.220/46 up to 10,000 m 

up to 30,000 ft 

Winter 4FGH20 TS10.220/47 up to 10,000 m 

up to 30,000 ft 

Winter 4FGH40 up to 20,000 ft 

Winter 4HM6 TS10.220/44 up to 6,000 m 

PZL W-12S FD-3/75 

Compass Airpath C2300 - - 

Stall Warning 

System 

PZL B-13 FD19/77 - 

Ludolph FK16 10.410/3 - 

Ludolph FK5 10.410/1 - 

Hamilton HI400 TSO C7c Type 1 - 

Presesion Aviation 

Inc. 

PAI-700 TSO 

Westerboer Speed Control - - 

up to 20,000 ft 

Revolution Counter VDO 333.230/009/1 - up to 4000 min -1 

Engine hour meter Winter FSZM TS-GW 1510 - 

VDO 331.811/010/2 - - 

Oil pressure meter VDO 350.271/031/7 - up to 10 bar 

Oil temp. meter VDO 310.274/082/1 - up to 150 °C 

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Subject Manufacturer Type TC No., Specification 

No. 

Range 

Fuel contents meter VDO 301.271/036/1 - 0 ··· 4 / 4 

Cylinder head 

temperature meter 

Limbach 170.215/001 - up to 375 °C 

Four-element straps Gadringer BaGu 5202 SchuGu 

2700 

40.070/32 

40.071/05 

Back-cushion One per seat, compressed 2 in. (50 mm) thick (if no parachute, minimum 2 in. thick, is 

used) 

9.2 Supplemental Equipment 

Depending on operational and environmental conditions, further equipment may be mandatory to 

supplementary to the minimum compulsory equipment. The supplementary equipment allowed to be installed 

in the Stemme S10-V is listed in the following selection list. 

At the moment, certification is only valid for daytime VFR flights. Flights from 30 min before sunrise and up to 

30 min after sunset require lighting equipment, consisting of LH and RH navigation lights, tail position light 

and anti collision light. 

VFR-Night flights are possible after accomplishment of the Stemme SB A31-10-072. 

Subject Manufacturer Type 

Lightning system 

TC No., 

Specification No. 

ACL / Position Lights Whelen / STEMME 

Stern Light Hella / STEMME 

Landing Light Hella / STEMME 

9.3 Additional Equipment and Systems 

Range, 

Remarks 

Different equipment and systems may be installed in the powered glider S10, which are not part of the 

minimum or supplementary equipment and which normally are not series standard. Basically the cases 

“Alternative Equipment”, "Additional Equipment" and "Optional Systems" have to be distinguished and treated 

differently. For further information please refer to the Service Bulletin A31-10-008. 

9.3.1 Alternative Equipment 

Special attention is to be paid to the case of equipment and systems which are not installed in addition to but 

as an alternative to the standard version and thus have an influence on the standard text of the Maintenance 

Manual. Here the rule applies that associated information is added to the corresponding passage of the 

standard text, with the original text (if any) and the amended text appearing in square brackets each. A 

reference number following the closed bracket is identical with the current revision number, the letter 

following the reference number indicates whether the text passage applies to the standard version ("s") or to 

the alternative version ("a") (example: [···] 3a ). 

All text passages in brackets which do not correspond to the aircraft's design configuration 

described on page 1 (standard version, if no entries) must be crossed out. 

If this procedure cannot be applied (amendments to illustrations), the STEMME Company will keep ready 

"special versions" of the pages concerned identified with the corresponding SB number. In the case of an 

overall revision, all versions of a page will be newly issued; the version applicable to the aircraft concerned is 

to be inserted. 

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9.3.2 Additional Equipment 

In addition to the minimum and supplementary equipment, installation of the following devices is allowed. A 

precondition is that the energy balance remains within certified limits and the certified weight of equipment in 

the instrument panel is not exceeded. Altogether 11 kg / 24 lbs instruments, including maximum 1 kg / 2.2 lbs 

of engine instruments, are certified. 

Additionally a ground and flight test must be performed, showing electromagnetic compatibility (EMC). 

Changes of equipment may be performed by qualified personnel only. An inspector must confirm the correct 

installation by an entry in the a/c-logbook, the EMC-test flight, the keeping of the energy balance and the 

inclusion of the changes into the equipment list and the weight and balance report. The above-mentioned 

inspection and operation documents must be added to Annex C of this Maintenance Manual. 

Subject Manufacturer Type TC No., 


Compass Bohli 46-MFK-1 

Range, 

Remarks 

Mechanical Winter 5StV5 ± 5 m/s 

Variometer Winter 5StVM5 ± 1000 ft/min 

Bohli 68-PVF-2 ± 10 kts 

VHF-COM Becker umpteen 

King-Bendix umpteen 

Dittel umpteen 

Terra umpteen 

Intercom PS Engineering 

(panel mount) 

Transponder/ 

Encoder 

TELEX 

(panel mount) 

Sigtronics (panel 

mount) 

Flightcom (panel 

mount) 

Flightcom (panel 

mount) 

all models 

Pro Com 4 

SPA-400 TSO 

403-MC 

ATC-2 

Softcom (portable) ATC-2 

Becker ATC-series 

Filser TRT-series 

Garmin GTX-series 

King-Bendix KT-series 

Terra TRT 250 D TSO-C74c 

Terra AT 3000 TSO-C88 

ACK A-30 TSO-C88a 

Ameri-King AK-series 

Emergency ACK E-01 

Transmitter (ELT) Pointer 3000 TSO C91 

Part ELT 

GPS & Moving Map Garmin all fix installed 

NAVITEC MC 3000 System 

Skyforce Tracker II 

TR 2000 

Skyforce Skymap II 

SM 2000 

CAA L301031 

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Subject Manufacturer Type TC No., 


Skyforce Colour Tracker 

CT 2000 

Skyforce Colour Skymap 

CM 2000 

EFIS Dynon Avionics EFIS D-10 System 

Electronic Vario, Filser/LX Navigation LX systems 

Soaring Computer ILEC SB-8 

Collision warning 

system 

SN-10 

Cambridge CAV II 

S-NAV 

L-NAV 

GPS-NAV 

300 series 

Peschges VP systems 

Holltronic Cenfis-system 

SDI-Pöschl C4 system 

Zs1 System 

GP 941 

FLARM Technology FLARM 

VHF NAV (VOR) Becker NR3301 series 

Becker IN 3300 (indicator) 

Becker IN 3360 (indicator) 

Terra TN 200D 

King-Bendix KX125 (COM/NAV) TSO-C37c, -C38c, - 

C40c 

Horizon LUN LUN 1202 

PC Flight systems EGYRO-series 

R.C.Allen RCA26AK-4 

Turn and Bank Gauting WZ404 

Indicator Gauting WZ402/14 

Keha 703 

Directional Gyro R.C.Allen RCA15AK-2 

Range, 

Remarks 

combined COM/VOR 

Fire Warning System Stemme Series equipment 

Voltmeter/Ammeter Filser SR001 Series equipment 

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9.3.3 Optional Systems 

Optional systems are not normally included in the Maintenance Manual. To each of these systems delivered 

by STEMME, a Service Bulletin approved by the LBA is assigned, providing the information necessary for 

correct installation and inspection (e. g. Serial No.'s, Documents, supplementary procedures). If installation 

requires additional instructions, an installation instruction is provided. If flight operation requires additional 

information, supplements to the Flight Manual are provided. Information required for maintained airworthiness 

are published as maintenance instructions, to be inserted in the Annex A of this Maintenance Manual and 

added to the list of maintenance instructions on the cover sheet of Annex A. 

The document no. Of the Service Bulletin and relevant documents are always identical except for the prefix 

(A31- Service Bulletin, A34- Installation Instruction, A36- Flight Manual Supplement). 

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Maintenance Manual STEMME S10-V Date of Issue ... - Stemme AG

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