STEMME TSA-M CHAPTER 11 PLACARDS AND MARKINGS

Transcription

STEMME TSA-M
MAINTENANCE MANUAL
CHAPTER 11
PLACARDS AND MARKINGS
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page Effectivity
PLACARDS AND MARKINGS - GENERAL .................................................11-00-00
Introduction
11-00-00
General Description
11-00-00
Page Numbering System for Interior / Exterior
Placards and Markings
11-00-00
1
1
1
EXTERIOR PLACARDS AND MARKINGS...................................................11-20-00
General
11-20-00
Tools, Equipment and Material
11-20-00
Removal/Installation
11-20-00
Maintenance
11-20-00
Additional Placards Aerotow
11-20-01
Additional Placards Wing Folding Device
11-20-02
201
201
201
201
202
201
201
Aerotow
Wing Folding
INTERIOR PLACARDS AND MARKINGS ...................................................11-30-00
General
11-30-00
Tools, Equipment and Material
11-30-00
Removal/Installation
11-30-00
Additional Placards Aerotow
11-30-01
Additional Placards S6-RT
11-30-02
Additional Placards ELT Kannad 406 AF/AP
11-30-03
201
201
201
202
201
201
201
Aerotow
S6-RT
ELT Kannad
1
11 - TOC
Page 01
Mar 16/12
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
PLACARDS AND MARKINGS - GENERAL
1. Introduction
A.
This chapter provides information about graphics, placards, labels and markings inside and
outside as well as its maintenance and repair.
2. General Description
In the following, a brief description and intended purpose of each section of this chapter is given.
A.
Section 11-00-00 - Placards and Markings General. This section provides a general overview of
content and purpose of the chapter. The structure is explained.
B.
Section 11-20-00 - Exterior Placards and Markings. This section gives maintenance and care
instructions to exterior placards, graphics, markings etc. and contains information about required
equipment and material.
C.
Section 11-30-00 - Interior placards and Markings. This section gives maintenance and care
instructions to interior placards, graphics, markings etc. and contains information about required
equipment and material.
3. Page Numbering System for Interior / Exterior Placards and Markings
A.
Placards and Markings are divided in two main groups - "Interior" and "Exterior".
Exterior placards and markings are described in section 11-20-00 of this chapter, the interior in
section 11-30-00.
11-00-00
Page 01
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
EXTERIOR PLACARDS AND MARKINGS
1. General
A.
This section gives maintenance and care instructions to exterior graphics, markings, etc.
2. Tools, Equipment and Material
Required in
Quantity
Equipment
Parts No.
3.A. and B.
3.A. and B.
1
as
Required
1
1
Heat gun
Isopropyl Alcohol
-
Commercially Available
Needle
Handy, Dense,
Closed cell foam
Block
-
3.B.
3.B.
Manufacturer
3. Removal / Installation
A.
Remove self-adhesive Graphics
NOTE: Reference marks should be made on aircraft before removing old graphics.
(1) Warm the graphic a little by using a heat gun (approx. 40-50°C / 104-122°F).
(2) Carefully separate a corner of the graphic from the aircraft and then pull downward on
graphic. Remove graphic.
(3) Remove all traces of old adhesive by using a cloth with isopropyl alcohol as required.
B.
Install self-adhesive Graphics
(1) Clean aircraft surface carefully. Remove all old adhesive traces using isopropyl alcohol.
(2) Remove paperliner from backside of graphic to expose adhesive.
(3) Position top edge of graphic precisely.
(4) Work uniformly downward and apply graphic to aircraft with a dry, clean cloth.
(5) Remove the premask (outer protective film) from the graphic.
(6) Remove air bubbles by perforating bubble with a small diameter needle and then flattening.
(7) Aftertreat rivet heads
(a) Perforate air bubbles around the rivet heads with a needle (10-12 places).
(b) Warm the graphic and structure around each rivet using a heat gun (approx. 40-50°C /
104-122°F).
(c) Work out all bubbles from around the rivet head using a handy closed cell foam block.
(8) Heat up again entire graphic for 10 - 15 minutes (approx. 40 - 50°C / 104-122°F)
11-20-00
Page 201
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
4. Maintenance
A.
The following instructions should be followed to guarantee a maximum service life for the
graphics:
(1) Clean aircraft exterior surface always as in chapter 12, section "Aircraft Exterior - Cleaning",
paragraph 4, described manner.
(2) Do not use any solvents for cleaning the graphics.
(3) Test other cleaning agents in a small inconspicuous place of the graphic.
(4) Do not allow fuel to spill on graphics. If fuel spills on graphics, wipe off by a cloth and rinse
with water thoroughly.
(5) Do not eliminate snow and ice on surfaces using peaked and sharp-edged instruments.
(6) If a high-pressure washer is used, keep nozzle at least 0,5 m (approx. 1,6 ft) from edge of
graphic.
11-20-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
E
D
E
A
C
D
C
B
B
Detergent Oil
API-SG or higher
3.5 bar
51 psi
Detail
A
Detail
B
(Metric Units)
Detail
B
(Imperial Units)
Exterior Placards and Markings
Figure 201 (Sheet 1 of 2)
11-20-00
Page 203
May 04/12
STEMME TSA-M
MAINTENANCE MANUAL
Detail- C
D-KXXX
Detail- E
Detail- D
(exemplary for German
Registration)
(exemplary for German Registration)
11-20-00
Page 204
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
A
Detail- A
or
500 daN
1125 lbf
Figure 201
EFFECTIVITY
Aircraft equipped with Aerotow Device
11-20-01
Page 201
May 04/12
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
A
Detail- A
View to lower side of right wing (intersection outer wing - winglet)
Wing leading egde
Note:
The placard has to be fitted to a definite position refering to wing spar position.
For detailed placard position contact the manufacturer to get a layout drawing.
Figure 201
EFFECTIVITY
Aircraft equipped with Wing Folding Device
11-20-02
Page 201
Mar 16/12
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
INTERIOR PLACARDS AND MARKINGS
1. General
A.
This section gives information about removal and installation of interior placards, markings etc.
B.
If the information on the placard is no longer completely readable or the placard is partially or has
totally come off, the placard must be replaced with a new one.
Required in
Quantity
Equipment
Parts No.
3.A
3.A
1
as
required
1
Heat gun
Isopropyl Alcohol
-
Needle
-
3.B
Manufacturer
A.
Remove self-adhesive Placards
(1) Heat up placard a little by using a heat gun (approx. 40-50°C / 104-122°F).
(2) Carefully separate a corner of the placard and then pull parallel to surface to remove it.
B.
Install self-adhesive Placards
(1) Remove protective film from backside of placard to expose adhesive.
(2) Position top edge of the placard precisely.
(3) Apply placard by rubbing with a dry, clean cloth.
EFFECTIVITY
001 - 010
11-30-00
Page 201
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
C
B
Z2
Z1
I
Y
E
D
S
A
P1
H
J
N2
N
P
P3
F
N1
P2
R
G
M
L
Q
K
N3
O
O2
O1
N4
Interior Placards and Markings
EFFECTIVITY
001 - 010
11-30-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
1. General
A.
B.
Required in
Quantity
Equipment
Parts No.
3.A
3.A
1
as
required
1
Heat gun
Isopropyl Alcohol
-
Needle
-
3.B
Manufacturer
A.
B.
EFFECTIVITY
Aircraft equipped with Professional Line Avionics
11-30-00
Page 201
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
C
B
Z2
Z1
I
Y
E
D
S
A
K
G
L1
L
M
P1
Q
N
P
P3
J
N2
P2
R
F
N1
L2
H
N3
O
O2
O1
N4
EFFECTIVITY
11-30-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
AUX
PUMP
TRANSF.
PUMP
LOW
FUEL
INSTR.
LIGHT
ACL
POS
TCU
MAP
INT
GEN
ENG.
BATT.
AUX
PUMP
NOSE
HEAVY
T
R
I
M
LAND
HEADLIGHT
EXT
ALT
AVIONIC
MASTER
Detail- A
Detail- B
Detail- D
ALT
FIELD
AUDIO
PANEL
VOLT
ELT
PROP
CTRL
SOAR
COMP
SCKT
NAV
GPS
TRIM
EFIS
STALL
WARN
XPDR
ENG
BUS
COMM
Detail- J
Detail- K
FUEL DIFF PRESSURE
2.5 +/- 1.0
Detail- E
TAIL
HEAVY
TCU
ISOLATION
Detail- C
PROP RPM
Detail- Y
SOCKET
12V / 4A
MASTER
ALTERNATOR
Detail- I
Detail- F
Detail- G
Detail- H
COWL FLAPS
PUSH:
OPEN
PULL:
CLOSED Detail- M
Detail-N Detail- O Detail- P Detail- L
A
I
R
B
R
A
K
E
S
T
H
R
O
T
T
L
E
F
L
A
P
S
PTT
NOSE
T
R
I
M
TAIL
C
H
O
K
E
Detail- Q
OFF
Detail- L1
ON
Detail- L2
LOCKED
Detail- P1
CENTER
Detail- P2
EXTENDED
Detail- P3
FULL POWER
Detail- O1
IDLE
Detail- O2
CRUISE
Detail- N1
NEUTRAL
Detail- N2
T/O LDG 1
Detail- N3
LDG 2
Detail- N4
Detail- R
AUX: 64 l
MAIN: 62.9 l
* - Not in Scale
AUX: 16.9 US gal
Detail- Z1
MAIN: 16.6 US gal Detail- Z2
Interior Placards and Markings*
EFFECTIVITY
11-30-00
Page 203
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
U
T
W
V
Detail- T
EFFECTIVITY
11-30-00
Page 204
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
1. General
A.
B.
Required in
Quantity
Equipment
Parts No.
3.A
3.A
1
as
required
1
Heat gun
Isopropyl Alcohol
-
Needle
-
3.B
Manufacturer
A.
B.
EFFECTIVITY
Aircraft equipped with Classic Line Avionics
11-30-00
Page 201
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
B
S
C
Z2
Z1
I
Y
E
D
A
K
G
L1
L
M
P1
Q
N
P
P3
J
N2
P2
R
F
N1
L2
H
N3
O
O2
O1
N4
EFFECTIVITY
11-30-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
AUX
PUMP
TRANSF.
PUMP
LOW
FUEL
AUX
PUMP
INSTR.
LIGHT
ACL
POS
TCU
MAP
INT
GEN
ENG.
BATT.
NOSE
HEAVY
T
R
I
M
LAND
HEADLIGHT
EXT
ALT
AVIONIC
MASTER
Detail- B
Detail- D
Detail- A
ALT
FIELD
INTER
COM
VOLT
ELT
PROP
CTRL
SOAR
COMP
FUEL DIFF PRESSURE
2.5 +/- 1.0
Detail- E
TAIL
HEAVY
TCU
ISOLATION
Detail- C
PROP RPM
Detail- Y
SOCKET
12V / 4A
MASTER
ALTERNATOR
Detail- I
COWL FLAPS
PUSH:
OPEN
PULL:
CLOSED Detail- M
A
I
R
B
R
A
K
E
S
T
H
R
O
T
T
L
E
F
L
A
P
S
PTT
NOSE
T
R
I
M
TAIL
C
H
O
K
E
Detail- Q
Detail- R
AUX: 64 l
MAIN: 62.9 l
* - Not in Scale
AUX: 16.9 US gal
Detail- F
Detail- G
Detail- H
OFF
Detail- L1
ON
Detail- L2
LOCKED
Detail- P1
CENTER
Detail- P2
EXTENDED
Detail- P3
FULL POWER
Detail- O1
IDLE
Detail- O2
CRUISE
Detail- N1
NEUTRAL
Detail- N2
T/O LDG 1
Detail- N3
LDG 2
Detail- N4
SCKT
TRIM
STALL
WARN
XPDR
ENG
BUS
COMM
Detail- J
Detail- K
Detail- Z1
EFFECTIVITY
11-30-00
Page 203
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
U
T
W
V
Detail- T
EFFECTIVITY
11-30-00
Page 204
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
1. General
A.
B.
Required in
Quantity
Equipment
Parts No.
3.A
3.A
1
as
required
1
Heat gun
Isopropyl Alcohol
-
Needle
-
3.B
Manufacturer
A.
B.
EFFECTIVITY
Aircraft equipped with Advanced Line Avionics
11-30-00
Page 201
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
B1
B2
C
Z2
Z1
I
Y
E
D
S
A
K
G
L1
L
M
P1
Q
N
P
P3
J
N2
P2
R
F
N1
L2
H
N3
O
O2
O1
N4
EFFECTIVITY
11-30-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
AUX
PUMP
LOW
FUEL
TRANSF.
PUMP
AUX
PUMP
TCU
INSTR.
LIGHT
MAP
Detail- B1
NOSE
HEAVY
ENG.
T
R
I
M
LAND
HEADLIGHT
POS
ACL
INT
GEN
BATT.
EXT
ALT
AVIONIC
MASTER
Detail- A
Detail- B2
Detail- D
ALT
FIELD
INTER
COM
VOLT
ELT
PROP
CTRL
SOAR
COMP
SCKT
GPS
TRIM
EFIS
STALL
WARN
XPDR
ENG
BUS
COMM
Detail- J
Detail- K
FUEL DIFF PRESSURE
2.5 +/- 1.0
Detail- E
TAIL
HEAVY
TCU
ISOLATION
Detail- C
PROP RPM
Detail- Y
SOCKET
12V / 4A
MASTER
Detail- F
Detail- G
Detail- H
ALTERNATOR
Detail- I
COWL FLAPS
PUSH:
OPEN
PULL:
CLOSED Detail- M
A
I
R
B
R
A
K
E
S
T
H
R
O
T
T
L
E
F
L
A
P
S
PTT
NOSE
T
R
I
M
TAIL
C
H
O
K
E
MAIN: 62.9 l
* - Not in Scale
ON
Detail- L2
LOCKED
Detail- P1
CENTER
Detail- P2
Detail- P3
FULL POWER
Detail- O1
Detail- Q
AUX: 16.9 US gal
Detail- L1
EXTENDED
Detail- R
AUX: 64 l
OFF
IDLE
Detail- O2
CRUISE
Detail- N1
NEUTRAL
Detail- N2
T/O LDG 1
Detail- N3
LDG 2
Detail- N4
Detail- Z1
EFFECTIVITY
11-30-00
Page 203
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
U
T
W
V
Detail- T
EFFECTIVITY
11-30-00
Page 204
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
Manufacturer: STEMME AG
Type: TSA-M
Model: S6
6.T. XX.XXX
Serial no.:
VNE (IAS)
[m MSL] [km/h]
Year of Constr.:
XXXX
Certificated for:
VNE
Never exceed Speed:
270 km/h
VA
Manoeuvering Speed:
190 km/h
Maximum Speeds
VRA
- Rough Air:
190 km/h
- Flaps extended
VFE
pos. Flaps: TO / LDG 1:
190 km/h
VFE
LDG 2:
140 km/h
XXX
Empty Weight:
kg
850 kg
Max. Take-Off Weight:
XX kg, otherwise ballast
Min. Seat Load:
XXX
Max. Cockpit Load:
kg
Permitted Flight Figures:
- None -
0
270
2000
270
3000
255
4000
245
5000
230
6000
220
8000
195
10000
170
12000
150
Detail- S
Detail- V
VNE (IAS)
[ft MSL]
[km/h]
0
270
6500
270
10000
255
Note: Check Load before every flight!
13000
245
Change in the cockpit load with load in the baggage
compartment:
16500
230
19500
220
26000
195
33000
170
39500
150
LMCL New= LMCL+ L x 2,2 LMCL New increased min. cockpit load
L MCL min. cockpit load
L
baggage weight
baggage weight
[kg]
Increase of min. cockpit load
by: [kg]
20 (max.)
15
10
5
44
33
22
11
Detail- S
Baggage
max. 20 kg
Detail- W
* - Not in Scale
Detail- U
Figure 201 (Sheet 4 of 4) - Metric Units
11-30-00
Page 205
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
Type: TSA-M
Model: S6
6.T. XX.XXX
Serial no.:
VNE (IAS)
Year of Constr.:
XXXX
Certificated for:
VNE
Never exceed Speed:
145 kts
VA
Manoeuvering Speed:
102 kts
Maximum Speeds
VRA
- Rough Air:
102 kts
- Flaps extended
VFE
102 kts
VFE
LDG 2:
75 kts
XXX
Empty Weight:
lbs
1874 lbs
XX lbs, otherwise ballast
Min. Seat Load:
XXX
Max. Cockpit Load:
lbs
- None -
Detail- V
compartment:
L
baggage weight
by: [lbs]
44 (max.)
33
22
11
97
73
49
24
145
6500
145
10000
138
13000
132
16500
19500
124
119
26000
105
33000
92
39500
81
VNE (IAS)
[ft MSL]
[mph]
0
168
6500
168
10000
159
13000
152
16500
143
19500
137
26000
121
33000
106
39500
93
Detail- S
Baggage
max. 44 lbs
Detail- W
* - Not in Scale
[kts]
0
Detail- S
baggage weight
[lbs]
[ft MSL]
Detail- U
Figure 201 (Sheet 4 of 4) - Imperial Units
11-30-00
Page 206
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
Type: TSA-M
Model: S6
6.T. XX.XXX
Serial no.:
VNE (IAS)
[m MSL] [km/h]
Year of Constr.:
XXXX
Certificated for:
VNE
Never exceed Speed:
270 km/h
VA
Manoeuvering Speed:
190 km/h
Maximum Speeds
VRA
- Rough Air:
190 km/h
- Flaps extended
VFE
190 km/h
VFE
LDG 2:
140 km/h
XXX
Empty Weight:
kg
850 kg
Min. Seat Load:
XXX
Max. Cockpit Load:
kg
- Intentional Spins -
0
270
2000
270
3000
255
4000
245
5000
230
6000
220
8000
195
10000
170
12000
150
Detail- S
Detail- V
VNE (IAS)
[ft MSL]
[km/h]
0
270
6500
270
10000
255
13000
245
compartment:
16500
230
19500
220
26000
195
33000
170
39500
150
L
baggage weight
baggage weight
[kg]
by: [kg]
20 (max.)
15
10
5
44
33
22
11
Detail- S
Baggage
max. 20 kg
Detail- W
* - Not in Scale
Detail- U
EFFECTIVITY
Aircraft equipped with Double Panel Airbrakes
11-30-00
Page 205
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
Type: TSA-M
Model: S6
6.T. XX.XXX
Serial no.:
VNE (IAS)
Year of Constr.:
XXXX
Certificated for:
VNE
Never exceed Speed:
145 kts
VA
Manoeuvering Speed:
102 kts
Maximum Speeds
VRA
- Rough Air:
102 kts
- Flaps extended
VFE
102 kts
VFE
LDG 2:
75 kts
XXX
Empty Weight:
lbs
1874 lbs
Min. Seat Load:
XXX
Max. Cockpit Load:
lbs
- Intentional Spins -
Detail- V
compartment:
L
baggage weight
by: [lbs]
44 (max.)
33
22
11
97
73
49
24
145
6500
145
10000
138
13000
132
16500
19500
124
119
26000
105
33000
92
39500
81
VNE (IAS)
[ft MSL]
[mph]
0
168
6500
168
10000
159
13000
152
16500
143
19500
137
26000
121
33000
106
39500
93
Detail- S
Baggage
max. 44 lbs
Detail- W
* - Not in Scale
[kts]
0
Detail- S
baggage weight
[lbs]
[ft MSL]
Detail- U
EFFECTIVITY
Aircraft equipped with Double Panel Airbrakes
11-30-00
Page 206
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
Type: TSA-M
Model: S6-RT
6.T. XX.XXX Year of Constr.:
Serial no.:
VNE (IAS)
[m MSL] [km/h]
XXXX
Certificated for:
VNE
Never exceed Speed:
270 km/h
VA
Manoeuvering Speed:
190 km/h
Maximum Speeds
VRA
- Rough Air:
190 km/h
VLO
- Landing Gear extended:
140 km/h
- Flaps extended
VFE
190 km/h
VFE
LDG 2:
140 km/h
XXX
Empty Weight:
kg
900 kg
Min. Seat Load:
XXX
Max. Cockpit Load:
kg
- None -
0
270
2000
270
3000
255
4000
245
5000
230
6000
220
8000
195
10000
170
12000
150
Detail- S
Detail- V
VNE (IAS)
[ft MSL]
[km/h]
0
270
6500
270
10000
255
13000
245
compartment:
16500
230
19500
220
26000
195
33000
170
39500
150
L
baggage weight
baggage weight
[kg]
by: [kg]
20 (max.)
15
10
5
44
33
22
11
Detail- S
Baggage
max. 20 kg
Detail- W
* - Not in Scale
Detail- U
EFFECTIVITY
Model S6-RT
11-30-00
Page 205
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
Type: TSA-M
Model: S6-RT
6.T. XX.XXX Year of Constr.:
Serial no.:
VNE (IAS)
XXXX
Certificated for:
VNE
Never exceed Speed:
145 kts
VA
Manoeuvering Speed:
102 kts
Maximum Speeds
VRA
- Rough Air:
102 kts
VLO
- Landing Gear extended:
75 kts
- Flaps extended
VFE
102 kts
VFE
LDG 2:
75 kts
XXX
Empty Weight:
lbs
1984 lbs
Min. Seat Load:
XXX
Max. Cockpit Load:
lbs
- None -
Detail- V
compartment:
L
baggage weight
by: [lbs]
44 (max.)
33
22
11
97
73
49
24
145
6500
145
10000
138
13000
132
16500
19500
124
119
26000
105
33000
92
39500
81
VNE (IAS)
[ft MSL]
[mph]
0
168
6500
168
10000
159
13000
152
16500
143
19500
137
26000
121
33000
106
39500
93
Detail- S
Baggage
max. 44 lbs
Detail- W
* - Not in Scale
[kts]
0
Detail- S
baggage weight
[lbs]
[ft MSL]
Detail- U
EFFECTIVITY
Model S6-RT
11-30-00
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MAINTENANCE MANUAL
A
T
O
W
R
E
L
E
A
S
E
Detail- A
Figure 202
EFFECTIVITY
11-30-01
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Nov 18/11
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MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
A
B
C
Detail- A
C
B
ON
Detail- B
OFF
Detail- C
D
LDG. GEAR EMERGENCY
PULL
Detail- D
EFFECTIVITY
Model S6-RT
11-30-02
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MAINTENANCE MANUAL
A
C1
E
C2
B
D
EFFECTIVITY
Model S6-RT
11-30-02
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MAINTENANCE MANUAL
Detail- B
HEATING
ALT
FIELD
VOLT
Landing Gear
Left Nose Right
Detail- A
L/G UP
Detail- C1
L/G DOWN
Detail- C2
PROP
CTRL
SCKT
TRIM
STALL
WARN
ENG
BUS
Detail- D
Detail- E
EFFECTIVITY
Model S6-RT
11-30-02
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Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
CHAPTER 12
SERVICING
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page
SERVICING - GENERAL..................................................................................12-00-00
Introduction
12-00-00
General Description
12-00-00
1
1
1
REPLENISHING - DESCRIPTION.................................................................12-10-00
General
12-10-00
Fuel Capacity
12-10-00
Approved Fuel
12-10-00
Engine Oil Capacity
12-10-00
Approved Engine Oil
12-10-00
Hydraulic Fluid
12-10-00
1
1
1
1
2
2
3
FUEL - SERVICING...........................................................................................12-11-00
General
12-11-00
Safety and Maintenance Precautions
12-11-00
Fueling and Defueling
12-11-00
301
301
301
301
ENGINE OIL - SERVICING.............................................................................12-12-00
General
12-12-00
Checking Engine Oil
12-12-00
Oil Change Intervals
12-12-00
Oil Changing
12-12-00
301
301
301
301
301
INDUCTION AIR FILTER - SERVICING ......................................................12-13-00
General
12-13-00
Air Filter Changing
12-13-00
Air Filter Cleaning
12-13-00
301
301
301
301
COOLING SYSTEM - SERVICING ................................................................12-14-00
General
12-14-00
Adding Coolant
12-14-00
Renewal of the Coolant
12-14-00
Flushing the Cooling System
12-14-00
301
301
301
301
302
BRAKE SYSTEM - SERVICING .......................................................................12-15-00
General
12-15-00
Hydraulic Fluid Replenishing
12-15-00
301
301
301
TIRES - SERVICING..........................................................................................12-16-00
General
12-16-00
Tire Servicing
12-16-00
301
301
301
12 - TOC
Page 01
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MAINTENANCE MANUAL
BATTERY - SERVICING ...................................................................................12-17-00
General
12-17-00
Battery Servicing
12-17-00
301
301
301
SCHEDULED SERVICING - DESCRIPTION ...............................................12-20-00
General
12-20-00
1
1
LUBRICANTS - DESCRIPTION......................................................................12-21-00
General
12-21-00
Service Notes
12-21-00
Definition of „As Needed“
12-21-00
Recommended Lubricants
12-21-00
1
1
1
1
1
LUBRICATION - SERVICING .........................................................................12-22-00
General
12-22-00
Lubrication Table
12-22-00
301
301
301
AIRCRAFT EXTERIOR CLEANING AND CARE........................................12-23-00
General
12-23-00
Safety Precautions
12-23-00
Cleaning and Care of the Windshield and Windows
12-23-00
Cleaning and Care of the Aircraft Exterior Surfaces
12-23-00
Cleaning Engine
12-23-00
Cleaning and Care of the Propeller
12-23-00
Cleaning Landing Gear
12-23-00
701
701
701
701
702
703
704
704
AIRCRAFT INTERIOR CLEANING AND CARE ........................................12-24-00
General
12-24-00
Aircraft Interior Cleaning
12-24-00
Cleaning Instrument Panel
12-24-00
Cleaning Cabin Floor
12-24-00
Cleaning Seats
12-24-00
701
701
701
701
702
702
HYDRAULIC FLUID SERVICING..................................................................12-30-00
General
12-30-00
Replenishing Hydraulic Fluid
12-30-00
Change Hydraulic Fluid
12-30-00
301
301
301
301
UNSCHEDULED SERVICING........................................................................12-50-00
General
12-50-00
Removing Snow and Ice
12-50-00
701
701
701
12 - TOC
Page 02
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
SERVICING - GENERAL
1. Introduction
A.
This chapter gives information for the replenishment of fluids as well as the lubrication of
components. The chapter also contains instructions necessary to carry out scheduled servicing.
The chapter is designed help authorized personnel to correctly service the aircraft.
A.
Section 12-00-00 - Servicing - General. This section provides a general overview of content and
purpose of the chapter.
B.
The subsequent sections are divided into 3 groups.
(1) Replenishment fluids
Provides information for the maintenance personnel to perform correctly the necessary
services during the daily aircraft operation. This group begins with section 12-10-00 Replenishing - Description. The section includes specifications of approved fluids and
information about tank and reservoir capacities.
(2) Scheduled Servicing
Provides information for the maintenance personnel to perform periodic service, such as
lubricating of components or cleaning of the aircraft. This group begins with section 12-20-00
Scheduled Servicing Description.
(3) Unscheduled Servicing
Provides information for the maintenance personnel to perform service, which is to be,
practiced irregularly such as removing ice and snow.
12-00-00
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Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
REPLENISHING - DESCRIPTION
1. General
A.
This chapter provides necessary information about fluids to be replenished during operation of
the S6.
2. Fuel Capacity
A.
The following table lists the aircraft fuel capacities.
WARNING:
USE ONLY FUEL PER ROTAX 914 SERIES OPERATORS MANUAL.
Litres
U.S.Gallons
Total Capacity
65/130*
17.2/34.4*
Usable Fuel
62.9/126.9*
16.65/31.55*
Unusable Fuel
2.1/3.1*
0.55/0.85*
*) Longe Range Configuration
3. Approved Fuel
A.
The following fuel is approved for use in the S6.
MOGAS
Designation/Description
European Standard
EN 228 Super, min. ROZ 95
EN 228 Super, plus min. ROZ 95
Canadian Standard
CAN/CGSB-3.5 Quality 3, min. AKI 91
U.S. Standard
ASTM D4814
AVGAS
U.S. Standard
NOTE:
AVGAS 100LL, ASTM D910
AVGAS 100LL places greater stress on the valve seats due to its high lead content and
forms increased deposits in the combustion chamber and lead sediments in the oil
system. Thus it should only be used in case of problems with vapor lock or when other
types of gasoline are unavailable (refer to ROTAX SI 914-019, latest revision and
Operators Manual for ROTAX 914, latest revision).
12-10-00
Page 01
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STEMME TSA-M
MAINTENANCE MANUAL
CAUTION:
USE ONLY FUEL SUITABLE FOR THE RESPECTIVE CLIMATIC ZONE.
OBEY THE LATEST EDITION OF SERVICE INSTRUCTION SI-914-019 FOR THE
SELECTION OF THE CORRECT FUEL.
NOTE:
Risk of vapour formation if using winter fuel for summer operation.
4. Engine Oil
A.
B.
Engine Oil Capacity
Litres
U.S. Quarts
Total engine
Oil capacity
3,2
3.17
Minimum
2,0
2.11
Oil Specification
CAUTION:
AT THE SELECTION OF SUITABLE LUBRICANTS, REFER TO THE ADDITIONAL
INFORMATION IN THE SERVICE INFORMATION SI-914-019, CURRENT ISSUE.
(1) Use only oil with API classification “SG” or higher.
(2) Due to the high stresses in the reduction gears, oils with gear additives such as high
performance motor cycle oils are required.
(3) Because of the incorporated friction clutch, oils with friction modifier additives are unsuitable
as this could result in a slipping clutch during normal operation.
(4) Heavy duty 4-stroke motor cycle oils meet all requirements. These oils are normally no
mineral oils but semi- or full synthetic oils.
(5) Oils primarity for Diesel engines are due to insufficient high temperature properties and
additives which favour clutch slipping, generally unsuitable.
NOTE:
For more information on required lubricants, refer to Rotax Aircraft Engines
Service Information SI-914-019, current issue.
CAUTION:
IF THE ENGINE IS MAINLY RUN ON AVGAS MORE FREQUENT OIL
CHANGES WILL BE REQUIRED. SEE SERVICE INFORMATION SI-914-019,
CURRENT ISSUE.
12-10-00
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STEMME TSA-M
MAINTENANCE MANUAL
C.
Recommended viscosity of oils for air temperature range:
Mean EnvironmentTemperature
Multi -Grade-Oils
-5°C (23 °F) to 40°C (104 °F)
-16°C (3.2 °F) to 40°C (104 °F)
-26°C (-14.8 °F) to 40°C (104 °F)
-30°C (-22 °F) to 40°C (104 °F)
SAE 20W-50
SAE 15W-50
SAE 10W-50
SAE 5W-50
SAE 20W-40
SAE 15W-40
SAE 5W-40
5. Hydraulic Fluid
A.
Only hydraulic fluid of DOT 4 standard should be used.
12-10-00
Page 03
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STEMME TSA-M
MAINTENANCE MANUAL
C.
Recommended viscosity of oils for air temperature range:
Mean EnvironmentTemperature
Multi -Grade-Oils
-5°C (23 °F) to 40°C (104 °F)
-16°C (3.2 °F) to 40°C (104 °F)
-26°C (-14.8 °F) to 40°C (104 °F)
-30°C (-22 °F) to 40°C (104 °F)
SAE 20W-50
SAE 15W-50
SAE 10W-50
SAE 5W-50
SAE 20W-40
SAE 15W-40
SAE 5W-40
5. Hydraulic Fluid
A.
Only hydraulic fluid of DOT 4 standard should be used.
6. Hydraulic Fluid - Hydraulic System Retractable Landing Gear
A.
Only hydraulic fluid of Univis HVI 13 is to be used (product of Exxon Mobile Corporation).
EFFECTIVITY
Model S6-RT
12-10-00
Page 03
May 04/12
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
FUEL - SERVICING
1. General
A.
Fuel Tanks
(1) For fuel storage the S6 is equipped with an integrated wing fuel tank (optional: two).
The fuel tank is placed in the inboard part of the right wing between the leading edge and
the spar. It has a filler cap on the top of the wing.
B.
Drain System
(1) The fuel system is equipped with drain valves to provide a means for the examination of fuel
in the system for contamination and grade or for defueling.
The wing fuel tank has a drain valve at its base. The drain valve is accessible from outside the
bottom of wing in the wing root area.
NOTE:
Chapter 28 "Fuel System" contains information in more detail related to the fuel system.
2. Safety and Maintenance Precautions
A.
Safety Precautions
WARNING:
DURING ALL FUEL SYSTEM SERVICING PROCEDURES, SERVICEABLE FIRE
FIGHTING EQUIPMENT MUST BE AVAILABLE.
AIRCRAFT AND FILLING FURNISHINGS MUST BE GROUNDED.
ALL ELECTRICAL EQUIPMENT OF THE AIRCRAFT SHOULD BE TURNED
OFF. THE ALT / BAT SWITCH SHOULD BE IN „OFF“
POSITION AND THE IGNITION KEY REMOVED FROM THE AIRCRAFT
NO SMOKING
(1) Before beginning, serviceable fire extinguisher (at least foam extinguisher) is to be positioned
and immediately available.
(2) Do not wear clothing that has a tendency to generate static electricity (i.e. synthetic fabrics).
(3) The footwear should have no wear metal tabs.
(4) Perform any fuel system servicing procedure only in a designated fuel loading / unloading
area.
(5) Ground equipment near the aircraft must be turned off.
(6) While filling do not turn on any electrical device.
(7) Pay attention to a proper grounding of aircraft and filling device:
(a) At first ground aircraft;
(b) If a mobile filling device is used. Ground filling device (same potential as aircraft);
(c) Earth/ground mobile filling device with airplane;
12-11-00
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B.
Maintenance Precautions
(1)
(2)
(3)
(4)
Use designated equipment for fuel loading / unloading to prevent contamination.
Only use approved anti-icing additive.
Perform blending of fuel in accordance to prescribed procedures.
Every blending of fuel is to be documented.
3. Fueling and Defueling
A.
Fueling
(1) Move aircraft in a designated fuel loading / fuel unloading area.
(2) Make sure that the ALT / BAT switch is in OFF position.
(3) Ground aircraft and filling device in above described manner.
(4) Open fuel filler cap.
(5) Fuel aircraft. Ensure approved grade of aviation fuel is used.
(6) Close fuel filler cap and check correct lock. Remove excess fuel from wing area using a cloth.
(7) Remove ground cables.
(8) Compare reading of fueled amount on filling device with readings on the fuel indicators in
the aircraft.
B.
Defueling
(1) Move aircraft in a designated fuel loading / fuel unloading area.
(2) Keep ready a sufficiently amount of fuel collectors.
(3) Make sure that the ALT / BAT switch is in OFF position.
(4) Ground aircraft and filling device in above described manner.
(5) Open fuel filler cap.
(6) By means of a defueling nozzle remove as much as possible fuel.
(7) Drain remaining fuel from the fuel tank drain at the bottom of wing.
(8) Make sure all drain valves are closed securely.
(9) Close fuel filler cap.
12-11-00
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ENGINE OIL - SERVICING
1. General
A.
This chapter provides information for checking and changing engine oil.
B.
The oil filler neck is located on the front of the exhaust pipe, accessible from the top. The oil filler
cap has a dipstick.
2. Checking Engine Oil
A.
Oil Checking Procedure (cold engine)
WARNING:
BEFORE CRANKING THE PROPELLER BY HAND MAKE SURE THE MAIN
AND THE IGNITION SWITCHES ARE OFF AND THE IGNITION KEY IS
REMOVED FROM AIRCRAFT.
WARNING:
AVOID SKIN CONTACT WITH ENGINE OIL. ESPECIALLY USED OIL
CONTAINS MATERIALS INJURIOUS TO HEALTH.
(1)
(2)
(3)
(4)
(5)
The aircraft should be in as near a level position as possible.
Open metal exhaust cover on the upper cowling.
Unscrew oil filler cap at the oil-filler neck and withdraw dipstick.
Wipe oil dipstick dry with a cloth.
Turn the propeller by hand in direction of engine rotation several times to pump oil from the
engine into the oil tank.
NOTE:
(6)
(7)
(8)
(9)
(10)
B.
The process is finished when air is returning back to the oil tank and can be noticed
by a murmur from the open oil tank.
Reinsert dipstick.
Withdraw dipstick and read oil level on dipstick.
Refill if necessary aviation grade engine oil with correct viscosity.
Reinsert oil dipstick, close filler cap, check for proper seating.
Close metal exhaust cover.
Oil Checking Procedure (warm engine)
WARNING:
AVOID SKIN CONTACT WITH ENGINE OIL. ESPECIALLY USED OIL
CONTAINS MATERIALS INJURIOUS TO HEALTH.
(1) After engine shut down wait approx. 10 to 15 minutes. The aircraft should be in as near a
level position as possible.
(2) Open metal exhaust cover on the upper cowling.
(3) Unscrew oil filler cap at the oil-filler neck and withdraw dipstick.
(4) Wipe oil dipstick dry with a cloth.
(5) Reinsert dipstick.
12-12-00
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MAINTENANCE MANUAL
(6)
(7)
(8)
(9)
Withdraw dipstick and read oil level on dipstick.
Refill if necessary aviation grade engine oil with correct viscosity.
Reinsert oil dipstick, close filler cap, check for proper seating.
Close metal exhaust cover.
3. Oil Change Intervals
A.
Oil Change Intervals
(1) The TSA-M is delivered with semi- or fully synthetic engine oil (API classification “SG” or
higher!). If it becomes necessary to add oil, engine oil of the same specification and of the
recommended viscosity (Refer to section 12-10-00 and ROTAX Service Information SI-914-019,
latest issue) must be used.
After the first 25 hours of operation, drain engine oil and change oil filter.
(2) For oil and oil filter change intervals, refer to ROTAX Operator's Manual and appropriate
Service Instruction (Lubricating Oil Recommendations), latest issue.
4. Oil Changing
A.
Oil Changing Procedures
(1) Run engine until operating temperature is achieved.
(2) Shut down engine.
WARNING:
HOT ENGINE COMPONENTS MAY CAUSE SKIN BURNS!
(3)
(4)
(5)
(6)
(7)
(8)
Remove upper and lower cowling.
Cut safety wire at drain plug at oil sump. Remove oil drain plug.
Allow oil to drain in a suitable container at least 10 to 15 minutes.
Change external oil filter and safety wire. Check suction oil screen.
Reinstall drain Plug, torque as required and safety wire.
Refill engine oil sump through filler neck using correct grade and quantity of engine oil
(Refer to section 12-10-00).
(9) Reinsert oil dipstick, close filler cap, check for proper seating.
(10) Run engine until normal operating temperature is achieved. Shut down engine.
WARNING:
HOT ENGINE COMPONENTS MAY CAUSE SKIN BURNS!
(11) Check oil system for leaks.
(12) Reinstall cowling.
(13) Document oil change as prescribed.
12-12-00
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INDUCTION AIR FILTER - SERVICING
1. General
A.
The air filter in the air induction system of the S6 keeps dust and dirt particles from entering the
system. It is located in the air filter box at the right side of the main frame. It is accessible after
removal of the lower cowling.
For increase of its effectiveness, the filter element is treated with a wetting agent. This element
has also been treated with a fire retardant.
B.
The condition of the air filter element will be determined primarily by engine operating
conditions. Therefore, it shall be regularly inspected, cleaned and if necessary replaced at least
every 100 hours of operation or every year whichever is the sooner.
2. Air Filter Changing
A.
Air Filter Changing Procedure
(1)
(2)
(3)
(4)
Remove lower cowling.
Remove air filter element by lossing clamping strap and replace by a new one.
Fix air filter element by tightening clamping strap to flange.
Install lower cowling.
3. Air Filter Cleaning
A.
Cleaning Procedures
CAUTION:
DO NOT WASH AND REUSE AIR FILTER ELEMENT.
(1) Remove air filter element as described above.
(2) Clean air filter from coarser dirt particles by blowing with compressed air from direction
opposite of normal airflow.
(3) Ensure air filter box is clean and free off debris.
(4) Install air filter as described above.
12-13-00
Page 301
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A
Air Filter Flange
Air Filter Box
Detail- A
Air Filter Element
Lower Cowling
Induction Air Filter
Figure 301
12-13-00
Page 302
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COOLING SYSTEM - SERVICING
1. General
A.
The cooling system of the ROTAX 914 series engines is designed for liquid cooling of the cylinder
heads and ram air cooling of the cylinders. The cooling system of the cylinder heads is a closed
circuit with an expansions tank. For a more detailed description and related maintenance practice
of the cooling system, refer to 75-20-00.
B.
Coolant
(1) The following type of coolant may be used:
(a) Conventional coolant based on ethylene glycol. The mixture ration should be 50%
antifreeze concentrate with additives against corrosion and 50 % pure water.
(b) For recommended coolants refer to latest Revision of Service Instruction “Selection of
suitable Operating Fluids for ROTAX Engine Type 912 and 914 (Series)”, SI-914-019 by
ROTAX.
(2) The maximum coolant quantity is 3,5 liters (3.7 U.S. quarts).
CAUTION:
ENSURE THAT ONLY ANTIFREEZE CONCENTRATE CONTAINING ADDITIVES
AGAINST CORROSION FOR LIGHT METAL ENGINES IS USED.
USE ANTIFREEZE CONCENTRATE IN ACCORDANCE TO MANUFACTURERS
INSTRUCTIONS.
C.
The coolant must be renewed every two years.
WARNING:
NEVER OPEN PRESSURE CAP OR RADIATOR CAP WHEN THE COOLING SYSTEM
IS HOT. FOR SAFETY'S SAKE, COVER CAP WITH A CLOTH AND OPEN SLOWLY.
SUDDEN OPENING OF THE CAP WOULD PROVOKE EXIT OF BOILING
COOLANT AND RESULT IN SEVERE SCALDS.
2. Adding Coolant
A.
Prior to adding coolant, the reason for the loss of the liquid must be investigated and corrected.
B.
Servicing procedures
(1) Remove engine cowling (refer to 71-10-00).
(2) When engine is cold, open pressure cap of the EXPANSION TANK and verify coolant level,
replenish as required up to top. The max. coolant level must be filled up to the top.
(3) Close pressure cap of EXPANSION TANK, check the conditions of the rubber sealing rings.
(4) Verify coolant level in the OVERFLOW BOTTLE, replenish as required. The coolant level
must be between "max." and "min." mark.
(5) Close cap of OVERFLOW BOTTLE and tighten. Ensure that the plugged vent hose remains
untwisted.
(6) Run engine to operating temperature and allow engine to cool down before checking again
coolant level at EXPANSION TANK and OVERFLOW BOTTLE. Replenish as necessary (refer
to 2 - 5).
(7) Install engine cowling (refer to 71-10-00).
12-14-00
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3. Renewal of the Coolant
A.
Servicing procedures
(1) Open the radiator cap, remove the bottom attachment screw (with sealing ring) of water
pump and drain the coolant.
(2) Install attachment screw (stainless steel) along with a new sealing ring. Tighten to 10 Nm (90
in.lb).
(3) Refill newly mixed coolant into expansion tank (highest point of the cooling System). Install
radiator cap.
(4) Run engine to operating temperature and allow engine to cool down before checking coolant
level. Replenish as necessary.
4. Flushing the Cooling System
A.
Servicing Procedure
(1) Open the lowest located coolant hose (either at water pump or radiator).
(2) Flush system with a water hose at a max. pressure of 2 bar (30 p.s.i.).
(3) Reconnect coolant hose.
(4) Refill newly mixed coolant into the expansion tank.
(5) Run engine to operating temperature and allow engine to cool down before checking coolant
level. Replenish as necessary.
12-14-00
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BRAKE SYSTEM - SERVICING
1. General
A.
B.
Ground service for the brake system is commonly limited to the replenishment of brake fluid. The
hydraulic fluid reservoir is located at the pilot's brake lever or if installed (optionally) at the copilot's brake lever.
After any maintenance at the brake system (component replacement etc.), or in case of non-correct
function of the system because of trapped air, the system must be bled. For the appropriate
procedure, refer to 32-40-00.
2. Hydraulic Fluid Replenishing
A.
Hydraulic Fluid Replenishing
CAUTION:
SERVICE ONLY WITH HYDRAULIC FLUID DOT 4.
(1) Gain access to the hydraulic fluid reservoir.
NOTE:
The hydraulic fluid reservoir is located at the pilot's brake lever or if installed
(optionally) at the co-pilot's brake lever.
(2) Remove filler plug from hydraulic fluid reservoir.
CAUTION: REMOVE EXCESSIVE HYDRAULIC FLUID IMMEDIATELY FROM PAINT
SURFACES TO PREVENT CHEMICAL ATTACK.
(3) Refill hydraulic fluid.
(4) Install filler plug.
12-15-00
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MAINTENANCE MANUAL
TIRES - SERVICING
1. General
A.
The landing gear of the S6 is equipped with tires of size 5.00-5. The required tire pressure is:
(a) Main Gear Tire: 3,5 bar ±
0,1 bar (51.0 ±
1.5 psi)
(b) Nose Gear Tire: 3,5 bar ±
0,2 bar (51.0 ±
3.0 psi)
The regular check of the tire pressure is the most important preventive measure in tire service.
Improper tire pressure causes deterioration in ground handling behavior of the aircraft and
reduces the service life of the tire.
Under pressure is indicated by excessive wear in the tire shoulder area, over pressure by excessive
wear in the center of tire.
2. Tire Servicing
WARNING:
WHILE SERVICING, DO NOT STAND IN ANY POSITION IN FRONT OF EITHER
BEAD AREA OF TIRE BECAUSE BURSTING TIRES HAVE THE TENDENCY TO
RUPTURE ALONG THE BEAD.
ALWAYS STAND AT A 90° ANGLE TO THE AXLE ALONG THE TIRE CENTERLINE.
A.
Service Notes
(1) If possible, do not expose the tires permanently to intensive solar radiation.
(2) Ensure tire pressure gages used are accurate.
(3) While checking tire pressure, the aircraft should be on a regular basis and the tire should be
cold.
(4) A freshly mounted and installed tube-type tire should be closely monitored during the first
time of operation. Air trapped between the tire and the tube at the time of mounting could
seep out, resulting in an under inflated tire.
B.
The tire service contains the following items:
(1) Check tire pressure regularly. If necessary inflate or drain air.
(2) Examine tires for wear, cuts, bruises, and foreign bodies in the tread.
(3) Check proper location of the red slide marks.
(4) Always remove oil, grease and mud from tires with soap and water.
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BATTERY - SERVICING
1. General
A.
No battery service is required, the battery is maintenance-free.
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SCHEDULED SERVICING - DESCRIPTION
1. General
A.
This section provides instructions necessary to carry out servicing that may be scheduled. It
includes instructions such as those for periodic lubrication of aircraft components; external and
internal cleaning. Intervals for such services are provided. This section does not include
lubrication procedures required for the accomplishment of maintenance practices.
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MAINTENANCE MANUAL
LUBRICANTS - DESCRIPTION
1. General
A.
This section should assist during the selection of the correct lubricants, which are used while
maintaining the S6.
For long faultless function of the components to be lubricated, it is recommended to use always
pure and authorized lubricants.
2. Service Notes
A.
Use of the lubricants
(1) Cleanliness is essential to good lubrication. Lubricants and required equipment must be kept
clean.
(2) Store the lubricants in accordance with the manufacturer's specifications and secure.
(3) Wipe grease fittings and areas to be lubricated with clean dry cloths before lubricating.
(4) When lubricating bearings, which are vented, force grease into fitting until old grease is
extruded. This is then to be removed.
(5) Chains and control cables are not to be lubricated unless to prevent corrosion.
3. Definition of "As Needed"
A.
In the following sections, time requirements for lubrication are shown either by a specific time
interval or by „As Needed“. Later means that no interval is determined for this item. The
mechanic himself must make the decision when lubrication is required.
B.
One or several simultaneously of the following conditions would indicate a need for lubrication:
(1) The old lubricant is removed.
(2) Dirt or wear residue are visible near the movement contact area.
(3) While moving squeaks, grinding or other abnormal sounds are audible.
(4) During the movement by the hand, jerky or restricted movement occurs throughout portions
of travel range.
4. Recommended Lubricants:
A.
Categories of lubricants, its specification and typical areas of application are provides subsequent.
Abbreviation
Specification
Description
GR
MIL-PRF-81322F
Grease, wide temperature range
OG
MIL-PRF-7870C
Oil, general purpose
PL
VV-P-236A
Technical Petrolatum
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PG
SS-G-659A
Powdered Graphite
GL
MIL-G-21164D
High and Low Temperature Grease
OL
MIL-PRF-32033
Light Oil
B.
For suitable lubricants refer to Illustrated Parts Catalog STEMME S6 (P530-901.500, latest Revision).
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LUBRICATION - SERVICING
1. General
A.
This section contains information on lubrication intervals for components or parts of the S6.
2. Lubrication Chart
A.
Figure 301 shows the location of components or parts to be regularly lubricated.
The following chart contains detailed information about the lubrication interval, the
recommended lubricant and the dispensing equipment for several components to be lubricated.
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G
B
F
B
D
A
K
C E
J
D
F
L
B
G
B
Lubrication Chart
Figure 301
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INDEX
A
ZONE
ACCESS
PLATE
100
ITEM
LUBE TYPE (APPL.)
Seat Rails and Stop Mechanism
INTERVAL
as needed
OG (Oil Can)
A
A
INDEX
ZONE
B
520
620
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Aileron Push Rod End Bearings
PG (Syringe)
INTERVAL
as needed
B
Note:
Aileron components omitted for clarity.
EFFECTIVITY
001 - 010
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INDEX
ZONE
C
200
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Battery Terminals
PL (Hand)
INTERVAL
as needed
annual
C
C
INDEX
ZONE
D
510
610
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Flap Push Rod End Bearings
PG (Syringe)
INTERVAL
as needed
D
Note:
Flap components omitted for clarity.
EFFECTIVITY
001 - 010
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INDEX
A
ZONE
ACCESS
PLATE
100
ITEM
LUBE TYPE (APPL.)
Lower Bearing of Seat Backrest
(Bushing of Mounting Axle)
INTERVAL
as needed
GR (Hand)
Note:
Coat seat rails with Teflon and slide backrest
along full range of adjustment several times.
Clean seat rails afterwards to prevent clothing
of occupants to get in contact with lubricants.
A
A
INDEX
ZONE
B
520
620
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Aileron Push Rod End Bearings
PG (Syringe)
INTERVAL
as needed
B
Note:
Aileron components omitted for clarity.
EFFECTIVITY
011 - 999
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INDEX
ZONE
C
200
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Battery Terminals
PL (Hand)
INTERVAL
as needed
annual
C
C
INDEX
ZONE
D
510
610
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Flap Push Rod End Bearings
PG (Syringe)
INTERVAL
as needed
D
Note:
Flap components omitted for clarity.
EFFECTIVITY
011 - 999
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INDEX
ZONE
E
200
INDEX
ZONE
F
510
610
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Wing / Mainframe Attachment
Bolts
ACCESS
PLATE
ITEM
any rigging/
de-rigging of A/C
annual
GR (Hand)
LUBE TYPE (APPL.)
Inner / Outer Wing Bolt
Front / Aft Shear Force Fitting
GR (Hand)
INTERVAL
INTERVAL
any rigging/
de-rigging of A/C
annual
F
F
F
Detail- F
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INDEX
ZONE
G
520
620
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Outer Wing / Winglet Bolt
Front / Aft Shear Force Fitting
INTERVAL
any rigging/
de-rigging of A/C
annual
GR (Hand)
G
G
G
Detail- G
INDEX
ZONE
H
200
ACCESS
PLATE
200EB
ITEM
LUBE TYPE (APPL.)
OL
Cowl Flap Hinges and
Actuation (all Hinges)
INTERVAL
as needed
annual
H
H
H
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INDEX
I
ZONE
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Canopy Locking Bolts
(incl. ROEGER-Hook)
100
GR
INTERVAL
as needed
I
I
I
INDEX
ZONE
J
300
330
I
I
I
ACCESS
PLATE
ITEM
I
LUBE TYPE (APPL.)
Horizontal Tail Fittings
GR
INTERVAL
any rigging/
de-rigging of A/C
annual
J
J
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INDEX
ZONE
K
100
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Rudder Control System:
Rudder Pedal Axles
INTERVAL
annual
GR
K
K
INDEX
ZONE
L
300
330
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Elevator Control System:
Connection fork Elevator Control
GR
INTERVAL
as needed
L
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INDEX
ZONE
M
200
300
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Elevator Control System:
all Roller Bearings
INTERVAL
as needed
GR
M
M
M
M
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INDEX
ZONE
N
100
510
610
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Aileron Control System:
- all Roller Bearings,
- connection wing intersection
INTERVAL
any rigging/
de-rigging of A/C
as needed
GR
N
any rigging/
de-rigging of A/C
as needed
N
N
as needed
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INDEX
ZONE
O
510
610
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Flap Control System:
refer to index no. D
O
PG (Syringe)
INTERVAL
as needed
Refer to index no. D.
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INDEX
ZONE
P
200
510
610
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Airbrake Control System:
- all Roller Bearings,
- connection wing intersection
P
GR
INTERVAL
any rigging/
de-rigging of A/C
as needed
any rigging/
de-rigging of A/C
3 Roller bearings:
as needed
P
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INDEX
ZONE
A
300
ACCESS
PLATE
ITEM
LUBE TYPE (APPL.)
Aerotow Release Clutch:
refer to Operating Manual Tail
Hook E22, Tost Company
Refer to OM
E22, Tost
INTERVAL
Refer to OM
E22, Tost
A
A
A
EFFECTIVITY
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MAINTENANCE MANUAL
INDEX
ZONE
A
100
200
ACCESS
PLATE
100CB
200CL/
200DR
ITEM
LUBE TYPE (APPL.)
OG (Oil Can)
All Landing Gear Door Hinges
(Main and Nose L/G)
INTERVAL
as needed
A
A
A
EFFECTIVITY
Model S6-RT
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MAINTENANCE MANUAL
AIRCRAFT EXTERIOR - CLEANING AND CARE
1. General
A.
The good flight performance of the S6 is achieved because of the modern construction and use of
specific materials. For efficient laminar flow, a clean surface is very important. Therefore, one
should always keep the entire aircraft clean especially the leading edges of the wing.
B.
Information on preventive measures on protection such as waxing specific surfaces is also given.
2. Safety Precautions
A.
B.
C.
D.
E.
Read and adhere to all manufacturers instructions, warnings and cautions on the cleaning/solvent
compounds used.
Do not use silicone-based wax to polish the aircraft exterior.
Do not clean aircraft at ambient temperatures close to 0°C (32°F) or below with water.
Cover all lubricated parts during any cleaning procedure.
During any application of cleaners (e.g. cleaning the engine) containing solvent, the other surfaces
are to be covered carefully or to be equipped with other protection.
3. Cleaning and Care of the Canopy
CAUTION:
NEVER USE GASOLINE, BENZENE, ALCOHOL, ACETONE, CARBON
TETRACHLORIDE, AND LACQUER THINNER OR GLASS CLEANER. THESE
MATERIALS WILL SOFTEN THE PLASTIC AND MAY CAUSE IT TO CRAZE.
CAUTION:
DO NOT USE CLEANERS WITH SUCH CHEMICAL SUPPLEMENTS WHOSE
EFFECT IS UNKNOWN ONTO THE WINDOWS SURFACE.
A.
Cleaning Canopy
(1) Park the aircraft in a hangar or in the shadows, avoid places with a lot of dust caused by wind
or vehicles.
(2) To prevent scratches, wash the windows carefully with plenty of mild soap and water
solution, using the palm of the hand to feel and dislodge dirt and mud.
A soft cloth, chamois leather or sponge should be used.
(3) Rinse thoroughly and then dry with a clean moist chamois.
(4) Remove oil and grease with a cloth moistened with isopropyl alcohol.
B.
Care of the Canopy
(1) As protection from mechanical and chemical actions and to cover of lightweight cuts on the
windows, a polish or a wax for acrylic glass can be applied in accordance with the
manufacturer's specifications.
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NOTE:
Before application of polish or wax, the surfaces are to be cleaned.
4. Cleaning and Care of the Aircraft Exterior Surfaces
A.
Procedure for cleaning the aircraft exterior surface
(1) Park the aircraft in a hangar or in the shadows, avoid places with a lot of dust caused by wind
or vehicles.
(2) Close canopy, if open, close access / inspection plates.
CAUTION
KEEP WATER AWAY FROM PITOT AND STATIC PORTS, ELECTRICAL AND
AVIONICS EQUIPMENT.
(3) Flush away loose dirt with water.
CAUTION:
DO NOT USE HARSH ABRASIVES, ALKALINE SOAPS OR DETERGENTS.
(4) Using a soft cleaning cloth or a sponge, wash with a mild, non-alkaline soap and water
solution.
(5) Rinse thoroughly with clean water and then dry with a soft cloth or chamois.
B.
Care of the Aircraft Exterior Surface
(1) To protect against corrosion, mechanical and chemical actions during operation, the exterior
surfaces can be waxed with a good commercially available polish or wax for aircraft's in
accordance with the manufacturer's instructions.
NOTE: Before application of wax or polish, the aircraft exterior surface is to be cleaned.
(2) After using cleaners containing any solvent or chemical, the appropriate surfaces should be
always waxed.
(3) If the aircraft is operated in a seacoast area or other salt-water environment, it must be
washed and waxed more frequently.
(4) A heavier wax layer on the leading edges of the wings and tail and on the cowl nose and
propeller spinner will reduce the abrasion encountered in these areas.
5. Cleaning Engine
A.
Safety and Maintenance Precautions
(1) Engine cleaning should be carried out during each 100-hour inspection.
(2) Handle chemical cleaners and solvents cautiously. Read and follow carefully the
manufacturer's instructions.
(3) The cleaning should be performed in the open air or rooms ventilated well.
(4) Suitable fire fighting and safety equipment should be available.
(5) Compressed air, if used to apply solvent or to dry components, should be adjusted to lowest
practical pressure.
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B.
Cleaning Engine Procedures
WARNING:
DO NOT SMOKE OR EXPOSE A FLAME WITHIN 100 FEET OF THE CLEANING
AREA.
(1) Remove Cowlings.
WARNING:
DO NOT USE GASOLINE OR OTHER HIGHLY FLAMMABLE SUBSTANCES.
DO NOT ATTEMPT TO WASH AN ENGINE WHEN IT IS STILL HOT OR
RUNNING.
(2) Carefully cover openings of electrical accessories e.g. of the alternator or the starter as
required.
(3) If engine is contaminated with salt or corrosive chemicals, first flush engine compartment
with water.
(4) Apply a suitable solvent or cleaning agent to the engine compartment in accordance with
(5) Allow the solvent to remain on the engine approx. ten minutes.
CAUTION:
(6)
(7)
(8)
(9)
(10)
CLEANING AGENTS SHOULD NEVER BE LEFT IN ENGINE COMPARTMENT.
REMAINS OF CLEANER OR SOLVENT MAY CAUSE DAMAGE TO
COMPONENTS SUCH AS NEOPRENE SEALS AND SILICONE FIRE SLEEVES.
Thoroughly rinse with clean warm water.
Allow engine to dry or dry it completely using compressed air.
Remove all coverings positioned to protection while cleaning.
Relubricate all control arms and moving parts as required.
Reinstall cowling.
WARNING:
DO NOT OPERATE THE ENGINE UNTIL EXCESS SOLVENT HAS
EVAPORATED OR OTHERWISE BEEN REMOVED.
BEFORE ROTATING THE PROPELLER BY HAND, ENSURE IGNITION SWITCH
IS OFF, MIXTURE CONTROL IS IN THE IDLE CUT-OFF POSITION, AND THE
THROTTLE IS CLOSED.
(11) Before starting engine, rotate the propeller by hand no less than five complete revolutions.
6. Cleaning and Care of the Propeller
A.
Clean propeller if necessary with any car wash solution or equivalent, but at least every 50 hours.
Remove grease and dirt with a commercial detergent, which is suitable for polyurethane-lacquers.
Small scratches and nicks should be protected during routine maintenance with a coating of water
resistant lacquer, preferably Polyurethane.
In time replace damaged or missing PU strip on the propeller leading edge.
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7. Cleaning Landing Gear
A.
The landing gear struts and wheel fairings are to be washed with clear water or with a mild soap
and water.
B.
After cleaning, the tires can be treated with a standard tire protective.
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B.
Cleaning Engine Procedures
WARNING:
DO NOT SMOKE OR EXPOSE A FLAME WITHIN 100 FEET OF THE CLEANING
AREA.
(1) Remove Cowlings.
WARNING:
DO NOT USE GASOLINE OR OTHER HIGHLY FLAMMABLE SUBSTANCES.
DO NOT ATTEMPT TO WASH AN ENGINE WHEN IT IS STILL HOT OR
RUNNING.
(2) Carefully cover openings of electrical accessories e.g. of the alternator or the starter as
required.
(3) If engine is contaminated with salt or corrosive chemicals, first flush engine compartment
with water.
(4) Apply a suitable solvent or cleaning agent to the engine compartment in accordance with
(5) Allow the solvent to remain on the engine approx. ten minutes.
CAUTION:
(6)
(7)
(8)
(9)
(10)
CLEANING AGENTS SHOULD NEVER BE LEFT IN ENGINE COMPARTMENT.
REMAINS OF CLEANER OR SOLVENT MAY CAUSE DAMAGE TO
COMPONENTS SUCH AS NEOPRENE SEALS AND SILICONE FIRE SLEEVES.
Thoroughly rinse with clean warm water.
Allow engine to dry or dry it completely using compressed air.
Remove all coverings positioned to protection while cleaning.
Relubricate all control arms and moving parts as required.
Reinstall cowling.
WARNING:
DO NOT OPERATE THE ENGINE UNTIL EXCESS SOLVENT HAS
EVAPORATED OR OTHERWISE BEEN REMOVED.
BEFORE ROTATING THE PROPELLER BY HAND, ENSURE IGNITION SWITCH
IS OFF, MIXTURE CONTROL IS IN THE IDLE CUT-OFF POSITION, AND THE
THROTTLE IS CLOSED.
(11) Before starting engine, rotate the propeller by hand no less than five complete revolutions.
6. Cleaning and Care of the Propeller
A.
Clean propeller if necessary with any car wash solution or equivalent, but at least every 50 hours.
Remove grease and dirt with a commercial detergent, which is suitable for polyurethane-lacquers.
Small scratches and nicks should be protected during routine maintenance with a coating of water
resistant lacquer, preferably Polyurethane.
In time replace damaged or missing PU strip on the propeller leading edge.
EFFECTIVITY
Model S6-RT
12-23-00
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7.
Cleaning Landing Gear
A.
The landing gear struts and wheel fairings are to be washed with clear water or with a mild soap
and water.
For Aircraft equipped with retractable landing gear:
A.
The landing gear struts as well as the retracting mechanism are to be washed with clear water or
with a mild soap and water. After washing the hydraulic cylinder rods must be dried.
NOTE:
B.
No residual water or soap may remain on the surface of the hydraulic cylinder rods.
After cleaning, the tires can be treated with a standard tire protective.
EFFECTIVITY
Model S6-RT
12-23-00
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AIRCRAFT INTERIOR - CLEANING AND CARE
1. General
A.
This section provides the necessary information to clean the aircraft interior properly. Several
recommended types of cleaning agents for different materials and the respective cleaning and
care procedures are contained herein.
2. Aircraft Interior Cleaning
A.
Interior panels such as sidewall panels or middle console may be cleaned using a mild detergent
solution. Stubborn deposits may be removed using a suitable material cleaner in accordance with
manufacturer's instructions. If in doubt, apply a small amount of cleaner to a small unobtrusive
part and test it for reaction.
3. Cleaning Instrument Panel
A.
The instrument panel and center pedestal can be wiped with a slightly moistened cloth. Ensure
the ALT / BAT switch is in OFF position. Put electrical systems and components of the aircraft into
operation only after complete drying the instrument panel.
4. Cleaning Cabin Floor
A.
The feet area, the area under the seats and the baggage compartment should be cleaned regularly
with a vacuum.
B.
The carpet consists of high-quality, dirt repelling material and usually demands only a minimum
of maintenance. If it becomes soiled, a standard carpet cleaner can be used.
5. Cleaning Seats
A.
The seat upholstery consists of a dirt repelling, hardwearing material. Even they should be
cleaned regularly to keep them in good condition. The following recommends should be
considered.
B.
To remove dust and loose dirt from seats, clean first with a vacuum.
For cleaning and care use foam type detergent, such as commercial available for car seats. Follow
the manufacturer's instructions.
C.
Blot up any spilled liquid promptly with an absorbent tissue or cloth. Press the blotting material
firmly and hold it for several seconds. Continue blotting until no more liquid is taken up.
Scrape off sticky materials cautiously with a dull knife, then clean area as required.
Oil spots may be removed with household spot removers. Before using, read the instructions on
the container, test it on an obscure place on the seat and use it sparingly.
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STEMME TSA-M
MAINTENANCE MANUAL
HYDRAULIC FLUID SERVICING
1. General
A.
This section provides instructions necessary to carry out servicing on the hydraulic system of the
retractable landing gear.
2. Replenish Hydraulic Fluid
A.
For replenishing hydraulic fluid, refer to 32-30-00.
3. Change Hydraulic Fluid
A.
For changing hydraulic fluid, refer to 32-30-00.
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UNSCHEDULED SERVICING
1. General
A.
This section contains those instructions necessary to carry out servicing that is considered by the
manufacturer to be normally unscheduled for example: for ice and snow removal from a parked
aircraft.
2. Removing Snow and Ice
CAUTION:
DO NOT ELIMINATE SNOW AND ICE ON SURFACES USING PEAKED AND
SHARP-EDGED INSTRUMENTS.
A.
After snowfall, the snow should be removed immediately from the surface of the aircraft to
prevent that after a thawing period the snow water freezes on the surface and/or in slits or gaps
again.
B.
Procedure
WARNING:
IF USING A LADDER, PAY PARTICULAR ATTENTION TO ITS STABILITY.
CAUTION:
DO NOT DAMAGE THE STALL WARNING SENSOR AND ACCESS FOR PITOT
STATIC TUBE ON LEFT INNER WING.
(1) Remove loose snow with a whiskbroom from the wing surface working outwards from the
wing root.
NOTE:
The areas between wings and ailerons and stabilizers and rudders are to be
treated especially carefully.
CAUTION: DO NOT DAMAGE THE ANTENNAE.
(2) Free cabin of snow.
(3) Remove snow from cowling, fuselage and empennage.
C.
In the case of ice, defrosting in a heated hangar is recommended.
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CHAPTER 20
STANDARD PRACTICES - AIRFRAME
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page
STANDARD PRACTICES AIRFRAME - GENERAL.....................................20-00-00
Introduction
20-00-00
General Description
20-00-00
1
1
1
FASTENER IDENTIFICATION AND TORQUE DATA ...............................20-10-00
General
20-10-00
Bolt Types
20-10-00
Torques
20-10-00
1
1
1
1
CONVERSION DATA.......................................................................................20-11-00
General
20-11-00
Conversion Factors
20-11-00
Standard Equivalents
20-11-00
1
1
1
3
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STEMME TSA-M
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STANDARD PRACTICES: AIRFRAME - GENERAL
1. Introduction
A.
This chapter describes standard maintenance practices applicable to the entire airframe and
related systems.
Maintenance procedures which are unique to a specific system / component / part are described in
the corresponding chapter.
B.
Within the maintenance of the S6, there are no standard practices or relevant safety regulations,
which require special knowledge other than that which is commonly expected for maintenance of
small aircraft. Therefore, this chapter should be particularly a location to refer for required
conversion data.
A.
Section 20-00-00 - Standard Practices Airframe - General. This section provides a general overview
of content and purpose of the chapter.
B.
Section 20-10-00 - Conversion Data. This section provides various formulae and tables for
converting metric and English measurements.
20-00-00
Page 01
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
FASTENER IDENTIFICATION AND TORQUE DATA
1. General
A.
This section contains information on the identification of bolts, on the correct usage of bolts and nuts, and
torque data.
CAUTION:
OBSERVE STANDARD OR RECOMMENDED BY THE MANUFACTURER
TORQUE VALUE AND THE INSTALLATION OF THE RECOMMENDED
SAFETYING DEVICE FOR EVERY FASTENER.
2. Bolt Types
A.
The bolts used in the S6 are of DIN 931 (ISO 4014) and LN 9037 metric specifications. They can be
identified by code marking(s) on the bolt heads. These markings generally denote the material of which the
bolt is made, whether the bolt is a standard type or a special purpose bolt, and sometimes include the
manufacturer.
Bolt heads marked with “x” indicate
a non-corrosion resistant steel bolt.
AN-BOLT
Surface
Cadmium Plated
Bolt heads marked with a dash indicate
a corrosion resistant steel bolt.
DIN-BOLT
Zink Coated
VEB
Manufacturer
10.6
Property Class
Typical Aircraft Bolt Markings
Figure 01
3. Torques
NOTE: When a specific torque is not provided in the maintenance instructions contained in this Maintenance
Manual, use the standard torque patterns shown in tables 01 thru 03.
A.
A correct torque application is very important. Undertorque can result in unnecessary wear of nuts and
bolts, as well as the parts they secure. Overtorque can cause failure of a bolt or nut from overstressing the
threaded areas. Uneven or additional loads that are applied to the assembly may result in wear or premature
failure. To ensure that correct torque is applied, observe the following:
(1) Be sure that the torque applied is for the size of the bolt shank not the wrench size.
(2) Calibrate the torque wrench at least once a year, or immediately after it has been abused or dropped, to
ensure continued accuracy.
(3) Be sure the bolt and nut threads are clean and dry, unless otherwise specified by the manufacturer.
(4) Run the nut down to near contact with the washer or bearing surface and check the friction drag torque
required to turn the nut. Whenever possible, apply the torque to the nut and not the bolt. This will
reduce rotation of the bolt in the hole and reduce wear.
20-10-00
Page 01
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
(5) Add the friction drag torque to the desired torque. This is referred to as "final torque," which should
register on the indicator or setting for a snap-over type torque wrench.
(6) Apply a smooth even pull when applying torque pressure. If chattering or a jerking motion occurs
during final torque, back off the nut and retorque.
(7) Many applications of bolts in aircraft/engines require stretch checks prior to reuse. This requirement is
due primarily to bolt stretching caused by overtorquing.
(8) When installing a castle nut, start alignment with the cotter pin hole at the minimum recommended
torque plus friction drag torque.
(9) Do not exceed the maximum torque plus the friction drag. If the hole and nut castellation do not align,
change washer or nut and try again. Exceeding the maximum recommended torque is not
recommended.
(10) When torque is applied to bolt heads or capscrews, apply the recommended torque plus friction drag
torque.
(11) If special adapters are used which will change the effective length of the torque wrench, the final
torque indication or wrench setting must be adjusted accordingly. Determine the torque wrench
indication or setting with adapter installed as shown in Figure 02.
B.
Tables 01 thru 03 show the recommended torque to be used when the manufacturer within the maintenance
procedures does not supply other specific torque.
Table 01:
Table 02:
Standard torques
Metric thread
M4
M5
M6
M8
M10
M12
Torque (Nm)
2,8
5,5
9,5
23
46
79
Torque (lb.ft)
2,1
4,1
7,0
17,0
33,9
58,3
Reduced torques for:
- Flight control system
- Composite parts
- in case of flat nuts, cage nuts, riveting nuts
Table 03:
Metric thread
M4
M5
M6
M8
M10
M12
Torque (Nm)
1,8
3,6
6,4
16
32,0
60,0
Torque (lb.ft)
1,3
2,7
4,7
11,8
23,6
44,3
Special torques
Torque
Part
Nm
Lb.ft
Rotax© IPC
Rotax© IPC
45 - 47
33 - 35
Oil cooler drain screw, Oil cooler fittings
25
18,5
Flight control pushrod heads: counter nuts DIN 439-M8
7,5
5,5
Flight control bell cranks: nuts on bolts 090.378/ 090.377 at wing center
46
33,9
Flight control: nuts on bolts LN 9037-10086 at inner wing left/ right mixer
36
26,5
Rotax© engine original screws
MT-Propeller© original nuts for propeller fixture
20-10-00
Page 02
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
1. Variant - The adapter will increase the effective length of the torque wrench.
Adapter Drive Centerline
Handgrip Centerline
Wrench Drive Centerline
E
Y
T
L
E
=
=
=
=
L
Apparent (indicated) Torque
Actual (Desired) Torque
Effective Length Leverl
Effective Length of Extension
Example:
T
L
Y
E
=
=
=
=
Formula:
14 Nm
30 cm
?
8 cm
Y=
T x L =Y
L+E
14 Nm x 0,3 m
4,2 Nm
=11,05 Nm
=
0,38
0,3 m + 0,08 m
2. Variant - The adapter will decrease the effective length of the torque wrench.
Wrench Drive Centerline
Handgrip Centerline
Adapter Drive Centerline
E
L
Formula:
Example:
T
L
Y
E
=
=
=
=
14 Nm
30 cm
?
8 cm
Y=
TxL
L-E
14 Nm x 0,3 m
0,3 m - 0,08 m
=Y
=
4,2 Nm
=19,09 Nm
0,22
Torque Wrench with Various Adapters
Figure 02
20-10-00
Page 03
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
CONVERSION DATA
1. General
A.
This chapter is designed to assist the operator to convert commonly used measuring
units found in this manual from imperial, and metric measuring systems.
B.
The tables with computed values are for the fast consulting by the user. The conversion
factors provide the possibility to carry out further conversions.
C
Equivalents are given for standard values.
2. Conversion factors
A.
Subsequent conversion factors of units of measurement are given from the metric system
to the American / British systems and vice versa.
(1) Distance and Length
Tab. 1 - Conversion of Distances and Length
Unit:
m
in.
ft.
yd
1 Meter; m
1 Inch; in. (")
1 Foot; ft. (')
1 Yard; yd.
1
0,0254
0,3048
0,914
39,37
1
12
36
3,281
0,083
1
3
1,09
0,02
0,33
1
Statute Mile = 1.609 Kilometer, Nautical Mile=1.852 Kilometer
NOTE:
For computed values from mm in inch refer to Fig. 1
(2) Square Measures
Tab. 2 Conversion of Square Measures
2
Unit
cm
1 cm2
2
1m
1 sq. in.
1 sq. ft.
1 sq. yd.
1
10000
6,452
929
8361
m
2
0,0001
1
0,00064516
0,092903
0,836127
Sq. in.
Sq. ft.
Sq. yd.
0,155
1550
1
144
1296
0,00108
10,764
0,006944
1
9
0,0001196
1,196
0,0007716
0,111111
1
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Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
(3) Cubic Measures
Tab. 3 - Conversion of Cubic Measures
Unit
l
m3
Cu. in.
Cu. ft.
Imp.-Gallons U.S.-Gallons
1 Liter
1 m3
1 cu. in.
1 cu. ft.
1 Imp.-Gallon
1 U.S.-Gallon*
1 U.S.-Quart
1
1000
0,01639
28,32
4,546
3,785
0,9463
0,001
1
0,00001639
0,028317
0,004546
0,003785
61,03
61023
1
1728
277,4
231
0,05332
35,315
0,0005787
1
0,160545
0,133183
0,22
219,97
0,003601
6,228783
1
0,832667
0,2642
264,175
0,004329
7,480519
1,20096
1
4
*= Liquid
(3) Surface loads
1 pound by
Square inch
= 1 psi.
1 kilopound by
Square inch = 1 kipsi
1 AT
= 1 lb./in.2
= 0,0703
= 1kip. /in.2
= 70,3100 kp/cm2 = 689,7411 N/cm2
= 14,7 lbs./in.2 = 1,0335
kp/cm2
kp/cm2 = 0,6896
= 10,1386
N/cm2
N/cm2
(4) Weights
1 ounce
1 pound
= 1 octane number.
= 1 lb.
= 16 octane numbers.
= 28,3495g
= 453,5920g
(5) Moments
1 pound inch
1 pound foot
NOTE:
= 1 lb. ft.
= 1 lb. In
= 12 lb. In.
= 0,01152 kpm
= 0,13825 kpm
= 0,11301 Nm
= 1,35623 Nm
For computed values from kpm to pound inch and Nm and vice versa refer
to Fig. 2.
(6) Temperature
1. Temp. Centigrade
2. Temp. Fahrenheit
NOTE:
= 5/9 (Temp. Fahrenheit -32)
= 9/5 (Temp. centigrade +32)
For converted values C° into °F and vice versa, refer to Fig. 3.
In this table read known temperature in center column (°C or °F) and then
read left column to convert to °C or right column to convert into °F.
20-11-00
Page 02
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
3. Equivalents for standard values
A.
For conversion data for converting standard drill sizes to inch and millimeter equivalents refer to
Fig. 4.
20-11-00
Page 03
Nov 18/11
0
0,00000
0,00394
0,00787
0,01181
0,01575
0,01969
0,02362
0,02756
0,03150
0,03543
0,0
0,00000
0,03937
0,07874
0,11811
0,15748
0,19685
0,23622
0,27559
0,31496
0,35433
0,39370
0,43307
0,47244
0,51181
0,55118
0,59055
0,62992
0,66929
0,70866
0,74803
mm
0
0,1
0,2
0,3
0,4
0,5
0,6
0,7
0,8
0,9
mm
0
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
0,39764
0,43701
0,47638
0,51575
0,55512
0,59449
0,63386
0,67323
0,71260
0,75197
0,00394
0,04331
0,08268
0,12205
0,16142
0,20079
0,24016
0,27953
0,31890
0,35827
0,1
0,00039
0,00433
0,00827
0,01220
0,01614
0,02008
0,02402
0,02795
0,03189
0,03583
0,01
0,40157
0,44094
0,48031
0,51969
0,55906
0,59843
0,63780
0,67717
0,71654
0,75591
0,00787
0,04724
0,08661
0,12598
0,16535
0,20472
0,24409
0,28346
0,32283
0,36220
0,2
0,00079
0,00472
0,00866
0,01260
0,01654
0,02047
0,02441
0,02835
0,03228
0,03622
0,02
0,40551
0,44488
0,48425
0,52362
0,56299
0,60236
0,64173
0,68110
0,72047
0,75984
0,01181
0,05118
0,09055
0,12992
0,16929
0,20866
0,24803
0,28740
0,32677
0,36614
0,3
0,00118
0,00512
0,00906
0,01299
0,01693
0,02087
0,02480
0,02874
0,03268
0,03661
0,03
0,40945
0,44882
0,48819
0,52756
0,56693
0,60630
0,64567
0,68504
0,72441
0,76378
0,01575
0,05512
0,09449
0,13386
0,17323
0,21260
0,25197
0,29134
0,33071
0,37008
0,4
0,00157
0,00551
0,00945
0,01339
0,01732
0,02126
0,02520
0,02913
0,03307
0,03701
0,04
0,41339
0,45276
0,49213
0,53150
0,57087
0,61024
0,64961
0,68898
0,72835
0,76772
0,01969
0,05906
0,09843
0,13780
0,17717
0,21654
0,25591
0,29528
0,33465
0,37402
0,5
0,00197
0,00591
0,00984
0,01378
0,01772
0,02165
0,02559
0,02953
0,03346
0,03740
0,05
0,41732
0,45669
0,49606
0,53543
0,57480
0,61417
0,65354
0,69291
0,73228
0,77165
0,02362
0,06299
0,10236
0,14173
0,18110
0,22047
0,25984
0,29921
0,33858
0,37795
0,6
0,00236
0,00630
0,01024
0,01417
0,01811
0,02205
0,02598
0,02992
0,03386
0,03780
0,06
0,42126
0,46063
0,50000
0,53937
0,57874
0,61811
0,65748
0,69685
0,73622
0,77559
0,02756
0,06693
0,10630
0,14567
0,18504
0,22441
0,26378
0,30315
0,34252
0,38189
0,7
0,00276
0,00669
0,01063
0,01457
0,01850
0,02244
0,02638
0,03031
0,03425
0,03819
0,07
0,42520
0,46457
0,50394
0,54331
0,58268
0,62205
0,66142
0,70079
0,74016
0,77953
0,03150
0,07087
0,11024
0,14961
0,18898
0,22835
0,26772
0,30709
0,34646
0,38583
0,8
0,00315
0,00709
0,01102
0,01496
0,01890
0,02283
0,02677
0,03071
0,03465
0,03858
0,08
0,42913
0,46850
0,50787
0,54724
0,58661
0,62598
0,66535
0,70472
0,74409
0,78346
0,03543
0,07480
0,11417
0,15354
0,19291
0,23228
0,27165
0,31102
0,35039
0,38976
0,9
0,00354
0,00748
0,01142
0,01535
0,01929
0,02323
0,02717
0,03110
0,03504
0,03898
0,09
STEMME TSA-M
MAINTENANCE MANUAL
Millimeter to Inches
Figure 1, Sheet 1.
20-11-00
Page 04
Nov 18/11
0,0
0,78740
0,82677
0,86614
0,90551
0,94488
0,98425
1,02362
1,06299
1,10236
1,14173
1,18110
1,22047
1,25984
1,29921
1,33858
1,37795
1,41732
1,45669
1,49606
1,53543
1,57480
1,61417
1,65354
1,69291
1,73228
1,77165
1,81102
1,85039
1,88976
1,92913
1,96850
mm
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
1,57874
1,61811
1,65748
1,69685
1,73622
1,77559
1,81496
1,85433
1,89370
1,93307
1,97244
1,18504
1,22441
1,26378
1,30315
1,34252
1,38189
1,42126
1,46063
1,50000
1,53937
0,79134
0,83071
0,87008
0,90945
0,94882
0,98819
1,02756
1,06693
1,10630
1,14567
0,1
1,58268
1,62205
1,66142
1,70079
1,74016
1,77953
1,81890
1,85827
1,89764
1,93701
1,97638
1,18898
1,22835
1,26772
1,30709
1,34646
1,38583
1,42520
1,46457
1,50394
1,54331
0,79528
0,83465
0,87402
0,91339
0,95276
0,99213
1,03150
1,07087
1,11024
1,14961
0,2
1,58661
1,62598
1,66535
1,70472
1,74409
1,78346
1,82283
1,86220
1,90157
1,94094
1,98031
1,19291
1,23228
1,27165
1,31102
1,35039
1,38976
1,42913
1,46850
1,50787
1,54724
0,79921
0,83858
0,87795
0,91732
0,95669
0,99606
1,03543
1,07480
1,11417
1,15354
0,3
1,59055
1,62992
1,66929
1,70866
1,74803
1,78740
1,82677
1,86614
1,90551
1,94488
1,98425
1,19685
1,23622
1,27559
1,31496
1,35433
1,39370
1,43307
1,47244
1,51181
1,55118
0,80315
0,84252
0,88189
0,92126
0,96063
1,00000
1,03937
1,07874
1,11811
1,15748
0,4
1,59449
1,63386
1,67323
1,71260
1,75197
1,79134
1,83071
1,87008
1,90945
1,94882
1,98819
1,20079
1,24016
1,27953
1,31890
1,35827
1,39764
1,43701
1,47638
1,51575
1,55512
0,80709
0,84646
0,88583
0,92520
0,96457
1,00394
1,04331
1,08268
1,12205
1,16142
0,5
1,59843
1,63780
1,67717
1,71654
1,75591
1,79528
1,83465
1,87402
1,91339
1,95276
1,99213
1,20472
1,24409
1,28346
1,32283
1,36220
1,40157
1,44094
1,48031
1,51969
1,55906
0,81102
0,85039
0,88976
0,92913
0,96850
1,00787
1,04724
1,08661
1,12598
1,16535
0,6
1,60236
1,64173
1,68110
1,72047
1,75984
1,79921
1,83858
1,87795
1,91732
1,95669
1,99606
1,20866
1,24803
1,28740
1,32677
1,36614
1,40551
1,44488
1,48425
1,52362
1,56299
0,81496
0,85433
0,89370
0,93307
0,97244
1,01181
1,05118
1,09055
1,12992
1,16929
0,7
1,60630
1,64567
1,68504
1,72441
1,76378
1,80315
1,84252
1,88189
1,92126
1,96063
2,00000
1,21260
1,25197
1,29134
1,33071
1,37008
1,40945
1,44882
1,48819
1,52756
1,56693
0,81890
0,85827
0,89764
0,93701
0,97638
1,01575
1,05512
1,09449
1,13386
1,17323
0,8
1,61024
1,64961
1,68898
1,72835
1,76772
1,80709
1,84646
1,88583
1,92520
1,96457
2,00394
1,21654
1,25591
1,29528
1,33465
1,37402
1,41339
1,45276
1,49213
1,53150
1,57087
0,82283
0,86220
0,90157
0,94094
0,98031
1,01969
1,05906
1,09843
1,13780
1,17717
0,9
STEMME TSA-M
MAINTENANCE MANUAL
Millimeter to Inches
Figure 1, Sheet 2.
20-11-00
Page 05
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
kpm
lb.in.
Nm
kpm
lb.in.
Nm
0,1
0,2
0,3
0,4
0,5
0,6
0,7
0,8
0,9
1,0
1,1
1,2
1,3
1,4
1,5
1,6
1,7
1,8
1,9
2,0
2,1
2,2
2,3
2,4
2,5
2,6
2,7
2,8
2,9
3,0
3,1
3,2
3,3
3,4
3,5
3,6
3,7
3,8
3,9
4,0
8,68
17,36
26,04
34,72
43,40
52,08
60,76
69,44
78,13
86,81
95,49
104,17
112,85
121,53
130,21
138,89
147,57
156,25
164,93
173,61
182,29
190,97
199,65
208,33
217,01
225,69
234,38
243,06
251,74
260,42
269,10
277,78
286,46
295,14
303,82
312,50
321,18
329,86
338,54
347,22
0,98
1,96
2,94
3,92
4,90
5,89
6,87
7,85
8,83
9,81
10,79
11,77
12,75
13,73
14,72
15,70
16,68
17,66
18,64
19,62
20,60
21,58
22,56
23,54
24,52
25,51
26,49
27,47
28,45
29,43
30,41
31,39
32,37
33,35
34,33
35,32
36,30
37,28
38,26
39,24
4,1
4,2
4,3
4,4
4,5
4,6
4,7
4,8
4,9
5,0
5,1
5,2
5,3
5,4
5,5
5,6
5,7
5,8
5,9
6,0
6,1
6,2
6,3
6,4
6,5
6,6
6,7
6,8
6,9
7,0
7,1
7,2
7,3
7,4
7,5
7,6
7,7
7,8
7,9
8,0
355,90
364,58
373,26
381,94
390,63
399,31
407,99
416,67
425,35
434,03
442,71
451,39
460,07
468,75
477,43
486,11
494,79
503,47
512,15
520,83
529,51
538,19
546,88
555,56
564,24
572,92
581,60
590,28
598,96
607,64
616,32
625,00
633,68
642,36
651,04
659,72
668,40
677,08
685,76
694,44
40,22
41,20
42,18
43,16
44,15
45,13
46,11
47,09
48,07
49,05
50,03
51,01
51,99
52,97
53,95
54,94
55,92
56,90
57,88
58,86
59,84
60,82
61,80
62,78
63,76
64,75
65,73
66,71
67,69
68,67
69,65
70,63
71,61
72,59
73,57
74,55
75,54
76,52
77,50
78,48
kpcm
lb.in.
Ncm
kpcm
lb.in.
Ncm
Torque Conversion Chart
Figure 2
20-11-00
Page 06
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
°C
°F
°C
°F
°C
°F
°C
°F
-73,3
-72,8
-72,2
-71,7
-71,1
-70,6
-70,0
-69,4
-68,9
-68,3
-100
-99
-98
-97
-96
-95
-94
-93
-92
-91
-148,0
-146,2
-144,4
-142,6
-140,8
-139,0
-137,2
-135,4
-133,6
-131,8
-56,7
-56,1
-55,6
-55,0
-54,4
-53,9
-53,3
-52,8
-52,2
-51,7
-70
-69
-68
-67
-66
-65
-64
-63
-62
-61
-94,0
-92,2
-90,4
-88,6
-86,8
-85,0
-83,2
-81,4
-79,6
-77,8
-40,0
-39,4
-38,9
-38,3
-37,8
-37,2
-36,7
-36,1
-35,6
-35,0
-40
-39
-38
-37
-36
-35
-34
-33
-32
-31
-40,0
-38,2
-36,4
-34,6
-32,8
-31,0
-29,2
-27,4
-25,6
-23,8
-23,3
-22,8
-22,2
-21,7
-21,1
-20,6
-20,0
-19,4
-18,9
-18,3
-10
-9
-8
-7
-6
-5
-4
-3
-2
-1
14,0
15,8
17,6
19,4
21,2
23,0
24,8
26,6
28,4
30,2
-67,8
-67,2
-66,7
-66,1
-65,6
-65,0
-64,4
-63,9
-63,3
-62,8
-90
-89
-88
-87
-86
-85
-84
-83
-82
-81
-130,0
-128,2
-126,4
-124,6
-122,8
-121,0
-119,2
-117,4
-115,6
-113,8
-51,1
-50,6
-50,0
-49,4
-48,9
-48,3
-47,8
-47,2
-46,7
-46,1
-60
-59
-58
-57
-56
-55
-54
-53
-52
-51
-76,0
-74,2
-72,4
-70,6
-68,8
-67,0
-65,2
-63,4
-61,6
-59,8
-34,4
-33,9
-33,3
-32,8
-32,2
-31,7
-31,1
-30,6
-30,0
-29,4
-30
-29
-28
-27
-26
-25
-24
-23
-22
-21
-22,0
-20,2
-18,4
-16,6
-14,8
-13,0
-11,2
-9,4
-7,6
-5,8
-17,8
-17,2
-16,7
-16,1
-15,6
-15,0
-14,4
-13,9
-13,3
-12,8
0
1
2
3
4
5
6
7
8
9
32,0
33,8
35,6
37,4
39,2
41,0
42,8
44,6
46,4
48,2
-62,2
-61,7
-61,1
-60,6
-60,0
-59,4
-58,9
-58,3
-57,8
-57,2
-80
-79
-78
-77
-76
-75
-74
-73
-72
-71
-112,0
-110,2
-108,4
-106,6
-104,8
-103,0
-101,2
-99,4
-97,6
-95,8
-45,6
-45,0
-44,4
-43,9
-43,3
-42,8
-42,2
-41,7
-41,1
-40,6
-50
-49
-48
-47
-46
-45
-44
-43
-42
-41
-58,0
-56,2
-54,4
-52,6
-50,8
-49,0
-47,2
-45,4
-43,6
-41,8
-28,9
-28,3
-27,8
-27,2
-26,7
-26,1
-25,6
-25,0
-24,4
-23,9
-20
-19
-18
-17
-16
-15
-14
-13
-12
-11
-4,0
-2,2
-0,4
1,4
3,2
5,0
6,8
8,6
10,4
12,2
-12,2
-11,7
-11,1
-10,6
-10,0
-9,4
-8,9
-8,3
-7,8
-7,2
10
11
12
13
14
15
16
17
18
19
50,0
51,8
53,6
55,4
57,2
59,0
60,8
62,6
64,4
66,2
Fahrenheit and Celsius Temperature Conversion
Figure 3, Sheet 1
20-11-00
Page 07
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
°C
°F
°C
°F
°C
°F
°C
°F
-6,7
-6,1
-5,6
-5,0
-4,4
-3,9
-3,3
-2,8
-2,2
-1,7
20
21
22
23
24
25
26
27
28
29
68,0
69,8
71,6
73,4
75,2
77,0
78,8
80,6
82,4
84,2
15,6
16,1
16,7
17,2
17,8
18,3
18,9
19,4
20,0
20,6
60
61
62
63
64
65
66
67
68
69
140,0
141,8
143,6
145,4
147,2
149,0
150,8
152,6
154,4
156,2
37,8
38,3
38,9
39,4
40,0
40,6
41,1
41,7
42,2
42,8
100
101
102
103
104
105
106
107
108
109
212,0
213,8
215,6
217,4
219,2
221,0
222,8
224,6
226,4
228,2
60,0
60,6
61,1
61,7
62,2
62,8
63,3
63,9
64,4
65,0
140
141
142
143
144
145
146
147
148
149
284,0
285,8
287,6
289,4
291,2
293,0
294,8
296,6
298,4
300,2
-1,1
-0,6
0,0
0,6
1,1
1,7
2,2
2,8
3,3
3,9
30
31
32
33
34
35
36
37
38
39
86,0
87,8
89,6
91,4
93,2
95,0
96,8
98,6
100,4
102,2
21,1
21,7
22,2
22,8
23,3
23,9
24,4
25,0
25,6
26,1
70
71
72
73
74
75
76
77
78
79
158,0
159,8
161,6
163,4
165,2
167,0
168,8
170,6
172,4
174,2
43,3
43,9
44,4
45,0
45,6
46,1
46,7
47,2
47,8
48,3
110
111
112
113
114
115
116
117
118
119
230,0
231,8
233,6
235,4
237,2
239,0
240,8
242,6
244,4
246,2
65,6
66,1
66,7
67,2
67,8
68,3
68,9
69,4
70,0
70,6
150
151
152
153
154
155
156
157
158
159
302,0
303,8
305,6
307,4
309,2
311,0
312,8
314,6
316,4
318,2
4,4
5,0
5,6
6,1
6,7
7,2
7,8
8,3
8,9
9,4
40
41
42
43
44
45
46
47
48
49
104,0
105,8
107,6
109,4
111,2
113,0
114,8
116,6
118,4
120,2
26,7
27,2
27,8
28,3
28,9
29,4
30,0
30,6
31,1
31,7
80
81
82
83
84
85
86
87
88
89
176,0
177,8
179,6
181,4
183,2
185,0
186,8
188,6
190,4
192,2
48,9
49,4
50,0
50,6
51,1
51,7
52,2
52,8
53,3
53,9
120
121
122
123
124
125
126
127
128
129
248,0
249,8
251,6
253,4
255,2
257,0
258,8
260,6
262,4
264,2
71,1
71,7
72,2
72,8
73,3
73,9
74,4
75,0
75,6
76,1
160
161
162
163
164
165
166
167
168
169
320,0
321,8
323,6
325,4
327,2
329,0
330,8
332,6
334,4
336,2
10,0
10,6
11,1
11,7
12,2
12,8
13,3
13,9
14,4
15,0
50
51
52
53
54
55
56
57
58
59
122,0
123,8
125,6
127,4
129,2
131,0
132,8
134,6
136,4
138,2
32,2
32,8
33,3
33,9
34,4
35,0
35,6
36,1
36,7
37,2
90
91
92
93
94
95
96
97
98
99
194,0
195,8
197,6
199,4
201,2
203,0
204,8
206,6
208,4
210,2
54,4
55,0
55,6
56,1
56,7
57,2
57,8
58,3
58,9
59,4
130
131
132
133
134
135
136
137
138
139
266,0
267,8
269,6
271,4
273,2
275,0
276,8
278,6
280,4
282,2
76,7
77,2
77,8
78,3
78,9
79,4
80,0
80,6
81,1
81,7
170
171
172
173
174
175
176
177
178
179
338,0
339,8
341,6
343,4
345,2
347,0
348,8
350,6
352,4
354,2
Figure 3, Sheet 2
20-11-00
Page 08
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
°C
°F
°C
°F
°C
°F
°C
°F
82,2
82,8
83,3
83,9
84,4
85,0
85,6
86,1
86,7
87,2
180
181
182
183
184
185
186
187
188
189
356,0
357,8
359,6
361,4
363,2
365,0
366,8
368,6
370,4
372,2
104,4
105,0
105,6
106,1
106,7
107,2
107,8
108,3
108,9
109,4
220
221
222
223
224
225
226
227
228
229
428,0
429,8
431,6
433,4
435,2
437,0
438,8
440,6
442,4
444,2
148,9
151,7
154,4
157,2
160,0
162,8
165,6
168,3
171,1
173,9
300
305
310
315
320
325
330
335
340
345
572,0
581,0
590,0
599,0
608,0
617,0
626,0
635,0
644,0
653,0
260,0
262,8
265,6
268,3
271,1
273,9
276,7
279,4
282,2
285,0
500
505
510
515
520
525
530
535
540
545
932,0
941,0
950,0
959,0
968,0
977,0
986,0
995,0
1004,0
1013,0
87,8
88,3
88,9
89,4
90,0
90,6
91,1
91,7
92,2
92,8
190
191
192
193
194
195
196
197
198
199
374,0
375,8
377,6
379,4
381,2
383,0
384,8
386,6
388,4
390,2
110,0
110,6
111,1
111,7
112,2
112,8
113,3
113,9
114,4
115,0
230
231
232
233
234
235
236
237
238
239
446,0
447,8
449,6
451,4
453,2
455,0
456,8
458,6
460,4
462,2
176,7
179,4
182,2
185,0
187,8
190,6
193,3
196,1
198,9
201,7
350
355
360
365
370
375
380
385
390
395
662,0
671,0
680,0
689,0
698,0
707,0
716,0
725,0
734,0
743,0
287,8
290,6
293,3
296,1
298,9
301,7
304,4
307,2
310,0
312,8
550
555
560
565
570
575
580
585
590
595
1022,0
1031,0
1040,0
1049,0
1058,0
1067,0
1076,0
1085,0
1094,0
1103,0
93,3
93,9
94,4
95,0
95,6
96,1
96,7
97,2
97,8
98,3
200
201
202
203
204
205
206
207
208
209
392,0
393,8
395,6
397,4
399,2
401,0
402,8
404,6
406,4
408,2
115,6
116,1
116,7
117,2
117,8
118,3
118,9
119,4
120,0
120,6
240
241
242
243
244
245
246
247
248
249
464,0
465,8
467,6
469,4
471,2
473,0
474,8
476,6
478,4
480,2
204,4
207,2
210,0
212,8
215,6
218,3
221,1
223,9
226,7
229,4
400
405
410
415
420
425
430
435
440
445
752,0
761,0
770,0
779,0
788,0
797,0
806,0
815,0
824,0
833,0
315,6
318,3
321,1
323,9
326,7
329,4
332,2
335,0
337,8
340,6
600
605
610
615
620
625
630
635
640
645
1112,0
1121,0
1130,0
1139,0
1148,0
1157,0
1166,0
1175,0
1184,0
1193,0
98,9
99,4
100,0
100,6
101,1
101,7
102,2
102,8
103,3
103,9
210
211
212
213
214
215
216
217
218
219
410,0
411,8
413,6
415,4
417,2
419,0
420,8
422,6
424,4
426,2
121,1
123,9
126,7
129,4
132,2
135,0
137,8
140,6
143,3
146,1
250
255
260
265
270
275
280
285
290
295
482,0
491,0
500,0
509,0
518,0
527,0
536,0
545,0
554,0
563,0
232,2
235,0
237,8
240,6
243,3
246,1
248,9
251,7
254,4
257,2
450
455
460
465
470
475
480
485
490
495
842,0
851,0
860,0
869,0
878,0
887,0
896,0
905,0
914,0
923,0
343,3
346,1
348,9
351,7
354,4
357,2
360,0
362,8
365,6
368,3
650
655
660
665
670
675
680
685
690
695
1202,0
1211,0
1220,0
1229,0
1238,0
1247,0
1256,0
1265,0
1274,0
1283,0
Figure 3, Sheet 4
20-11-00
Page 09
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
°C
°F
°C
°F
°C
°F
°C
°F
371,1
373,9
376,7
379,4
382,2
385,0
387,8
390,6
393,3
396,1
700
705
710
715
720
725
730
735
740
745
1292,0
1301,0
1310,0
1319,0
1328,0
1337,0
1346,0
1355,0
1364,0
1373,0
482,2
485,0
487,8
490,6
493,3
496,1
498,9
501,7
504,4
507,2
900
905
910
915
920
925
930
935
940
945
1652,0
1661,0
1670,0
1679,0
1688,0
1697,0
1706,0
1715,0
1724,0
1733,0
593,3
596,1
598,9
601,7
604,4
607,2
610,0
612,8
615,6
618,3
1100
1105
1110
1115
1120
1125
1130
1135
1140
1145
2012,0
2021,0
2030,0
2039,0
2048,0
2057,0
2066,0
2075,0
2084,0
2093,0
704,4
707,2
710,0
712,8
715,6
718,3
721,1
723,9
726,7
729,4
1300
1305
1310
1315
1320
1325
1330
1335
1340
1345
2372,0
2381,0
2390,0
2399,0
2408,0
2417,0
2426,0
2435,0
2444,0
2453,0
398,9
401,7
404,4
407,2
410,0
412,8
415,6
418,3
421,1
423,9
750
755
760
765
770
775
780
785
790
795
1382,0
1391,0
1400,0
1409,0
1418,0
1427,0
1436,0
1445,0
1454,0
1463,0
510,0
512,8
515,6
518,3
521,1
523,9
526,7
529,4
532,2
535,0
950
955
960
965
970
975
980
985
990
995
1742,0
1751,0
1760,0
1769,0
1778,0
1787,0
1796,0
1805,0
1814,0
1823,0
621,1
623,9
626,7
629,4
632,2
635,0
637,8
640,6
643,3
646,1
1150
1155
1160
1165
1170
1175
1180
1185
1190
1195
2102,0
2111,0
2120,0
2129,0
2138,0
2147,0
2156,0
2165,0
2174,0
2183,0
732,2
735,0
737,8
740,6
743,3
746,1
748,9
751,7
754,4
757,2
1350
1355
1360
1365
1370
1375
1380
1385
1390
1395
2462,0
2471,0
2480,0
2489,0
2498,0
2507,0
2516,0
2525,0
2534,0
2543,0
426,7
429,4
432,2
435,0
437,8
440,6
443,3
446,1
448,9
451,7
800
805
810
815
820
825
830
835
840
845
1472,0
1481,0
1490,0
1499,0
1508,0
1517,0
1526,0
1535,0
1544,0
1553,0
537,8
540,6
543,3
546,1
548,9
551,7
554,4
557,2
560,0
562,8
1000
1005
1010
1015
1020
1025
1030
1035
1040
1045
1832,0
1841,0
1850,0
1859,0
1868,0
1877,0
1886,0
1895,0
1904,0
1913,0
648,9
651,7
654,4
657,2
660,0
662,8
665,6
668,3
671,1
673,9
1200
1205
1210
1215
1220
1225
1230
1235
1240
1245
2192,0
2201,0
2210,0
2219,0
2228,0
2237,0
2246,0
2255,0
2264,0
2273,0
760,0
762,8
765,6
768,3
771,1
773,9
776,7
779,4
782,2
785,0
1400
1405
1410
1415
1420
1425
1430
1435
1440
1445
2552,0
2561,0
2570,0
2579,0
2588,0
2597,0
2606,0
2615,0
2624,0
2633,0
454,4
457,2
460,0
462,8
465,6
468,3
471,1
473,9
476,7
479,4
850
855
860
865
870
875
880
885
890
895
1562,0
1571,0
1580,0
1589,0
1598,0
1607,0
1616,0
1625,0
1634,0
1643,0
565,6
568,3
571,1
573,9
576,7
579,4
582,2
585,0
587,8
590,6
1050
1055
1060
1065
1070
1075
1080
1085
1090
1095
1922,0
1931,0
1940,0
1949,0
1958,0
1967,0
1976,0
1985,0
1994,0
2003,0
676,7
679,4
682,2
685,0
687,8
690,6
693,3
696,1
698,9
701,7
1250
1255
1260
1265
1270
1275
1280
1285
1290
1295
2282,0
2291,0
2300,0
2309,0
2318,0
2327,0
2336,0
2345,0
2354,0
2363,0
787,8
790,6
793,3
796,1
798,9
801,7
804,4
807,2
810,0
812,8
1450
1455
1460
1465
1470
1475
1480
1485
1490
1495
2642,0
2651,0
2660,0
2669,0
2678,0
2687,0
2696,0
2705,0
2714,0
2723,0
Figure 3, Sheet 4
20-11-00
Page 10
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
°C
°F
°C
°F
°C
°F
°C
°F
815,6
818,3
821,1
823,9
826,7
829,4
832,2
835,0
837,8
840,6
1500
1505
1510
1515
1520
1525
1530
1535
1540
1545
2732,0
2741,0
2750,0
2759,0
2768,0
2777,0
2786,0
2795,0
2804,0
2813,0
926,7
929,4
932,2
935,0
937,8
940,6
943,3
946,1
948,9
951,7
1700
1705
1710
1715
1720
1725
1730
1735
1740
1745
3092,0
3101,0
3110,0
3119,0
3128,0
3137,0
3146,0
3155,0
3164,0
3173,0
1037,8
1040,6
1043,3
1046,1
1048,9
1051,7
1054,4
1057,2
1060,0
1062,8
1900
1905
1910
1915
1920
1925
1930
1935
1940
1945
3452,0
3461,0
3470,0
3479,0
3488,0
3497,0
3506,0
3515,0
3524,0
3533,0
1148,9
1151,7
1154,4
1157,2
1160,0
1162,8
1165,6
1168,3
1171,1
1173,9
2100
2105
2110
2115
2120
2125
2130
2135
2140
2145
3812,0
3821,0
3830,0
3839,0
3848,0
3857,0
3866,0
3875,0
3884,0
3893,0
843,3
846,1
848,9
851,7
854,4
857,2
860,0
862,8
865,6
868,3
1550
1555
1560
1565
1570
1575
1580
1585
1590
1595
2822,0
2831,0
2840,0
2849,0
2858,0
2867,0
2876,0
2885,0
2894,0
2903,0
954,4
957,2
960,0
962,8
965,6
968,3
971,1
973,9
976,7
979,4
1750
1755
1760
1765
1770
1775
1780
1785
1790
1795
3182,0
3191,0
3200,0
3209,0
3218,0
3227,0
3236,0
3245,0
3254,0
3263,0
1065,6
1068,3
1071,1
1073,9
1076,7
1079,4
1082,2
1085,0
1087,8
1090,6
1950
1955
1960
1965
1970
1975
1980
1985
1990
1995
3542,0
3551,0
3560,0
3569,0
3578,0
3587,0
3596,0
3605,0
3614,0
3623,0
1176,7
1179,4
1182,2
1185,0
1187,8
1190,6
1193,3
1196,1
1198,9
1201,7
2150
2155
2160
2165
2170
2175
2180
2185
2190
2195
3902,0
3911,0
3920,0
3929,0
3938,0
3947,0
3956,0
3965,0
3974,0
3983,0
871,1
873,9
876,7
879,4
882,2
885,0
887,8
890,6
893,3
896,1
1600
1605
1610
1615
1620
1625
1630
1635
1640
1645
2912,0
2921,0
2930,0
2939,0
2948,0
2957,0
2966,0
2975,0
2984,0
2993,0
982,2
985,0
987,8
990,6
993,3
996,1
998,9
1001,7
1004,4
1007,2
1800
1805
1810
1815
1820
1825
1830
1835
1840
1845
3272,0
3281,0
3290,0
3299,0
3308,0
3317,0
3326,0
3335,0
3344,0
3353,0
1093,3
1096,1
1098,9
1101,7
1104,4
1107,2
1110,0
1112,8
1115,6
1118,3
2000
2005
2010
2015
2020
2025
2030
2035
2040
2045
3632,0
3641,0
3650,0
3659,0
3668,0
3677,0
3686,0
3695,0
3704,0
3713,0
1204,4
1207,2
1210,0
1212,8
1215,6
1218,3
1221,1
1223,9
1226,7
1229,4
2200
2205
2210
2215
2220
2225
2230
2235
2240
2245
3992,0
4001,0
4010,0
4019,0
4028,0
4037,0
4046,0
4055,0
4064,0
4073,0
898,9
901,7
904,4
907,2
910,0
912,8
915,6
918,3
921,1
923,9
1650
1655
1660
1665
1670
1675
1680
1685
1690
1695
3002,0
3011,0
3020,0
3029,0
3038,0
3047,0
3056,0
3065,0
3074,0
3083,0
1010,0
1012,8
1015,6
1018,3
1021,1
1023,9
1026,7
1029,4
1032,2
1035,0
1850
1855
1860
1865
1870
1875
1880
1885
1890
1895
3362,0
3371,0
3380,0
3389,0
3398,0
3407,0
3416,0
3425,0
3434,0
3443,0
1121,1
1123,9
1126,7
1129,4
1132,2
1135,0
1137,8
1140,6
1143,3
1146,1
2050
2055
2060
2065
2070
2075
2080
2085
2090
2095
3722,0
3731,0
3740,0
3749,0
3758,0
3767,0
3776,0
3785,0
3794,0
3803,0
1232,2
1235,0
1237,8
1240,6
1243,3
1246,1
1248,9
1251,7
1254,4
1257,2
2250
2255
2260
2265
2270
2275
2280
2285
2290
2295
4082,0
4091,0
4100,0
4109,0
4118,0
4127,0
4136,0
4145,0
4154,0
4163,0
Figure 3, Sheet 5
20-11-00
Page 11
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
°C
°F
°C
°F
°C
°F
°C
°F
1260,0
1262,8
1265,6
1268,3
1271,1
1273,9
1276,7
1279,4
1282,2
1285,0
2300
2305
2310
2315
2320
2325
2330
2335
2340
2345
4172,0
4181,0
4190,0
4199,0
4208,0
4217,0
4226,0
4235,0
4244,0
4253,0
1371,1
1373,9
1376,7
1379,4
1382,2
1385,0
1387,8
1390,6
1393,3
1396,1
2500
2505
2510
2515
2520
2525
2530
2535
2540
2545
4532,0
4541,0
4550,0
4559,0
4568,0
4577,0
4586,0
4595,0
4604,0
4613,0
1482,2
1485,0
1487,8
1490,6
1493,3
1496,1
1498,9
1501,7
1504,4
1507,2
2700
2705
2710
2715
2720
2725
2730
2735
2740
2745
4892,0
4901,0
4910,0
4919,0
4928,0
4937,0
4946,0
4955,0
4964,0
4973,0
1593,3
1596,1
1598,9
1601,7
1604,4
1607,2
1610,0
1612,8
1615,6
1618,3
2900
2905
2910
2915
2920
2925
2930
2935
2940
2945
5252,0
5261,0
5270,0
5279,0
5288,0
5297,0
5306,0
5315,0
5324,0
5333,0
1287,8
1290,6
1293,3
1296,1
1298,9
1301,7
1304,4
1307,2
1310,0
1312,8
2350
2355
2360
2365
2370
2375
2380
2385
2390
2395
4262,0
4271,0
4280,0
4289,0
4298,0
4307,0
4316,0
4325,0
4334,0
4343,0
1398,9
1401,7
1404,4
1407,2
1410,0
1412,8
1415,6
1418,3
1421,1
1423,9
2550
2555
2560
2565
2570
2575
2580
2585
2590
2595
4622,0
4631,0
4640,0
4649,0
4658,0
4667,0
4676,0
4685,0
4694,0
4703,0
1510,0
1512,8
1515,6
1518,3
1521,1
1523,9
1526,7
1529,4
1532,2
1535,0
2750
2755
2760
2765
2770
2775
2780
2785
2790
2795
4982,0
4991,0
5000,0
5009,0
5018,0
5027,0
5036,0
5045,0
5054,0
5063,0
1621,1
1623,9
1626,7
1629,4
1632,2
1635,0
1637,8
1640,6
1643,3
1646,1
2950
2955
2960
2965
2970
2975
2980
2985
2990
2995
5342,0
5351,0
5360,0
5369,0
5378,0
5387,0
5396,0
5405,0
5414,0
5423,0
1315,6
1318,3
1321,1
1323,9
1326,7
1329,4
1332,2
1335,0
1337,8
1340,6
2400
2405
2410
2415
2420
2425
2430
2435
2440
2445
4352,0
4361,0
4370,0
4379,0
4388,0
4397,0
4406,0
4415,0
4424,0
4433,0
1426,7
1429,4
1432,2
1435,0
1437,8
1440,6
1443,3
1446,1
1448,9
1451,7
2600
2605
2610
2615
2620
2625
2630
2635
2640
2645
4712,0
4721,0
4730,0
4739,0
4748,0
4757,0
4766,0
4775,0
4784,0
4793,0
1537,8
1540,6
1543,3
1546,1
1548,9
1551,7
1554,4
1557,2
1560,0
1562,8
2800
2805
2810
2815
2820
2825
2830
2835
2840
2845
5072,0
5081,0
5090,0
5099,0
5108,0
5117,0
5126,0
5135,0
5144,0
5153,0
1648,9
1651,7
1654,4
1657,2
1660,0
1662,8
1665,6
1668,3
1671,1
1673,9
3000
3005
3010
3015
3020
3025
3030
3035
3040
3045
5432,0
5441,0
5450,0
5459,0
5468,0
5477,0
5486,0
5495,0
5504,0
5513,0
1343,3
1346,1
1348,9
1351,7
1354,4
1357,2
1360,0
1362,8
1365,6
1368,3
2450
2455
2460
2465
2470
2475
2480
2485
2490
2495
4442,0
4451,0
4460,0
4469,0
4478,0
4487,0
4496,0
4505,0
4514,0
4523,0
1454,4
1457,2
1460,0
1462,8
1465,6
1468,3
1471,1
1473,9
1476,7
1479,4
2650
2655
2660
2665
2670
2675
2680
2685
2690
2695
4802,0
4811,0
4820,0
4829,0
4838,0
4847,0
4856,0
4865,0
4874,0
4883,0
1565,6
1568,3
1571,1
1573,9
1576,7
1579,4
1582,2
1585,0
1587,8
1590,6
2850
2855
2860
2865
2870
2875
2880
2885
2890
2895
5162,0
5171,0
5180,0
5189,0
5198,0
5207,0
5216,0
5225,0
5234,0
5243,0
1676,7
1679,4
1682,2
1685,0
1687,8
1690,6
1693,3
1696,1
1698,9
1701,7
3050
3055
3060
3065
3070
3075
3080
3085
3090
3095
5522,0
5531,0
5540,0
5549,0
5558,0
5567,0
5576,0
5585,0
5594,0
5603,0
Figure 3, Sheet 6
20-11-00
Page 12
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
mm
Drill
in.
mm
Drill
in.
mm
Drill
in.
0,34
0,37
0,40
0,41
0,46
80
79
1/64
78
77
- 76
75
74
73
72
- 71
70
69
68
1/32
- 67
66
65
64
63
- 62
61
60
59
58
- 57
56
3/64
55
54
- 53
1/16
52
51
50
0,0135
0,0145
0,0156
0,0160
0,0180
- 0,0200
0,0210
0,0225
0,0240
0,0250
- 0,0260
0,0280
0,0292
0,0310
0,0313
- 0,0320
0,0330
0,0350
0,0360
0,0370
- 0,0380
0,0390
0,0400
0,0410
0,0420
- 0,0430
0,0465
0,0469
0,0520
0,0550
- 0,0595
0,0625
0,0635
0,0670
0,0700
1,85
1,93
1,98
1,99
2,06
49
48
5/64
47
46
0,0730
0,0760
0,0781
0,0785
0,0810
4,09
4,22
4,31
4,37
4,39
2,08
2,18
2,26
2,37
2,38
45
44
43
42
3/32
- 41
40
39
38
37
- 36
7/64
35
34
33
- 32
31
1/8
30
29
- 28
9/64
27
26
25
- 24
23
5/32
22
21
0,0820
0,0860
0,0890
0,0935
0,0937
- 0,0960
0,0980
0,0995
0,1015
0,1040
- 0,1065
0,1093
0,1100
0,1110
0,1130
- 0,1160
0,1200
0,1250
0,1285
0,1360
- 0,1405
0,1406
0,1440
0,1470
0,1495
- 0,1520
0,1540
0,1562
0,1570
0,1590
4,50
4,57
4,62
4,70
4,76
20
19
18
11/64
17
- 16
15
14
13
3/16
0,1610
0,1660
0,1695
0,1719
0,1730
- 0,1770
0,1800
0,1820
0,1850
0,1875
12
11
10
9
8
- 7
13/64
6
5
4
- 3
7/32
2
1
A
- 15/64
B
C
D
E
- 1/4
F
G
17/64
H
0,1890
0,1910
0,1935
0,1960
0,1990
- 0,2010
0,2031
0,2040
0,2055
0,2090
- 0,2130
0,2187
0,2210
0,2280
0,2340
- 0,2344
0,2380
0,2420
0,2460
0,2500
- 0,2500
0,2750
0,2610
0,2656
0,2660
0,51
0,53
0,57
0,61
0,64
0,66
0,71
0,74
0,79
0,80
0,81
0,84
0,89
0,91
0,94
0,97
0,99
1,02
1,04
1,07
1,09
1,18
1,19
1,32
1,40
1,51
1,59
1,61
1,70
1,78
2,44
2,49
2,53
2,58
2,64
2,71
2,78
2,79
2,82
2,87
2,95
3,05
3,18
3,26
3,45
3,57
3,57
3,66
3,73
3,80
3,86
3,91
3,97
3,99
4,04
4,80
4,85
4,91
4,98
5,05
5,11
5,16
5,18
5,22
5,31
5,41
5,55
5,61
5,79
5,94
5,95
6,05
6,15
6,25
6,35
6,35
6,99
6,63
6,75
6,76
Equivalents for Drill Sizes
Figure 4.
20-11-00
Page 13
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
CHAPTER 21
VENTILATION
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page Effectivity
VENTILATION - GENERAL............................................................................21-00-00
Introduction
21-00-00
General Description
21-00-00
1
1
1
VENTILATION - MAINTENANCE PRACTICES .........................................21-20-00
Canopy Outlet Removal/Installation
21-20-00
Side Wall Outlets Removal/Installation
21-20-00
201
201
201
CABIN HEATING - GENERAL .......................................................................21-40-00
Introduction
21-40-00
General Description
21-40-00
Operation of Cabin Heating System
21-40-00
1
1
1
1
Cabin Heating
Cabin Heating
Cabin Heating
Cabin Heating
CABIN HEATING - MAINTENANCE PRACTICES.....................................21-40-00
General
21-40-00
Bleeding of Heating System
21-40-00
Renewal of Heating System Hoses
21-40-00
Removal and Installation of Heat Exchanger
21-40-00
Removal and Installation of Magnetic Valve and Check Valve
21-40-00
201
201
201
201
203
203
Cabin Heating
Cabin Heating
Cabin Heating
Cabin Heating
Cabin Heating
Cabin Heating
Page 01
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STEMME TSA-M
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STEMME TSA-M
MAINTENANCE MANUAL
VENTILATION - GENERAL
1. Introduction
A.
This chapter describes those systems and components, which furnish a means of ventilating the
cabin.
2. General Description (Refer to Figure 1)
A.
Fresh air for ventilation with outside temperature comes through air intakes located near the
propeller dome at the nose of the aircraft and flows through several adjustable air outlets into the
cabin.
One outlet is installed between the instrument panel and the canopy hinge. It allows to ventilate
and to defog the canopy glass. This outlet is controlled by a push-pull knob in the instrument
panel (Ref. 31-00-00).
On each cockpit side wall three air outlets are provided. The amount of air per side can be
adjusted by a knob located in the air outlet support at each side wall. The control knob can be
moved in or against flight direction (Ref. Figure 1). If the control knob is in the most forward
position the air flow from outside is stopped. The air stream direction can be adjusted by each
outlet.
B.
Optionally the outside air ventilation of the STEMME S6 can be combined with a liquid to air
cabin heating system which is fed through the engine cooling circuit.
21-00-00
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A
B
C
Air Flow
Control Knobs
Detail- A
D
Detail- B
Air Outlet
Air Outlet
FWD Canopy
Detail- C
Air Outlet Support
Detail- D
Ventilation - Component Location
Figure 01
21-00-00
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STEMME TSA-M
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VENTILATION – MAINTENANCE PRACTICES
1. General
A.
Maintenance is limited to removal and installation of the components.
2. Canopy Outlet Removal/Installation
A.
Remove Canopy Outlet
(1) Disconnect flexible air duct from outlet.
(2) Remove screws securing outlet to the front gearbox frame and remove outlet.
B.
Install Canopy Outlet
(1) Position outlet on the front gearbox frame and secure it with screws.
(2) Reconnect flexible air duct to outlet.
3. Side Wall Outlets Removal/Installation
A.
Remove Side Wall Outlets
NOTE:
Removal of the left and right outlets is typical.
(1) Disconnect flexible air duct from side air outlet support.
(2) Remove screws securing outlet support to the sidewall and remove support with the outlets.
B.
Install Side Wall Outlets
(1) Position air outlet support to side wall and secure with 3 screws.
(2) Reconnect flexible air duct to air outlet support.
21-20-00
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MAINTENANCE MANUAL
CABIN HEATING - GENERAL
1. Introduction
A.
This chapter describes systems and components of the cabin heating system.
2. General Description (Refer to Figure 1)
A.
With the cabin heating system installed the standard cabin ventilation of the Stemme S6 is
combined with a liquid to air heating system, which is fed through a heat exchanger in the cockpit
by the engine cooling circuit.
The hose for heating liquid flow towards cockpit heat exchanger is connected to the supply line of
the engine cooling system radiator. The return line of the heater is connected to the return line of
the radiator.
The two hoses (supply and return) lead from the engine cooling circuit through the cockpit to the
heat exchanger, installed at the front gear bulkhead. After leading through the engine firewall first
and the cockpit rear wall afterwards, the hoses runs through a CFRP channel along the left side
center tunnel and under the pilots leg rest and cockpit floor. The CFRP channel as well as all hoses
are heat-insulated to protect structure and pilot against excessive warming above comfort
respectively structural temperature limits.
The heat exchanger integrated in a GFRP box and mounted to the left inner side front gear
bulkhead has an air inlet for intake air and three outlets, connected to the ventilation for canopy
and ventilation outlets in the cabin side panels.
B.
For temperature regulation as well as for emergency shut-off of liquid flow one magnetic shut-off
valve is installed in the supply line and and a check valve in the return line. The valves are located
outside of the cockpit behind the cockpit rear wall. The temperature regulation respectively
operation the magnetic shut-off valve is operated via a central switch, located in the lower left
section of the instrument panel. With the heating system switch in OFF position the magnetic
shut-off valve is closed and the circulation is interrupted.
3. Operation of Cabin Heating System
The cabin heating is operated in combination with control of the cabin ventilation. The cabin
heating is activated by a switch on the instrument panel. By switching the heating ON the
magnetic valve is opened and the circulation starts. Pressure is supplied by the engine cooling
circuit and the engine water pump. Adversely, the heating circuit is shut off (magnetic valves
closed) when deactivated.
When the cabin heating is activated the heating power is regulated by adjustment of the cabin
ventilation air outlets. When the heating system is deactivated, ventilation with fresh air from
outside is supplied without pre-heating.
EFFECTIVITY
Aircraft equipped with Cabin Heating
21-40-00
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A
Engine Cooling
Circuit
Detail- A
CFRP Heat
Insulation Tunnel
Magnetic Shut-Off
Valve and
Check Valve
Heat Exchanger
at Front Gear Bulkhead
Cabin Heating - System Components
Figure 01
EFFECTIVITY
21-40-00
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STEMME TSA-M
MAINTENANCE MANUAL
CABIN HEATING – MAINTENANCE PRACTICES
1. General
A.
Maintenance is limited to removal and installation of the heating system components and
ventilation of heating system circuit.
2. Bleeding of Heating System
A.
Bleeding of Heating Circuit
NOTE:
(1)
(2)
(3)
(4)
(5)
(6)
(7)
Bleeding of heating system must be performed only with cold engine.
Remove heat exchanger cover in front cockpit section.
Lift heat exchanger out of box carefully, take care of the hoses.
Turn on master switch (Batt).
Turn ON heating (magnetic valve is open).
Screw out bleed valve of the heat exchanger.
Fill heat exchanger to the brim with suitable cooling liquid (refer to 12-14-00)
Srew in bleed valve, tighten.
WARNING:
(8)
(9)
(10)
(11)
BEFORE ENGINE START PAY ATTENTION TO CLEAR PROPELLER AREA.
Start engine while heating system is turned ON.
Leave engine running for 2 to 4 minutes.
Turn engine off while leaving master switch and heating system ON.
Untighten bleed valve of the heat exchanger carefully that steam can escape.
CAUTION: DANGER OF BURNS BECAUSE OF HOT COOLING LIQUID.
(12)
(13)
(14)
(15)
(16)
(17)
(18)
Let engine and cooling liquid cool down to ambient temperature.
Screw out bleed valve of heat exchanger.
Refill cooling liquid to the brim if necessary.
Srew in bleed valve, tighten.
Turn OFF heating system and master switch (Batt).
Insert heat exchanger into box carefully, take care of the hoses.
Install heat exchanger cover.
3. Renewal of Heating System Hoses
A.
Remove Heating System Hoses
(1) Loosen clamps of the magnetic shut-off valve and the check valve.
(2) Loosen plug of magnetic shut-off valve.
(3) Remove magnetic shut-off valve and check valve. Collect cooling liquid.
(4) Remove heat exchanger cover in front cockpit section.
(5) Lift heat exchanger out of box carefully, take care of the ventilation hoses.
(6) Screw out bleed valve of the heat exchanger to drain last cooling liquid.
(7) Loosen hose clamps at the heat exchanger, disconnect hoses, remove heat exchanger.
EFFECTIVITY
21-40-00
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A
GFRP Housing Box for
Heat Exchanger
Air outlet
Canopy Ventilation
Fan
Heat Exchanger
Air outlets Cockpit
Ventilation
Heating Liquid Flow
Supply/Return Line
Detail- A
Heat Exchanger Assembly
Figure 201
EFFECTIVITY
21-40-00
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(8) Pull back hoses at the control stick section. Pull hoses out under front cockpit floor section.
(9) Pull hoses forward at front opening of the hose guard (CFRP Insulation Tunnel).
B.
Install Heating System Hoses
(1) Fit hoses in CFRP hose tunnel.
(2) Fit hoses in the control stick section under front floor section of the cockpit.
(3) Connect hoses to heat exchanger.
(4) Screw bleed valve into heat exchanger.
(5) Screw in magnetic shut-off valve and check valve.
(6) Connect electricity plug to magnetic shut-off valve.
(7) Connect hoses to magnetic shut-off valve and check valve and tighten clamps.
(8) Refill engine cooling-system with cooling liquid.
(9) Bleed the heating circuit as described under corresponding heading repeating
steps (3) to (18).
4. Removal and Installation of Heat Exchanger
Maintenance practices are described in point 3, part A and B.
5. Removal and Installation of Magnetic Valve and Check Valve
Maintenance practices are described in point 3, part A and B.
EFFECTIVITY
21-40-00
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CHAPTER 23
COMMUNICATIONS
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page Effectivity
COMMUNICATIONS - GENERAL ................................................................23-00-00
Introduction
23-00-00
General Description
23-00-00
1
1
1
SPEECH COMMUNICATION - DESCRIPTION .........................................23-10-00
Introduction
23-10-00
Description and Operation
23-10-00
1
1
1
Professional
Professional
Professional
SPEECH COMMUNICATION - MAINTENANCE PRACTICES...............23-10-00
General
23-10-00
Nav / Com Radio Removal/Installation
23-10-00
201
201
201
Professional
Professional
Professional
Introduction
23-10-00
23-10-00
1
1
1
Classic
Classic
Classic
General
23-10-00
23-10-00
201
201
201
Classic
Classic
Classic
Introduction
23-10-00
23-10-00
1
1
1
Advanced
Advanced
Advanced
General
23-10-00
23-10-00
201
201
201
Advanced
Advanced
Advanced
AUDIO INTEGRATING - DESCRIPTION ....................................................23-50-00
General
23-50-00
Garmin GMA 340 Audio Control Unit Description
23-50-00
01
01
01
Professional
Professional
Professional
AUDIO INTEGRATING - TROUBLESHOOTING.......................................23-50-00
General
23-50-00
Troubleshooting
23-50-00
101
101
101
Professional
Professional
Professional
AUDIO INTEGRATING - MAINTENANCE PRACTICES..........................23-50-00
General
23-50-00
Garmin GMA 340 Audio Control Unit Removal/Installation
23-50-00
Inspection/Check
23-50-00
Adjustment/Test
23-50-00
201
201
201
202
203
Professional
Professional
Professional
Professional
Professional
Page 01
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TABLE OF CONTENTS (Continued)
Title
Chapter
Section
Subject
Page Effectivity
AUDIO INTEGRATING - MAINTENANCE PRACTICES ..........................23-50-00
General
23-50-00
PM 1000 Removal/Installation
23-50-00
Inspection/Check
23-50-00
Adjustment/Test
23-50-00
201
201
201
202
202
Classic
Classic
Classic
Classic
Classic
AUDIO INTEGRATING - MAINTENANCE PRACTICES ..........................23-50-00
General
23-50-00
PM 1000 Removal/Installation
23-50-00
Inspection/Check
23-50-00
Adjustment/Test
23-50-00
201
201
201
202
202
Advanced
Advanced
Advanced
Advanced
Advanced
23 - TOC
Page 02
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STEMME TSA-M
MAINTENANCE MANUAL
COMMUNICATIONS - GENERAL
1. Introduction
A.
This chapter describes and provides maintenance instructions to such components and systems,
which furnish a means of communicating from one occupant to another and between the aircraft
and other aircraft or ground stations.
B.
Technical publications available from the manufacturer or vendor of the various components and
systems, which are not covered in this manual, must be utilized as required for maintenance of
those components and systems.
A.
The standard equipment of the S6 includes the VHF speech communication portion of a GARMIN
GNS 430 VHF Communications Transceiver/ VOR/ ILS Receiver/ GPS Receiver in combination
with a GARMIN GMA 340 Audio Panel. The GNS 430 is mounted in the center of the instrument
panel above the transponder and the GMA 340 above the GNS 430.
For detailed information on the GMA 340 Audio Panel, refer to 23-50-00.
B.
The power supply of the GNS 430 is accomplished via a voltage converter set at 14 Volts-. The
current is connected through the "AVIONICS" switch. The radio and the intercom system are
protected by the circuit breakers labeled NAV/COM and ICS.
C.
The S6 can optionally be equipped with other instruments for communication than the above
mentioned GARMIN systems.
This chapter includes short description and maintenance instructions for optional communication
equipment, if applicable. Refer to manufacturers publications for further information.
23-00-00
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STEMME TSA-M
MAINTENANCE MANUAL
SPEECH COMMUNICATION – DESCRIPTION
1. Introduction
A.
This section covers the portion of the system which utilizes voice modulated electromagnetic
waves to transmit and/or receive messages from air-to-air, or air-to-ground installations. It
includes the VHF speech communications portion of the GNS 430.
The GNS 430 is a combination of a VHF communications transceiver and a Navigation
Management System which includes GPS sensor, VOR/Localizer and Glideslope receivers.
For information on the Navigation Management System of the GNS 430, refer to chapter 34
"NAVIGATION SYSTEMS" and the applicable User Manuals.
B.
For a complete description of the GNS 430, refer to the GARMIN GNS 430 Pilot's Guide and
Reference, P/N 190-00140-00, latest revision.
C.
GNS 430 Specifications
(1) Physical
Unit Size:
W/D/H - 159 mm (6.25 in.) / 279 mm (11.00 in.) / 67 mm
(2.65 in.)
Unit Weight:
3,0 kg (6.6 lbs) installed
(2) Power
Input:
13.8/27.5 Volts DC
(3) Environmental Temperature:
-20°C to +55°C (operating range)
Humidity:
95% non-condensing
Altitude:
-457 m (-1,500 ft) to 15.240 m (50,000 ft)
(4) VHF COM
Channels:
760 (25 kHz spacing) or 2280 (8.33 kHz spacing)
Frequency Range: 118.000 MHz to 136.975 MHz
Transmit Power: 10 watts minimum
2. Description and Operation
A.
Fig. 1 shows the GNS 430 front view with short explanations.
B.
GNS 430 VHF Speech Communication Portion - Description
(1) The GNS 430 speech communications portion consists of a digitally tuned integrated VHF
communications (COM) transceiver. The transceiver receives all narrow- and wide-band
VHF communication transmissions within a frequency range of 118.000 MHz to 136.975 MHz
in 25.0 kHz steps (760 channels) or for use in Europe in 8.33 kHz steps (2280 channels).
The tuning controls are located at the left side of the transceiver front panel. Frequency
tuning is accomplished by rotating the large (for MHz) and small (for kHz) knobs to select a
standby frequency. For its use this frequency must be transferred to the active window.
Auto-tuning enters a frequency from a menu.
(2) The VHF-NAV/COM dipole antenna is laminated onto the inner shell of the vertical stabilizer
and cannot be removed and replaced.
C.
Key and Knob Functions of the GNS 430 VHF Speech Communication Portion (Refer to Figure 01):
(1) The COM power/volume knob (2) controls unit power and communications radio volume.
Press momentarily to enable/disable automatic squelch control.
(2) The VLOC volume knob (1) controls audio volume for the selected VOR/ Localizer frequency.
EFFECTIVITY
23-10-00
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Press momentarily to enable/disable the ident tone.
(3) The large left knob (4) is used to tune the megahertz (MHz) value of the standby frequency
for the COM transceiver or the VLOC receiver, whichever is currently selected by the tuning
cursor.
(4) The small left knob (5) is used to tune the kilohertz (kHz) value of the standby frequency for
the COM transceiver or the VLOC receiver, whichever is currently selected by the tuning
cursor. Press this knob momentarily to toggle the tuning cursor between the COM and
VLOC windows.
(5) The COM flip-flop key (3) is used the swap the active and standby COM frequencies. Press
and hold to select emergency channel (121.500 MHz).
(6) The VLOC flip-flop key (6) is used to swap the active and standby VLOC frequencies (i.e.,
make the selected standby frequency active).
3
2
WPT
DTK
1
DIS
GS
4
5
6
Jackscrew
Access Hole
Garmin GNS 430 Front View
Figure 01
EFFECTIVITY
23-10-00
Page 02
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SPEECH COMMUNICATION - TROUBLESHOOTING
1. General
A.
For troubleshooting procedures of the speech communication portion of the Garmin GNS 430
system, refer to 23-50-00.
EFFECTIVITY
23-10-00
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MAINTENANCE MANUAL
SPEECH COMMUNICATION – MAINTENANCE PRACTICES
1. General
A.
The scope of maintenance is limited to the removal and installation of system components. For
removal and installation procedures of the GNS 430, refer to 34-40-00.
B.
Refer to Garmin 400 Series Installation Manual, P/N 190-00140-02, latest revision for additional
maintenance information on the GNS 430 System.
2. VHF COM Antenna
A.
The VHF COM Antenna is integrated in the vertical tail fin structure. There is no maintenance
required.
EFFECTIVITY
23-10-00
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MAINTENANCE MANUAL
1. Introduction
A.
includes the VHF speech communications portion of the Becker AR 4201.
B.
For a complete description of the Becker AR 4201, refer to the Becker AR 4201 Pilot's Guide and
Reference, P/N 0894.036 - 071, latest revision.
C.
Becker AR 4201 Specifications
(1) Physical
Unit Size:
W/D/H - 60.6 mm (2.39 in.) / 192 mm (7.56 in.) / 60.6 mm
(2.39 in.)
Unit Weight:
(2) Power
Input:
13.8 Volts DC
“Standby”
< 70 mA
Reception mode < 500 mA
Transmission mode < 2.5 A
Humidity:
95% non-condensing
Altitude:
-457 m (-1,500 ft) to 15.240 m (50,000 ft)
(4) VHF COM
Channels:
A.
Becker AR 4201 Speech Communication Portion - Description
(1) The Becker AR 4201 VHF transceiver enables voice communication on 760 channels in the
118.000 MHz to 136.975 MHz range with a channel spacing of 25 kHz.speech.
B.
Key and Knob Functions of the Becker AR 4201 Speech Communication Portion (Ref. to Figure 01):
(1) The COM power/volume knob (ON/OFF switch), combined with volume control is for
activation and adjustment of volume.
(2) The Function key (”MDE”) is for mode selection.
(3) The Exchange key (key with up and down arrow) has the following functions depending on
selected mode:
Mode 1:
Exchange of preset frequency and acti e frequency.
Mode 3:
Switching between temperature and operating voltage indication.
(4) The Store key (”STO”) provides storage of set frequency or in mode 2 a change between the
channel selection mode and scan mode.
(5) The Squelch key (”SQL”) is for switching the squelch on or off. When the key is pressed, the
bottom line indicated ON or OFF.
(6) The Frequency selector switch (outer outer rotary switch of right control knob) switches the
indicated frequency in 1 MHz steps or the storage channel upwards or downwards in steps
of 10.
EFFECTIVITY
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(7) The Frequency selector (inner rotary switch of right control knob) switches the indicated
frequency in 25 kHz steps or the storage channel by 1 step in each case upwards or
downwards, without carry over.
EFFECTIVITY
23-10-00
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1. General
A.
The scope of maintenance is limited to the removal and installation of the Becker AR 4201.
B.
Refer to Becker AR 4201 Installation and Operation Manual, P/N 0894.036 - 071, latest revision for
additional maintenance information on the Becker AR 4201.
2. VHF COM Antenna
A.
required.
3. Becker AR 4201 Removal/Installation
A.
Remove Becker AR 4201
(1) Ensure battery and main avionics switches are in OFF position.
(2) Remove instrument panel cover (Refer to 31-10-00).
(3) Disconnect electrical connectors and associated wiring to allow removal of the Becker AR
4201 VHF COM instrument.
(4) Remove screws securing instrument to panel front side.
(5) Carefully remove Becker AR 4201 from panel rack by sliding out of the panel tray.
B.
Install Becker AR 4201
CAUTION:
CHECK WIRING CONNECTIONS FOR ERRORS BEFORE INSERTING THE
BECKER AR 4201 INTO THE TRAY. INCORRECT WIRING COULD CAUSE
INTERNAL COMPONENT DAMAGE.
(1) Slide the VHF instrument into the rack.
(2) Insert screws to fix instrument to panel rack.
(3) Connect electrical wiring to Becker AR 4201 VHF COM instrument. Pay attention to correct
cable routing.
(4) Install instrument panel cover (Refer to 31-10-00).
(5) Perform functional test.
EFFECTIVITY
23-10-00
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STEMME TSA-M
MAINTENANCE MANUAL
1. Introduction
A.
includes the VHF speech communications portion of the Becker AR 4201.
B.
For a complete description of the Becker AR 4201, refer to the Becker AR 4201 Pilot's Guide and
Reference, P/N 0894.036 - 071, latest revision.
C.
Becker AR 4201 Specifications
(1) Physical
Unit Size:
W/D/H - 60.6 mm (2.39 in.) / 192 mm (7.56 in.) / 60.6 mm
(2.39 in.)
Unit Weight:
(2) Power
Input:
13.8 Volts DC
“Standby”
< 70 mA
Reception mode < 500 mA
Transmission mode < 2.5 A
Humidity:
95% non-condensing
Altitude:
-457 m (-1,500 ft) to 15.240 m (50,000 ft)
(4) VHF COM
Channels:
A.
Becker AR 4201 Speech Communication Portion - Description
(1) The Becker AR 4201 VHF transceiver enables voice communication on 760 channels in the
118.000 MHz to 136.975 MHz range with a channel spacing of 25 kHz.speech.
B.
Key and Knob Functions of the Becker AR 4201 Speech Communication Portion (Ref. to Figure 01):
(1) The COM power/volume knob (ON/OFF switch), combined with volume control is for
activation and adjustment of volume.
(2) The Function key (”MDE”) is for mode selection.
(3) The Exchange key (key with up and down arrow) has the following functions depending on
selected mode:
Mode 1:
Exchange of preset frequency and acti e frequency.
Mode 3:
Switching between temperature and operating voltage indication.
(4) The Store key (”STO”) provides storage of set frequency or in mode 2 a change between the
channel selection mode and scan mode.
(5) The Squelch key (”SQL”) is for switching the squelch on or off. When the key is pressed, the
bottom line indicated ON or OFF.
(6) The Frequency selector switch (outer outer rotary switch of right control knob) switches the
indicated frequency in 1 MHz steps or the storage channel upwards or downwards in steps
of 10.
EFFECTIVITY
23-10-00
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(7) The Frequency selector (inner rotary switch of right control knob) switches the indicated
frequency in 25 kHz steps or the storage channel by 1 step in each case upwards or
downwards, without carry over.
EFFECTIVITY
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1. General
A.
The scope of maintenance is limited to the removal and installation of the Becker AR 4201.
B.
Refer to Becker AR 4201 Installation and Operation Manual, P/N 0894.036 - 071, latest revision for
additional maintenance information on the Becker AR 4201.
2. VHF COM Antenna
A.
required.
3. Becker AR 4201 Removal/Installation
A.
Remove Becker AR 4201
(3) Disconnect electrical connectors and associated wiring to allow removal of the Becker AR
4201 VHF COM instrument.
(4) Remove screws securing instrument to panel front side.
(5) Carefully remove Becker AR 4201 from panel rack by sliding out of the panel tray.
B.
Install Becker AR 4201
CAUTION:
BECKER AR 4201 INTO THE TRAY. INCORRECT WIRING COULD CAUSE
(1) Slide the VHF instrument into the rack.
(2) Insert screws to fix instrument to panel rack.
(3) Connect electrical wiring to Becker AR 4201 VHF COM instrument. Pay attention to correct
cable routing.
(4) Install instrument panel cover (Refer to 31-10-00).
(5) Perform functional test.
EFFECTIVITY
23-10-00
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AUDIO INTEGRATING – DESCRIPTION
1. General
A.
This section covers that portion of the system which controls the output of the communications
and navigation receivers into the flight crew headphones and speakers, and the output of the
flight crew microphones into the communication transmitters.
1. Garmin GMA 340 Audio Control Unit Description
A.
The GMA 340 intercom system consists primarily of the GMA 340 audio control unit, located on
the instrument panel in the avionics column, the pilot and co-pilot audio jacks mounted on the
middle console near the seat backs, and the Push-To-Talk (PTT) switches located on the control
sticks.
The Garmin GMA 340 Audio Panel (Refer to Figure 201) provides audio amplification, audio
selection, marker beacon control (optional), and a voice activated intercom system for the headsets
and microphones.
The system allows audio switching for up to three transceivers (COM 1,COM 2, and COM 3) and
five receivers (NAV 1, NAV 2, ADF, DME, and MKR). A fail-safe mode connects the pilot
headphone and microphone to COM 1 if power is removed or if the Mic Selector switch is turned
to the OFF position.
B.
For a complete description of the GMA 340 Audio Panel, refer to the GARMIN GMA 340 Audio
Panel Pilot's Guide, P/N 190-00149-10, Rev. A, or higher.
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AUDIO INTEGRATING - TROUBLESHOOTING
1. General
A.
This section lists some of the more common troubles, which may be encountered in maintaining
the audio integrating system, their probable causes and remedies
B.
If a problem on the audio integrating system occurs, at first check all electrical connections and
wiring for proper conditions.
2. Troubleshooting
A.
Refer to wiring diagrams P308-150.014 and P312-250.011.
B.
For more details and interpreting possible error messages of the GNS 430W and GMA 340 please
refer to the manuals of the manufacturers.
Trouble
Probable Cause
No power supply at GNS 430W
Remedy
Switch on battery switch and
Avionics Master
GNS 430W not fully inserted into the
rack
Make sure that GNS 430W
is proper inserted and locked
No power supply at GMA 340
Switch on battery switch and
Avionics Master
GMA 340 not fully inserted into the
rack
Make sure that GMA 340 is
proper inserted and locked
GNS 430W does not transmit when PTT
is pushed
Wrong settings at Audio Panel GMA
340
Check settings and activate
COM1
Lamp COM1 MIC does not blink when
PTT is pushed
Connection between stick and Audio
Panel interrupted
Check stick connectors S1,
S2 and panel plug P3
Ground station does not receive voice
although GNS 430W shows “TX”
Wrong frequency tuned
Verify that the correct
frequency is tuned
Headsets Pilot and Copilot are
reversed
Pilot or Crew isolation activated on
GMA 340
Microphone of the headset defective
Plug Headsets into the
correct related sockets
Deactivate pilot or crew
isloation
Replace headset
COM antenna not proper connected
Check antenna connections
and wiring
No display on GNS 430W (dark screen)
when switched on
No display on GMA 340 (dark lights)
when switched on
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Trouble
No ground station voice is audible
although the GNS430 shows “RX”
Probable Cause
Volume setting at GNS430, GMA340
or at Headset too low
Remedy
Adjust Volume settings
Squelch setting at GNS430 too high
Reduce squelch setting
Wrong settings at GMA340
Activate COM1 , deactivate
pilot or crew isolation at
GMA340
Replace headsets
Earphones of Headset defective
Environmental noise audible in
earphones although neither pilot nor
copilot is talking
Voice squelch setting at GMA340 too
low
Set BOTH squelch to a
suitable level where only the
voices will activate the
intercom
Audio signals audible on one side of
headphones only
Headset set to Stereo
Set headphone to MONO
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AUDIO INTEGRATING – MAINTENANCE PRACTICES
1. General
A.
This section provides maintenance information for that portion of the system which controls the
output of the communications and navigation receivers into the flight crew headphones and
speakers, and the output of the flight crew microphones into the communication transmitters.
B.
Refer to Garmin GMA 340 Audio Panel Installation Manual, P/N 190-00149-01, Rev. K or later for
additional maintenance information on the GMA 340.
2. Garmin GMA 340 Audio Control Unit Removal/Installation
A.
Remove Garmin GMA 340 Audio Control Unit
(2) Insert a 3/32 Allen wrench into the jackscrew access hole on the faceplate (Refer to Figure
201).
(3) Turn jackscrew counterclockwise to loosen locking cam. Cam will move the unit out and
disengage from the electrical connectors.
(4) Carefully pull audio control unit from the rack.
B.
Install Garmin GMA 340 Audio Control Unit
CAUTION:
GMA 340 INTO THE TRAY. INCORRECT WIRING COULD CAUSE INTERNAL
COMPONENT DAMAGE.
(1) Slide the unit into the rack until the jackscrew makes contact with the receptacle located in
the back plate.
(2) Insert a 3/32 Allen wrench into the jackscrew access hole on the faceplate (Refer to Figure
201).
(3) Turn the Allen wrench clockwise until the unit is secured in the rack. Continue turning until
tight, but do not over-tighten.
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3. Inspection/Check
A.
Except for marker beacon operation (optional), an in-aircraft checkout may be performed in the
aircraft on the ramp with known good microphone, headset, speaker and avionics receivers. Item
numbers in parentheses refer to front panel controls shown in figure 201.
(1) Lamps
(a) Apply power to the unit by rotating the pilot intercom knob (2) clockwise.
(b) The GMA 340 test button (10) checks the internal LED annunciators and marker beacon
LED's (12). Press TEST to confirm operation of the LED's.
(c) Cover the photocell (11) with a finger and observe that the LED annunciators dim
automatically.
(d) Check the front panel backlighting and dimming function. Each annunciation is
illuminated.
(2) Fail Safe Operation
(a) Turn the unit off by rotating the pilot intercom knob (2) counter clockwise.
(b) Check the failsafe operation by exercising the COM 1 microphone, microphone key and
audio over the headphones.
MKR/BCN
COM
NAV
12
10
11
AOM
SQ
MKR
MUTE
COM1
COM2
COM3
NAV1
DME
NAV2
TEST
ADF
SQ
HI
LO
OFF/
VOL
SENS
SPKR
COM1
MIC
COM2
MIC
COM3
MIC
COM
1/2
CABIN AUDIO
PILOT
ICS ISOLATION
VOL
PULL
PA
CREW
PASS
VOL
COPILOT
PILOT
1
3
2
Jackscrew
Access Hole
4
5
6
7
8
9
ICS
GMA 340 Audio Panel, Front View
Figure 201
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(c) Turn the unit back on to continue testing.
(3) Transceiver
(a) Perform a ramp test radio check by exercising the installed transceivers, microphone,
microphone key and audio over the headphones and speaker. Verify that
communications are loud and clear and PTT operation is correct.
(4) ICS
(a) Set the intercom to the ALL mode [Crew (6) and Pilot (7) LED's off.]
(b) Plug in headsets at pilot and co-pilot ICS position.
(c) Adjust squelch (9) and volume (8) for each position and verify that the ICS is working
properly.
(d) Check ICS positions for isolation and proper operation of volume and squelch controls
(1, 2, 8 and 9).
(e) Press the PA button (5). Verify that microphone audio is heard over the speaker.
(5) Aircraft Receivers
(a) Select the audio source corresponding to each installed avionics unit and check for audio
over the headsets.
(b) Check for pilot/copilot audio isolation when pressing the COM 1/2 button (3).
(c) Press the SPKR button (4) and verify that any selected audio is heard over the speaker.
4. Adjustment / Test
A.
The following adjustments can be made through access holes in the top cover of the GMA 340:
(1) Marker beacon audio level (optional).
(2) Marker beacon sensitivity (optional).
(3) Aircraft radio speaker output level
(4) Pilot PA microphone speaker output level
(5) Copilot PA microphone speaker output level
(5) MUSIC 1 mute trip level
Refer to Garmin GMA 340 Audio Panel Installation Manual, P/N 190-00149-01, Rev. K or later for
detailed instructions regarding these adjustments.
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1. General
A.
B.
The PS Engineering Inc. PM 1000 intercom system consists primarily of the PM 1000 audio control
unit, located on the instrument panel in the avionics column, the pilot and co-pilot audio jacks
mounted on the middle console near the seat backs, and the Push-To-Talk (PTT) switches located
on the control sticks.
The PM 1000 is a 4-place, panel-mounted intercom with individual volume and squelch controls
for the pilot and copilot. Both pilot and copilot have transmit capabilities over the radio. The PM
1000 allows only the person who presses their PTT to be heard over the aircraft radio. If both pilot
and copilot press the PTT at the same time, the copilot will override. Pilot regains priority by
switching the unit off.
C.
For a complete description of the PM 1000 Intercom, refer to the PM 1000 Pilot's Guide, P/N 202 123 - 0001, latest Revision.
D.
Refer to PM 1000 Intercom Installation Manual, P/N 202 - 123 - 0003, latest Revision.
2. PM 1000 Intercom Unit Removal/Installation
A.
Remove PM 1000 Intercom
(3) Disconnect electrical connector to allow removal of the PM 1000 Intercom.
(4) Remove screws securing intercom to panel front side.
(5) Carefully remove PM 1000 from panel rack by sliding out of the panel tray.
B.
Install PM 1000 Intercom
CAUTION:
(1)
(2)
(3)
(4)
(5)
CHECK WIRING CONNECTIONS FOR ERRORS BEFORE INSERTING THE PM
1000 INTERCOM INTO THE PANEL. INCORRECT WIRING COULD CAUSE
Slide the intercom into the rack.
Insert screws to fix PM 1000 to panel rack.
Connect electrical plug to PM 1000 Intercom. Pay attention to correct cable routing.
Install instrument panel cover (Refer to 31-10-00).
Perform functional test.
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3. Inspection/Check
A.
An in-aircraft checkout may be performed in the aircraft on the ramp with known good
microphone, headset, speaker and avionics receivers. For further information refer to PM 1000
Intercom Installation Manual, P/N 202 - 123 - 0003, latest Revision.
(1) Apply power to the aircraft and avionics.
(2) Plug headsets into the pilot and copilot positions.
(3) Verify that the pilot position can transmit and receive with the PM 1000 II in the OFF position
(left hand/upper volume knob fully counterclockwise).
(4) Rotate the pilot volume clockwise, about half way. Verify that the “Pwr/Xmt” light comes on,
and shows green. If the LED is red, stop testing and trouble-shoot the microphone PTT
installation.
(5) Verify that the pilot can transmit and receive on the COM transceivers.
(6) Verify that the LED in the intercom changes from green to red when a microphone is keyed.
(7) Verify proper intercom operation for pilot and copilot. For more information, refer to PM 1000
installation manual.
(8) Verify proper transmit and receive operation on the copilot position, noting that the copilot
PTT switch allows proper transmission on the selected transceiver.
(9) Verify proper Intercom system operation in the ALL and ISO modes.
(10) Verify that the intercom system does not adversely affect any other aircraft system by
systematically switching the unit on and off, while monitoring the other avionics and
electrical equipment on the aircraft.
A.
The following adjustments can be made with control knobs on the cover of the PM 1000 II:
(1) Pilot’s volume control knob to adjust loudness of the intercom and music for the pilot’s
headset.
(2) Copilot’s volume control knob to adjust the volume for the copilot.
(3) Adjustment of the trip level for individual VOX circuits of pilot and copilot (squelch control)
allows the use of dissimilar headsets.
(5) Mode selection between ISO (pilot isolated from intercom, only connected to radio) and ALL.
Refer to PM 1000 Installation Manual, P/N 202 - 123 - 0003, latest Revision for detailed instructions
regarding these adjustments.
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1. General
A.
B.
The PS Engineering Inc. PM 1000 intercom system consists primarily of the PM 1000 audio control
unit, located on the instrument panel in the avionics column, the pilot and co-pilot audio jacks
mounted on the middle console near the seat backs, and the Push-To-Talk (PTT) switches located
on the control sticks.
The PM 1000 is a 4-place, panel-mounted intercom with individual volume and squelch controls
for the pilot and copilot. Both pilot and copilot have transmit capabilities over the radio. The PM
1000 allows only the person who presses their PTT to be heard over the aircraft radio. If both pilot
and copilot press the PTT at the same time, the copilot will override. Pilot regains priority by
switching the unit off.
C.
For a complete description of the PM 1000 Intercom, refer to the PM 1000 Pilot's Guide, P/N 202 123 - 0001, latest Revision.
D.
Refer to PM 1000 Intercom Installation Manual, P/N 202 - 123 - 0003, latest Revision.
2. PM 1000 Intercom Unit Removal/Installation
A.
Remove PM 1000 Intercom
(3) Disconnect electrical connector to allow removal of the PM 1000 Intercom.
(4) Remove screws securing intercom to panel front side.
(5) Carefully remove PM 1000 from panel rack by sliding out of the panel tray.
B.
Install PM 1000 Intercom
CAUTION:
(1)
(2)
(3)
(4)
(5)
CHECK WIRING CONNECTIONS FOR ERRORS BEFORE INSERTING THE PM
1000 INTERCOM INTO THE PANEL. INCORRECT WIRING COULD CAUSE
Slide the intercom into the rack.
Insert screws to fix PM 1000 to panel rack.
Connect electrical plug to PM 1000 Intercom. Pay attention to correct cable routing.
Install instrument panel cover (Refer to 31-10-00).
Perform functional test.
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3. Inspection/Check
A.
An in-aircraft checkout may be performed in the aircraft on the ramp with known good
microphone, headset, speaker and avionics receivers. For further information refer to PM 1000
Intercom Installation Manual, P/N 202 - 123 - 0003, latest Revision.
(1) Apply power to the aircraft and avionics.
(2) Plug headsets into the pilot and copilot positions.
(3) Verify that the pilot position can transmit and receive with the PM 1000 II in the OFF position
(left hand/upper volume knob fully counterclockwise).
(4) Rotate the pilot volume clockwise, about half way. Verify that the “Pwr/Xmt” light comes on,
and shows green. If the LED is red, stop testing and trouble-shoot the microphone PTT
installation.
(5) Verify that the pilot can transmit and receive on the COM transceivers.
(6) Verify that the LED in the intercom changes from green to red when a microphone is keyed.
(7) Verify proper intercom operation for pilot and copilot. For more information, refer to PM 1000
installation manual.
(8) Verify proper transmit and receive operation on the copilot position, noting that the copilot
PTT switch allows proper transmission on the selected transceiver.
(9) Verify proper Intercom system operation in the ALL and ISO modes.
(10) Verify that the intercom system does not adversely affect any other aircraft system by
systematically switching the unit on and off, while monitoring the other avionics and
electrical equipment on the aircraft.
A.
The following adjustments can be made with control knobs on the cover of the PM 1000 II:
(1) Pilot’s volume control knob to adjust loudness of the intercom and music for the pilot’s
headset.
(2) Copilot’s volume control knob to adjust the volume for the copilot.
(3) Adjustment of the trip level for individual VOX circuits of pilot and copilot (squelch control)
allows the use of dissimilar headsets.
(5) Mode selection between ISO (pilot isolated from intercom, only connected to radio) and ALL.
Refer to PM 1000 Installation Manual, P/N 202 - 123 - 0003, latest Revision for detailed instructions
regarding these adjustments.
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CHAPTER 24
ELECTRICAL POWER
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page Effectivity
ELECTRICAL POWER - GENERAL...............................................................24-00-00
Introduction
24-00-00
General Description
24-00-00
01
01
01
ELECTRICAL POWER – TROUBLESHOOTING ........................................24-00-00
Troubleshooting
24-00-00
101
101
BATTERY SYSTEM – DESCRIPTION ...........................................................24-31-00
Introduction
24-31-00
24-31-00
01
01
01
BATTERY – MAINTENANCE PRACTICES...................................................24-31-00
General
24-31-00
Battery Removal/Installation
24-31-00
201
201
201
EXTERNAL ALTERNATOR SYSTEM – DESCRIPTION.............................24-32-00
Introduction
24-32-00
24-32-00
01
01
01
INTERNAL ALTERNATOR SYSTEM – DESCRIPTION .............................24-33-00
Introduction
24-33-00
24-33-00
01
01
01
SOLAR PANEL SYSTEM – GENERAL...........................................................24-40-00
Introduction
24-40-00
General Description
24-40-00
01
01
01
Solar Panel
Solar Panel
Solar Panel
SOLAR PANEL SYSTEM – MAINTENANCE PRACTICES ........................24-40-00
General
24-40-00
Functional Check of the Solar Panel
24-40-00
Cleaning and Care of the Solar Panel
24-40-00
201
201
201
201
Solar Panel
Solar Panel
Solar Panel
Solar Panel
DC LOAD DISTRIBUTION – GENERAL ......................................................24-60-00
Introduction
24-60-00
General Description
24-60-00
01
01
01
DC LOAD DISTRIBUTION – TROUBLESHOOTING................................24-60-00
Troubleshooting
24-60-00
101
101
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TABLE OF CONTENTS (Continued)
Title
Chapter
Section
Subject
Page Effectivity
MAIN BUS – MAINTENANCE PRACTICES ................................................24-61-00
General
24-61-00
Main Bus Removal/Installation .................................................................24-61-00
Adjustment / Test
24-61-00
201
201
202
202
ENGINE BUS – MAINTENANCE PRACTICES............................................24-62-00
General
24-62-00
Engine Bus Removal/Installation
24-62-00
Adjustment / Test
24-62-00
201
201
202
202
AVIONICS BUS – MAINTENANCE PRACTICES........................................24-63-00
General
24-63-00
Avionics Bus Removal/Installation
24-63-00
Adjustment / Test
24-63-00
201
201
201
202
INTERNAL GENERATOR BUS – MAINTENANCE PRACTICES.............24-64-00
General
24-64-00
Internal Generator Bus Removal/Installation
24-64-00
Adjustment / Test
24-64-00
201
201
202
202
ELECTRICAL GROUND – MAINTENANCE PRACTICES........................24-65-00
General
24-65-00
Electrical Ground Removal/Installation
24-65-00
Adjustment / Test
24-65-00
201
201
201
202
24 - TOC
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ELECTRICAL POWER - GENERAL
1. Introduction
A.
This chapter describes such units and components, which generate, control, and supply AC and
DC electrical power for other systems.
A.
Reference:
(1) General Wiring Diagram P308-006.000
B.
The aircraft is equipped with a 14V DC electrical system. It is powered by a 12V battery, a belt
driven external alternator, and the internal generator of the ROTAX engine.
The battery provides electrical power to the system when the engine is not running. It is charged
by the external alternator when the engine is running. The battery is located at the rear part of the
steel frame.
The external alternator provides electrical power to the system when the engine is running. It is
the main power source of the system and charges the battery. The alternator is mounted at the left
front side of the engine body, inside the firewall.
The internal generator is mounted at the crankshaft of the engine. It is able to provide electrical
power without a battery. The internal generator powers the main fuel feeder pump, the fuel
circulation pump and the turbo-charger control unit (TCU). Thanks to the internal generator, the
engine is able to run independent from the main electrical system.
C.
Adjustment / Test
The following voltages levels indicate the condition of the electrical system
Item
Condition
Voltage
Battery, engine not running
without load
12,4 +/- 0,4V
with load
12,0 +/- 0,4V
battery is to charge
< 11,5 V
Engine running, alternator on
depending on load and rpm
13,8 +/- 0,4V
Internal generator bus
13,8 +/- 0,4V
The voltage can be measured either by the on-board voltmeter or with a handheld multimeter on
the main bus against steel frame ground.
NOTE:
The aircraft's fiber composite airframe doesn't provide electrical ground. Electrical
ground is provided on different ground points, connected to the steel frame via wires.
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That's why there is a significant voltage drop between battery and load devices,
depending on load current and wire length. That's why a voltage below the limits
mentioned above and measured directly at a load device is not relevant to estimate the
system condition.
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ELECTRICAL POWER - TROUBLESHOOTING
1. General
A.
the electrical system, their probable causes and remedies
B.
If a problem on the electrical system occurs, at first check all electrical connections and wiring for
proper conditions.
2. Troubleshooting
Trouble
Probable Cause
Remedy
No power on electrical system
voltmeter shows 0
battery discharged or disconnected
check battery voltage and
connectors, especially
ground
CB MASTER activated
troubleshoot circuit and reset
CB
defective master relay
check / replace master relay
red warning light on when engine is
running
voltmeter indicates less than 13 V
amperemeter indicates discharge
no alternator output:
CB ALT or ALT FIELD activated
defective belt
defective alternator
check CB ALT
check CB ALT FIELD
check belt drive
replace alternator
yellow generator warning light on when
engine is running
engine rpm too low
yellow light should go off at
more than 1500 rpm
defective voltage regulator
replace regulator
when switch ENG on:
no TCU self test
main and circulation fuel pump not
working
no yellow generator warning light on
no power on internal generator system check both fuses INT GEN
on instrument panel and
TCU board
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BATTERY SYSTEM - DESCRIPTION
1. Introduction
A.
This chapter describes the function of the battery related components of the electrical system.
B.
Reference
(1) General Wiring Diagram P308-006.000
2. Descriptions and Operation
A.
B.
The battery system concists of the following components:
ATA
Description
Location
24-31-01
24-31-02
24-31-03
24-31-04
24-31-05
24-31-06
battery
CB master
master relais
shunt
amperemeter
voltmeter
rear steel frame
instrumentpanel
tcu board
tcu board
instrumentpanel
instrumentpanel
The battery is mounted on the rear part of the steel frame. It's negative pole is connected directly
to the master ground stud at the steel frame. The positive pole is connected to the starter relay and
to the master relay. The master relay is controlled from the master switch, marked BATT, on the
instrument panel. The master relay is ground-switched, that means the positive side of the coil is
connected permanently to the battery plus pole, while the BATT switch provides ground to
activate the relay. The control circuit of the master relay is not fused.
From the master relay the power runs via a shunt to the MASTER CB. The shunt provides a
current-related voltage to the amperemeter, indicating charging or discharging of the battery. At
the MASTER CB the main bus is connected. The voltage of the main electrical system is measured
at the main bus and displayed by the voltmeter. The voltmeter is marked red at voltage below
11,5V. At and below that voltage a battery charging is mandatory.
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BATTERY - MAINTENANCE PRACTICES
1. General
A.
The maintenance limits to removal and installation of the battery. For the necessary regular
service refer to Chapter 12, Section "Battery - Servicing".
2. Battery Removal/Installation
A.
Remove Battery
(1) Ensure BATT switch is in OFF position.
(2) Remove right side engine cowling.
(3) Remove battery cover.
(4) Disconnect ground cable.
(5) Disconnect positive cable.
(6) Remove battery from mounting tray.
B.
Install Battery
(1) Place battery into mounting tray, positive pole points in flight direction.
(2) Connect positive cable. Apply a small amount of acid-free grease to protect the stud.
(3) Connect negative cable. Apply a small amount of acid-free grease to protect the stud.
(4) Install and secure the battery cover.
(5) Switch BATT on and check voltage.
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EXTERNAL ALTERNATOR SYSTEM - DESCRIPTION
1. Introduction
A.
This section describes the design and function of the external, belt-driven alternator system.
B.
For detailed maintenance information, refer to applicable engine maintenance manual (Ref. Intro).
C.
Reference:
(1) General Wiring Diagram (Refer to Fig. 01(3), 91-00-01)
A.
The alternator system consists of the following components:
ATA
Description
Location
24-32-01
24-32-02
24-32-03
24-32-04
24-32-05
external alternator
CB alternator
CB alt field
alternator warning light
fuse alternator warning light
engine
instrument panel
instrument panel
instrument panel
instrument panel
B.
The external alternator is mounted on the left front side of the engine body. It includes built-in
rectifiers and regulator which convert the origin 3-phases alternating voltage to directed voltage
of nominal 14V. Alternator's ground connection is provided by alternator housing, alternator
mounting and engine body to the steel frame. The positive pole is connected via a plug at the
right side fire wall to ALTERNATOR CB. From this CB alternator power is connected to the main
bus. The voltage of the alternator is displayed by the voltmeter. Because the output voltage of the
alternator is higher than battery voltage, a running alternator will charge the battery. This is
indicated at the amperemeter: positive current means charging, negative current discharging of
the battery.
The alternator needs electrical power from a connected battery for a proper function. That's why
the B+ pole must not removed from a running alternator. The alternator's field is supplied from
the electrical system via the CB ALT FIELD. There is a red warning light that indicates low or non
output of alternator.
C.
Fuses
All related fuses are located on a fuse holder under the glare shield, behind the right portion of
the instrument panel. The position of the fuses is marked on the cover of the fuse holder.
Fuse
ALT LMP
Rating
1 amp
24-32-00
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
INTERNAL ALTERNATOR SYSTEM - DESCRIPTION
1. Introduction
A.
This section describes the design and function the internal, crank shaft mounted generator system.
B.
For detailed maintenance information, refer to applicable engine maintenance manual (Ref. Intro).
C.
Reference:
A.
The alternator system consists of the following components:
ATA
Description
Location
24-32-01
24-32-02
24-32-03
24-32-04
24-32-05
fuse internal generator
internal generator
voltage regulator
internal generator warning light
capacitor
TCU board
engine
TCU board
instrument panel
TCU board
24-64-01 fuse internal generator
24-64-02 diode
24-64-03 internal generator bus
instrument panel
TCU board
TCU board
B.
The internal alternator is mounted on the aft end of the engine's crank shaft. It consists of a
rotating permanent magneto that induces charge to the generator coil. It's output is connected via
a plug at the upper side of the fire wall to TCU board on the right side of steel frame. The output
wires carry an alternating voltage to a remote rectifier-regulator on the TCU board. The fuse INT
GEN on the TCU board protects the output of the regulator. This regulator outputs nominal 14V.
The regulator needs electrical power from a connected battery for a proper function. This
reference voltage is provided by the interconnection wire from the instrument panel to the TCU
board, protected by another fuse INT GEN on the instrument panel. Once started by the main
electrical system, the voltage regulation process is buffered by the capacitor on the TCU board,
simulating a battery. From that moment the system is able to operate independent from main
electrical system. The diode in the interconnection wire prevents current flow from internal
generator system to main electrical system. Caused by this diode, the battery voltage measured
on the internal generator system is approx. 0,5V lower than on the main electrical system.
There is a yellow warning light that indicates low or non output of generator.
C.
Fuses
The related fuses are located on:
- fuse holder under the glare shield, behind the right portion of the instrument panel
- fuse holder on TCU board
The position of the fuses is marked on the cover of the fuse holder.
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MAINTENANCE MANUAL
Fuse
Rating
INT GEN (on instrument panel) 10 amp
INT GEN (on TCU board)
15 amp
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STEMME TSA-M
MAINTENANCE MANUAL
SOLAR PANEL SYSTEM - GENERAL
1. Introduction
A.
This chapter describes components and maintenance of the solar panel system, installed as option
on the upper center fuselage cowling.
A.
The solar panel system of the STEMME S6 allows a battery charge independently of the engine
operation, i.e. both during gliding operation as well as in the off state on the ground with
electrical Master-switch (Batt) deactivated.
B.
The solar panel system consists of the solar cells, arranged in the front area of the upper center
fuselage cowling, the charge controller and wiring.
For details refer to block diagram P308-250.070, chapter 91-00-04.
C.
The four solar cells are connected in parallel and short-circuit-proof in themselves. The cells are
bonded to the shell of the upper center fuselage cowling and wired inside the center fuselage by a
connecting plug to the charge controller.
D.
The charge controller is internally fused (refer 91-00-04) and attached directly by screws on the
battery box. The controller is permanently connected to the battery and thus permanently
activated when exposed to solar radiation (charging of the battery with electrical Master-switch
deactivated with sufficient solar radiation).
EFFECTIVITY
Aircraft equipped with Solar Panel
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
SOLAR PANEL SYSTEM - MAINTENANCE PRACTICES
1. General
A.
The maintenance of the solar panel system is limited to functional check of the solar cells and
cleaning and care.
2. Functional Check of the Solar Panel
A.
Exposed to full solar radiation a short excursion of the a/c voltage on the voltmeter of the
instrument panel can be recognized when the connecting plug of the solar panel cowling is
connected to the a/c electrical system.
3. Cleaning and Care of the Solar Panel
A.
Cleaning and Care
(1) To ensure maximum performance of the solar panel system and to avoid damage the solar
panel should be cleaned regularly and inspected for damage.
(2) Clean the solar panel with a soft, scratch-free and moistened cloth.
In case of gross contamination carefully clean with clear water and a soft sponge to avoid
scratching.
(3) Visually inspect the solar panels on the surface and round the edge for damage and for
detachment from the cowling shell.
EFFECTIVITY
Aircraft equipped with Solar Panel
24-40-00
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
DC LOAD DISTRIBUTION - GENERAL
1. Introduction
A.
This chapter describes such units and components, which distribute DC electrical load to the
electrical aircraft systems.
A.
Reference:
B.
The system consists of the following subsystems:
24-61-00
24-62-00
24-63-00
24-64-00
24-65-00
C.
Main bus
Engine bus
Avionics bus
Internal Generator bus
Electrical Ground system
The electrical system is designed in a way that allows both operation modes of the aircraft:
powered flight and soaring without engine on. That's why the distribution system includes means
to separately shut off the electrical subsystems related to the engine. With engine off, the aircraft
can continue the flight while the electrical system is powered by the battery only.
Caused by this two possible operation modes of the aircraft, the electrical equipment is classified
into systems essential for flight and systems non-essential for flight. Most of the engine
monitoring systems are classified as non-essential for flight, because the aircraft can fly safe
without engine.
The most of the non-essential for flight systems are protected by fuses and not reachable by the
pilot during flight.
The systems essential for flight are protected by push-to-release circuit breakers. These CBs are
arranged in two vertical rows on the right side of the instrument panel, visible and reachable by
the pilot.
A number of systems requiring on/of switches are protected by rocker switches on the left lower
instrument panel. These rocker switches include circuit breaker functionality.
To provide the option to operate engine system and main system separately, the master switch of
the electrical system is separated into the functions BATT(ery)and ENG(ine). The switches are
mechanical interlocked: it is not possible to switch ENG on without switch BATT on. And it is not
possible to switch BATT off without switching ENG off. That is necessary to avoid untypical
switching conditions in the electrical system, especially related to the alternator.
The base of the electrical distribution system is the main bus. The power of the battery and the
alternators are applied via two master CBs to the main bus. The main bus feeds subsystems
generally necessary for flight.
The engine bus is connected to the main bus via a master CB and the engine bus relay. The relay is
operated by the switch ENG. The engine bus supplies all subsystems necessary for engine
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STEMME TSA-M
MAINTENANCE MANUAL
operation and monitoring. It also powers the alternator field.
The avionics bus is connected to the main bus via protector switch AVIONICS MASTER. This
rocker switch includes circuit breaker function. The avionics bus powers all communication and
navigation instruments.
D.
Adjustment / Test
The following voltages levels indicate the condition of the electrical system.
Item
Condition
Voltage
Battery, engine not running
without load
12,4 +/- 0,4V
with load
12,0 +/- 0,4V
battery is to charge
< 11,5 V
Engine running, alternator on
13,8 +/- 0,4V
Internal generator bus
13,8 +/- 0,4V
The voltage can be measured either by the on-board voltmeter or with a handheld multimeter on
the main bus against steel frame ground.
NOTE:
The aircraft's fiber composite airframe doesn't provide electrical ground. Electrical
ground is provided on different ground points, connected to the steel frame via wires.
That's why there is a significant voltage drop between battery and load devices,
depending on load current and wire length. That's why a voltage below the limits
mentioned above and measured directly at a load device is not relevant to estimate the
system condition.
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STEMME TSA-M
MAINTENANCE MANUAL
DC LOAD DISTRIBUTION - TROUBLESHOOTING
1. General
A.
the DC load distribution system, their probable causes and remedies
B.
If a problem on the electrical system occurs, at first check all electrical connections and wiring for
proper conditions.
2. Troubleshooting
Trouble
Probable Cause
Remedy
No power on electrical system
voltmeter shows 0
battery discharged or disconnected
check battery voltage and
connectors, especially
ground
CB MASTER activated
troubleshoot circuit and reset
CB
defective master relay
check / replace master relay
red warning light on when engine is
running
voltmeter indicates less than 13 V
amperemeter indicates discharge
no alternator output:
CB ALT or ALT FIELD activated
defective belt
defective alternator
check CB ALT
check CB ALT FIELD
check belt drive
replace alternator
yellow generator warning light on when
engine is running
engine rpm too low
yellow light should go off at
more than 1500 rpm
defective voltage regulator
replace regulator
when switch ENG on:
no TCU self test
main and circulation fuel pump not
working
no yellow generator warning light on
no power on internal generator system check both fuses INT GEN
on instrument panel and
TCU board
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
MAIN BUS – MAINTENANCE PRACTICES
1. General
A.
Maintenance is limited to removal and installation of components.
B.
Reference:
C.
The system consists of the following components:
D.
ATA
Description
Location
24-61-01
24-61-02
24-61-03
24-61-04
combined switch BATT and ENG
main bus - section 1
instrument panel
instrument panel
instrument panel
instrument panel
The Main bus is powered when the BATT switch is on. Battery power is applied to the main bus
via CB MASTER. When the engine is running the alternator's power is applied to the main bus via
CB ALTERNATOR. The main bus is physically divided into three sections.
Section 1 is a small bus bar that connects the outputs of the CBs MASTER and ALTERNATOR.
From there a wire runs to the main bus section 2, represented by a bus bar on the input side of the
left row of CBs on the right instrument panel. Refer to Figure 201 for standard layout of CBs.
The following systems are connected to section 2:
(1) Engine bus
(2) Stall warning
(3) Trim
(4) Propeller control
(5) Auxiliary socket
(6) Voltmeter
(7) Amperemeter
Another wire leads from the main bus section 2 to section 3, represented by the rocker switches on
the left lower instrument panel.
Systems connected to section 3:
(1) Avionics bus
(2) Lighting
E.
Troubleshooting:
At any kind of trouble on the main bus, check the CBs and visually check the conditions of the
wiring, the connectors and especially the screw connections of CB's
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MAINTENANCE MANUAL
2. Main Bus Removal/Installation
A.
Before handling single components of the electrical systems, switch BATT off and disconnect the
negative battery wire from aircraft ground.
Circuit breakers and protector rocker switches are latched from the pilt's side into the instrument
panel. Disconnect electrical wires and bus bar from the backside first, than push the elements
carefully out.
A.
The condition of the main bus is displayed on the voltmeter and amperemeter.
For comprehensive test procedure and voltage limits, refer 24-00-00.
Alt Field
Voltmeter
Propeller pitch-control
Auxiliary Socket
Trim
Stall Warning
Engine Bus
Circuit Breakers - Overview
Figure 201
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MAIN BUS – MAINTENANCE PRACTICES
1. General
A.
B.
Reference:
C.
D.
ATA
Description
Location
24-61-01
24-61-02
24-61-03
24-61-04
combined switch BATT and ENG
instrument panel
instrument panel
instrument panel
instrument panel
The Main bus is powered when the BATT switch is on. Battery power is applied to the main bus
via CB MASTER. When the engine is running the alternator's power is applied to the main bus via
CB ALTERNATOR. The main bus is physically divided into three sections.
Section 1 is a small bus bar that connects the outputs of the CBs MASTER and ALTERNATOR.
From there a wire runs to the main bus section 2, represented by a bus bar on the input side of the
left row of CBs on the right instrument panel. Refer to Figure 201 for standard layout of CBs.
(1) Engine bus
(2) Stall warning
(3) Trim
(4) Propeller control
(5) Auxiliary socket
(6) Voltmeter
(7) Amperemeter
Another wire leads from the main bus section 2 to section 3, represented by the rocker switches on
the left lower instrument panel.
(1) Avionics bus
(2) Lighting
E.
Troubleshooting:
At any kind of trouble on the main bus, check the CBs and visually check the conditions of the
wiring, the connectors and especially the screw connections of CB's
EFFECTIVITY
Model S6-RT
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MAINTENANCE MANUAL
2. Main Bus Removal/Installation
A.
Before handling single components of the electrical systems, switch BATT off and disconnect the
carefully out.
A.
The condition of the main bus is displayed on the voltmeter and amperemeter.
For comprehensive test procedure and voltage limits, refer 24-00-00.
Landing Gear CTRL
Stall Warning
Voltmeter
Propeller pitch-control
Auxiliary Socket
Trim
Engine Bus
Landing Gear PWR
Figure 201
EFFECTIVITY
Model S6-RT
24-61-00
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MAINTENANCE MANUAL
ENGINE BUS – MAINTENANCE PRACTICES
1. General
A.
B.
Reference:
C.
ATA
Description
Location
24-62-01
24-62-02
24-62-02
24-62-03
cb engine bus
engine bus relay
engine bus section 1
engine bus section 2
instrument panel
instrument panel
instrument panel
instrument panel
Battery power is applied from the main bus section 2 to the engine bus via CB ENG BUS and
engine bus relay. The relay is operated by the switch ENG. When the engine is running alternator
power is applied to the engine bus. The engine bus is physically divided into two sections.
Section 1 is represented by the fuse holder on the right electronic board, behind the right portion
of instrument panel. The fuses protect engine monitoring and control circuits.
(1) Alternator warning light
(2) Starter control circuit
(3) Cylinder head temperature indication
(4) Oil temp indication
(5) Oil pressure indication
(6) Low fuel warning
(7) Internal generator (interconnection line)
(8) Fuel pressure indication
(9) Tachometer
(10) Ignition retarding module
(11) Fuel flow indication
(12) Fuel level indication
Another wire leads from the engine bus relay to section 2, represented by the two most left
protector rocker switches on the left lower instrument panel.
(1) Transfer Pump
(2) Auxiliary Pump
D.
Fuses
All related fuses are located on a fuseholder under the glare shield, behind the right portion of the
instrument panel. The position of the fuses is marked on the the fuse holder cover.
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MAINTENANCE MANUAL
Fuse
ALT LMP
Starter
OIL P/CHT L
OIL T/CHT R
Low Fuel
INT GEN
FUEL PRESS
TACHO
IGN RET
FUEL FLOW
Fuel L
Fuel R
Rating
1 amp
3 amp
1 amp
1 amp
1 amp
10 amp
1 amp
1 amp
1 amp
3 amp
1 amp
1 amp
The protector rocker switches are latched from the face side into the instrument panel. Disconnect
electrical wires and bus bar from the backside first, than push the elements carefully out.
E.
Troubleshooting:
At any kind of trouble on the engine bus, check the fuses first. Than check visually the conditions
of the wiring, the connectors and especially screw connections.
2. Engine Bus Removal/Installation
A.
Before handling components of the electrical systems, switch BATT off and disconnect the
carefully out.
A.
Power on the engine bus is indicated by:
(1) Audible fuel pumps
(2) The Yellow INT GEN warning light is on.
(3) The red EXT GEN warning light is on.
(4) The TCU performs the self test.
B
For a comprehensive test procedure and voltage limits, refer to 24-00-00.
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AVIONICS BUS – MAINTENANCE PRACTICES
1. General
A.
B.
Reference:
C.
ATA
Description
24-63-01 protector switch AVIONICS MASTER
24-63-02 avionics bus
D.
Location
instrument panel
instrument panel
Battery power is applied from the main bus section 3 to the avionics bus via protector rocker
switch AVIONICS MASTER on the left lower instrument panel. When the engine is running
alternator power is applied to the avionics bus.
The avionics bus is physically represented by the most right row of circuit breakers on the
instrument panel. Refer to Figure 201 for standard layout of avionics Cbs.
Avionics devices not equipped with an own on/off switch are powered immediately powered on
when AVIONICS MASTER is switched on. It is recommended to switch AVIONICS MASTER on
after starting the engine.
The following basic systems are connected to the avionics bus (example):
(1) VHF COMM
(2) Intercom / Audio panel
(3) VHF NAV
(4) XPDR
(5) GPS
(6) EFIS / Artificial horizon
For the currently installed avionics equipment, refer to the effective Equipment List in the aircraft
file.
F.
Troubleshooting:
2. Avionics Bus Removal/Installation
A.
The protector rocker switches and the CBs are latched from the face side into the instrument
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MAINTENANCE MANUAL
carefully out.
A.
To test the avionics bus, switch related instruments or devices on.
Some electronic devices provide the optional indication of their power supply voltage. This can
help to test the actual voltage at the avionics bus.
B
Intercom / Audio Panel
ELT
Soaring Computer / El. Variometer
NAV / GPS
EFIS / Artificial Horizon
Transponder
COM-Radio
Figure 201
24-63-00
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MAINTENANCE MANUAL
AVIONICS BUS – MAINTENANCE PRACTICES
1. General
A.
B.
Reference:
C.
ATA
Description
24-63-01 protector switch AVIONICS MASTER
24-63-02 avionics bus
D.
Location
instrument panel
instrument panel
Battery power is applied from the main bus section 3 to the avionics bus via protector rocker
switch AVIONICS MASTER on the left lower instrument panel. When the engine is running
alternator power is applied to the avionics bus.
The avionics bus is physically represented by the most right row of circuit breakers on the
instrument panel. Refer to Figure 201 for standard layout of avionics Cbs.
Avionics devices not equipped with an own on/off switch are powered immediately powered on
when AVIONICS MASTER is switched on. It is recommended to switch AVIONICS MASTER on
after starting the engine.
The following basic systems are connected to the avionics bus (example):
(1) VHF COMM
(2) Intercom / Audio panel
(3) VHF NAV
(4) XPDR
(5) GPS
(6) EFIS / Artificial horizon
For the currently installed avionics equipment, refer to the effective Equipment List in the aircraft
file.
F.
Troubleshooting:
2. Avionics Bus Removal/Installation
A.
The protector rocker switches and the CBs are latched from the face side into the instrument
EFFECTIVITY
Model S6-RT
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MAINTENANCE MANUAL
carefully out.
A.
To test the avionics bus, switch related instruments or devices on.
Some electronic devices provide the optional indication of their power supply voltage. This can
help to test the actual voltage at the avionics bus.
B
Intercom / Audio Panel
ELT
Soaring Computer / El. Variometer
NAV / GPS
EFIS / Artificial Horizon
Transponder
COM-Radio
Figure 201
EFFECTIVITY
Model S6-RT
24-63-00
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MAINTENANCE MANUAL
INTERNAL GENERATOR BUS – MAINTENANCE PRACTICES
1. General
A.
B.
Reference:
C.
D.
ATA
Description
Location
24-33-01
24-64-01
24-64-02
24-64-03
diode
internal generator bus
tcu board
instrument panel
tcu board
tcu board
Battery power is applied from the engine bus section 1 to the internal generator bus via fuse INT
GEN at fuse holder behind instrument panel. Thanks to the diode, current can flow from engine
bus to internal generator bus only, but not vice versa. When the engine is running power of the
internal generator is applied to the bus via fuse INT GEN on the fuse holder at the TCU board.
The internal generator bus is physically represented by the fuse holder on the TCU board.
The following basic systems are connected to the internal generator bus:
(1) Main fuel feeder pump
(2) Circulation pump
(3) Yellow internal generator warning light
(4) Turbo-charger control unit TCU
(5) Buffer capacitor (not fused)
E.
Fuses
All related fuses are located on a fuse holder at TCU board. The position of the fuses is marked on
the cover of the fuse holder.
Fuse
MAIN PUMP
CIRC.PUMP
INT GEN
GEN WARN LAMP
TCU
F.
Rating
3 amp
5 amp
15 amp
1 amp
3 amp
Troubleshooting:
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2. Internal Generator Bus Removal/Installation
A.
A.
Power on the internal generator bus is indicated by:
B
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ELECTRICAL GROUND – MAINTENANCE PRACTICES
1. General
A.
B.
Reference:
C.
System of Ground Points beside steel frame and engine body:
D.
ATA
Description
Location
24-65-01
24-65-02
24-65-03
24-65-04
24-65-04
24-65-05
24-65-06
Ground Stud No. 1
Ground Stud No. 2
reserved
Instrument panel ground stud
Instrument panel ground bus left
Instruement panel ground bus right
TCU-board ground stud
steel frame, close to battery mount
right front bottom of instrument panel
Right front bottom of instrument panel
bottom of instrument panel
bottom of instrument panel
fixing screw of starter relay
Because the fiber composite fuselage of the aircraft doesn't provide sufficient electrical ground,
some ground points are located at several areas of the aircraft. That ground points are connected
by wires to the steel frame and the batterie's negative pole. The steel frame and the engine body
represent the central ground point of the aircraft. Starter and external alternator are grounded to
the engine body by their own case. The shock mounts of the engine are bridged by one 16mm²
jumper.
Ground stud No. 1
Two bolts of M6 and M8 size, welded to the metal battery mount, provide the master ground point
Grounded systems:
(1) Battery
(2) Starter / Engine body / External Alternator
(3) External power supply socket
(4) TCU board
Ground stud No.2
One Bolt of M6 size, screwd to the steel frame, front, top center
Grounded systems:
(1) Instrument Panel ground
(2) Fuel Pumps
(3) Lights
Instrument Panel ground stud
One bolt of M6 size is screwed onto the metal instrument pane and provide the ground
connection to the instrument panel body. This stud is linked by an AWG 8 wire to the master
ground stud.
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Instrument ground bus left
A terminal bar is riveted to the left bottom of instrument panel. All electrical devices on the left
side of instrument panel are grounded here.
Instrument ground bus right
A terminal bar is riveted to the right bottom of instrument panel. All electrical devices on the right
side and center of instrument panel are grounded here.
E.
Fuses
All related fuses are located on a fuse holder at TCU board. The position of the fuses is marked on
the cover of the fuse holder.
Fuse
MAIN PUMP
CIRC.PUMP
INT GEN
GEN WARN LAMP
TCU
F.
Rating
3 amp
5 amp
15 amp
1 amp
3 amp
Troubleshooting:
2. Electrical Ground Removal/Installation
A.
A.
Power on the engine bus is indicated by:
B
4. Inspections / Checks
A.
Refer to schedules inspections.
B.
Visually inspect the conditions of the ground poits and related wires that:
(1) Connections are tightened.
(2) No corrosion, dirt or moisture is present.
(3) Wires are not damaged or broken.
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MAINTENANCE MANUAL
CHAPTER 25
EQUIPMENT AND FURNISHINGS
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page Effectivity
EQUIPMENT / FURNISHINGS - GENERAL................................................25-00-00
Introduction
25-00-00
General Description
25-00-00
1
1
1
SEATS - MAINTENANCE PRACTICES .........................................................25-10-00
General
25-10-00
Seat Removal/Installation
25-10-00
Seat Rails Removal/Installation
25-10-00
201
201
201
203
001 - 010
001 - 010
001 - 010
001 - 010
SEATS - MAINTENANCE PRACTICES .........................................................25-10-00
General
25-10-00
Seat Removal/Installation
25-10-00
25-10-00
201
201
201
203
011 - 999
011 - 999
011 - 999
011 - 999
RESTRAINT SYSTEMS - MAINTENANCE PRACTICES............................25-11-00
General
25-11-00
Restraint System Removal/Installation
25-11-00
201
201
201
CABIN INTERIOR - MAINTENANCE PRACTICES....................................25-21-00
General
25-21-00
Panels, Coverings and Carpets Removal/Installation
25-21-00
201
201
202
001 - 010
001 - 010
001 - 010
CABIN INTERIOR - MAINTENANCE PRACTICES....................................25-21-00
General
25-21-00
Panels, Coverings and Carpets Removal/Installation
25-21-00
201
201
202
011 - 999
011 - 999
011 - 999
STORAGE BAGS / TIE-DOWNS - MAINTENANCE PRACTICES ............25-50-00
General
25-50-00
201
201
EMERGENCY - DESCRIPTION......................................................................25-60-00
Introduction
25-60-00
25-60-00
1
1
1
KANNAD ELT
KANNAD ELT
KANNAD ELT
EMERGENCY - MAINTENANCE PRACTICES ...........................................25-60-00
General
25-60-00
Emergency Locator Transmitter (ELT) Removal / Installation
25-60-00
ELT Antenna Removal / Installation
25-60-00
Battery Replacement
25-60-00
Adjustment/Test
25-60-00
Inspection/Check
25-60-00
201
201
201
201
202
202
203
KANNAD ELT
KANNAD ELT
KANNAD ELT
KANNAD ELT
KANNAD ELT
KANNAD ELT
KANNAD ELT
Page 01
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
EQUIPMENT / FURNISHINGS - GENERAL
1. Introduction
A.
This chapter describes removable items of equipment and interior trim contained in the flight and
baggage compartment of the STEMME S6.
A.
The seats consists of cushioned seat-pans, integrated into the cockpit-floor and backrests
adjustable in position and inclination. Every seat is equipped with a four-point-safety-harness
and a central lock. The abdominal-belts are mounted at mounting-positions at the left and right
sides of the seat-pan. The shoulder belts are mounted at the crossbar located above and behind the
backrests.
B.
The cabin interior is designed comfortable but functionally and easy-care. For maintenance
purposes the panels and coverings can be removed.
C.
The baggage compartment of the S6 is located at the front of the tail-boom-section, directly behind
the mid-section steel frame of the fuselage. A maximum payload of 20 kg (44 lbs) may be loaded
into the compartment. It can be loaded through a forward-opening door at the top of the fuselage.
The locks are engaged with quick-closing push-buttons at the rear of the door.
25-00-00
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
SEATS - MAINTENANCE PRACTICES
1. General
A.
The seat-pans itself are integrated into the CFRP cockpit-floor-structure of the S6 and cannot be
removed except of the cushion.
The backrests of the seats are fabricated from carbon composite materials and equipped with
adjustable cushioned safety head rests at the top. Depending of the use of parachutes the
backrests can be equipped with cushions optionally.
Optionally, the backrest position can be adjusted at the bottom and the slope of the backrest can
be adjusted at the top corresponding to the ergonomic requirements of a wide pilot spectrum.
For adjustment of position the backrest can be moved along the lower mounting rails. By pushing
the release knob in the forward area of the seat-pan the supporting gas spring strut for seat
backrest adjustment is unlocked and the backrest can be moved along the rails into the desired
position. After adjustment the gas spring strut has to be blocked by pulling the adjustment knob
for locking.
The slope of the backrest can be adjusted optionally by placing a small lever in one of several
detents near the mounting of the seat-belts.
2. Seat Removal/Installation
A.
Remove Seat Backrest
(1) Remove seat-pan cushion.
(2) Remove cushion of backrest, if installed.
(3) Remove cover for front fuselage tunnel (refer to 25-21-00).
(4) Unhinge pawl for slope adjustment at the top of the backrest.
(5) Remove stop bolts at front ends of seat rails.
(6) Unhinge gas spring strut at the front attachment by removing cotter pin and bolt. Unlock gas
spring strut blocking if necessary.
(7) Move the seat backrest forward out of the seat rails. Pay attention not to cant the rails and to
keep the ball track free from dirt.
(8) Remove seat backrest from the aircraft.
B.
Install Seat Backrest
(1) Position seat backrest with the seat tracks linearly to the lower mounting rails. Retract gas
spring strut completely.
(2) Insert ball track slides to seat rails from the front end. Pay attention not to cant the slides in
the rails.
(3) Insert stop bolts at front ends of seat rails.
(4) Install locking bolt and cotter pin to attach the gas spring strut to the backrest structure.
(5) Install cover for front fuselage tunnel (refer to 25-21-00).
(6) Adjust seat backrest.
(7) Install cushion for seat backrest.
(8) Install seat-pan cushion.
EFFECTIVITY
001 - 010
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MAINTENANCE MANUAL
A
Detail- A
Seat Installation
Figure 201
EFFECTIVITY
001 - 010
25-10-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
3.
A.
Remove Seat Rails
(1) Remove Seat (Refer to pt. 2)
(2) Remove screws securing seat rails to fuselage structure.
(3) Remove seat rails from front fuselage structure.
B.
Install Seat Rails
(1) Position seat rails and secure to fuselage structure with screws.
(2) Install seat (Refer to pt. 2).
Seat Rails Installation
Figure 202
EFFECTIVITY
001 - 010
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
SEATS - MAINTENANCE PRACTICES
1. General
A.
The seat-pans itself are integrated into the CFRP cockpit-floor-structure of the S6 and cannot be
removed except of the cushion.
The backrests of the seats are fabricated from carbon composite materials and equipped with
integrated cushioned safety head rests at the top. Depending of the use of parachutes the
backrests can be equipped with cushions optionally.
Optionally, the backrest position can be adjusted at the bottom and the slope of the backrest can
be adjusted at the top corresponding to the ergonomic requirements of a wide pilot spectrum.
For adjustment of position the backrest can be moved in several steps along the lower mounting
rails. By pulling the adjusting rail left and right to the inside at the same time the backrest is
unlocked and can be moved to the desired position. To avoid wedge of adjustment the left and
right rail have to be moved simultaneously . After adjustment the rails have to be locked in the
next notch position.
The slope of the backrest can be adjusted optionally by placing a small lever in one of several
detents near the mounting of the seat-belts.
2. Seat Removal/Installation
A.
Remove Seat Backrest
(1) Remove seat-pan cushion.
(2) Remove cushion of backrest, if installed.
(3) Unhinge pawl for slope adjustment at the top of the backrest.
(4) Unhinge backrest by unlocking the lower adjustment and moving the seat track along the
lower mounting rails to the forward end position.
(5) Remove backrest of the seat.
B.
Install Seat Backrest
(1) Position seat backrest with the seat tracks linearly to the lower mounting rails.
(2) Insert seat tracks of backrest to mounting rails simultaneously on both sides with the
adjustment spring kept unlocked.
(3) Adjust slope attachment pawl at the top of the backrest.
(4) Install cushion for seat backrest.
(5) Install seat-pan cushion.
EFFECTIVITY
011 - 999
25-10-00
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STEMME TSA-M
MAINTENANCE MANUAL
A
Detail- A
Seat Installation
Figure 201
EFFECTIVITY
011 - 999
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STEMME TSA-M
MAINTENANCE MANUAL
3.
A.
Removal/Installatio Seat Rails
(1) Remove Seat (Refer to pt. 2)
(2) The seat rails are riveted with the front fuselage structure. To remove the seat rails the rivets
have to be removed.
For reinstallation of a new seat rail the rail has to be revited with structure again.
(3) Install Seat (Refer to pt. 2).
EFFECTIVITY
011 - 999
25-10-00
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
RESTRAINT SYSTEMS - MAINTENANCE
1. General
A.
The seats are equipped with automatic, four point seat belts/shoulder harness assemblies. To
fasten the seat belts/shoulder harness a central rotary buckle is used. The adjustable shoulder
harnesses are attached to a crossbar located behind the seat backrests.
The adjustable seat belts are attached to fitting bolts on the seat bulkhead, to the left and right side
of the seat pans.
B.
Maintenance is limited to removal and installation of restraint systems.
2. Restraint Systems Removal/Installation
A.
Remove Restraint System
(1) Release upper backrest adjustment and swing backrest to the front.
(2) Pull the shoulder belts out of the belt straps and remove from shoulder harness crossbar.
(3) Pull the seat belts out of the belt straps and remove from attachment bolts on the left and
right side of the seat pan.
B.
Install Restraint System
(1) Install seat belts to attachment bolts on the left and right side of the seat pan. Pull the belts
into the belt straps.
Pay attention to correct allocation for the left and right side and routing of the belts.
(2) Release upper backrest adjustment and swing backrest to the front.
(3) Pull shoulder harnesses through openings in the seat backrest and install belts to shoulder
harness crossbar. Pull the belts into the belt straps.
Pay attention to correct allocation for the left and right side and routing of the belts.
(4) Check function and tight fitting of four point seat belts/shoulder harness assembly and
central rotary buckle.
25-11-00
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
CABIN INTERIOR - MAINTENANCE PRACTICES
1. General
A.
The panels, coverings and carpets can be removed for maintenance purposes.
B.
For cabin interior cleaning and care refer to Chapter 12, Section "Cabin interior - Cleaning and
Care".
2. Panels, Coverings and Carpets Removal and Installation
A.
Panels and Coverings are typically attached with small screws to the aircraft fuselage structure.
B.
Seat cushions are fixed with hook and loop fasteners to the cockpit floor.
C.
To remove the carpet in the rudder-pedal area remove clamp for bowden cable rudder pedal
adjustment first. Remove screws of cable clamp therefore. The carpet is additionaly fixed with
hook and loop fasteners. Installation in reverse sequence.
D.
See Fig. 201 for an exploded view of cabin interior and recommended sequence of removal /
installation.
EFFECTIVITY
001 - 010
25-21-00
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MAINTENANCE MANUAL
A
Detail- A
Panels and Covers
Figure 201 (1)
EFFECTIVITY
001 - 010
25-21-00
Page 202
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STEMME TSA-M
MAINTENANCE MANUAL
1. General
A.
B.
Care".
A.
B.
C.
D.
installation.
EFFECTIVITY
011 - 999
25-21-00
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MAINTENANCE MANUAL
A
Detail- A
Panels and Covers
Figure 201 (1)
EFFECTIVITY
011 - 999
25-21-00
Page 202
Nov 18/11
STEMME TSA-M
MAINTENANCE MANUAL
1. General
A.
B.
Care".
A.
B.
C.
D.
installation.
EFFECTIVITY
25-21-00
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MAINTENANCE MANUAL
A
B
Detail- A
Detail- B
C
Detail- C
Panels and Covers
Figure 201 (1)
EFFECTIVITY
25-21-00
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STEMME TSA-M
MAINTENANCE MANUAL
STORAGE BAGS / CARGO TIE-DOWNS - MAINTENANCE PRACTICES
1. General
A.
The cabin provides several trays to store small baggage and documents etc.
There are storage bags located on each outer cabin side wall. Behind each seat backrest a baggage
net is provided.
B.
The baggage compartment in the tailboom front section is provided with four cargo tie-down
rings to anchor baggage. Baggage nets or belts may be used to hold baggage in position during
the flight.
The cargo tie-down rings are screwed directly to the baggage compartment tailboom structure.
2. Cabin storage bags / nets Removal and Installation
A.
The storage bags at the cabin side wall are typically attached with small screws and / or hook and
loop fasteners to the cabin side wall.
B.
The baggage nets behind the seat backrests at the cabin rear wall are attached with small screws to
the cabin rear wall structure.
2. Cargo Tie-Downs Baggage Compartment Removal and Installation
A.
The cargo tie-down rings are screwed directly to the baggage compartment tailboom structure.
Each cargo tie-down ring is attached with two screws to the baggage compartment side wall.
25-50-00
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
CHAPTER 26
FIRE DETECTION
EFFECTIVITY
013 - 999
STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
TABLE OF CONTENTS
Title
Chapter
Section
Subject
Page Effectivity
FIRE DETECTION - GENERAL ......................................................................26-00-00
Introduction
26-00-00
General Description
26-00-00
1
1
1
013 - 999
013 - 999
013 - 999
fIRE DETECTION - MAINTENANCE PRACTICES ....................................26-10-00
General
26-10-00
Fire Detection System Functional Check
26-10-00
201
201
201
013 - 999
013 - 999
013 - 999
EFFECTIVITY
013 - 999
Page 01
26 - TOC
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STEMME TSA-M
MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
FIRE DETECTION - GENERAL
1. Introduction
A.
This chapter contains information about the fire detection system of the STEMME S6. The task of
the electrical fire detection system is, to detect increasing temperature inside the fire wall above
the normal operating temperature and giving an optical and acoustical warning signal to the pilot.
A.
The engine compartment of the STEMME S6 is equipped with a fire detection system, which gives
an optical and acoustical warning to the pilot in case of engine fire by detection of increased
temperature inside the fire wall above normal operating temperature. The system is designed “failsafe”, so that damage or other interruption of the signal lines also raises the alarm signal.
Possible fire sources inside the firewall are the carburetors and the turbocharger region. For
temperature monitoring 2 bimetallic thermal sensors are mounted on the outside of the fire wall
above the carburators and another 2 sensors are mounted on the left and right containment of the
fire wall outlet and exhaust shaft. The sensor switching temperature is set to 160° C [320° F]. The
system is powered by the onboard power supply (no separate power supply).
On the instrument panel is a pushbutton switch with integrated red warning light which is
labeled "FIRE", and a relay and a piezo transducer. The relay switches the piezo transducer and the
red warning light. The fire warning system is supplied through a fuse from the main bus of the
electrical system. The electrical fire warning system is activated when BATT switch is on (main bus
powered). If the warning light pushbutton is pressed, or one or more thermal sensors are
activated, the negative wire to the relay is interrupted, red warning light and the piezoelectric
transducer are activated. The pilot then is alerted via the fixed red light and a continuous warning
signal. A manual reset of the alarm is not possible.
B.
For further information of electrical wiring of fire detection system refer to Chapter 91-00-00 of this
manual.
EFFECTIVITY
013 - 999
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MAINTENANCE MANUAL
STEMME TSA-M
MAINTENANCE MANUAL
FIRE DETECTION - MAINTENANCE PRACTICES
1. General
A.
Maintenance of the fire warning system is limited to visual inspections of all components and the
functional check of the warning light pushbutton.
In case of a malfunction at first check all electrical connections, wirings and the separate fire
warning fuse.
Otherwise contact the manufacturer.
2. Fire Detection System Functional Check
A.
The functional check of the fire detection system is part of the pre-flight-inspection of the aircraft
(refer to chapter 4, Flight Manual STEMME S6).
B.
The proper function of the fire warning system has to be checked before every flight by operating
the warning light pushbutton.
Push the fire-warning button to check function. With pushing the button the red warning light
and the continuous acoustic alarm signal has to work.
EFFECTIVITY
013 - 999
26-10-00
Page 201
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STEMME TSA-M
MAINTENANCE MANUAL

STEMME TSA-M CHAPTER 11 PLACARDS AND MARKINGS

Transcription

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