STEMME S6, S6-RT Maintenance Manual

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MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

Issued: December 2010

STEMME

2010

STEMME TSA-M

MODELS:

S6 S6-RT

Doc.-No. P500-006.000 Rev. 9

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Revision Number

Date of

Revision

Revised

Chapters

Descriptions of Revisions

Date

Inserted

RECORD OF REVISIONS

20.12.2010

18.03.2011

28.06.2011

04.07.2011

26.09.2011

01.11.2011

18.11.2011

28.02.2012

16.03.2012

04.05.2012

26, 31, 91

05, 06, 21, 91

05, 11, 12, 53,

06, 11, 12, 20,

28, 57, 71

24, 71, 91

all

10, 11

05, 11, 12, 28, 31, 32, 57, 71,

72, 75

First complete Issue

Installation Fire Warning

Introduction Cabin Heating (Option)

Introduction Aerotow Equipment (Option)

Flap Setting Cruise -4.0°, Documentary Changes

Introduction Solar Panel (Option)

Introduction Retractable Landing Gear, 900 kg MTOW (Model S6-RT), Documentary Changes (incl. change of header all pages)

100h TBO Front Gear Box

Introduction Wing Folding Device (Option)

Documentary Changes, Corrections

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CHAPTER 00

INTRODUCTION

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00 - TOC

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TABLE OF CONTENTS

Chapter Section

Title Subject Page

INTRODUCTION .............................................................................................00-00-00 1

General 00-00-00 1 List of Vendor Technical Publications 00-00-00 1 Structure of Maintenance Manual 00-00-00 2 Using the Maintenance Manual 00-00-00 4 List of Chapters 00-00-00 7 List of Effective Pages 00-00-00 9 Applicable Service Bulletins 00-00-00 11

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No.

Manual No./Part No.

Manual Title

Vendor

Doc-No. P400-006.000 / E / FAA latest Revision

Airplane Flight Manual TSA-M Model: S6

STEMME AG

Doc-No. P400-006.001 / E / FAA latest Revision

Airplane Flight Manual TSA-M Model: S6-RT

STEMME AG

Doc-No. P530-901.500 latest Revision

Illustrated Parts Catalog STEMME S6 STEMME AG

Doc-No. A35- 10SMRE latest Revision

Small Repairs of Composite Material Parts for STEMME Aircraft

STEMME AG

ROTAX Part. No. 809606, Rev. 1, September 01/2007, or a later Revision

Maintenance Manual (Line) for ROTAX 914 Series

ROTAX Aircraft Engines

ROTAX Part. No. 809603, Rev. 1, January 01/2008, or a later Revision

Maintenance Manual (Heavy) for ROTAX 912 and 914 Series

ROTAX Aircraft Engines

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INTRODUCTION

1. General

This maintenance manual provides necessary for the maintenance of the S6 information to the maintenance personnel. It contains detailed descriptions of the systems, troubleshooting, and maintenance practices.

In this handbook are only contained maintenance practices about jobs, which are to be practiced at the aircraft itself: e.g. removal and installation of components. The maintenance instructions for engine and propeller are given by their own Maintenance Manuals.

Maintenance, repairs and inspections must be accomplished in accordance with the instructions given in this Maintenance Manual (MM).

2. List of Vendor Technical Publications

A. Use the MM in conjunction with vendor technical publications listed in the table 01.

No.

Manual No./Part No.

Manual Title

Vendor

Doc-No. P400-006.000 / E / FAA latest Revision

Airplane Flight Manual TSA-M Model: S6

STEMME AG

Doc-No. P400-006.001 / E / FAA latest Revision

Airplane Flight Manual TSA-M Model: S6-RT

STEMME AG

Doc-No. P530-901.500 latest Revision

Illustrated Parts Catalog STEMME S6 STEMME AG

Doc-No. A35- 10SMRE latest Revision

Small Repairs of Composite Material Parts for STEMME Aircraft

STEMME AG

ROTAX Part. No. 809606, Rev. 1, September 01/2007, or a later Revision

Maintenance Manual (Line) for ROTAX 914 Series

ROTAX Aircraft Engines

ROTAX Part. No. 809603, Rev. 1, January 01/2008, or a later Revision

Maintenance Manual (Heavy) for ROTAX 912 and 914 Series

ROTAX Aircraft Engines

Table 1 - List of Vendor Technical Publications

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No.

Manual No./Part No.

Manual Title

Vendor

ROTAX Part. No. 899470, Rev. 0, December 01/2007, or a later Revision

Illustrated Parts Catalog ROTAX 912 A/F/S/UL/ULS/ULSFR and 914 F/UL

ROTAX Aircraft Engines

ROTAX Part. No. 899643, Rev. 01, February 01/2008, or a later Revision

Operator’s Manual for ROTAX 914 Series ROTAX Aircraft Engines

E-118, Issue No. 33, September 18th, 2007 or a later Issue

Operation & Installa tion Manual, Electrically Controlled Var iable Pitch Propeller

mt-Propeller Entwicklung GmbH

Garmin p/n 190-00356-02, latest revision

400W series Installation Manual Garmin International

Garmin p/n 190-00180-00, latest revision

GI-102A/GI-106A Installation Manual Gar min International

Garmin p/n 190-00149-01, latest revision

GMA340 Audio Panel Installation Manual Garmin International

Garmin p/n 190-00207-02, latest revision

GTX 330/GTX330D Transponder Installation Manual

Garmin International

14 ---

Operating Manual for Aero tow Release, Type Tail Clutch E22 (german)

TOST GmbH, Flugzeuggerätebau München

Table 1 - List of Vendor Technical Publications (Continued)

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3. Structure of the Maintenance Manual

The MM has been prepared in accordance with the Air Transport Association (ATA) Specification Number 100 for Manufacturers Technical Data.

A. Division of Subject Matter

The MM is divided into 5 major sections. Each of these sections is subdivided into chapters. A list of effective pages and the table of contents are provided at the beginning of each MM chapter.

(1) General Ch. 05 - 12 (2) Airframe Systems Ch. 20 - 37 (3) Structures Ch. 51 - 57 (4) Propeller Ch. 61 (5) Power Plant Ch. 71 - 80

Each chapter is separated by a cover sheet with the chapter number and the title.

B. The Page Numbering System

(1) The page numbering system consists of three-element numbers separated by dashes.

The first element of the division identify a system: e.g. 27 – Flight Controls (a chapter)

The following element designate a subsystem in the system:

e.g. 27-30 Elevator (a section)

If a system consists of several subsystems, further sections are added: e.g. 27 - 31 Elevator Trim control (a further section)

The last element permits the identification of the individual units in a system or subsystem. However, this is used if it is necessary.

Example

27 - 10 - 00

Chapter/ Section/ Subject/ System Subsystem Unit (here Flight- (here Controls) Ailerons)

(2) When the chapter/system element number is followed with zeros in the section/subsystem

and subject/unit element number (28-00-00), the information is applicable to the entire system.

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(3) When the section/subsystem element number is followed with zeros in the subject/unit

element number (28-20-00), the information is applicable to subsystem within the system.

(4) The subject/unit element number is used to identify information applicable to units within

the subsystems.

This breakdown of the chapters provides a good overview and facilitates exchange of revised pages. Since the most of systems are relatively simple and noncomplex, the third element is used only at more complicated systems, i.e. if it appears necessary to treat a unit or device in greater detail.

(5) All maintenance data given in the MM is separated into specific types of information.

That facilitates work with the manual. For this purpose, page number blocks are reserved depending on type of information.

Page 1 - 99 Description and Operation Page 101 - 199 Troubleshooting Page 201 - 299 Maintenance Practices Page 301 - 399 Servicing Page 401 - 499 Removal/Installation Page 501 - 599 Adjustment/Test Page 601 - 699 Inspection/Check Page 701 - 799 Cleaning/Painting Page 801 - 899 Repairs

A page number as an example:

Page 301 First page with service instructions

12 - 17 - 00

14.11.08 Publication date

Servicing Battery

(6) Figures are numbered consecutively within each topic.

Example: Fig. 201 1. Illustration for maintenance

Fig. 202 2. Illustration for maintenance etc.

C. Page Order

(1) In the Front of the Manual:

Title Record of Revisions Record of Temporary Revisions Introduction

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(2) Each chapter begins with:

Title Table of Contents

D. Figures

The figures within the sections of a chapter are numbered in accordance with the appropriate page number block. Numbering is beginning by one (1) and continuous.

4. Using the Maintenance Manual

A. To obtain information about a specific system, refer to the List of Effective Chapters in front of

manual in order to find the corresponding chapter number here. In the table of contents of the respective chapter, one then finds closer information about the arrangement of material.

B. Effectivity and Effectivity Block

This Maintenance Manual is "customized". It includes the following effectivity identification system to show modification and/or configurational differences.

(1) The MM starts with a List of Effective Chapters. Each chapter is listed with the date of issue

or revision.

(2) To identify the aircraft an effectivity statement (i.e. Garmin Avionics) or a six-digit numeric

indicator is shown in the effectivity column in the table of contents if applicable. (a) The six-digit numeric indicator begins with the last three digits of the lowest assigned

number, to indicate first effectivity, and ends with the last three digits of the highest assigned number, to indicate last effectivity, of an unbroken sequence of assigned numbers. A hyphen is shown between the numbers. Open ended effectivity is indicated by "999" in the last effectivity if applicable. For example: 023-999 indicates aircraft 023 and subsequent.

(3) Effectivity Block

The system provides further direct annotation of the applicability on pages. On pages not applicable for all models of the aircraft type, all serial numbers or equipment variants at the bottoms left-hand corner a effectivity block appears. The effectivity identification placed

in this block may be a six-digit numeric indicator (Ref. to (2)(a)) or an effectivity statement. (Refer to Figure 01) All information appearing on that page applies only to the aircraft noted in the effectivity block, respectively for aircraft equipped with mentioned item.

NOTE: Pages with no effectivity block may be followed by pages which have

effectivity blocks and vice versa and bear identical page numbers.

NOTE: The contents of pages with effectivity block extends or subsitutes the

contents of pages with identical page numbers with no effectivity block.

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C. Revisions

(1) Maintenance manual revisions, result by different reasons (regulation changes, technical

changes, typographical errors and so on), will be published regularly. This manual has been prepared in loose-leaf form for ease in inserting revisions. The ATA format in presentation and numbering allows quick reference to data in each section. Logical and convenient Table of Contents at the beginning of each chapter to aid in locating specific data within that chapter.

(2) Identifying Revised Material

(a) Revisions and /or additions will be identified by a vertical black line (revision bar) along

the outside of the page opposite only that portion of the printed matter that was changed. This also applies to illustrations.

(b) When technical changes cause unchanged text to appear on a different page(s), a

revision bar will be placed in the outside margin, opposite the chapter/section/subject, page number and date of all affected pages, providing no other revision bar appears on the page.

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Meter

Common

Meter Plus

PSI Desired

Value (VDC)

Unit under

test

Pin 2 (blk) Pin 4 (red) 0 4.95 to 5.0 3010016,17,18 Pin 2 (blk) Pin 1 (wht) 0 1.70 to 2.10 3010016,17,18

Pin 2 (bik) Pin 3 (grn) 0 1.70 to 2.10 3010016,17,18 Pin 3 (grn) Pin 1 (wht) 0 -0.003 to +0.003 3010016,17,18 Pin 3 (grn) Pin 1 (wht) 10 0.031 to +0.034 3010016 Pin 3 (grn) Pin 1 (wht) 30 0.028 to +0.032 3010017 Pin 3 (grn) Pin 1 (wht) 60 0.028 to +0.032 3010018

77-40-00

Page 101

Feb 26/10

EFFECTIVITY

Aircraft equipped with VM 1000 Engine Management System

Effectivity Block

Figure 01

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D. WARNINGS, CAUTIONS, and NOTES

If maintenance operations on the airplane are practiced, general safety and maintenance rules must be always considered. In addition, the MM contains adjuncts to the text used to highlight or emphasize important and critical instructions.

WARNING:

HAZARD FOR MAINTENANCE PERSONNEL!

CAUTION:

HAZARD FOR SYSTEMS AND EQUIPMENT!

NOTE:

Specific information

E. Abbreviations

Where it appears reasonable, abbreviations are used. They are conforming to a recognized standard.

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5. List of Chapters

Chapter Title Date

GENERAL

00 Introduction Mar 16/12 02 General Nov 18/11

04 Airworthiness Feb 28/12 05 Time Limits / Maintenance Checks May 04/12 06 Dimensions and Areas Nov 18/11 07 Lifting & Shoring Nov 18/11 08 Leveling and Weighing Nov 18/11 09 Towing and Taxiing Nov 18/11 10 Parking, Mooring, Storage & Return to Service Mar 16/12 11 Placards and Markings 12 Servicing

AIRFRAME SYSTEMS

20 Standard Practices Airframe Nov 18/11 21 Ventilation Nov 18/11 23 Communications Nov 18/11 24 Electrical Power Nov 18/11 25 Equipment and Furnishings Nov 18/11 26 Fire Detection Nov 18/11 27 Flight Control System Nov 18/11 28 Fuel 31 Indicating/Recording Systems 32 Landing Gear 33 Lights Nov 18/11 34 Navigation Nov 18/11

STRUCTURES

51 Structures - General Nov 18/11 52 Doors Nov 18/11 53 Fuselage Nov 18/11 55 Stabilizers Nov 18/11 57 Wings

PROPELLER

61 Propeller Nov 18/11

May 04/12 May 04/12

May 04/12 May 04/12 May 04/12

May 04/12

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5. List of Chapters (continued)

Chapter Title Date

POWER PLANT

71 Power Plant

72 Engine Drive Section 74 Ignition Nov 18/11 75 Engine Cooling System

76 Engine Controls Nov 18/11 77 Engine Indicating Nov 18/11 78 Exhaust Nov 18/11 79 Oil Nov 18/11 80 Starting Nov 18/11

91 Charts and Wiring Diagrams Nov 18/11

May 04/12 May 04/12

May 04/12

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Titel Page Record of Revisions 00-00-00 01 Nov 18/11 00-00-00 02 Nov 18/11 00-00-00 03 Nov 18/11 00-00-00 04 Nov 18/11 00-00-00 05 Nov 18/11 00-00-00 06 Nov 18/11 00-00-00 07 Nov 18/11 00-00-00 08 May 04/12 00-00-00 09 May 04/12 00-00-00 10 May 04/12 00-00-00 11 May 04/12 00-00-00 12 May 04/12 00-00-00 13 May 04/12 00-00-00 14 May 04/12 00-00-00 15 Nov 18/11 00-00-00 16 May 04/12 00-00-00 17 May 04/12 02-Title 02-TOC 01 Nov 18/11 02-00-00 01 Nov 18/11 S6 02-00-00 02 Nov 18/11 S6 02-00-00 03 Nov 18/11 S6 02-00-00 01 Nov 18/11 S6-RT 02-00-00 02 Nov 18/11 S6-RT 02-00-00 03 Nov 18/11 S6-RT 04-Title 04-ROR 01 Feb 28/12 04-TOC 01 Nov 18/11 04-00-00 01 Nov 18/11 04-00-01 01 Feb 28/12 S6 04-00-01 02 Nov 18/11 S6 04-00-01 03 Nov 18/11 S6 04-00-01 01 Feb 28/12 S6-RT 04-00-01 02 Nov 18/11 S6-RT 04-00-01 03 Nov 18/11 S6-RT 05-Title 05-TOC 01 Nov 18/11 05-00-00 01 Nov 18/11 05-10-00 01 May 04/12 05-10-00 02 May 04/12 05-20-00 01 Nov 18/11

05-20-00 02 Nov 18/11 05-20-00 03 Nov 18/11 05-20-00 04 Nov 18/11 05-20-00 05 Nov 18/11 05-20-00 06 Nov 18/11 05-20-00 07 Nov 18/11 05-20-00 08 May 04/12 05-20-00 09 Nov 18/11 05-20-00 10 Nov 18/11 05-20-00 11 Nov 18/11 05-20-00 12 Nov 18/11 05-20-00 13 Nov 18/11 05-20-01 01 Nov 18/11 Cabin Heating 05-20-02 01 Nov 18/11 Aerotow 05-20-03 01 Nov 18/11 S6-RT 05-20-03 02 Nov 18/11 S6-RT 05-20-03 03 May 04/12 S6-RT 05-30-00 01 Nov 18/11 05-50-00 201 Nov 18/11 05-50-00 202 Nov 18/11 05-50-00 201 Nov 18/11 S6-RT 05-50-00 202 Nov 18/11 S6-RT 06-Title 06-TOC 01 Nov 18/11 06-00-00 01 Nov 18/11 06-10-00 01 Nov 18/11 S6, 001 - 012 06-10-00 02 Nov 18/11 S6, 001 - 012 06-10-00 03 Nov 18/11 S6, 001 - 012 06-10-00 01 Nov 18/11 S6, 013 - 999 06-10-00 02 Nov 18/11 S6, 013 - 999 06-10-00 03 Nov 18/11 S6, 013 - 015 06-10-00 03 Nov 18/11 S6, 016 - 999 06-10-00 01 Nov 18/11 S6-RT 06-10-00 02 Nov 18/11 S6-RT 06-10-00 03 Nov 18/11 S6-RT 06-20-00 01 Nov 18/11 06-20-00 02 Nov 18/11 06-30-00 01 Nov 18/11 06-30-00 02 Nov 18/11 06-30-00 03 Nov 18/11 06-30-00 01 Nov 18/11 Cabin Heating 06-30-00 02 Nov 18/11 Cabin Heating 06-30-00 03 Nov 18/11 Cabin Heating

6. List of Effective Pages

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06-30-00 01 Nov 18/11 S6-RT 06-30-00 02 Nov 18/11 S6-RT 06-30-00 03 Nov 18/11 S6-RT 07-Title 07-TOC 01 Nov 18/11 07-00-00 01 Nov 18/11 07-10-00 201 Nov 18/11 07-10-00 202 Nov 18/11 08-Title 08-TOC 01 Nov 18/11 08-00-00 01 Nov 18/11 08-10-00 201 Nov 18/11 S6 08-10-00 202 Nov 18/11 S6 08-10-00 203 Nov 18/11 S6 08-10-00 204 Nov 18/11 S6 08-10-00 205 Nov 18/11 S6 08-10-00 206 Nov 18/11 S6 08-10-00 207 Nov 18/11 S6 08-10-00 201 Nov 18/11 S6-RT 08-10-00 202 Nov 18/11 S6-RT 08-10-00 203 Nov 18/11 S6-RT 08-10-00 204 Nov 18/11 S6-RT 08-10-00 205 Nov 18/11 S6-RT 08-10-00 206 Nov 18/11 S6-RT 08-10-00 207 Nov 18/11 S6-RT 09-Title 09-TOC 01 Nov 18/11 09-00-00 01 Nov 18/11 09-10-00 201 Nov 18/11 09-10-00 202 Nov 18/11 09-20-00 201 Nov 18/11 10-Title 10-TOC 01 Mar 16/12 10-00-00 01 Mar 16/12 10-10-00 201 Nov 18/11 10-10-01 201 Nov 18/11 10-10-01 202 Nov 18/11 10-10-01 203 Nov 18/11 10-10-01 204 Nov 18/11 10-10-01 205 Nov 18/11 10-10-01 206 Nov 18/11 10-10-02 201 Mar 16/12 Wing Folding 10-11-00 201 Nov 18/11

10-11-00 202 Nov 18/11 10-20-00 201 Nov 18/11 10-30-00 201 Nov 18/11 11-Title 11-TOC 01 Mar 16/12 11-00-00 01 Nov 18/11 11-20-00 201 Nov 18/11 11-20-00 202 Nov 18/11 11-20-00 203 May 04/12 11-20-00 204 Nov 18/11 11-20-01 201 May 04/12 Aerotow 11-20-02 201 Mar 16/12 Wing Folding 11-30-00 201 Nov 18/11 001 - 010 11-30-00 202 Nov 18/11 001 - 010 11-30-00 201 Nov 18/11 Prof. Avionics 11-30-00 202 Nov 18/11 Prof. Avionics 11-30-00 203 Nov 18/11 Prof. Avionics 11-30-00 204 Nov 18/11 Prof. Avionics 11-30-00 201 Nov 18/11 Class. Avionics 11-30-00 202 Nov 18/11 Class. Avionics 11-30-00 203 Nov 18/11 Class. Avionics 11-30-00 204 Nov 18/11 Class. Avionics 11-30-00 201 Nov 18/11 Adv. Avionics 11-30-00 202 Nov 18/11 Adv. Avionics 11-30-00 203 Nov 18/11 Adv. Avionics 11-30-00 204 Nov 18/11 Adv. Avionics 11-30-00 205 Nov 18/11 11-30-00 206 Nov 18/11 11-30-00 205 Nov 18/11 2-Panel Airbrakes 11-30-00 206 Nov 18/11 2-Panel Airbrakes 11-30-00 205 Nov 18/11 S6-RT 11-30-00 206 Nov 18/11 S6-RT 11-30-01 201 Nov 18/11 Aerotow 11-30-02 201 Nov 18/11 S6-RT 11-30-02 202 Nov 18/11 S6-RT 11-30-02 203 Nov 18/11 S6-RT 12-Title 12-TOC 01 Nov 18/11 12-TOC 02 Nov 18/11 12-00-00 01 Nov 18/11 12-10-00 01 Nov 18/11 12-10-00 02 May 04/12 12-10-00 03 May 04/12

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12-10-00 03 May 04/12 S6-RT 12-11-00 301 Nov 18/11 12-11-00 302 Nov 18/11 12-12-00 301 Nov 18/11 12-12-00 302 May 04/12 12-13-00 301 Nov 18/11 12-13-00 302 Nov 18/11 12-14-00 301 Nov 18/11 12-14-00 302 Nov 18/11 12-15-00 301 Nov 18/11 12-16-00 301 Nov 18/11 12-17-00 301 Nov 18/11 12-20-00 01 Nov 18/11 12-21-00 01 Nov 18/11 12-21-00 02 Nov 18/11 12-22-00 301 Nov 18/11 12-22-00 302 Nov 18/11 12-22-00 303 Nov 18/11 001 - 010 12-22-00 304 Nov 18/11 001 - 010 12-22-00 303 Nov 18/11 011 - 999 12-22-00 304 Nov 18/11 011 - 999 12-22-00 305 Nov 18/11 12-22-00 306 Nov 18/11 12-22-00 307 Nov 18/11 12-22-00 308 Nov 18/11 12-22-00 309 Nov 18/11 12-22-00 310 Nov 18/11 12-22-00 311 Nov 18/11 12-22-00 312 Nov 18/11 12-22-01 301 Nov 18/11 Aerotow 12-22-02 301 Nov 18/11 S6-RT 12-23-00 701 Nov 18/11 12-23-00 702 Nov 18/11 12-23-00 703 Nov 18/11 12-23-00 704 Nov 18/11 12-23-00 703 Nov 18/11 S6-RT 12-23-00 704 Nov 18/11 S6-RT 12-24-00 701 Nov 18/11 12-30-00 301 Nov 18/11 12-50-00 701 Nov 18/11 20-Title 20-TOC 01 Nov 18/11 20-00-00 01 Nov 18/11

20-10-00 01 Nov 18/11 20-10-00 02 Nov 18/11 20-10-00 03 Nov 18/11 20-11-00 01 Nov 18/11 20-11-00 02 Nov 18/11 20-11-00 03 Nov 18/11 20-11-00 04 Nov 18/11 20-11-00 05 Nov 18/11 20-11-00 06 Nov 18/11 20-11-00 07 Nov 18/11 20-11-00 08 Nov 18/11 20-11-00 09 Nov 18/11 20-11-00 10 Nov 18/11 20-11-00 11 Nov 18/11 20-11-00 12 Nov 18/11 20-11-00 13 Nov 18/11 21-Title 21-TOC 01 Nov 18/11 21-00-00 01 Nov 18/11 21-00-00 02 Nov 18/11 21-20-00 201 Nov 18/11 21-40-00 01 Nov 18/11 Cabin Heating 21-40-00 02 Nov 18/11 Cabin Heating 21-40-00 201 Nov 18/11 Cabin Heating 21-40-00 202 Nov 18/11 Cabin Heating 21-40-00 203 Nov 18/11 Cabin Heating 23-Title 23-TOC 01 Nov 18/11 23-TOC 02 Nov 18/11 23-00-00 01 Nov 18/11 23-10-00 01 Nov 18/11 Prof. Avionics 23-10-00 02 Nov 18/11 Prof. Avionics 23-10-00 101 Nov 18/11 Prof. Avionics 23-10-00 201 Nov 18/11 Prof. Avionics 23-10-00 01 Nov 18/11 Class. Avionics 23-10-00 02 Nov 18/11 Class. Avionics 23-10-00 201 Nov 18/11 Class. Avionics 23-10-00 01 Nov 18/11 Adv. Avionics 23-10-00 02 Nov 18/11 Adv. Avionics 23-10-00 201 Nov 18/11 Adv. Avionics 23-50-00 01 Nov 18/11 Prof. Avionics 23-50-00 101 Nov 18/11 Prof. Avionics 23-50-00 102 Nov 18/11 Prof. Avionics

6. List of Effective Pages (continued)6. List of Effective Pages (continued)

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23-50-00 201 Nov 18/11 Prof. Avionics 23-50-00 202 Nov 18/11 Prof. Avionics 23-50-00 203 Nov 18/11 Prof. Avionics 23-50-00 201 Nov 18/11 Class. Avionics 23-50-00 202 Nov 18/11 Class. Avionics 23-50-00 201 Nov 18/11 Adv. Avionics 23-50-00 202 Nov 18/11 Adv. Avionics 24-Title 24-TOC 01 Nov 18/11 24-TOC 02 Nov 18/11 24-00-00 01 Nov 18/11 24-00-00 02 Nov 18/11 24-00-00 101 Nov 18/11 24-31-00 01 Nov 18/11 24-31-00 201 Nov 18/11 24-32-00 01 Nov 18/11 24-33-00 01 Nov 18/11 24-33-00 02 Nov 18/11 24-40-00 01 Nov 18/11 Solar Panel 24-40-00 201 Nov 18/11 Solar Panel 24-60-00 01 Nov 18/11 24-60-00 02 Nov 18/11 24-60-00 101 Nov 18/11 24-61-00 201 Nov 18/11 24-61-00 202 Nov 18/11 24-61-00 201 Nov 18/11 S6-RT 24-61-00 202 Nov 18/11 S6-RT 24-62-00 201 Nov 18/11 24-62-00 202 Nov 18/11 24-63-00 201 Nov 18/11 24-63-00 202 Nov 18/11 24-63-00 201 Nov 18/11 S6-RT 24-63-00 202 Nov 18/11 S6-RT 24-64-00 201 Nov 18/11 24-64-00 202 Nov 18/11 24-65-00 201 Nov 18/11 24-65-00 202 Nov 18/11 25-Title 25-TOC 01 Nov 18/11 25-00-00 01 Nov 18/11 25-10-00 201 Nov 18/11 001 - 010 25-10-00 202 Nov 18/11 001 - 010 25-10-00 203 Nov 18/11 001 - 010

25-10-00 201 Nov 18/11 011 - 999 25-10-00 202 Nov 18/11 011 - 999 25-10-00 203 Nov 18/11 011 - 999 25-11-00 201 Nov 18/11 25-21-00 201 Nov 18/11 001 - 010 25-21-00 202 Nov 18/11 001 - 010 25-21-00 201 Nov 18/11 011 - 999 25-21-00 202 Nov 18/11 011 - 999 25-21-00 201 Nov 18/11 Aerotow 25-21-00 202 Nov 18/11 Aerotow 25-50-00 201 Nov 18/11 26-Title 013 - 999 26-TOC 01 Nov 18/11 013 - 999 26-00-00 01 Nov 18/11 013 - 999 26-10-00 201 Nov 18/11 013 - 999 27-Title 27-TOC 01 Nov 18/11 27-00-00 01 Nov 18/11 27-10-00 01 Nov 18/11 27-10-00 02 Nov 18/11 27-20-00 01 Nov 18/11 27-20-00 02 Nov 18/11 27-30-00 01 Nov 18/11 27-30-00 02 Nov 18/11 27-31-00 01 Nov 18/11 27-31-00 101 Nov 18/11 27-31-00 201 Nov 18/11 27-31-00 202 Nov 18/11 27-50-00 01 Nov 18/11 27-50-00 02 Nov 18/11 27-60-00 01 Nov 18/11 27-60-00 02 Nov 18/11 28-Title 28-TOC 01 Nov 18/11 28-00-00 01 Nov 18/11 28-00-00 02 Nov 18/11 28-00-00 03 Nov 18/11 28-20-00 01 May 04/12 28-20-00 02 Nov 18/11 28-20-00 101 Nov 18/11 28-20-00 201 Nov 18/11 28-20-00 202 Nov 18/11 28-20-00 203 Nov 18/11

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28-20-00 204 Nov 18/11 28-40-00 01 Nov 18/11 28-40-00 101 Nov 18/11 28-40-00 201 Nov 18/11 28-40-00 202 Nov 18/11 28-40-00 203 Nov 18/11 28-40-00 204 Nov 18/11 31-Title 31-TOC 01 Nov 18/11 31-00-00 01 May 04/12 31-00-00 02 Nov 18/11 31-00-00 03 Nov 18/11 Prof. Avionics 31-00-00 03 Nov 18/11 Class. Avionics 31-00-00 03 Nov 18/11 Adv. Avionics 31-00-00 03 Nov 18/11 S6-RT 31-10-00 201 Nov 18/11 31-10-00 202 Nov 18/11 32-Title S6 32-TOC 01 Nov 18/11 S6 32-00-00 01 Nov 18/11 S6 32-00-00 201 Nov 18/11 S6 32-10-00 01 Nov 18/11 S6 32-10-00 02 Nov 18/11 S6 32-10-00 201 Nov 18/11 S6 32-10-00 202 Nov 18/11 S6 32-10-00 203 Nov 18/11 S6 32-10-00 204 Nov 18/11 S6 32-20-00 01 Nov 18/11 S6 32-20-00 201 Nov 18/11 S6 32-20-00 202 Nov 18/11 S6 32-20-00 203 Nov 18/11 S6 32-20-00 204 Nov 18/11 S6 32-20-00 205 Nov 18/11 S6 32-40-00 01 Nov 18/11 S6 32-40-00 02 Nov 18/11 S6 32-40-00 201 Nov 18/11 S6 32-40-00 202 Nov 18/11 S6 32-40-00 203 Nov 18/11 S6 32-40-00 204 Nov 18/11 S6 32-40-00 205 Nov 18/11 S6 32-40-00 206 Nov 18/11 S6 32-40-00 207 Nov 18/11 S6 32-40-00 208 Nov 18/11 S6

32-40-00 209 Nov 18/11 S6 32-40-00 210 Nov 18/11 S6 32-40-00 211 Nov 18/11 S6 32-40-00 212 Nov 18/11 S6 32-Title S6-RT 32-TOC 01 Nov 18/11 S6-RT 32-00-00 01 Nov 18/11 S6-RT 32-00-00 201 Nov 18/11 S6-RT 32-10-00 01 Nov 18/11 S6-RT 32-10-00 02 May 04/12 S6-RT 32-10-00 201 Nov 18/11 S6-RT 32-10-00 202 May 04/12 S6-RT 32-10-00 203 Nov 18/11 S6-RT 32-10-00 204 Nov 18/11 S6-RT 32-20-00 01 Nov 18/11 S6-RT 32-20-00 201 Nov 18/11 S6-RT 32-20-00 202 Nov 18/11 S6-RT 32-20-00 203 Nov 18/11 S6-RT 32-20-00 204 Nov 18/11 S6-RT 32-20-00 205 Nov 18/11 S6-RT 32-30-00 01 Nov 18/11 S6-RT 32-30-00 02 Nov 18/11 S6-RT 32-30-00 201 Nov 18/11 S6-RT 32-30-00 202 May 04/12 S6-RT 32-30-00 203 Nov 18/11 S6-RT 32-30-00 204 May 04/12 S6-RT 32-30-00 205 Nov 18/11 S6-RT 32-30-00 206 May 04/12 S6-RT 32-30-00 207 Nov 18/11 S6-RT 32-31-00 01 Nov 18/11 S6-RT 32-31-00 201 Nov 18/11 S6-RT 32-31-00 202 Nov 18/11 S6-RT 32-31-00 203 Nov 18/11 S6-RT 32-40-00 01 Nov 18/11 S6-RT 32-40-00 02 Nov 18/11 S6-RT 32-40-00 201 Nov 18/11 S6-RT 32-40-00 202 Nov 18/11 S6-RT 32-40-00 203 Nov 18/11 S6-RT 32-40-00 204 Nov 18/11 S6-RT 32-40-00 205 Nov 18/11 S6-RT 32-40-00 206 Nov 18/11 S6-RT 32-40-00 207 Nov 18/11 S6-RT 32-40-00 208 Nov 18/11 S6-RT

6. List of Effective Pages (continued)6. List of Effective Pages (continued)

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32-40-00 209 Nov 18/11 S6-RT 32-40-00 210 Nov 18/11 S6-RT 32-40-00 211 Nov 18/11 S6-RT 32-40-00 212 Nov 18/11 S6-RT 33-Title 33-TOC 01 Nov 18/11 33-00-00 01 Nov 18/11 33-10-00 201 Nov 18/11 Interior Lights 33-40-00 201 Nov 18/11 Exterior Lights 33-40-00 202 Nov 18/11 Exterior Lights 33-40-00 203 Nov 18/11 Exterior Lights 34-Title 34-TOC 01 Nov 18/11 34-TOC 02 Nov 18/11 34-00-00 01 Nov 18/11 34-10-00 01 Nov 18/11 Prof. Avionics 34-10-00 02 Nov 18/11 Prof. Avionics 34-10-00 201 Nov 18/11 34-10-00 202 Nov 18/11 34-11-00 01 Nov 18/11 34-11-00 201 Nov 18/11 34-20-00 101 Nov 18/11 Prof. Avionics 34-20-00 201 Nov 18/11 Prof. Avionics 34-20-00 202 Nov 18/11 Prof. Avionics 34-20-00 201 Nov 18/11 Class. Avionics 34-20-00 202 Nov 18/11 Class. Avionics 34-20-00 203 Nov 18/11 Class. Avionics 34-20-00 101 Nov 18/11 Adv. Avionics 34-20-00 201 Nov 18/11 Adv. Avionics 34-20-00 202 Nov 18/11 Adv. Avionics 34-40-00 101 Nov 18/11 Prof. Avionics 34-40-00 201 Nov 18/11 Prof. Avionics 34-40-00 202 Nov 18/11 Prof. Avionics 34-40-00 101 Nov 18/11 Adv. Avionics 34-40-00 201 Nov 18/11 Adv. Avionics 34-40-00 202 Nov 18/11 Adv. Avionics 34-50-00 201 Nov 18/11 Prof. Avionics 34-50-00 202 Nov 18/11 Prof. Avionics 34-50-00 201 Nov 18/11 Class. Avionics 34-50-00 202 Nov 18/11 Class. Avionics 34-50-00 203 Nov 18/11 Class. Avionics 34-50-00 201 Nov 18/11 Adv. Avionics 34-50-00 202 Nov 18/11 Adv. Avionics

51-Title 51-TOC 01 Nov 18/11 51-00-00 01 Nov 18/11 51-00-00 02 Nov 18/11 51-10-00 201 Nov 18/11 51-20-00 201 Nov 18/11 52-Title 52-TOC 01 Nov 18/11 52-00-00 01 Nov 18/11 52-00-00 01 Nov 18/11 S6-RT 52-10-00 201 Nov 18/11 52-10-00 202 Nov 18/11 53-Title 53-TOC 01 Nov 18/11 53-00-00 01 Nov 18/11 53-01-00 01 Nov 18/11 Aerotow 53-01-00 201 Nov 18/11 Aerotow 53-01-00 202 Nov 18/11 Aerotow 53-01-00 203 Nov 18/11 Aerotow 53-01-00 204 Nov 18/11 Aerotow 53-01-00 205 Nov 18/11 Aerotow 53-10-00 01 Nov 18/11 001 - 010 53-10-00 02 Nov 18/11 001 - 010 53-10-00 01 Nov 18/11 011 - 999 53-10-00 02 Nov 18/11 011 - 999 53-10-00 03 Nov 18/11 53-10-00 04 Nov 18/11 53-10-00 05 Nov 18/11 53-10-00 201 Nov 18/11 55-Title 55-TOC 01 Nov 18/11 55-00-00 01 Nov 18/11 55-10-00 201 Nov 18/11 55-20-00 201 Nov 18/11 55-20-00 202 Nov 18/11 55-30-00 201 Nov 18/11 55-40-00 201 Nov 18/11 55-40-00 202 Nov 18/11 57-Title 57-TOC 01 Nov 18/11 57-00-00 01 Nov 18/11 57-10-00 201 Nov 18/11 57-10-00 202 Nov 18/11

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57-20-00 201 Nov 18/11 57-20-00 202 Nov 18/11 57-30-00 201 Nov 18/11 57-30-00 202 Nov 18/11 57-50-00 201 May 04/12 57-50-00 202 Nov 18/11 57-50-00 203 May 04/12 57-50-00 204 Nov 18/11 57-50-00 205 Nov 18/11 57-50-00 206 Nov 18/11 57-70-00 201 Nov 18/11 57-70-00 202 Nov 18/11 57-70-00 201 Nov 18/11 2-Panel Airbrakes 57-70-00 202 Nov 18/11 2-Panel Airbrakes 61-Title 61-TOC 01 Nov 18/11 61-00-00 01 Nov 18/11 61-00-00 101 Nov 18/11 61-10-00 201 Nov 18/11 61-10-00 202 Nov 18/11 61-10-00 203 Nov 18/11 61-10-00 204 Nov 18/11 61-10-00 205 Nov 18/11 61-10-00 206 Nov 18/11 61-11-00 201 Nov 18/11 61-11-00 202 Nov 18/11 61-11-00 203 Nov 18/11 61-11-00 204 Nov 18/11 61-20-00 201 Nov 18/11 71-Title 71-TOC 01 Nov 18/11 71-00-00 01 Nov 18/11 71-00-01 01 Nov 18/11 71-00-01 02 Nov 18/11 71-00-01 101 Nov 18/11 71-00-01 102 Nov 18/11 71-00-01 103 Nov 18/11 71-00-01 104 Nov 18/11 71-00-01 201 Nov 18/11 71-00-01 202 Nov 18/11 71-00-01 203 Nov 18/11 71-00-01 204 Nov 18/11 71-10-00 201 Nov 18/11

71-10-00 202 Nov 18/11 71-10-00 201 Nov 18/11 Solar Panel 71-10-00 202 Nov 18/11 Solar Panel 71-10-00 201 Nov 18/11 S6-RT 71-10-00 202 Nov 18/11 S6-RT 71-20-00 201 Nov 18/11 71-20-00 202 Nov 18/11 71-30-00 201 Nov 18/11 71-30-00 202 Nov 18/11 71-30-00 201 May 04/12 Firewall Cover 71-30-00 202 May 04/12 Firewall Cover 71-60-00 201 Nov 18/11 71-60-00 202 Nov 18/11 72-Title 72-TOC 01 Nov 18/11 72-00-00 01 Nov 18/11 72-10-00 201 Nov 18/11 001 - 030 72-10-00 202 Nov 18/11 001 - 030 72-10-00 203 Nov 18/11 001 - 030 72-10-00 204 Nov 18/11 001 - 030 72-10-00 201 May 04/12 031 - 999 72-10-00 202 May 04/12 031 - 999 72-10-00 203 May 04/12 031 - 999 72-10-00 204 May 04/12 031 - 999 74-Title 74-TOC 01 Nov 18/11 74-00-00 01 Nov 18/11 74-00-00 02 Nov 18/11 74-10-00 201 Nov 18/11 74-10-00 202 Nov 18/11 74-10-00 203 Nov 18/11 74-10-00 204 Nov 18/11 74-11-00 101 Nov 18/11 74-11-00 201 Nov 18/11 75-Title 75-TOC 01 Nov 18/11 75-00-00 01 Nov 18/11 001 - 023 75-00-00 02 Nov 18/11 001 - 023 75-10-00 201 Nov 18/11 001 - 023 75-10-00 202 Nov 18/11 001 - 023 75-10-00 203 Nov 18/11 001 - 023 75-10-00 204 Nov 18/11 001 - 023 75-10-00 205 Nov 18/11 001 - 023

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75-00-00 01 May 04/12 024 - 999 75-00-00 02 May 04/12 024 - 999 75-10-00 201 May 04/12 024 - 999 75-10-00 202 May 04/12 024 - 999 75-10-00 203 May 04/12 024 - 999 75-10-00 204 May 04/12 024 - 999 75-10-00 205 May 04/12 024 - 999 76-Title 76-TOC 01 Nov 18/11 76-00-00 01 Nov 18/11 76-10-00 201 Nov 18/11 001 - 010 76-10-00 202 Nov 18/11 001 - 010 76-10-00 203 Nov 18/11 001 - 010 76-10-00 204 Nov 18/11 001 - 010 76-10-00 201 Nov 18/11 011 - 999 76-10-00 202 Nov 18/11 011 - 999 76-10-00 203 Nov 18/11 011 - 999 76-10-00 204 Nov 18/11 011 - 999 77-Title 77-TOC 01 Nov 18/11 77-00-00 01 Nov 18/11 77-10-00 201 Nov 18/11 77-10-00 202 Nov 18/11 77-20-00 01 Nov 18/11 77-20-00 101 Nov 18/11 77-20-00 201 Nov 18/11 78-Title 78-TOC 01 Nov 18/11 78-00-00 01 Nov 18/11 78-10-00 201 Nov 18/11 78-10-00 202 Nov 18/11 78-10-00 203 Nov 18/11 79-Title 79-TOC 01 Nov 18/11 79-00-00 01 Nov 18/11 79-00-00 02 Nov 18/11 79-10-00 201 Nov 18/11 79-10-00 202 Nov 18/11 79-20-00 201 Nov 18/11 79-20-00 202 Nov 18/11 79-30-00 201 Nov 18/11 80-Title 80-TOC 01 Nov 18/11

80-00-00 01 Nov 18/11 80-10-00 201 Nov 18/11 80-10-00 202 Nov 18/11 91-Title 91-TOC 01 Nov 18/11 91-00-00 01 Nov 18/11 91-00-01 01 Nov 18/11 91-00-01 02 Nov 18/11 91-00-01 03 Nov 18/11 001 - 012 91-00-01 04 Nov 18/11 001 - 012 91-00-01 05 Nov 18/11 001 - 012 91-00-01 06 Nov 18/11 001 - 012 91-00-01 03 Nov 18/11 013 - 999 91-00-01 04 Nov 18/11 013 - 999 91-00-01 05 Nov 18/11 013 - 999 91-00-01 06 Nov 18/11 013 - 999 91-00-01 07 Nov 18/11 91-00-01 08 Nov 18/11 91-00-01 09 Nov 18/11 91-00-02 01 Nov 18/11 Cabin Heating 91-00-03 01 Nov 18/11 Aerotow 91-00-04 01 Nov 18/11 Solar Panel 91-00-05 01 Nov 18/11 S6-RT

6. List of Effective Pages (continued)

00-00-00

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CHAPTER 02

GENERAL

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02 - TOC

Page 01

TABLE OF CONTENTS

Chapter Section

Title Subject Page

GENERAL...........................................................................................................02-00-00 1

Introduction 02-00-00 1 General Description 02-00-00 1

Technical Data 02-00-00 1

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GENERAL

1. Introduction

A. This chapter provides a brief general description of the aircraft including a set of technical data.

2. General Description

A. The STEMME S6 is a twin-seat high performance powered sailplane with an innovative

propulsion concept and a sophisticated aerodynamic design. The wing is a carbon fiber reinforced composite design. The fuselage is manufactured as a hybrid construction (carbon, kevlar, glass) with an extremely rigid central steel tube framework. The seats are arranged side by side and equipped with dual controls.

The wing is attached to the fuselage in the upper third section of the fuselage behind the cockpit. The wing consists of an one-piece central wing with flaps and two outboard wings with SchemppHirth air brakes and inboard and outboard ailerons. The tail unit is designed as a T-tail.

The S6 has a fixed tricycle type landing gear with a steerable nose gear. The main gear is equipped with single disc hydraulic brake assemblies. Strut and wheel fairings are provided to improve the aerodynamic properties.

The engine is located in the middle portion of fuselage, behind the cabin and mounted to a highstrength steel tube cage. The engine power is transmitted via an internal gear, a composite driveshaft and a front reduction gear to a three-blade, constant-speed propeller. The propeller pitch is controlled electrically.

3. Technical Data

NOTE: For dimensions and areas, also refer to 06-10-00.

A. Overall Dimensions

Wing Span 18,00 m 59.1 ft. Wing Span Folded 7,20 m 23.6 ft.

Wing Area 17,42 m 187.5 ft. Aspect Ratio 18,62 Length 8,52 m 28 ft. Height 2,45 m 8 ft.

B. Weights

Maximum Takeoff Weight (MTOW) 850 kg 1874 lbs Empty Weight 655 kg 1444 lbs Total Payload 195 kg 430 lbs

2 2

Max. Wing Loading 48,79 kg/m 10 lbs/ft

2 2

Min. Wing Loading (empty weight +70kg) 37,5 kg/m 7.7 lbs/ft

02-00-00

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Figure 01

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Model S6

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C. Power Plant

Engine ROTAX 914F Max. Takeoff Power (MTOP) at 5800 RPM 84,5 kW 113.2 hp Max. Continuous Power (MCP) at 5500 RPM 73,4 kW 98.4 hp Fuel Capacity, standard (R/H fuel tank) 1x 65 l 1x 17.2 US gal. Fuel Capacity, optional (R/H + L/H fuel tank) 2x 65 l 2x 17.2 US gal. Unusable Fuel, R/H 2.1 l 0.55 US gal. Unusable Fuel, L/H 1 l 0.3 US gal.

D. Landing Gear

Type Tricycle, fixed Wheel Track 1889 mm 6.2 ft. Wheel Base 1970 mm 6.5 ft.

E. Performances

For performance data refer to the applicable Flight Manual (refer to 00-00-00, List of Vendor Technical Publications).

02-00-00

Page 03

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EFFECTIVITY

Model S6

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GENERAL

1. Introduction

A. This chapter provides a brief general description of the aircraft including a set of technical data.

2. General Description

A. The STEMME S6 is a twin-seat high performance powered sailplane with an innovative

The S6 has a retractable tricycle type landing gear with a steerable nose gear. All three landing gear legs are equipped with separate gear doors to cover each of the landing gear legs and the wheel wells completely and aerodynamically. The wheels of the main landing gear are each equipped with a single disc hydraulic brake assemby.

3. Technical Data

NOTE: For dimensions and areas, also refer to 06-10-00.

A. Overall Dimensions

Wing Span 18,00 m 59.1 ft. Wing Span Folded 7,20 m 23.6 ft.

Wing Area 17,42 m 187.5 ft. Aspect Ratio 18,62 Length 8,52 m 28 ft. Height 2,45 m 8 ft.

B. Weights

Maximum Takeoff Weight (MTOW) 900 kg 1984 lbs Empty Weight 680 kg 1499 lbs Total Payload 220 kg 485 lbs

2 2

Max. Wing Loading 51,66 kg/m 10.6 lbs/ft

2 2

Min. Wing Loading (empty weight +70kg) 43,05 kg/m 8.8 lbs/ft

02-00-00

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Model S6-RT

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Figure 01

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C. Power Plant

D. Landing Gear

Type Tricycle, retractable Wheel Track 1889 mm 6.2 ft. Wheel Base 1970 mm 6.5 ft.

E. Performances

For performance data refer to the applicable Flight Manual (refer to 00-00-00, List of Vendor Technical Publications).

02-00-00

Page 03

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Model S6-RT

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CHAPTER 04

AIRWORTHINESS LIMITATIONS

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04 - RECORD OF REVISIONS

Page 01

RECORD OF REVISIONS - CHAPTER 04

Revision

Number

Date of

Revision

Revised

Pages

Descriptions of Revisions

Agency Approval

of Chapter 4

Signature and Date

First Issue

Introduction Retractable Landing Gear, 900kg MTOW (Model S6-RT)

100h TBO Front Gear Box

20.12.2010

18.11.2011

28.02.2012

all

04-00-01,

p. 02

04-00-01,

p. 01

The technical content of this revision is approved under the authority of EASA.21J.250

Feb 28/12

The technical content of this revision is approved under the authority of EASA.21J.250

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04 - TOC

Page 01

TABLE OF CONTENTS

Chapter Section

Title Subject Page

AIRWORTHINESS LIMITATIONS - GENERAL ..........................................04-00-00 1

Introduction 04-00-00 1 General Description 04-00-00 1

COMPONENT LIFE LIMITS...........................................................................04-00-01 1

General 04-00-01 1 Component Life Limits 04-00-01 1

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04-00-00

Page 01

AIRWORTHINESS LIMITATIONS - GENERAL

1. Introduction

A. This chapter sets out the mandatory replacement time, and so far as is necessary, inspection

periods for structure as well as structural inspection procedures for the S6. It contains information about the service life of such parts or components that must be overhauled or replaced at specific flight time limits. Compliance with the specified times and intervals is mandatory for maintaining the airworthiness of the aircraft.

B. The primary purpose of this chapter is to set in front of the manual a reference of mandatory

measures to maintain the airworthiness of the aircraft.

ALL NON-DOCUMENTARY CHANGES OF THE CHAPTER 04, "AIRWORTHINESS LIMITATIONS" ARE AGENCY APPROVED.

C. For time limits of products with separate TC from further manufacturers installed in the aircraft

(e.g. Engine, Propeller etc.), maintenance checks and inspections, refer to chapter 05: “Time Limits / Maintenance Checks“ of this manual.

2. General Description

In the following, a brief description and intended purpose of each section of this chapter is given.

A. Section 04-00-00 - Airworthiness Limitations - Introduction. This section provides a general

overview of content and purpose of the chapter.

B. Section 04-00-01 Component Time Limits. This section contains prescribed service life of

components and parts up to the replacement or overhaul.

Nov 18/11

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CHAPTER 04

AIRWORTHINESS LIMITATIONS

- FAA -

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04 - RECORD OF REVISIONS- FAA -

Page 01

RECORD OF REVISIONS - CHAPTER 04

Revision

Number

Date of

Revision

Revised

Pages

Descriptions of Revisions

FAA Approval

of Chapter 4

Signature and Date

Nov 18/11

First Issue

Introduction Retractable Landing Gear, 900kg MTOW (Model S6-RT)

100h TBO Front Gear Box

20.12.2010

18.11.2011

28.02.2012

all

04-00-01,

p. 02

04-00-01,

p. 01

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TABLE OF CONTENTS

Chapter Section

Title Subject Page

AIRWORTHINESS LIMITATIONS - GENERAL ..........................................04-00-00 1

Introduction 04-00-00 1 General Description 04-00-00 1

COMPONENT LIFE LIMITS...........................................................................04-00-01 1

General 04-00-01 1 Component Life Limits 04-00-01 1

04 - TOC

Page 01

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- FAA -

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04-00-00

Page 01

AIRWORTHINESS LIMITATIONS - GENERAL

1. Introduction

A. For U.S. registered aircraft the airworthiness limitations section is FAA approved and specifies

maintenance required under §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.

B. This chapter sets out the mandatory replacement time, and so far as is necessary, inspection

C. The primary purpose of this chapter is to set in front of the manual a reference of mandatory

measures to maintain the airworthiness of the aircraft.

ALL NON-DOCUMENTARY CHANGES OF THE CHAPTER 04, "AIRWORTHINESS LIMITATIONS" ARE FAA APPROVED.

D. For time limits of products with separate TC from further manufacturers installed in the aircraft

(e.g. Engine, Propeller etc.), maintenance checks and inspections, refer to chapter 05: “Time

Limits / Maintenance Checks“ of this manual.

2. General Description

In the following, a brief description and intended purpose of each section of this chapter is given.

A. Section 04-00-00 - Airworthiness Limitations - Introduction. This section provides a general

overview of content and purpose of the chapter.

B. Section 04-00-01 Component Time Limits. This section contains prescribed service life of

components and parts up to the replacement or overhaul.

Nov 18/11

- FAA -

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04-00-01

Page 01

COMPONENT LIFE LIMITS

1. General

A. Different components and parts of the aircraft are certified for specific service life. On reaching

this life limits, these components must be replaced with new components or with ones which have life remaining.

For monitoring the permissible service life the installation or removal of each item must be

recorded in the aircraft logbook.

2. Component Life Limits

A. Under specific circumstances the replacement of parts or components may be required before

attaining the life limits as listed below.

B. For parts whose service life is limited by permanent load action, precise replacement times are

defined. By the process of fatigue tests and their results, the component life limits may be changed. These changes will be announced by STEMME in such cases.

C. Replace the components shown in the following table, on or before reaching the applicable life

limits:

Cha. Component Manufacturer/ P/N Permissible operating Note

Type (STEMME) time by

Overhaul Replacement

N/A Airframe STEMME sundry 6000h 6000h (1)

72 Tooth belt front STEMME 050.251 100h - (2)(3)

gear box

72 Tooth belt STEMME 830.185 - 5 years

72 Ultra-bushing STEMME 830.116 - 12 years

front gear suspension

71/72 Drive Shaft STEMME 290.228 400h - (2)(3)(4)

71 Cone bearing STEMME 830.021 - 5 years

of engine suspension

78 Rubber sus- STEMME 830.054 - 5 years

pension of the exhaust muffler

EFFECTIVITY

Model S6

Feb 28/12

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04-00-01

Page 02

C. Replacement and Overhaul Schedule (Continued)

Cha. Component Manufacturer/ P/N Permissible operating Note

Type (STEMME) time by

Overhaul Replacement

04-00-01

Page 02

NOTES:

(1) Extension of service life exceeding 6000 h can be achieved only for individual airplanes after a

comprehensive inspection of the airframe carried out by the manufacturer according to an approved program.

(2) The stated times are provisional within the TBO development program. Based on sufficient

operating experience they may be further raised or reduced if necessary (extension of TBO and/or service life is intended) and will be notified by a new revision of this chapter.

(3) The TBO expires in each case of:

(a) impact stop (possible ground touch of the propeller); (b) Non-observance of the periodical inspections as they are fixed in the Maintenance

Manual;

72 Flexible disk of STEMME 830.020 - 12 years

the drive shaft system

28 Fuel check valve STEMME 830.445 5 years 10 years (5)

28 Fuel hoses STEMME 820.051 and - 5 years

820.052

79 Oil hoses STEMME 820.006 and - 5 years

820.013

75 Coolant hoses STEMME 820.011 - 5 years

32 Brake hoses STEMME 820.007 - 10 years

32 Elastomer parts STEMME 290.317 - 5 years

in the Main (assembly) Landing Gear

32 Elastomer parts STEMME 830.155 and - 5 years

in the Nose 830.156 Landing Gear

32 Ultra-bushing in STEMME 830.118 - 12 years

the nose wheel steering

Nov 18/11

EFFECTIVITY

Model S6

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04-00-01

Page 03

Damaging by ground contact, bird strike, stone strike or similar which require a „large repair“, the manufacturer decides which parts of the complete drive system are affected and if a repair may be practicable or if an overhaul or replacement have to be performed.

(4) The drive shaft cannot be overhauled. Instead of an overhaul it will be checked by a load test

at STEMME.

(5) Overhaul of the fuel check valves mean, that the check valves will be checked visually after 5

years. During this check they shall be especially inspected for signs of brittleness or change in color. In such a case the parts shall be replaced.

Nov 18/11

EFFECTIVITY

Model S6

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04-00-01

Page 01

COMPONENT LIFE LIMITS

1. General

A. Different components and parts of the aircraft are certified for specific service life. On reaching

this life limits, these components must be replaced with new components or with ones which have life remaining.

For monitoring the permissible service life the installation or removal of each item must be

recorded in the aircraft logbook.

2. Component Life Limits

A. Under specific circumstances the replacement of parts or components may be required before

attaining the life limits as listed below.

B. For parts whose service life is limited by permanent load action, precise replacement times are

defined. By the process of fatigue tests and their results, the component life limits may be changed. These changes will be announced by STEMME in such cases.

C. Replace the components shown in the following table, on or before reaching the applicable life

limits:

Cha. Component Manufacturer/ P/N Permissible operating Note

Type (STEMME) time by

Overhaul Replacement

N/A Airframe STEMME sundry 6000h 6000h (1)

72 Tooth belt front STEMME 050.251 100h - (2)(3)

gear box

72 Tooth belt STEMME 830.185 - 5 years

72 Ultra-bushing STEMME 830.116 - 12 years

front gear suspension

71/72 Drive Shaft STEMME 290.228 400h - (2)(3)(4)

71 Cone bearing STEMME 830.021 - 5 years

of engine suspension

78 Rubber sus- STEMME 830.054 - 5 years

pension of the exhaust muffler

EFFECTIVITY

Model S6-RT

Feb 28/12

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C. Replacement and Overhaul Schedule (Continued)

Cha. Component Manufacturer/ P/N Permissible operating Note

Type (STEMME) time by

Overhaul Replacement

NOTES:

(1) Extension of service life exceeding 6000 h can be achieved only for individual airplanes after a

comprehensive inspection of the airframe carried out by the manufacturer according to an approved program.

04-00-01

Page 02

Feb 26/10

04-00-01

Page 02

Nov 18/11

EFFECTIVITY

Model S6-RT

72 Flexible disk of STEMME 830.020 - 12 years

the drive shaft system

28 Fuel check valve STEMME 830.445 5 years 10 years (5)

28 Fuel hoses STEMME 820.051 and - 5 years

820.052

79 Oil hoses STEMME 820.006 and - 5 years

820.013

75 Coolant hoses STEMME 820.011 - 5 years

32 Brake hoses STEMME 820.007 - 10 years

32 Hydraulic Hoses STEMME 292.102, - 10 years

292.103,

292.104,

292.105,

292.116 and

292.117

32 Pressure STEMME 830.680 2 years 5 years

Accumulators

32 Elastomer parts STEMME 290.808 - 5 years

in the Main (assembly) Landing Gear

32 Elastomer parts STEMME 830.155 and - 5 years

in the Nose 830.156 Landing Gear

32 Ultra-bushing in STEMME 830.118 - 12 years

the nose wheel steering

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(2) The stated times are provisional within the TBO development program. Based on sufficient

operating experience they may be further raised or reduced if necessary (extension of TBO and/or service life is intended) and will be notified by a new revision of this chapter.

(3) The TBO expires in each case of:

(a) impact stop (possible ground touch of the propeller); (b) Non-observance of the periodical inspections as they are fixed in the Maintenance

Manual; (c) non-authorized replacement of essential parts. Damaging by ground contact, bird strike, stone strike or similar which require a „large repair“, the manufacturer decides which parts of the complete drive system are affected and if a repair may be practicable or if an overhaul or replacement have to be performed.

(4) The drive shaft cannot be overhauled. Instead of an overhaul it will be checked by a load test

at STEMME.

(5) Overhaul of the fuel check valves mean, that the check valves will be checked visually after 5

years. During this check they shall be especially inspected for signs of brittleness or change in color. In such a case the parts shall be replaced.

04-00-01

Page 03

Nov 18/11

EFFECTIVITY

Model S6-RT

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MAINTENANCE MANUAL

STEMME TSA-M

CHAPTER 05

TIME LIMITS / MAINTENANCE CHECKS

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05 - TOC

Page 01

TABLE OFCONTENTS

Chapter Section

Title Subject Page

TIME LIMITS / MAINTENANCE CHECKS - GENERAL ...........................05-00-00 1

Introduction 05-00-00 1 General Description 05-00-00 1

TIME LIMITS......................................................................................................05-10-00 1

General 05-10-00 1 Replacement and Overhaul Schedule 05-10-00 1

SCHEDULED MAINTENANCE CHECKS....................................................05-20-00 1

General 05-20-00 1 Inspection Intervals 05-20-00 1

Definition Periodic Inspections 05-20-00 1 Definition Special Hours Inspections 05-20-00 1

Inspection Time Intervals Chart S6 05-20-00 2

DAILY INSPECTIONS......................................................................................05-30-00 1

General 05-30-00 1 Preflight Inspection 05-30-00 1 After Flights 05-30-00 1

UNSCHEDULED MAINTENANCE CHECKS .............................................05-50-00 1

General 05-50-00 1 Special Checks 05-50-00 1

Nov 18/11

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05-00-00

Page 01

TIME LIMITS / MAINTENANCE CHECKS - GENERAL

1. Introduction

A. This chapter provides recommended scheduled and unscheduled maintenance checks and

inspections for the S6.

B. Chapter 04 "Airworthiness Limitations" of this manual contains the mandatory life limits (service

life) of components and parts.

2. General Description

The following sets out a brief description and intended purpose of each section of this chapter.

A. Section 05-00-00 Time limits / Maintenance checks - Introduction. This section provides a general

overview of content and purpose of the chapter.

B. Section 05-10-00 Time Limits. This section contains manufacturer recommended time limits for

replacement and overhaul of parts.

C. Section 05-20-00 Scheduled Maintenance Checks. This section contains information about

recommended scheduled maintenance and inspections. Recommended maintenance and Inspections of the systems and components of the S6 as well as the relevant intervals are contained in a chart.

D. Section 05-30-00 Daily Inspections. The preflight check and the checks after flights are described.

E. Section 05-50-00 Unscheduled Maintenance Checks. This section contains checks that are to be

conducted after unusual events such as a hard landing.

Nov 18/11

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05-10-00

Page 01

NOTES:

(1) The stated times are provisional within the TBO development program. Based on sufficient

operating experience they may be further raised or reduced if necessary (extension of TBO

TIME LIMITS

1. General

A. This section contains part manufacturer recommended time limits for replacement and overhaul

of parts.

2. Replacement and Overhaul Schedule

A. The following parts or components must be replaced or overhauled at the specified intervals.

Under specific circumstances the replacement/overhaul of parts or components may be required before attaining the time limits as listed below.

B. On expiry of a part's permissible operating times the affected part has to be sent to the

manufacturer or to a from the manufacturer approved repair/overhaul workshop for inspection. The organisation 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.

C. Replacement and Overhaul Schedule

Cha. Component Manufacturer/ P/N Permissible operating Note

Type (STEMME) time by

Overhaul Replacement

71 Rotax Engine ROTAX 914F 830.400 refer to - (2)(3)

note (3)

61 Constant Speed MT-Propeller 830.044 refer to - (1)(2)(4)

Propeller MTV 7A/170-51 note (4)

71 Rubber parts ROTAX refer to IPC - 5 years (6)

of engine ROTAX 914F

25 Seat belt various 835.000 - 12 years (5)

835.001

53 Tow Release Tost, E22 830.693 refer to - (7)

(Option) note (7)

May 04/12

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05-10-00

Page 02

and/or service life is intended) and will be notified by a new revision of this chapter.

(2) The TBO expires in each case of:

(a) impact stop (possible ground touch of the propeller); (b) Non-observance of the periodical inspections as they are fixed in the Maintenance

(3) Refer to latest issue of ROTAX Aicraft Engines TBO Service Bulletin (SB) “Extension of the

Time Between Overhaul (TBO)”, and to ROTAX Aircraft Engines Maintenance Manual for ROTAX Engine Type 914F Serie.

(4) Refer to latest issue of the mt-propeller Service Bulletin No. 1.-( ), and to the mt-propeller

E-118 Operation and Installation Manual.

(5) Replacement is required after a heavy overloading (e.g. due to an accident), refer also to the

operating instructions of the manufacturer.

(6) All rubber parts of the engine Rotax 914F must be renewed. Subjected are the carburetor

venting hoses (between airbox and carburetor float chambers, between fuel pressure control and pressure sensor), the air hoses between Turbo Charger and Airbox, the connecting hoses on the compensating tube, the V-belt, all rubber hoses of the cooling system, and the rubber diaphragms and the rubber flange on both carburetors.

(7) The installed aerotow release clutch type E22 by Tost company has to be overhauled by the

manufacturer every 10.000 actuations or every 2000 launches of aerotow (based on assumption of about 5 actuations per launch in normal aerotow flight operation). In case of more or less than 5 actuations per flight the permitted number of launches has to be reduced or increased correspondingly, which lies in the responsibility of the aircraft holder. The manufacturer recommends a general overhaul after 4 years. Refer to Operating Manual for Tost Release E22 and service information provided by manufacturer to get further information.

May 04/12

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05-20-00

Page 01

SCHEDULED MAINTENANCE CHECKS

1. General

A. The inspection time intervals chart contained in this chapter provides the recommended intervals

at which maintenance and maintenance checks are to be carried out on the aircraft.

B. Inspections, preventive maintenance work and repairs must be carried out by qualified personnel.

In any case, the specific national laws and regulations are obligatory.

NOTE: Read maintenance instructions in the appropriate sections of this manual before carrying

out any adjustments.

WARNING: PRIOR TO ANY MAINTENANCE WORK SWITCH OFF MASTER SWITCH AND

IGNITION!

2. Inspection Intervals

A. The intervals for general maintenance depend on operating conditions, climate, hangarage, etc.

The types and intervals of the minimum scheduled maintenance established for the S6 are indicated in the table below.

3. Definition Periodic Inspections

A. Periodic inspections are those which must be performed every 100, 200, 600 and 1000 engine

operating hours. They have to be carried out in accordance with the following S6 Inspection Time Interval Chart. This means for example that every 100 hr of operation (100, 200, 300 hr ...) a 100 hr check and all 200 hr (200, 400, 600 hr ...) additional checks as per maintenance interval chart must be carried out. The same must be applied for the additional 600 hr and 1000 hr inspections.

B. For 100 hr periodic inspections marked additionally as (X) for annual inspection an inspection is to

be carried out periodically after every 100 engine operating hours or every 12 months, whichever applies first.

C. The airframe periodic inspections must be performed every 100 flight hours of a/c (flight hours

documented in the a/c logbook).

D. Additional engine periodic inspections must be performed every 50 engine operating hours,

containing the following check points:

- 5.1.9 - 1; 5.1.11 - 6 (recommended for the engine by ROTAX)

- 5.1.10 - 5 and 6 (obligatory, if more than 30% of operation with leaded fuel, e.g. AVGAS 100 LL)

4. Definition Special Hours Inspections

A. In order to demonstrate continued airworthiness, the aircraft / engine must be inspected

additionally once after the first 25 engine operating hours or 100 flight hours, whichever applies first. This applies to newly delivered and to overhauled aircrafts / engines.

Nov 18/11

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05-20-00

Page 02

Nov 18/11

5. S6 Inspection Time Interval Chart

A. The maintenance and checks listed in the following chart are to be practiced in the specified

periods and are to be documented in a required manner.

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Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

05-20-00

Page 03

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

1. Check service life limits of all components and installed equipment.

3. Inspect a/c surfaces and markings (especially registration and national flag), renew if necessary.

4. Check all drain and ventilation holes.

5. Check all lubrication points and grease if required.

6. Check function of the entire flight control system. Play allowed (at control surface with control device fixed, measured in direction of movement): max. 2.5 mm / 0.1 in

7. Check slackness of aileron, flap and elevator controls. Play allowed (hinges): only axial: 0.4

8. Check friction and forces in the control system.

9. After any maintenance on the control systems, check deflection of control surfaces and document values in a report

Thoroughly clean a/c. Remove or open all necessary inspection plates, access doors, fairings and cowlings.

± 0.1 mm / 0.016 ± 0.004 in

10. After accomplishing maintenance on drive system, perform an engine run-up.

1. Check fuel system components at spare bridge of center wing.

2. Check drain valves for leaks.

5.1.2 Wings and Fuel System Components in the Central Wing

5.1.1 General

(X)

11-00-00

06-30-00

12-22-00

06-10-00

Nov 18/11

B. S6 Inspection Time Intervals Chart:

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Page 04

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

5.1.3 Front Fuselage

3. Check vent line outlets at end ribs of central wing.

4. Check function and leak tightness of quick-release couplings (supply lines) to and from fuselage.

5. Check all fuel filters and replace if required.

6. Check fuel filler cap for leakage and wing for any signs of wing fuel tank leakage.

7. Check condition and backlash of wing fittings, check safety device of wing attachment bolts. Maximum play allowed for all wing bolts: Axial: 0.4 mm / 0.016 in Radial: 0.15 mm / 0.006 in For front and aft shear force bolts (inner wing outer wing, outer wing - winglet) only radial play is allowed.

8. Check condition, security and function of fuel pumps (located under the spar).

9. Check condition of wing flaps and ailerons, check clearance between components spanwise 3 ± 0.5 mm / 0.12 ± 0.02 in., check gap sealings and fairings on flap/aileron links, check security of axial stops.

10. Check entire control linkage and bearings in the center wing and in the wing attachment area, verify the spring pin on each quick-connector is attached securely.

11. Inspect bell-crank levers and adjacent components of wing flap and aileron control system.

12. Check condition of airbrakes. Clearance between cover strap and wing shell (spanwise, overall): 4 ± 0.5 mm / 0.16 ± 0.02 in

1. Check condition and security of drive gear attachment.

2. Verify the gap between Center wing and fuselage is at least 2 ± 0.5 mm / 0.08 ± 0.02 in.

(X)

Nov 18/11

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Page 05

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

3. Check security and condition of drive gear cowlings. Clearance allowed (all around): 1 +1.0, -0.5 mm / 0.04 + 0.04, -0.02 in

1. Inspect canopy for damage and check proper function of locking mechanism, grease canopy locks. Clearance allowed (all around): 2 ± 1.0 mm / 0.08 ± 0.04 in

2. Canopy emergency jettison: Check function.

3. Check function of lateral canopy gas springs (canopy must remain in open position).

4. Check seat belts and their attachments.

5. Check controls in front fuselage for foreign objects, condition and proper installation.

6. Check condition and security of all instruments, switches, circuit breakers, fuses and wiring.

7. Check condition and integrity of ventilation hoses.

8. Check rudder pedals and control cables. Check provisions for pedal adjustment. Play allowed (at rudder, with pedals fixed, measured in direction of movement): max. 2.5 mm / 0.1 in

9. Check condition, security and adjustment mechanism of the seats.

1. Check condition of center fuselage steel frame (corrosion, deformation). Check paint for cracks.

2. Check condition of framework/tailboom connection.

3. Check condition of upper and lower connection framework / front fuselage.

5.1.5 Center Fuselage (except for fairings)

5.1.4 Cockpit

Nov 18/11

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Page 06

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

Nov 18/11

4. Check condition and security of landing gear attachment.

5. Check condition of entire control linkage in the center fuselage.

6. Main battery: Check electrical terminals, condition and security of mounting tray.

1. Visual inspect members of elevator control looking into the forward and aft end of tail boom.

2. Visual inspect members of rudder control looking into the forward and aft end of tail boom.

3. Check trim control system.

4. Check tail skid for security and wear.

5. Check attachment of ballast compartment for cracks.

6. Check baggage compartment door for correct closure.

7. Check attachment points in the baggage compartment for security.

1. Check rudder system and fittings for condition and security. Play allowed (hinges): only axial: 0.4 ± 0.1 mm / 0.016 ± 0.004 in

2. Check backlash in fittings of horizontal stabilizer when installed. Maximum play allowed for front and aft fitting: Axial: 0.15 mm / 0.006 in Radial: 0.15 mm / 0.006 in

3. Check gap sealings and zigzag tape on the empennage.

5.1.6 Tail Boom

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

5.1.7 Empennage

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05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

Nov 18/11

1. Check condition of supply, return and drain lines outside the engine compartment, supply and return lines inside the engine compartment.

2. Check condition, security and function of fuel pumps.

3. Replace main fuel pump. (acc. to ROTAX)

4. Check fuel shut-off valve. Inspect firewall feedthroughs of the fuel supply and return lines for security and leakage.

5. Check condition of fire protective sleeves on fuel supply and return lines in the engine compartment.

1. General visual inspection of engine and auxiliaries for damage, abnormalities and leakage.

2. Check friction torque in free rotation of engine gear box.

3. Inspect overload clutch.

4. Check of the engine gear box.

5. Check of fuel filters, renew if necessary.

6. Check idle speed.

7. Inspect float chamber assembly for contamination and corrosion at minimum one time a year.

8. Check of carburetors with inspection of ventilation of the float chambers and disassembling/assembling for checking.

9. Check carburetor synchronization.

5.1.9 Engine and Engine Mounts

(X)

(1)

XXR* 05-20-00

28-20-00

R* 05-20-00

5.1.8 Fuel System Components in the Fuselage

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

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Page 08

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

May 04/12

10. Inspect carburetor sockets for condition, damage.

11. Check condition of fuel lines, pressure connection lines and compensating tube assy at the carburetor’s airbox. Check for leakage and correct installation.

12. Check engine wiring and its connections for secure fit and damage.

13. Check the V-belt tension and attachment of auxiliary generator.

14. Check spark plugs and renew them if necessary.

15. Replace spark plugs.

16. Check spark plug connectors for tight fit. (Minimum pull-off force is 30 N / 7 lb)

17. Check compression pressure by differential pressure method.

18. Check mountings of turbocharger, muffler and other external parts for tight fit. Inspect safety wiring, renew if necessary.

19. Check condition of exhaust elbows and exhaust system for crack formation and uncharacteristic gunpowder burns (leaks).

20. Check mounting points of the engine at the engine frame (engine mounts).

21. Check engine frame for condition, crack formation and deformation.

22. Perform engine cleaning after completion of all maintenance steps for the engine (after completion of 5.1.13).

R* 05-20-00

(1)

(X)

(1)

(X)

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

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Page 09

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

Nov 18/11

1. Check condition of oil radiator and oil tank assemblies.

2. Check oil lines (from/to engine and turbocharger) and oil drainline for condition, leakage and correct routing.

3. Check condition and routing of fire protective sleeves.

4. Oil change. Check drain screws of oil tank and crankcase for metal particles or foreign matter with every oil change.

5. Oil filter change. Inspect the old oil filter insert for metal particles and foreign matter.

6. Check oil quantity after refilling.

1. Check the cooling system components: expansion tank, refill container, overflow bottle (especially ventilation bore) and radiator.

2. Check coolant level, replenish if necessary.

3. Check condition of coolant hoses and pipes, check for leakage and correct routing.

4. Visual inspection of water pump for leakage (leakage bore at the base of the water pump).

5. Flush the liquid cooling system when renewing coolant.

6. Inspect cylinder shaft cooling fins for obstructions and condition.

(X)

R* 05-20-00

12-14-00

R* 05-20-00

12-12-00

12-14-00

5.1.11 Cooling System (Liquid Cooling, Ram Air Cooling)

5.1.10 Lubrication System

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

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Page 10

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

1. Check condition of air filter.

1. Throttle and choke: Check end stops of carburetor controls, springs and condition of bowden-cables.

2. Check TCU and waste gate servo assy for condition and free movement.

3. Check oil pressure sensor, oil temperature sensor, cylinder head temperature sensor, exhaust gas temperature sensor (if installed), fuel pressure and fire warning sensors (if installed) for condition and security.

4. Check function of engine instruments.

1. Check condition of upper center fuselage fairing. Clearance allowed to surrounding parts (all around): 1 ± 0.5 mm / 0.04 ± 0.02 in

2. Check condition of LH and RH engine cowling (Clearance allowed refer to pt. 1).

3. Check condition of the fire protective painting of the cowling. Repair if necessary.

4. Check condition and verify function of inlet and outlet cowl flaps (fully opened and fully closed position). Check the flaps close correctly.

5. Check condition of firewall sheets.

1. Remove spinner dome.

5.1.13 Engine Controls & Monitoring

12-13-00

R* 05-20-00

(X)

5.1.12 Air Induction System

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

5.1.14 Center Fuselage Fairing, Engine Cowlings and Fire-Wall

5.1.15 Propeller

Nov 18/11

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Page 11

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

2. Check blades and all visible hub parts for cracks, deformation, position and security.

3. Check cable routing, cable condition and connection.

4. Check carbon brush block and slip rings for wear.

5. Check spinner and back plates for cracks and security.

6. Check all locks for function.

7. Check flange bolts and stop nuts for correct torque.

8. Check function of the electric actuation motor.

9. Clean slip rings and carbon brushes (must be free from oil and grease).

10. Verify the blade tip play is max. 3 mm (1/8 in.), and the angular play is max. 2°.

11. Visual inspection of the propeller blades. Repair erosion sheath if necessary or replace it (use only material from the manufacturer!).

12. Check adjustment of propeller blade T/O and cruise pitch. Check respective setting of blades and check for discrepancies.

13. Check function of pitch change and time for pitch change in each direction.

14. Check propeller blade T/O-position indication and pre-setting before reaching T/O-position.

1. Check condition and security of drive shaft flanges (paint markings). Check of engine-side drive-shaft flange connection. Visually check M8 bolt connection, self-locking nuts and locking varnish.

(X)

MT**/6

MT**/6, 7

MT**/6

5.1.16 Drive Shaft with Front Gear

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

Nov 18/11

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Page 12

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

1. Remove main gear fairings and inspect for damages.

2. Verify the bearings of the wheel shoes are free moveable.

3. Inspect the main gear legs and trailing arms for deformation and possible cracks as a result of an excessive load.

4. Check condition of main gear tires and creep markings. Check tire pressure: 3.5 ± 0.1 bar / 51.0 ± 1.5 p.s.i.

5. Check function of rocking arm spring damping system.

6. Check wheel bearings for freedom of movement and excessive play.

7. Check brake master cylinder and wheel brake cylinders incl. hoses and lines.

8. Check brake discs and brake linings (at least 1,5 mm / 0.06 in.).

9. Check quantity of brake fluid.

10. Renew brake fluid (DOT 4) if indicated.

1. Remove fairings and inspect for damages.

2. Check condition of nose gear tire and check tire pressure: 3.5 ± 0.2 bar / 51.0 ± 3.0 p.s.i.

3. Visually inspect wheel fork for cracks or deformations.

4. Check function of wheel fork damping system.

12-15-00

(X)

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

5.1.17 Main Landing Gear (Fix L/G)

5.1.18 Nose Landing Gear (Fix L/G)

Nov 18/11

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Page 13

05-20-00

* ROTAX Maintenance Manual (ref. 00-00-00, 2.A), Cha./para. ** mt-propeller, E-118 (ref. 00-00-00, 2.A), /para. (1) if more than 30% of operation with leaded fuel (AVGAS 100 LL)

1. Check condition of pressure system , renew filters/water separators if required.

2. Check condition and function of flight instruments (refer to equipment list).

1. Check wiring of the electric system.

2. Check condition of all electrical devices installed.

3. Check condition and function of all switches.

4. Check condition of all ground terminals.

5. Visually check electric distribution box.

1. Check NAV and COM equipment for proper installation and security and compare to equipment list.

2. Check condition, function and, if applicable, service life limits of NAV and COM equipment (refer to records of operating times).

3. Check all antennas installed.

5.1.20 Electrical System (except for engine and TCU)

5.1.21 COM / NAV Equipment

5.1.19 Flight Instrumentation and Pressure Systems

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

Nov 18/11

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Page 01

05-20-01

EFFECTIVITY

Aircraft equipped with Cabin Heating

1. Check service life limits of heating system parts together with engine cooling system.

2. Check refrigerant hoses of the heating system.

3. Check Heat Exchanger and magnetic shut-off valve.

4. Check fan at Heat Exchanger and duct system.

5. Check heating switch and air flow control knobs.

6. Check electric cables and its plugs.

5.2.1 Cabin Heating System (Option)

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

Nov 18/11

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Page 01

05-20-02

1. Remove cover of cockpit middle console to get access to aerotow release lever.

2. Clean aerotow release clutch E22 and check for function and condition. Pay attention to required TBO of aerotow release clutch.

3. Lubricate aerotow release clutch as required.

4. Perform functional check of release mechanism with original ring couple installed at clutch. Check for free movement and required freerange at release lever of at least 10 mm [0.39 in] to ensure safe locking of release clutch.

5. Visually inspect bowden cable, cable thimbles and hinges to front and aft attachment for damage or deformations and installed locking. Replace bowden cable and teflon cable mantle if necessary (rough-running/damaged).

6. Inspect front hinge of bowden cable at center fuselage tunnel next to aerotow release lever for abrasion and wear of cable and bearing clamp. Replace cable and/or bearing clamp if necessary.

7. Check aerotow release lever in the cockpit for tight fit, free movement and correct adjustment of stop plate.

8. Reinstall cover of cockpit middle console.

05-10-00

12-22-00

(X)

5.3.1 Aerotow Equipment (Option)

Nov 18/11

EFFECTIVITY

Aircraft equipped with Aerotow Device

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

Page 88

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Page 01

05-20-03

Nov 18/11

EFFECTIVITY

Model S6-RT

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

1. Ensure the aircraft to be fixed and secured to a crane or jacked for any inspections on retractable landing gear and hydraulic actuation.

1. Inspect the main gear legs and trailing arms for deformation and possible cracks as a result of an excessive load.

2. Check condition of main gear tires and creep markings. Check tire pressure: 3.5 ± 0.1 bar / 51.0 ± 1.5 p.s.i.

3. Check function of rocking arm spring damping system.

4. Check wheel bearings for freedom of movement and excessive play.

5. Check brake master cylinder and wheel brake cylinders incl. hoses and lines.

6. Check brake discs and brake linings (at least 1,5 mm / 0.06 in.).

7. Check quantity of brake fluid.

8. Renew brake fluid (DOT 4) if indicated.

9. Check drag struts condition, locking mechanics, attachments, hinges and final postion micro switches for damage, deformation and dirt.

10. Check hydraulic actuators for damage, deformation, leakage and dirt.

11. Check main landing gear deflector if clean and freemoving, also at rail (steel frame side).

12. Check all final position micro switches for damage and dirt.

07-10-00

12-15-00

(X)

5.4.1 Main Landing Gear (Retractable L/G)

5.4 Retractable Landing Gear (Retractable L/G)

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1. Check condition of nose gear tire and check tire pressure: 3.5 ± 0.2 bar / 51.0 ± 3.0 p.s.i.

2. Visually inspect wheel fork for cracks or deformations.

3. Check function of wheel fork damping system.

4. Check drag strut condition, locking mechanics, attachments, hinges and all final postion micro switches for damage, deformation and dirt.

5. Check hydraulic actuator for damage, deformation, leakage and dirt.

1. Check nose and main landing gear doors for condition, correct mounting, actuation, damage and gas springs.

2. Check doors to be fully closed when landing gear is retracted with functional check under 5.4.5.

1. Check hydraulic fluid level at dipstick of hydraulic drive unit (min. lower mark, max. upper mark). Refill if necessary.

2. Check pressure reservoir for pressure of 90 bar / 1305 psi ± 8% (refer to Flight Manual, chapter 4.5). If pressure is lower, activate main switch (BATT) with landing gear switch DOWN. Hydraulic drive unit has to pump up reservoir up to 90 bar / 1305 psi ± 8% automatically (red check light has to go out above 90 bar / 1305 psi ± 8%).

3. Check all hydraulic lines and both pressure reservoir bottles, fittings and hydraulic actuation unit for condition, damage and leakage.

5.4.4 Hydraulic Drive Unit

5.4.3 Landing Gear Doors

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

Page 02

05-20-03

Nov 18/11

EFFECTIVITY

Model S6-RT

5.4.2 Nose Landing Gear (Retractable L/G)

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5.4.5 Functional Tests

5.4.6 Engine Cooling System

Page 03

05-20-03

May 04/12

Reference Initials

Motor 100h

Motor 25h

Airframe

100h

Motor 200h

Motor 600h

Motor 1000h

Annual

Type and Subject of Inspection

No.

1. With aircraft fixed on crane perform functional test of landing gear actuation. Check free movement of nose and main landing gear over complete range. Check for collision to structure of landing gear doors.

2. Check function of landing gear warning by extending air-brakes with landing gear retracted. Acoustical warning has to come up.

3. Perform functional test of landing gear emergency extension. Check hydraulic fluid level afterwards (ref. 5.4.4).

1. Check function of cooling radiator fan during engine test run (engine coolant temperature has to stabilize during warm up).

EFFECTIVITY

Model S6-RT

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STEMME TSA-M

05-30-00

Page 01

Daily Inspections

1 General

A. Daily inspections include the pre-flight and post-flight checks. These visual inspections must be

performed each day the aircraft is used.

2. Pre-Flight Check

WARNING: ALL STEPS OF THE PRE-FLIGHT CHECK MUST BE PERFORMED CAREFULLY

BEFORE FIRST FLIGHT OF THE DAY AND AFTER AN AIRCRAFT RE-ASSEMBLY. OMITTING THESE CHECKS OR DOING THEM CARELESSLY MAY CAUSE HEAVY ACCIDENTS.

A. The pre-flight check must be done before the first flight of the day by the responsible pilot. The

walk-around shows the pilot the general condition of the aircraft and its systems.

B. For the pre-flight check procedure, refer to the S6 Airplane Flight Manual, Section 4.

3. Post-Flight Check

A. This check must be performed after the last flight of the day. The post-flight check includes all

inspections of the pre-flight check. Additionally: (1) Refuel the airplane as per recommendations in the AFM. (2) Record into the log book each problem found in flight and during the post-flight check. (3) Park the aircraft. For parking procedure, refer to 10-10-00. (4) If necessary, moor the aircraft. For the appropriate information, refer to 10-20-00.

Nov 18/11

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UNSCHEDULED MAINTENANCE CHECKS

1. General

A. Special checks are to be carried out only in circumstances, outside routine inspections, where

event have occurred that may have caused damage to the aircraft or an impairment of airworthiness possibly during the operation of the aircraft.

Furthermore, the 25-hour inspection necessary for a newly delivered aircraft and its engine, as well as for overhauled engines and after extensive airframe repairs, falls under the special checks since it must only be carried out once after the first 25 hours of operation of the aircraft.

2. Special Checks

A. 25-Hour Inspection

After the first 25 hours of operation an inspection within the specifications of a 100-hour inspection is to be completed (Refer to 05-20-00).

B. Hard Landing Concerning the Landing Gear and Tail Boom

After an excessively hard landing or other unusual loads of the landing gear a thorough inspection of the affected components and their attachment is required. Even if no obvious defects are detectable, a visual inspection must be carried out. Examination contains parts of 100 hours inspection listed in the STEMME S6 Inspection Time Intervals Chart (Refer to section "Scheduled Maintenance Checks" of this chapter) concerning the landing gear.

C. Engine Fire

After an engine fire perform the following steps:

WARNING: IF SUSPECTED THAT PARTS OF THE STRUCTURE OR OF THE COWLING

WOULD BE ABLE TO HAVE BEEN DAMAGED BY THE HIGH TEMPERATURES (DETECTABLY AMONG OTHER THINGS BY BLISTERING ON THE PROTECTIVE COATING), ALWAYS THE MANUFACTURER SHOULD BE CONTACTED FOR THE APPRAISAL OF THE DEFECTS BEFORE THE AIRCRAFT IS PUT INTO OPERATION AGAIN.

(1) Disconnect battery (refer to 24-30-00). (2) Remove engine cowling (refer to 72-10-00). (3) Examine engine cowling. Check for signs of fire damage. (4) Examine electrical cables for damaged insulation. (5) Examine fuel lines for damage of the fire-protection sleeves. (6) Check oil lines for damage of the fire-protection sleeves. (7) Check air filter element for fire damage. (8) Examine engine mount and shock mounts for any fire damage. (9) Check all other hoses and pipes, as well as all gaskets and seals for fire damage.

05-50-00

Page 201

Nov 18/11

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(10) Replace damaged items. (11) Install engine cowling (refer to 72-10-00). (12) Perform an engine test run (refer to 05-20-00).

D. Violent Stop of the Engine

In event that the propeller was touching ground or the engine was inadvertently stopped violently (shock loading) the engine with the propeller gear box must be disassembled and inspected by an authorized workshop.

CAUTION: ONLY QUALIFIED TECHNICIANS (AUTHORIZED BY AVIATION AUTHORITY

AND AFTER SUCCESSFUL ATTENDANCE OF THE RELEVANT ROTAX TRAINING COURSE) ARE AUTHORIZED TO PERFORM THIS WORK.

Check additional equipment (external alternator, hydraulic governor, ignition unit, coolant and oil hoses) for damage.

Page 202

05-50-00

Nov 18/11

Page 97

MAINTENANCE MANUAL

STEMME TSA-M

UNSCHEDULED MAINTENANCE CHECKS

1. General

A. Special checks are to be carried out only in circumstances, outside routine inspections, where

event have occurred that may have caused damage to the aircraft or an impairment of airworthiness possibly during the operation of the aircraft.

2. Special Checks

A. 25-Hour Inspection

After the first 25 hours of operation an inspection within the specifications of a 100-hour inspection is to be completed (Refer to 05-20-00).

B. Hard Landing Concerning the Landing Gear and Tail Boom

C. Engine Fire

After an engine fire perform the following steps:

WARNING: IF SUSPECTED THAT PARTS OF THE STRUCTURE OR OF THE COWLING AS

WELL AS THE MAIN LANDING GEAR DOORS WOULD BE ABLE TO HAVE BEEN DAMAGED BY THE HIGH TEMPERATURES (DETECTABLY AMONG OTHER THINGS BY BLISTERING ON THE PROTECTIVE COATING), THE MANUFACTURER IS TO BE CONTACTED FOR THE APPRAISAL OF THE DEFECTS BEFORE THE AIRCRAFT IS PUT INTO OPERATION AGAIN.

(1) Disconnect battery (refer to 24-30-00). (2) Remove engine cowling (refer to 72-10-00). (3) Examine engine cowling. Check for signs of fire damage. (4) Examine electrical cables for damaged insulation. (5) Examine fuel lines for damage of the fire-protection sleeves. (6) Check oil lines for damage of the fire-protection sleeves. (7) Check air filter element for fire damage. (8) Examine engine mount and shock mounts for any fire damage. (9) Check landing gear hydraulic system (hydraulic hoses, actuators, pressure

05-50-00

Page 201

Nov 18/11

EFFECTIVITY

Model S6-RT

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accumulators as well as all gaskets) for fire damage. (10) Check all other hoses and pipes, as well as all gaskets and seals for fire damage. (11) Replace damaged items. (12) Install engine cowling (refer to 72-10-00). (13) Perform an engine test run (refer to 05-20-00).

D. Violent Stop of the Engine

CAUTION: ONLY QUALIFIED TECHNICIANS (AUTHORIZED BY AVIATION AUTHORITY

AND AFTER SUCCESSFUL ATTENDANCE OF THE RELEVANT ROTAX TRAINING COURSE) ARE AUTHORIZED TO PERFORM THIS WORK.

Check additional equipment (external alternator, hydraulic governor, ignition unit, coolant and oil hoses) for damage.

Page 202

05-50-00

Nov 18/11

EFFECTIVITY

Model S6-RT

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CHAPTER 06

DIMENSIONS AND AREAS

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