C172 Thirlet

Thielert Aircraft Engines GmbH Tel.
+49-(0)37204/ 696-0
Fax +49-(0)37204/ 696-2912
Platenenstr. 14
www.centurion-engines.com
D - 09350 Lichtenstein info@centurion-engines.com
Supplement
Pilot´s Operating Handbook
for the
(Reims) Cessna (F) 172
N&P
Equipped with
TAE 125-01 and TAE 125-02-99
Installation
Issue 3
MODEL No.
SERIAL No.
REGISTER No.
This supplement must be attached to the EASA approved

Pilot´s Operating Handbook when the TAE 125-01 or
TAE 125-02-99 installation has been installed in accordance
with EASA STC A.S.01527 or EASA STC 10014287.
The information contained in this supplement supersede or add

to the information published in the EASA approved Pilot´s
Operating Handbook only as set forth herein.
For limitations, procedures, performance and loading
information not contained in this supplement, consult the EASA
approved Pilot´s Operating Handbook.
This supplement Pilot‘s Operating Handbook is approved with

EASA AFM Approval 10036563.
TAE-Nr.: 20-0310-20023
This page intentionally left blank
Supplement POH Reims/Cessna (F) 172 N&P
APPROVAL
The content of approved chapters is approved by EASA. All
other content is approved by TAE under the authority of EASA
DOA No. EASA.21J.010 in accordance with Part 21.
LOG OF REVISIONS
Approved
Revision Section Description
Date Endorsed
3/0 all new Issue 23.08.2010 EASA AFM

Approval
10031525
3/1 1 New oil, editorial changes April 14, 2011
2 New oil
3 Procedures updated
5 Editorial changes
6 Editorial changes
9 New section
Page iii
Issue 3
Revision 5, May 2013
Approved
Revision Section Description
Date Endorsed
3/2 1 New gearbox oil, Sept. 22, EASA AFM

Fuel capacity integral fuel 2011 Approval
tank 10036563
2 New gearbox oil,

Fuel capacity integral fuel
tank
5 Flight performance with

integral fuel tanks
7 Editorial changes
3/3 1 New fuel, new gearbox oil March 16,

2012
2 New fuel, new gearbox oil
4 New fuel,
Procedures updated
6 New fuel
3/4 1 New gearbox oil March 11,

2013
2 New gearbox oil
5 Editorial changes
Page iv
Issue 3
LIST OF APPLICABLE CHAPTERS

Sections Issue/Revision Date
1 3/4 March 2013
2 3/4 March 2013
3 3/1 April 2011
4 3/3 March 2012
5 3/3 March 2013
6 3/2 March 2012
7 3/1 Sept. 2011
8 3/0 July 2010
9 3/0 April 2011
General remark
The content of this POH supplement is developed on basis of

the EASA-approved POH.
Page vi
Issue 3
TABLE OF CONTENTS
COVER SHEET
LOG OF REVISIONS......................................................page iii
LIST OF APPLICABLE CHAPTERS.............................. page vi
GENERAL REMARK ..................................................... page vi
TABLE OF CONTENTS ................................................page vii
CONVERSION TABLES ...............................................page viii
ABBREVIATIONS ..........................................................page xii
SECTION 1 GENERAL
(a non-approved chapter)
SECTION 2 LIMITATIONS
(an approved chapter)
SECTION 3 EMERGENCY PROCEDURES
SECTION 4 NORMAL PROCEDURES
SECTION 5 PERFORMANCE
SECTION 6 HANDLING ON GROUND
MAINTENANCE
SECTION 7 WEIGHT & BALANCE
SECTION 8 SPECIAL EQUIPMENT LIST
SECTION 9 SUPPLEMENTS
Page vii
Issue 3
Revision 3, March 2012
CONVERSION TABLES
VOLUME
Conversion factor Conversion factor
Unit [Abbr.]
SI to US / Imperial US / Imperial to Si
Liter [l]
[l] / 3.7854 = [US gal]
[l] / 0.9464 = [US qt]
[l] / 4.5459 = [[lmp gal]
[l] x 61.024 = [in³]
[US gal] x 3.7854 = [l]
US gallon [US gal]
[[US qt] x 0.9464 = [l]
US quart [US qt]
[[lmp gal] x 4.5459 = [l]
Imperial gallon [lmp gal]
[in³] / 61.024 = [l]
Cubic inch [in³]
TORQUE
Unit [Abbr.]
Kilopondmeter [kpm] [kpm] x 7.2331 = [ft.lb]
[kpm] x 86.7962 = [in.lb]
Foot pound [ft.lb] [ft.lb] / 7.2331 = [kpm]

Inch pound [in.lb] [in.lb] / 86.7962 = [kpm]
TEMPERATURE
Unit [Abbr.]
Degree Celsius [ºC] [ºC] x 1.8 + 32 = [ºF]
Degree Fahrenheit [ºF] ([ºF] - 32) / 1.8 = [ºC]
SPEED
Unit [Abbr.]
Kilometers per hour [km/h] [km/h] / 1.852 = [kts]
[km/h] / 1.609 = [mph]
Meters per second [m/s] [m/s] x 196.85 = [fpm]
Miles per hour [mph] [mph] x 1.609 = [km/h]
Knots [kts] [kts] x 1.852 = [km/h]
Feet per minute [fpm] [fpm] / 196.85 = [m/s]
Page viii
Issue 3
PRESSURE
Unit [Abbr.]
Bar [bar] [bar] x 14.5038 = [psi]
Hectopascal [hpa] [hpa] / 33.864= [inHg]
=Millibar [mbar]
[mbar] / 33.864 = [inHg]
Pounds per square inch psi] / 14.5038 = [bar]
[psi] inches of mercury [inHg] x 33.864 = [hPa]
column [inHg]
[inHg] x 33.864 = [mbar]
MASS
Unit [Abbr.]
Kilogramm [kg] [kg] / 0.45359 = [lb]
Pound [lb] [lb] x 0.45359 = [kg]
LENGTH
Unit [Abbr.]
Meter [m] [m] / = 0.3048 [ft]
Millimeter [mm] [mm] / = 25.4 [in]
Kilometer [km] [km] / = 1.852 [nm]
[km] / = 1.609 [sm]
Inch [in] [in] x 25.4 = [mm]
Foot [ft] [ft] x 0.3048 = [m]
Nautical mile [nm] [nm] x 1.852 = [km]
Statute mile [sm] [sm] x 1.609 = [km]
FORCE
Unit [Abbr.]
Newton [N] [N] / 4.448 = [lb]
Decanewton [daN] [daN] / 0.4448 = [lb]
Pound [lb] [lb] x 4.448 = [N]
[lb] x 0.4448 = [daN]
Page ix
Issue 3
°C °F
150 302
140 282
130
262
120
242
110
222
100
202
90
182
80
162
70
60 142
50 122
40 102
30
82
20
62
10
42
0
22
-10
2
-20
-18
-30
-40 -38
-50 -58
Page x
Issue 3
Page xi
Issue 3
ABBREVIATIONS
TAE Thielert Aircraft Engines GmbH, developing

and manufacturing company of the TAE 125
engine
FADEC Full Authority Digital Engine Control
CED 125 Compact Engine Display

Multifunctional instrument for indication of
engine data of the TAE 125
AED 125 Auxiliary Engine Display

Multifunctional instrument for indication of
engine and airplane data
Page xii
Issue 3
SECTION 1
GENERAL
CONVENTIONS IN THIS HANDBOOK
This manual contains following conventions and warnings.

They should be strictly followed to rule out personal injury,
property damage, impairment to the aircraft's operating safety
or damage to it as a result of improper functioning.
WARNING: Non-compliance with these safety rules

could lead to injury or even death.
CAUTION: Non-compliance with these special notes

and safety measures could cause damage
to the engine or to the other components.
Note: Information added for a better

understanding of an instruction.
UPDATE AND REVISION OF THE MANUAL
WARNING: A safe operation is only assured with an up

to date POH supplement. Information about
actual POH supplement issues and
revisions are published in the TAE Service
Bulletin TM TAE 000-0004.
Note: The TAE-No of this POH supplement is

published on the cover sheet of this
supplement.
Page 1-1
Issue 3
ENGINE
Engine manufacturer:............... Thielert Aircraft Engines GmbH
Engine model: ........................... TAE 125-01 or TAE 125-02-99
The TAE 125-02-99 is the successor of the 125-01. Both engine

variants have the same power output and the same propeller
speeds but different displacement. While the TAE 125-01 has
1689 ccm, the TAE 125-02-99 has 1991 ccm. Both TAE 125
engine variants are liquid cooled in-line four-stroke 4-cylinder
motors with DOHC (double overhead camshaft) and are direct
Diesel injection engines with common-rail technology and
turbocharging. Both engine variants are controlled by a FADEC
system. The propeller is driven by a built-in-gearbox (i=1.69)
with mechanical vibration damping and overload release. The
engine variants have an electrical self starter and an alternator.
WARNING: The engine requires an electrical power
source for operation. If the main battery and
alternator fail simultaneously, the engine
will only operate for a maximum of 30
minutes on FADEC backup battery power.
Therefore, it is important to pay attention to
indications of alternator failure.
Due to this specific characteristic, all of the information from the

flight manual recognized by EASA are no longer valid with
reference to:
• carburetor and carburetor pre-heating
• ignition magnetos and spark plugs, and
• mixture control and priming system
PROPELLER
Manufacturer:.........................MT Propeller Entwicklung GmbH
Model: ........................................................... MTV-6-A/187-129
Number of blades:.................................................................... 3
Diameter: ........................................................................ 1.87 m
Type: ..................................................................constant speed
Page 1-2
Issue 3
FUELS and LIQUIDS

CAUTION: Use of unapproved fuels may result in damage
to the engine and fuel system components,
resulting in possible engine failure.
Fuel: .............................................JET A-1/JET-A (ASTM 1655)
Alternative: .............................................. Diesel (DIN EN 590)
.....................................Fuel No.3 (GB 6537-2006)
....................... JP-8, JP-8+100 (MIL-DTL-83133E)
Only TAE 125-02-99 (C2.0):
......................................... TS-1 (GOST 10227-86)
......................TS-1 (GSTU 320.00149943.011-99)
Engine oil: ...................................... AeroShell Oil Diesel Ultra
................................. AeroShell Oil Diesel 10W-40
..........................................Shell Helix Ultra 5W-30
..........................................Shell Helix Ultra 5W-40
Gearbox oil: .................. Shell Getriebeöl EP 75W-90 API GL-4
........................................ Shell Spirax EP 75W-90
.............................Shell Spirax GSX 75W-80 GL-4
..................................... Shell Spirax S4 G 75W-90
............................. Shell Spirax S6 GXME 75W-80
Only TAE 125-02-99 (C2.0):
........................................ Shell Spirax S6 ATF ZM
CAUTION: Use approved oil with exact declaration only!
Coolant:................Water/Radiator Protection at a ratio of 50:50
Radiator Protection: ............. BASF Glysantin Protect Plus/G48
......................... Mobil Antifreeze Extra/G48
........................ESSO Antifreeze Extra/G48
Comma Xstream Green - Concentrate/G48
.................................. Zerex Glysantin G 48
WARNING: The engine must not be started under any
circumstances if the level is too low.
CAUTION: Normally it is not necessary to fill the cooling

liquid or gearbox oil between maintenance
intervals. If the level is too low, please notify
the service department immediately.
Page 1-3
Issue 3
Note: The freezing point of the coolant is -36°C.
INSTRUMENT PANEL
Components of the new installation can be seen as example in
the following Figure.
Some installations are equipped with a key switch for the starter
instead of the push button and the switch "Engine Master" is
designated "IGN". For these installations, the appropriate note
in brackets (Switch resp.), ("IGN" resp.) is added subsequently
throughout the entire supplement for the Pilot´s Operating
Handbook.
Figure 1-1 Example of Instrument panel with TAE 125 installation
13. "Alt. Air Door" Alternate Air Door

(Carburetor Heat Button N/A)
19. "Starter"-Push Button (Switch resp.) for Starter
21. "BAT"-Switch for Battery
22. "MAIN"-Switch for Main Bus
28. CED 125 (Tachometer N/A)
The Compact Engine Display contains indication of
Propeller Rotary Speed, Oil Pressure, Oil Temperature,
Coolant Temperature, Gearbox Temperature and Load.
Page 1-4
Issue 3
51. AED 125 SR with indication of Fuel Flow, Fuel Temperature,

Voltage and a warning light "Water Level" (yellow) for low
coolant level
54. "Force B"-Switch for manually switching the FADEC
59. "Fuel Pump"-Switch for the Electrical Fuel Pump
60. "ALT"-Switch or Circuit Breaker for Alternator
62. Fuse Electrical Fuel Pump
63. Fuses, among other for Alternator Warning light, Starter,
FADEC and Main Bus
72. "Engine Master" ("IGN" resp.)-Switch
electrical supply FADEC
73. Lightpanel with:
"FADEC" Test Knob
"A FADEC B" Warning Lights for FADEC A and B
"Alt" Alternator Warning Light (red)
"AED" Caution Light (Yellow) for AED 125
"CED" Caution Light (yellow) for CED 125
"CED/AED" - Test/Confirm Knob for CED 125, AED 125
and Caution Lights (yellow)
"Fuel L";"Fuel R" Caution Lights for low fuel level (yellow)
"Glow" Glow Control Light (yellow)
Figure 1-2 Lightpanel
Page 1-5
Issue 3
FUEL SYSTEM (Left, Right)

The fuel system of both TAE 125 installations includes the
original standard or long-range tanks of the Cessna 172.
Additional sensors for Fuel Temperature and "Low Level"
Warning are installed.
The fuel flows out of the tanks to the Fuel Selector Valve with
the positions LEFT, RIGHT and OFF, through a reservoir tank
to the fuel shut-off valve and then via the electrically driven Fuel
Pump to the fuel filter. There is no BOTH position.
The electrically driven Fuel Pump supports the fuel flow to the
Filter Module if required. Upstream to the Fuel Filter Module a
thermostat-controlled Fuel Pre-heater is installed. Then, the
engine-driven feed pump and the high-pressure pump supply
the rail, from where the fuel is injected into the cylinders
depending upon the position of the thrust lever and regulation
by the FADEC.
Surplus fuel flows to the Filter Module and then through the Fuel
Selector Valve back into the pre-selected tank. A temperature
sensor in the Filter Module controls the heat exchange between
the fuel feed and return.
Since the desity of diesel and jetfuel (0.84kg/l) is higher than of
AVGAS (0.715kg/l), the usable fuel capacity was reduced by
this factor through the fuel filler neck, to stay within the approved
wing load.
Fuel Capacity
Total Usebale Total Unuseable
Tanks Total Capacity
Fuel Fuel
2 Standard-Tanks: 33.6 US gal 3 US gal 36.6 US gal
each 18.30 US gal (69.4l) (127.4 l) (11.4 l) (138.8 l)
2 Long-Range Tanks: 41.9 US gal 4 US gal 45.9 US gal
each 22.95 US gal (86.8 l) (158.6 l) (15.1 l) (173.6 l)
2 Integral Tanks (normal
58 US gal 6 US Gal 52 US gal
category):
(219.6 l ) (22.8 l ) (196.8 l )
each 29 US gal (119.8 l)
2 Integral Tanks
47.9 US gal 6 US Gal 41.9 US gal
(utility category):
(181.4 l ) (22.8 l) (158.6 l )
each 23.95 US gal (90.7 l )
Page 1-6
Issue 3
FUEL SYSTEM (Left, Right)
CAUTION: In flight conditions with downward pointing

wing, switch the fuel selector to the upper
fuel tank.
Engine
60°C
Fuelfiltermodule
Electrical
Pump
Fuel selector &

shut-off valve
Fuel tank left Fuel tank right
Fuel tank ventilation line
Fuel tank temperature indication

Fuel tank level indication
Low fuel warning
Figure 1-3a Scheme of the Fuel System (Left, Right)
Page 1-7
Issue 3
FUEL SYSTEM (Left, Right, Both)

The fuel system of installations includes the original standard
or long-range tanks of the Cessna 172. Additional sensors for
Fuel Temperature and "Low Level" Warning are installed.
The fuel flows out of the tanks to the Fuel Selector Valve with
the positions LEFT, RIGHT and BOTH, through a reservoir tank
to the fuel shut-off valve and then via the electrically driven Fuel
Pump to the fuel filter.
The electrically driven Fuel Pump supports the fuel flow to the
Filter Module if required. Fuel can be shut off by the seperate
shutoff valve. and then through the Fuel Selector Valve back
into the pre-selected tank, if BOTH is selected the fuel returns
to both tanks.
Since the density of diesel and jet fuel (0.84 kg/l) is higher than
AVGAS (0.715 kg/l), the usable fuel capacity was reduced by
this factor through the fuel filler neck, to stay within the approved
wing load.
Fuel Capacity
Fuel Fuel
each 18.30 US gal (69.4l) (127.4 l) (11.4 l) (138.8 l)
each 22.95 US gal (86.8 l) (158.6 l) (15.1 l) (173.6 l)
category):
(219.6 l ) (22.8 l ) (196.8 l )
2 Integral Tanks
(utility category):
(181.4 l ) (22.8 l) (158.6 l )
each 23.95 US gal (90.7 l )
Page 1-8
Issue 3
FUEL SYSTEM (Left, Right, Both)

CAUTION In flight conditions with downward pointing
wing, switch the fuel selector to the upper
fuel tank or to the position BOTH
CAUTION In turbulent air it is strongly recommended

to use the BOTH position.
Figure 1-3b Scheme of the Fuel System (Left, Right, Both)
Note The handling of the fuel selector positions

left, right and both are described in the
original POH
Page 1-9
Issue 3
ELECTRICAL SYSTEM
The electrical system of both TAE125 installation differs from
the previous installation and is equipped with the following
operating and display elements:
1. Switch "Main Bus"

This switch controls the Main Bus. The Main Bus is necessa-
ry to be able to run FADEC and engine with Battery/Alterna-
tor without disturbance in the event of onboard electrical
system malfunctions. Normally, Alternator, Main Bus and
Battery have to be switched on simultaneously.
2. Circuit Breaker (Switch resp.) "Alternator"

Controls the alternator. Must be ON in normal operation.
3. Switch "Battery"
Controls the Battery.
4. Push Button (Switch resp.) "Starter"

Controls the magneto switch of the starter.
5. Ammeter
The Ammeter shows the alternator current. In case of battery
discharge if alternator inoperative the alternator warning light
will illuminate.
6. Warning Light "Alternator"

Illuminates when the power output of the alternator is too low
or the Circuit Breaker "Alternator" (Switch resp.) is switched
off. Normally, this warning light always illuminates when the
"Engine Master" ("IGN" resp.) is switched on without
revolution and extinguishes immediately after starting the
engine.
7. Switch "Fuel Pump"

This switch controls the electrical fuel pump.
Page 1-10
Issue 3
8. Switch "Engine Master" ("IGN" resp.)

Controls the two redundant FADEC components and the
Alternator Excitation Battery with two independent contacts.
The Alternator Excitation Battery is used to ensure that the
Alternator continues to function properly even if the main
battery fails.
WARNING: If the "Engine Master" is switched off, the

power supply to the FADEC is interrupted
and the engine will shut down.
9. Switch "Force B"

If the FADEC does not automatically switch from A-FADEC
to the B-FADEC in case of an emergency despite of obvious
necessity, this switch allows to switch manually to the
B-FADEC.
WARNING: When operating on FADEC backup battery

only, the "Force B" switch must not be
activated. This will shut down the engine.
10.FADEC Backup Battery

The electrical system includes a FADEC backup battery to
ensure power supply to A-FADEC in case that supply from
both battery and alternator is interrupted. The engine can be
operated for a maximum of 30 minutes when powered by the
FADEC backup battery only. Only A-FADEC is connected to
the backup battery.
The basic wiring of the TAE 125 installation is available in 14V
as well as 28V versions.
Page 1-11
Issue 3
%,%#4 -!)."53
EXTERNAL POWER
05-0
PLUG
,!.$).'
,)'(4
"!44%29 4!8)
,)'(4
BATTERY .!6)'!4)/.
#,/#+ ,)'(4
342/"%
,)'(4
',/7 %#5! %#5"
(/52-%4%2
PITOT HEAT
! (optional)
&!$%# " %.').%-!34%2

0)4/4
(%!4
4%34
&/2#%" !,4%2.!4/2 )NST0ANEL

WITHSWITCHGUARD
$)--%23 #ABIN
2$/INST
!,4
452.).$)#!4/2
!,4%2.!4/2 !,4%2.!4/2
7!2.).',)'(4 2%'5,!4/2
%8#)4!4)/."!44%29 &5%,'!5'%
,/7&5%, 34!24
34!24%2
,(2( 0USH "UTTON
34!,,7!2.).'
!%$ !58),)!29
#!54)/. !%$ %.').%$)30,!9
!%$#%$
4%34 #/.&)2-
#/-0!#4
#%$ %.').%$)30,!9
#%$
#!54)/.
SWITCH TYPE !6)/.)#3

CIRCUIT BREAKER
CAUTION &
SWITCH WARNING
LIGHT
CIRCUIT PUSH
BREAKER BUTTON
Figure 1-4a Basic wiring of the electrical system with alternator cir-
cuit breaker, without FADEC backup battery
Page 1-12
Issue 3
%,%#4 -!)."53
EXTERNAL POWER
05-0
PLUG
,!.$).'
,)'(4
"!44%29 4!8)
,)'(4
BATTERY .!6)'!4)/.
#,/#+ ,)'(4
&!$%#"!#+50"!44%29
342/"%
,)'(4
',/7 %#5! %#5"
(/52-%4%2
PITOT HEAT
! (optional)
&!$%# " %.').%-!34%2

0)4/4
(%!4
4%34
&/2#%" !,4%2.!4/2 )NST0ANEL

WITHSWITCHGUARD
$)--%23 #ABIN
2$/INST
!,4
WITHSWITCHGUARD
452.).$)#!4/2
!,4%2.!4/2 !,4%2.!4/2
7!2.).',)'(4 2%'5,!4/2
%8#)4!4)/."!44%29 &5%,'!5'%
,/7&5%, 34!24
34!24%2
,(2( 0USH "UTTON
34!,,7!2.).'
!%$ !58),)!29
#!54)/. !%$ %.').%$)30,!9
!%$#%$
4%34 #/.&)2-
#/-0!#4
#%$ %.').%$)30,!9
#%$
#!54)/.
SWITCH TYPE !6)/.)#3

CIRCUIT BREAKER
CAUTION &
SWITCH WARNING
LIGHT
CIRCUIT PUSH
BREAKER BUTTON
Figure 1-4b Basic wiring of the electrical system with alternator

switch and FADEC backup battery
Page 1-13
Issue 3
FADEC-RESET
In case of a FADEC-warning, one or both FADEC warning lights
are flashing. If then the "FADEC" Test Knob is pressed for at
least 2 seconds,
a) the active warning lights will extinguish if it was a LOW
category warning.
b) the active warning lights will be illuminated steady if it
was a HIGH category warning.
CAUTION: If a FADEC-warning occurred, contact your

service center.
When a high category warning occurs the pilot should land as

soon as practical, since the affected FADEC ECU has
diagnosed a severe fault. A low category fault has no significant
impact on engine operation.
Refer also to the engine OM-02-01 or OM-02-02 for additional
information.
COOLING
The TAE 125 variants are fitted with a fluid-cooling system
whose three-way thermostat regulates the flow of coolant
between the large and small cooling circuit.
The coolant exclusively flows through the small circuit up to a
cooling water temperature of 84°C and then between 84 and
94°C both through the small and the large circuit.
If the cooling water temperature rises above 94°C, the complete
volume of coolant flows through the large circuit and therefore
through the radiator. This allows a maximum cooling water
temperature of 105°C.
There is a sensor in the expansion reservoir which sends a
signal to the warning light "Water level" on the instrument panel
if the coolant level is low.
The cooling water temperature is measured in the housing of
the thermostat and passed on to the FADEC and CED 125.
The connection to the heat exchanger for cabin heating is
always open; the warm air supply is regulated by the pilot over
the heating valve. See Figure 1-5a.
Page 1-14
Issue 3
In normal operation the control knob "Shut-off Cabin Heat" must

be OPEN, with the control knob "Cabin Heat" the supply of
warm air into the cabin can be controlled.
In case of certain emergencies (refer to section 3), the control
knob "Shut-off Cabin Heat" has to be closed according to the
appropriate procedures.
Aircraft having a TAE 125-02-99 engine installation, can be
equipped with a gearbox oil cooler that is connected to the
coolant circuit.
Coolant level warning
IN OUT Cooling system TAE 125

schematic
Expansion Tank
Flow direction
Coolant OUT
radiator
IN
Water pump OUT

Heating radiator
IN
IN
Flow direction
Flow direction
External Small
circuit Engine circuit
OUT
Temperature sensor
Thermostat Pressure valve
Heating
Thermostat positions: circuit
- external circuit
- both circuits
- small circuit
-> Heating circuit always open
Figure 1-5a Cooling system TAE 125-01 & TAE 125-02-99
Page 1-15
Issue 3
Coolant level warning
IN OUT Cooling system TAE 125

schematic
Expansion Tank
Flow direction
Coolant OUT
radiator
IN
Water pump OUT

Heating radiator
IN
IN
Flow direction
Flow direction
External Small
circuit Engine circuit
Gearbox oil cooler
OUT (oil/ water heat
exchanger)
OUT
Gearbox oil
Temperature sensor
IN
Thermostat Pressure valve
Heating
Thermostat positions: circuit
- external circuit
- both circuits
- small circuit
-> Heating circuit always open
Figure 1-5b Cooling system TAE 125-02-99 with Gearbox Oil Cooler
Page 1-16
Issue 3
SECTION 2
LIMITATIONS
WARNING: It is not allowed to start up the engine using
external power. If starting the engine is not
possible using battery power, the condition
of the battery must be verified before flight.
WEIGHT LIMITS
Normal Category Cessna 172 N:
Maximum Ramp Weight: ................... 1044 kg (2302 lbs)
Maximum Takeoff Weight: ................. 1043 kg (2300 lbs)
Maximum Landing Weight ................. 1043 kg (2300 lbs)
Utility Category Cessna 172 N:

Maximum Ramp Weight: ..................... 908 kg (2002 lbs)
Maximum Takeoff Weight: ................... 907 kg (2000 lbs)
Maximum Landing Weight ................... 907 kg (2000 lbs)
Normal Category Cessna 172 P:

Maximum Ramp Weight: ................... 1090 kg (2402 lbs)
Maximum Takeoff Weight: ................. 1089 kg (2400 lbs)
Maximum Landing Weight ................. 1089 kg (2400 lbs)
Utility Category Cessna 172 P:
Maximum Ramp Weight: ..................... 954 kg (2102 lbs)
Maximum Takeoff Weight: ................... 953 kg (2100 lbs)
Maximum Landing Weight ................... 953 kg (2100 lbs)
Page 2-1
Issue 3
MANEUVER LIMITS
CAUTION: Intentionally initiating negative G

maneuvers is prohibited
Normal Category: No change
Utility Category: Intentionally initiating spins is prohibited
FLIGHT LOAD FACTORS

No change
CAUTION Avoid extended negative g-loads duration.

Extended negative g-loads can cause
propeller control and engine problems.
Note: The load factor limits for the engine must

also be observed. Refer to the Operation &
Maintenance Manual for the engine.
ENGINE OPERATING LIMITS

Engine manufacturer:............... Thielert Aircraft Engines GmbH
Engine model: ........................... TAE 125-01 or TAE 125-02-99
Take-off and Max. continuous power:.............. 99 kW (135 HP)
Take-off and Max. continuous RPM:........................ 2300 min-1
Note: In the absence of any other explicit

statements, all of the information on RPM in
this supplement to the Pilot´s Operating
Handbook are propeller RPM.
Note: This change of the original aircraft is

certified up to an altitude of 17,500 ft.
Page 2-2
Issue 3
Engine operating limits for take-off and continuous operation:
WARNING: It is not allowed to start the engine outside

of these temperature limits.
Note: The operating limit temperature is a

temperature limit below which the engine
may be started, but not operated at the
Take-off RPM. The warm-up RPM to be
selected can be found in Section 4 of this
supplement.
Oil temperature:
Minimum engine starting temperature: ................................. -32 °C
Minimum operating limit temperature: ....................................50 °C
Maximum operating limit temperature: .................................140 °C
Coolant temperature:
Minimum engine starting temperature: ................................. -32 °C
Minimum operating limit temperature: ...................................60 °C
Gearbox temperature:
Mininum operating limit temperature: ................................... -30 °C
Min. fuel temperature limits in the fuel tank:
Minimum permissible Minimum permissible
fuel temperature in fuel temperature in
Fuel
the fuel tank before the fuel tank during
Take-off the flight
JET A-1,
JET A,
Fuel No.3
JP-8, -30° -35°
JP-8+100,
TS-1 (only
C2.0)
Diesel greater than 0° -5°
Page 2-3
Issue 3
Table 2-3a Minimum fuel temperature limits in the fuel tank
WARNING: The fuel temperature of the fuel tank not

used should be observed if its later use is
intended.
WARNING: The following applies to Diesel and JET fuel

mixtures in the tank:
As soon as the proportion of Diesel in the
tank is more than 10% Diesel, the fuel
temperature limits for Diesel operation must
be observed. If there is uncertainty about
which fuel is in the tank, the assumption
should be made that it is Diesel.
Minimum oil pressure: ....................................................1.2 bar

Minimum oil pressure (at Take-off power) .....................2.3 bar
Minimum oil pressure (in flight) ......................................2.3 bar
Maximum oil pressure.....................................................6.0 bar
Maximum oil pressure (cold start < 20 sec.): .................6.5 bar
Maximum oil consumption: .........................0.1 l/h (0.1 quart/h)
Page 2-4
Issue 3
ENGINE INSTRUMENT MARKINGS

The engine data of the TAE 125 installation to be monitored are
integrated in the combined engine instrument CED-125.
The ranges of the individual engine monitoring parameters are

shown in the following table.
R ed A m be r G re e n A m be r R ed
In s t ru m e n t
ra n g e ra n g e ra n g e ra nge ra n g e
T ac ho m eter [R P M ] ----------- -------------- 0-2300 ------- > 2300
Oil pres s ure [bar] 0-1.2 1.2-2.3 2.3-5.2 5.2-6.0 > 6.0
C o o lant
[°C ] < -32 -32 …+ 60 60-101 101-105 > 105
tem perature
Oil
[°C ] < -32 -32 …+ 50 50-125 125-140 > 140
tem perature
Gearbo x
[°C ] ---------- ---------- < 115 115-120 > 120
tem perature
Lo ad [%] --------- ---------- 0-100 ---------- ----------
Table. 2-3b Markings of the engine instruments
Note: If an engine reading is in the yellow or red

range, the "Caution" light is activated.
It only extinguishes when the "CED-Test/
Confirm" button is pressed. If this button is
pressed longer than a second, a selftest of
the instrument is initiated.
Figure 2-1a AED 125 Figure 2-1b CED 125
Page 2-5
Issue 3
PERMISSIBLE FUEL GRADES
CAUTION: Using non-approved fuels and additives

can lead to dangerous engine malfunctions.
Fuel: ........................................................JET A-1 (ASTM 1655)

Alternative: ............................................. JET-A (ASTM D 1655)
........................................Fuel No.3 (GB 6537-2006)
............................................JP-8 (MIL-DTL-83133E)
....................................JP-8+100 (MIL-DTL-83133E)
................................................. Diesel (DIN EN 590)
Only TAE 125-02-99 (C2.0):
............................................ TS-1 (GOST 10227-86)
.........................TS-1 (GSTU 320.00149943.011-99)
MAXIMUM FUEL QUANTITIES

Due to the higher specific density of Kerosene and Diesel in
comparison to Aviation Gasoline (AVGAS) with the TAE 125
installation the permissible tank capacity has been reduced.
Fuel Capacity
Fuel Fuel
each 18.30 US gal (59.4l) (127.4 l) (11.4 l) (138.8 l)
each 22.95 US gal (86.8 l) (128.6 l) (15.1 l) (173.6 l)
category):
(219.6 l ) (22.8 l ) (196.8 l )
2 Integral Tanks
(utility category):
(181.4 l ) (22.8 l) (158.6 l )
each 23.95 US gal (90.7 l )
Page 2-6
Issue 3
CAUTION: To prevent air from penetrating into the fuel

system avoid flying the tanks dry. As soon as
the "Low Level" Warning Light illuminates,
switch to a tank with sufficient fuel or land.
CAUTION With ¼ tank or less, prolonged

uncoordinated flight is prohibited when
operating on either left or right tank.

Note The tanks are equipped with a Low Fuel

Warning. If the fuel level is below
10 l (2.6 US gal) usable fuel, the "Fuel L" or
"Fuel R" Warning Light illuminates
respectively.
PERMISSIBLE OIL TYPES
Engine oil: .......................................... AeroShell Oil Diesel Ultra
..................................... AeroShell Oil Diesel 10W-40
............................................. Shell Helix Ultra 5W-30
............................................. Shell Helix Ultra 5W-40
Gearbox oil: ...................... Shell Getriebeöl EP 75W-90 API GL-4
........................................ Shell Spirax EP 75W-90
................................ Shell Spirax GSX 75W-80 GL-4
..................................... Shell Spirax S4 G 75W-90
............................. Shell Spirax S6 GXME 75W-80
Only TAE 125-02-99 (C2.0):
........................................ Shell Spirax S6 ATF ZM
CAUTION: Use approved oil with exact designation only!
PERMISSIBLE COOLING LIQUID

Coolant: .................... Water/Radiator Protection at a ratio of 50:50
Radiator Protection: .................. BASF Glysantin Protect Plus/G48
............................ Mobil Antifreeze Extra/G48
........................... ESSO Antifreeze Extra/G48
... Comma Xstream Green - Concentrate/G48
......................................Zerex Glysantin G 48
Page 2-7
Issue 3
PLACARDS
Near the fuel tank caps:

With standard tanks:
JET FUEL ONLY

JET A-1 / DIESEL
"CAP. 63.7 LITER (16.8 U.S. GAL.)
USABLE TO BOTTOM OF FILLER INDICATOR TAB"
With long-range tanks:

JET FUEL ONLY
JET A-1 / DIESEL
"CAP. 79.3 LITER (20.9 U.S. GAL.)
USABLE TO BOTTOM OF FILLER INDICATOR TAB"
Normal category aircraft with integral fuel tanks:
JET FUEL ONLY

JET A-1/ DIESEL
"CAP. 98.4 LITER (26 U.S. GAL.)
USABLE TO BOTTOM OF FILLER INDICATOR TAB“
Utility category aircraft with integral fuel tanks:
JET FUEL ONLY

JET A-1/ DIESEL
"CAP. 79.3 LITER (20.9 U.S. GAL.)
USABLE TO BOTTOM OF FILLER INDICATOR TAB“
Page 2-8
Issue 3
At the fuel selector valve:

With standard tanks:
Left and Right position: 63.7 Ltr/ 16.8 gal
Both position: 127.4 Ltr/ 33.6 gal
With long-range tanks:

Normal category aircraft with integral fuel tanks:

Left and Right position: 98.4 Ltr/ 26 gal
Both position: 196.8 Ltr/ 52 gal
Utility category aircraft with integral fuel tanks:

On the oil funnel or at the flap of the engine cowling:

"Oil, see POH supplement"
If installed, at the flap of the engine cowling to the External
Power Receptacle:
"ATTENTION 12 V DC OBSERVE CORRECT POLARITY"
OR
„ATTENTION 24 V DC OBSERVE CORRECT POLARITY“
All further placards contained in this section of the EASA-

approved POH remain valid.
Page 2-9
Issue 3
Page 2-10
Issue 3
SECTION 3
EMERGENCY PROCEDURES
INDEX OF CHECKLISTS
ENGINE MALFUNCTION ................................................................3-2
During Take-off (with sufficient Runway ahead).........................3-2
Immediately after Take-off..........................................................3-3
During Flight ...............................................................................3-3
Restart after Engine Failure .......................................................3-4
FADEC Malfunction in Flight ......................................................3-5
Abnormal Engine Behavior.........................................................3-7
FIRES...............................................................................................3-8
Engine Fire when starting Engine on Ground ............................3-8
Engine Fire in Flight ...................................................................3-8
Electrical Fire in Flight ................................................................3-9
ENGINE SHUT DOWN IN FLIGHT................................................ 3-10
EMERGENCY LANDING...............................................................3-10
Emergency Landing with Engine out........................................ 3-10
FLIGHT IN ICING CONDITIONS ................................................... 3-11
RECOVERY FROM SPIRAL DIVE................................................ 3-12
ELECTRICAL POWER SUPPLY SYSTEM
MALFUNCTIONS ..........................................................................3-13
Alternator Warning light illuminates during normal
Engine Operation ..................................................................... 3-15
Ammeter shows Battery Discharge during normal
Engine Operation for more than 5 Minutes .............................. 3-16
Total Electrical Failure.............................................................. 3-17
ROUGH ENGINE OPERATION OR LOSS OF POWER............... 3-18
Decrease in Power ................................................................... 3-18
Ice Formation in the Carburetor ............................................... 3-18
Soiled spark Plugs.................................................................... 3-18
Ignition Magnet Malfunctions....................................................3-18
Oil pressure too low.................................................................. 3-19
Oil temperature "OT" too high: ................................................. 3-19
Coolant temperature "CT" too high:.......................................... 3-20
Light "Water Level" illuminates................................................. 3-20
Gearbox temperature "GT" too high: ....................................... 3-20
Fuel Temperature too high: ...................................................... 3-20
Fuel Temperature too low: ....................................................... 3-21
Propeller RPM too high: ........................................................... 3-21
Fluctuations in Propeller RPM:................................................. 3-22
Page 3-1
Issue 3
Revision 1, April 2011
GENERAL
WARNING: Due to an engine shut-off or a FADEC

diagnosed failure there might be a loss
propeller valve currency which leads in a
low pitch setting of the propeller. This might
result in overspeed.
Airspeeds below 100 KIAS are suitable to
avoid overspeed in failure case. If the
propeller speed control fails, climbs can be
performed at 65 KIAS and a powersetting of
100%.
ENGINE MALFUNCTION
DURING TAKE-OFF (WITH SUFFICENT RUNWAY AHEAD)
(1) Thrust Lever - IDLE
(2) Brakes - APPLY
(3) Wing flaps (if extended) - RETRACT to increase the
braking effect on the runway
(4) Engine Master (“IGN“ resp.) - OFF
(5) Circuit Breaker (Switch resp.) “Alternator“ and Switches
"Main Bus" and "Battery" - OFF
Page 3-2
Issue 3
IMMEDIATELY AFTER TAKE-OFF
If there is an engine malfunction after take-off, at first lower the

nose to keep the airspeed and attain gliding attitude. In most
cases, landing should be executed straight ahead with only
small corrections in direction to avoid obstacles.
WARNING: Altitude and airspeed are seldom sufficient
for a return to the airfield with a 180° turn
while gliding.
(1) Airspeed.............................. 65 KIAS (wing flaps retracted)
............................60 KIAS (wing flaps extended)
(2) Fuel Shut-off Valve - CLOSED
(4) Wing flaps - as required (Full down recommended)
DURING FLIGHT
Note: Flying a tank dry activates both FADEC
warning lights flashing.
In case that one tank was flown dry, at the first signs of
insufficient fuel feed proceed as follows:
(1) Fuel Shut-off Valve - OPEN (push full in)
(2) Immediately switch the Fuel Selector to tank with
sufficientfuel quantity, if the BOTH option is installed, select
the fuel selector position BOTH position
(3) Electrical Fuel Pump - ON
(4) Check the engine (engine parameters, airspeed/altitude
change, whether the engine responds to changes in the
Thrust Lever position).
(5) If the engine acts normally, continue the flight and land as
soon as practical..
WARNING: The high-pressure pump must be checked
before the next flight.
Page 3-3
Issue 3
RESTART AFTER ENGINE FAILURE
Whilst gliding to a suitable landing strip, try to determine the

reason for the engine malfunction . If time permits and a restart
of the engine is possible, proceed as follows:
(1) Airspeed between 65 and 85 KIAS
(2) Glide below 13,000 ft
(3) Fuel Shut-off Valve - OPEN (push full in)
(4) Fuel Selector switch to tank with sufficientfuel quantity, if
the BOTH option is installed, select the fuel selector
position BOTH position
(7) Engine Master (“IGN“ resp.) OFF and then ON
(if the propeller does not turn, then additionally Starter ON)
Note: The propeller will normally continue to turn

as long as the airspeed is above 65 KIAS/
75 mph. Should the propeller stop at an
airspeed of more than 65 KIAS/ 75 mph or
more, the reason for this should be found
out before attempting a restart.
If it is obvious that the engine or propeller is
blocked, do not use the Starter.
Note: If the Engine Master is in position OFF, the

Load Display shows no value even if the
propeller is turning.
(8) Check the engine power: Thrust lever 100%, engine

parameters, check altitude and airspeed
Page 3-4
Issue 3
FADEC MALFUNCTION IN FLIGHT

Note: The FADEC consists of two components
that are independent of each other: FADEC
A and FADEC B. In case of malfunctions in
the active FADEC, it automatically switches
to the other.
a) One FADEC Light is flashing
1. Press FADEC-Testknob at least 2 seconds
2. FADEC light extinguished (LOW warning category):
a) Continue flight normally,
b) Inform service center after landing.
3. FADEC light steady illuminated (HIGH warning category)
a) Observe the other FADEC light.
b) Land as soon as practical.
c) Select an airspeed to avoid engine overspeed.
d) Inform service center after landing.
Page 3-5
Issue 3
b) Both FADEC Lights are flashing

Note: CED load display should be considered
unreliable with both FADEC lights
illuminated. Use other indications to assess
engine condition.
1. Press FADEC-Testknob at least 2 seconds
2. FADEC Lights extinguished (LOW warning category):
a) Continue flight normally,
b) Inform service center after landing.
3. FADEC Lights steady illuminated (HIGH warning category):
a) Check the available engine power,
b) Expect engine failure.
c) Flight can be continued, however the pilot should
i) Select an appropriate airspeed to avoid engine
overspeed.
ii) Land as soon as possible.
iii) Be prepared for an emergency landing.
d) Inform service center after landing.
4. In case a tank was flown empty, proceed at the first signs of
insufficient fuel feed as follows:
a) Immediately switch the Fuel Selector to tank with suffi-
cientfuel quantity, if the BOTH option is installed, se-
lect the fuel selector position BOTH
b) Electrical Fuel Pump - ON
c) Select an airspeed to avoid engine overspeed.
d) Check the engine (engine parameters, airspeed/alti-
tude change, whether the engine responds to changes
in the Thrust Lever position).
e) If the engine acts normally, continue the flight and land
as soon as practical.
WARNING: The high-pressure pump must be checked
Page 3-6
Issue 3
ABNORMAL ENGINE BEHAVIOR

If the engine acts abnormally during flight and the system does
not automatically switch to the B-FADEC, it is possible switch to
the B-FADEC manually.
WARNING: It is only possible to switch from the
automatic position to B-FADEC (A-FADEC
is active in normal operation, B-FADEC is
active in case of malfunction). This only
becomes necessary when no automatic
switching occurred in case of abnormal
engine behavior.
(1) Select an appropriate airspeed to avoid engine overspeed
WARNING: When operating on FADEC backup battery
only, the "Force B" switch must not be
activated. This will shut down the engine.
(2) "Force-B" switch to B-FADEC
(3) Flight may be continued, but the pilot should:
i) Select an airspeed to avoid engine overspeed
ii) Land as soon as practical
iii) Be prepared for an emergency landing
Page 3-7
Issue 3
FIRES
ENGINE FIRE WHEN STARTING ENGINE ON GROUND
(3) Electrical Fuel Pump - OFF
(4) Switch "Battery" - OFF
(5) Extinguish the flames with a fire extinguisher, wool blankets
or sand.
(6) Examine the fire damages thoroughly and repair or replace
the damaged parts before the next flight
ENGINE FIRE IN FLIGHT
(1) Engine Master - OFF
(3) Electrical Fuel Pump - OFF (if in use)
(4) Switch "Main Bus" - OFF
(5) Cabin heat and ventilation OFF (closed) except the fresh
air nozzles on the ceiling
(6) Establish Best Glide Speed
(7) Perform emergency landing (as described in the procedure
"Emergency Landing With Engine Out")
Page 3-8
Issue 3
ELECTRICAL FIRE IN FLIGHT

The first sign of an electrical fire is the smell of burned cable
insulation. In this event proceed as follows:
(1) Main Bus - OFF
(2) Avionics Master - OFF
(3) Fresh Air Nozzles, Cabin Heat and Ventilation - OFF
(closed)
(4) Fire Extinguisher - Activate (if available)
(5) All electrical consumers - Switch OFF, leave Alternator,
Battery and Engine Master ON
WARNING: After the fire extinguisher has been used,
make sure that the fire is extinguished
before exterior air is used to remove smoke
from the cabin.
(6) If there is evidence of continued electrical fire, consider

turning off Battery and Alternator.
WARNING: If the FADEC Backup battery is not installed
this will shut down the engine and require
an emergency landing (refer to
“EMERGENCY LANDING WITH ENGINE
OUT”). The engine has been demonstrated
to continue operating for a maximum of 30
minutes when powered by the FADEC
Backup battery only.
(7) Fresh Air Nozzles, Cabin Heat and Ventilation - ON (open)

(8) Check Circuit Breaker, do not reset if open
If the fire has been extinguished:
(9) Main Bus - ON
(10) Avionics Master - ON
WARNING: Turn on electrical equipment required to
continue flight depending on the situation
and land as soon as practical. Do only
switch ON one at a time, with delay after
each.
Page 3-9
Issue 3
ENGINE SHUT DOWN IN FLIGHT
If it is necessary to shut down the engine in flight (for instance,

abnormal engine behavior does not allow continued flight or
there is a fuel leak, etc.), proceed as follows:
(1) Select an airspeed to avoid engine overspeed (best glide
recommended)
(4) Electrical Fuel Pump - OFF (if in use)
(5) If the propeller also has to be stopped (for instance, due to
excessive vibrations)
i) Reduce airspeed below 55 KIAS
ii) When the propeller is stopped, continue to
glide at 65 KIAS
EMERGENCY LANDING
EMERGENCY LANDING WITH ENGINE OUT
If all attempts to restart the engine fail and an emergency

landing is imminent, select suitable site and proceed as follows:
(1) Airspeed
i) 65 KIAS (flaps retracted)
ii) 60 KIAS (flaps extended)
(4) Wing Flaps - as required (Full down recommended)
(6) Cabin Doors - unlock before touch-down
(7) Touch-down - slightly nose up attitude
(8) Brake firmly
Note: Gliding Distance. Refer to "Maximum Glide"

in the approved Pilot‘s Operating
Handbook.
Page 3-10
Issue 3
FLIGHT IN ICING CONDITIONS
WARNING: It is prohibited to fly in known icing

conditions.
In case of inadvertent icing encounter proceed as follows:

(1) Pitot Heat switch - ON (if installed)
(2) Turn back or change the altitude to obtain an outside air
temperature that is less conducive to icing.
(3) Pull the cabin heat control full out and open defroster
outlets to obtain maximum windshield defroster airflow.
Adjust cabin air control to get maximum defroster heat
and airflow.
(4) Advance the Thrust Lever to increase the propeller speed
and keep ice accumulation on the propeller blades as low
as possible.
(5) Watch for signs of air filter icing and pull the "Alternate Air
Door" control if necessary. An unexplaned loss in engine
power could be caused by ice blocking the air intake filter.
Opening the "Alternate Air Door" allows preheated air from
the engine compartment to be aspirated.
(6) Plan a landing at the nearest airfield. With an extremely
rapid ice build up, select a suitable "off airfield" landing side.
(7) With an ice accumulation of 0.5 cm or more on the wing
leading edges, a significantly higher stall speed should be
expected.
(8) Leave wing flaps retracted. With a severe ice build up on
the horizontal tail, the change in wing wake airflow direction
caused by wing flap extension could result in a loss of
elevator effectiveness.
(9) Open left window, if practical, scrape ice from a portion of
the windshield for visibility in the landing approach.
(10) Perform a landing approach using a forward slip, if
necessary, for improved visibility.
(11) Approach at 65 to 75 KIAS depending upon the amount of
the accumulation.
(12) Perform a landing in level attitude.
Page 3-11
Issue 3
RECOVERY FROM SPIRAL DIVE

If a spiral is encountered in the clouds, proceed as follows:
(1) Retard Thrust Lever to idle position
(2) Stop the turn by using coordinated aileron and rudder
control to align the symbolic airplane in the turn coordinator
with the horizontal reference line.
(3) Cautiously apply elevator back pressure to slowly reduce
the airspeed to 80 KIAS.
(4) Adjust the elevator trim control to maintain an 80 KIAS
glide.
(5) Keep hands off the control wheel, using rudder control to
hold a straight heading.
(6) Readjust the rudder trim (if installed) to relieve the rudder
of asymmetric forces.
(7) Clear the engine occasionally, but avoid using enough
power to disturb the trimmed glide.
(8) Upon breaking out of clouds, resume normal cruising flight
and continue the flight.
Page 3-12
Issue 3
ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS
CAUTION: The TAE 125 requires an electrical power

source for its operation. If the alternator
fails, continued engine operation time is
dependent upon the remaining capacity of
the main battery, the FADEC backup
battery and equipment powered.
The engine has been demonstrated to
continue operating for approximately 120
minutes based upon the following
assumptions:
Equipment Time switched on

in [min] in [% ]
NAV/COM 1 receiving ON 120 100
NAV/COM 1 transmitting ON 12 10
NAV/COM 2 receiving OFF 0 0
NAV/COM 2 transmitting OFF 0 0
GPS ON 60 50
Transponder ON 120 100
Fuel Pump OFF 0 0
AED-125 ON 120 100
Battery ON 120 100
CED-125 ON 120 100
Landing Light ON 12 10
Flood Light ON 1.2 1
Pitot Heat ON 24 20
W ing Flaps ON 1.2 1
Interior Lighting OFF 0 0
Nav Lights OFF 0 0
Beacon OFF 0 0
Strobes OFF 0 0
ADF OFF 0 0
Intercom OFF 0 0
Engine Control ON 120 100
Table 3-1a
Page 3-13
Issue 3
WARNING If the power supply from both alternator and

main battery is interrupted, continued
engine operation is dependent on the
remaining capacity of the FADEC backup
battery. The engine has been demonstrated
to continue operating for a maximum of 30
minutes when powered by the FADEC
backup battery only. In this case, all electri-
cal equipment will not operate:
- land immidiately
- do not switch the „FORCE-B“ switch, this
will shut down the engine
CAUTION: This table only gives a reference point. The

pilot should turn off all nonessential items
and supply power only to equipment which
is absolutely necessary for continued flight
depending upon the situation.
If deviated from this recommendation, the

remaining engine operating time may
change.
Page 3-14
Issue 3
ALTERNATOR WARNING LIGHT ILLUMINATES DURING

NORMAL ENGINE OPERATION.
(1) Ammeter - CHECK.
(2) Circuit Breaker (Switch resp.) “Alternator“ CHECK - ON
(3) Battery Switch CHECK -ON
CAUTION If the FADEC was supplied by battery only

until this point, the RPM can momentarily
drop, when the alternator will be switched
on. In any case: leave the alternator
switched ON!
(4) Electrical load - REDUCE IMMEDIATELY as follows:

i) NAV/ COM 2 – OFF
ii) Fuel Pump – OFF
iii) Landing Light – OFF (use as required for land-
ing)
iv) Taxi Light – OFF
v) Strobe Light – OFF
vi) Nav Lights – OFF
vii) Beacon – OFF
viii)Interior Lights – OFF
ix) Intercom – OFF
x) Pitot Heat – OFF (use as required)
xi) Autopilot – OFF
xii) Non-essential equipment – OFF
(5) The pilot should:
i) Land as soon as practical.
ii) Be prepared for an emergency landing.
iii) Expect an engine failure
Page 3-15
Issue 3
AMMETER SHOWS BATTERY DISCHARGE DURING

NORMAL ENGINE OPERATION FOR MORE THAN
5 MINUTES
Note: When the AED Ammeter indication is
illuminated at the outer left side and the
voltage indication is decreasing
simultaneously, the battery is being
discharged.
(1) Circuit Breaker (Switch resp.) "Alternator" CHECK - ON

(2) Battery Switch CHECK -ON
CAUTION If the FADEC was supplied by battery only
until this point, the RPM can momentarily
drop, when the alternator will be switched
on. In any case: leave the alternator
switched ON!
(3) Electrical load - REDUCE IMMEDIATELY as follows:
i) NAV/ COM 2 – OFF
ii) Fuel Pump – OFF
iii) Landing Light – OFF (use as required for
landing)
iv) Taxi Light – OFF
v) Strobe Light – OFF
vi) Nav Lights – OFF
vii) Beacon – OFF
viii)Interior Lights – OFF
ix) Intercom – OFF
x) Pitot Heat – OFF (use as required)
xi) Autopilot – OFF
xii) Non-essential equipment – OFF
(4) The pilot should:
i) Land as soon as practical
ii) Be prepared for an emergency landing
Page 3-16
Issue 3
TOTAL ELECTRICAL FAILURE

(all equipment inoperative, except engine)
WARNING: If the power supply from both alternator and

main battery is interrupted simultaneously,
continued engine operation is dependent
on the remaining capacity of the FADEC
backup battery. The engine has been
demonstrated to continue operating for a
maximum of 30 minutes when powered by
the FADEC backup battery only. In this
case, all other electrical equipment will not
operate.
WARNING: If the aircraft was operated on battery

power only until this point (alternator
warning light illuminated), the remaining
engine operating time may be less than 30
minutes.
WARNING: Do not active the FORCE-B switch, this will

shut down the engine.
(1) Circuit Breaker (Switch resp.) “Alternator“ CHECK - ON

(2) Battery Switch CHECK – ON
(3) Land as soon as possible
i) Be prepared for an emergency landing
ii) Expect an engine failure
Page 3-17
Issue 3
ROUGH ENGINE OPERATION OR LOSS OF POWER

DECREASE IN POWER
(1) Push Thrust Lever full forward (Take-off position)
(2) Fuel Selector to tank with sufficient fuel quantity and
temperature, if the BOTH option is installed, select the fuel
selector BOTH position.
(4) Reduce airspeed to 65-85 KIAS (best glide recommended),
(max. 100 KIAS)
(5) Check engine parameters (FADEC lights, oil pressure and
temperature, fuel quantity)
If normal engine power is not achieved, the pilot should:

WARNING: The high presure pump must be checked

ICE FORMATION IN THE CARBURETOR

- N/A, since this is a Diesel engine -
SOILED SPARK PLUGS

IGNITION MAGNET MALFUNCTIONS

Page 3-18
Issue 3
OIL PRESSURE TOO LOW (< 2.3 BAR IN CRUISE (YELLOW

RANGE) OR < 1.2 BAR AT IDLE (RED RANGE)):
(1) Reduce power as quickly as possible
(2) Check oil temperature: If the oil temperature is high or near
operating limits,
i) Land as soon as possible
Note: During warm-weather operation or longer

climbouts at low airspeed engine
temperatures could rise into the yellow
range and trigger the "Caution" light. This
warning allows the pilot to avoid
overheating of the engine as follows:
(3) Increase the climbing airspeed, reduce angle of climb

(4) Reduce power, if the engine temperatures approache the
red range
OIL TEMPERATURE "OT" TOO HIGH (RED RANGE):
(1) Increase airspeed and reduce power as quickly as possible
(2) Check oil pressure: if the oil pressure is lower than normal
(< 2.3 bar in cruise or < 1.2 bar at idle),
i) Land as soon as possible
(3) If the oil pressure is in the normal range:
Page 3-19
Issue 3
COOLANT TEMPERATURE "CT" TOO HIGH (RED RANGE):

(2) Cabin Heat - COLD
(3) If this reduces the coolant temperature to within the normal
operating range quickly, continue to fly normally and
observe coolant temperature. Cabin heat as required.
(4) As far as this does not cause the coolant temperature to
drop,
LIGHT "WATER LEVEL" ILLUMINATES
(2) Coolant temperature "CT" check and observe
(3) Oil temperature "OT" check and observe
(4) As far as coolant temperature and/or oil temperature are
rising into yellow or red range,
GEARBOX TEMPERATURE "GT" TOO HIGH (RED RANGE):
(1) Reduce power to 55% - 75% as quickly as possible
(2) Land as soon as practical.
FUEL TEMPERATURE TOO HIGH (RED RANGE):
(1) Switch to fuel tank with lower fuel temperature, if this con-
tains sufficient fuel
(2) Reduce engine power, if possible
(3) If fuel temperature remains in Red Range, land as soon as
possible
Page 3-20
Issue 3
FUEL TEMPERATURE TOO LOW (AMBER RANGE for Diesel

Operation, RED RANGE for Kerosine Operation):
The fuel in the selected tank will be heated by the return flow,
the temperature in the non-active tank must be monitored.
(1) Switch to fuel tank with higher fuel temperature, if this con-
tains sufficient fuel
(2) Change to altitude with higher outside air temperature
(3) If use of the non-active tank is intended, switch fuel selector
to BOTH when installed
PROPELLER RPM TOO HIGH:
With propeller RPM between 2,400 and 2,500 for more than 10
seconds or over 2,500:
(1) Reduce power
(2) Reduce airspeed below 100 KIAS or as appropriate to
prevent propeller overspeed
(3) Set power as required to maintain altitude and land as soon
as practical.
Note: If the propeller speed control fails, climbs

be performed at 65 KIAS and a power
setting of 100%.
In case of overspeed the FADEC will
reduce the engine power at higher
airspeeds to avoid propeller speeds above
2500 rpm.
Page 3-21
Issue 3
FLUCTUATIONS IN PROPELLER RPM:

If the propeller RPM fluctuates by more than + / - 100 RPM with
a constant Thrust Lever position:
(1) Change the power setting and attempt to find a power set-
ting where the propeller RPM no longer fluctuates.
(2) If this does not work, set the maximum power at an
airspeed < 100 KIAS until the propeller speed stabilizes.
(3) If the problem is resolved, continue the flight
(4) If the problem continues, select a power setting where the
propeller RPM fluctuations are minimum. Fly at an airspeed
below 100 KIAS/ and land as soon as practical.
Page 3-22
Issue 3
SECTION 4
NORMAL PROCEDURES
PREFLIGHT INSPECTION
Figure 4-1a Preflight Inspection
Note: Visually check airplane for general

condition during walk around inspection. In
cold weather, remove even small
accumulations of frost, ice or snow from
wing, tail and control surfaces. Also, make
sure that control surfaces contain no
internal accumulations of ice or debris. Prior
to flight, check that pitot heater (if installed)
is warm to touch within 30 seconds with
battery and pitot heat switches on. If a night
flight is planned, check operation of all
lights, and make sure a flashlight is
available.
Page 4-1
Issue 3
(1) CABIN
(1) Pilot´s Operating Handbook - AVAILABLE IN THE
AIRPLANE
(2) Airplane Weight and Balance - CHECKED
(3) Parking Brake - SET
(4) Control Wheel Lock - REMOVE
(5) "Engine Master" ("IGN" resp.)- OFF
(6) Avionics Power Switch - OFF.
(7) "Shut-off Cabin Heat" - OFF (Push Full Forward)
WARNING: When turning on the Battery switch, using

an external power source, or pulling the
propeller through by hand, treat the
propeller as if the Engine Master ("IGN"
resp.) was on.
(8) Battery and Main Bus switches - ON

(9) Fuel Quantity Indicators and Fuel Temperature
CHECK
(10) Light "Water Level" - CHECK OFF
(11) Battery and Main Bus switches - OFF
(12) Entry in log-book concerning type of fuel filled -
CHECK
(13) Static Pressure Alternate Source Valve - CHECK
(14) Fuel Selector Valve - tank with sufficient fuel quantity
(15) Fuel Shut-off Valve - ON (Push Full In)
(16) Baggage Door - CHECK, lock with key if the child's
seat is supposed to be occupied.
(2) EMPENNAGE
(1) Rudder Gust Lock (if attached) - REMOVE
(2) Tail Tie - Down - DISCONNECT
(3) Control Surfaces - CHECK freedom of movement and
security
Page 4-2
Issue 3
(3) RIGHT WING Trailing Edge

(1) Aileron - CHECK freedom of movement and security
(2) Flap - CHECK for security and condition
(4) RIGHT WING
(1) Wing Tie-Down - DISCONNECT
(2) Main Wheel Tire - CHECK for proper inflation and
general condition (weather checks, tread depth and
wear, etc.)
.
WARNING If, after repeated sampling, evidence of

contamination still exists, the airplane
should not be flown. Tanks should be
drained and system purged by qualified
maintenance personnel. All evidence of
contamination must be removed before
further flight.
(3) Fuel Tank Sump Quick Drain Valves - DRAIN at least

a cupful of fuel (using sampler cup) from each sump
location to check for water, sediment and the right type
of fuel (Diesel or JET-A1) before each flight and after
each refueling. If water is observed, take further
samples until clear and then gently rock wings and
lower tail to the ground to move any additional
contaminants to the sampling points. Take repeated
samples from all fuel drain points until all
contamination has been removed. If contaminants are
still present, refer to above WARNING and do not fly
airplane.
(4) Fuel Quantity - CHECK VISUALLY for desired level
not above marking in fuel filler.
(5) Fuel Filler Cap - SECURE
Page 4-3
Issue 3
(5) NOSE
(1) Reservoir-tank Quick Drain Valve - DRAIN at least a
cupful of fuel (using sampler cup) form valve to check
for water, sediment and proper fuel grade (Diesel or
JET-A1) before each flight and after each refueling. If
water is ovserved, take further samples until clear and
then gently rock wings and lower tail to the ground to
move any additional contaminants to the sampling
point. Take repeated samples until all contamination
has been removed.
(2) Before first flight of the day and after each refueling -
DRAIN the Fuel Strainer Quick Drain Valve with the
sampler cup to remove water and sediment from the
screen. Ensure that the screen drain is properly closed
again. If water is discovered, there might be even more
water in the fuel system. Therefore, take further
samples from Fuel Strainer and the Tank Sumps.
(3) Engine Oil Dipstick/Filler Cap
a) Oil level - CHECK
b) Dipstick/filler cap - SECURE.
Do not operate below the minimum dipstick indication.
(4) Engine Air and Cooling Inlets - CLEAR of obstructions.
(5) Landing Light - CHECK for condition and cleanliness
(6) Propeller and Spinner - CHECK for nicks and security.
(7) Gearbox Oil Level - CHECK the oil has to cover at least
half of the inspection glass
(8) Nose Wheel Strut and Tire- CHECK for proper inflation
of strut and general condition (weather checks, tread
depth and wear, etc.) of tire.
(9) Left Static Source Opening - CHECK for stoppage
Page 4-4
Issue 3
(6) LEFT WING

(1) Fuel Quantity - CHECK VISUALLY for desired level
not above marking in fuel filler.
(2) Fuel Filler Cap - SECURE
(3) Fuel Tank Sump Quick Drain Valves - DRAIN at least
a cupful of fuel (using sampler cup) from each sump
location to check for water, sediment and the right type
of fuel (Diesel or JET-A1) before each flight and after
each refueling. If water is observed, take further
samples until clear and then gently rock wings and
lower tail to the ground to move any additional
contaminants to the sampling points. Take repeated
samples from all fuel drain points until all
contamination has been removed. If contaminants are
still present, refer to previous WARNING (see right
wing) and do not fly airplane.
(4) Main Wheel Tire- CHECK for proper inflation and
general condition (weather checks, tread depth and
wear, etc.)
(7) LEFT WING Leading Edge

(1) Pitot Tube Cover (if mounted) - REMOVE and CHECK
for pitot stoppage
(2) Fuel Tank Vent Opening - CHECK for stoppage
(3) Stall Warning Opening - CHECK for stoppage. To
check the system, place a clean handkerchief over the
vent opening and apply suction; a sound from the
warning horn will confirm system operation.
(4) Wing Tie-Down - DISCONNECT
(8) LEFT WING Trailing Edge

(1) Aileron - CHECK freedom of movement and security.
(2) Flap - Check for security and conditions
Page 4-5
Issue 3
BEFORE STARTING ENGINE

(1) Preflight Inspection - COMPLETE
(2) Seats and Seat Belts - ADJUST and LOCK.
(3) Brakes - TEST and SET., Parking Brake - SET
(4) Avionics Power Switch, Autopilot (if installed) and Electrical
Equipment - OFF.
CAUTION: The Avionics Power Switch must be off

during engine start to prevent possible
damage to avionics.
(5) Circuit Breakers (including CB Alternator, if installed) -

CHECK IN
(6) Battery, Alternator (if Switch installed) and Main Bus
Switches - ON
CAUTION: The electronic engine control needs an

electrical power source for its operation. For
normal operation Battery, Alternator and
Main Bus have to be switched on. Separate
switching is only allowed for tests and in the
event of emergencies.
(7) Fuel Quantity and Temperature - CHECK

(8) Fuel Selector Valve - SET to tank with sufficient fuel
quantity or to BOTH position if this option is installed.The
fuel temperature limitations must be observed.
Note: If the optional LEFT,RIGHT, BOTH fuel

selector is installed it is recommenced to
select the BOTH position
(9) Fuel Shut-off Valve -OPEN (Push Full In)

(10) Alternate Air Door - CLOSED
(11) Thrust Lever - CHECK for freedom of movement
(12) Load Display - CHECK 0% at Propeller RPM 0
Page 4-6
Issue 3
STARTING ENGINE
WARNING: Do not use ground power unit for engine
starts. It is not allowed to start up the
engine using external power. If starting the
engine is not possible using battery power,
the condition of the battery must be verified
before flight.
(1) Electrical Fuel Pump- ON

(3) Area Aircraft / Propeller - CLEAR
(4) "Engine Master" ("IGN" resp.) - ON , wait until the Glow
Control light extinguishes
(5) Starter - ON
Release when engine starts, leave Thrust Lever in idle
(6) Oil Pressure - CHECK
CAUTION: If after 3 seconds the minimum oil pressure
of 1 bar is not indicated:
shut down the engine immediately!
(7) CED-Test Knob - PRESS (to delete Caution light)

(8) Ammeter - CHECK for positive charging current
(9) Voltmeter - CHECK for green range
(10) FADEC Backup Battery test
a) Alternator - OFF, engine must operate normally
b) Battery - OFF, for min. 10 seconds;
engine must operate normally, the red FADEC lamps
must not be illuminated
c) Battery - ON
d) Alternator - ON
WARNING: It must be ensured that both battery and

alternator are ON!
(11) Navigation Lights and Flashing Beacon- ON (as required).

(12) Master Switch - ON
Page 4-7
Issue 3
(13) Radios- ON
(14) Ammeter – Check positive charge, alternator warning light
must be OFF
(15) Voltmeter – Check in green range
(17) Flaps - RETRACT
WARM UP
(1) Let the engine warm up about 2 minutes at 890 RPM.
(2) Increase RPM to 1,400 until Oil Temperature 50°C, Coolant
Temperature 60°C.
BEFORE TAKE-OFF
(2) Cabin Doors and Windows - CLOSED and LOCKED
(3) Flight Controls - FREE and CORRECT
(4) Flight Instruments - CHECK and SET
(5) Fuel quantity - CHECK
(6) Fuel Selector Valve - SET to tank with sufficient fuel
quantity or to the BOTH position if this option is
installed.The fuel temperature limitations must be
observed.
Note If the optional LEFT, RIGHT, BOTH, fuel
selector is installed it is recommended to
select the BOTH position
(7) Elevator Trim and Rudder Trim (if installed) - SET for
Takeoff
(8) FADEC and propeller adjustment function check:
a) Thrust Lever - IDLE (both FADEC lights should be
OFF).
b) FADEC Test Button - PRESS and HOLD button for
entire test.
c) Both FADEC lights - ON, RPM increases
Page 4-8
Issue 3
WARNING: If the FADEC lights do not come on at this

point, it means that the test procedure has
failed and take off should not be attempted.
d) The FADEC automatically switches to B-component

(only FADEC B light is ON)
e) The propeller control is excited, RPM decreases
f) The FADEC automatically switches to channel A
(only FADEC A light is ON), RPM increases
g) The propeller control is excited, RPM decreases
h) FADEC A light goes OFF, idle RPM is reached, the test
is completed.
i) FADEC Test Button - RELEASE.
WARNING: If there are prolonged engine misfires or the

engine shuts down during the test, take off
may not be attempted.
WARNING: The whole test procedure has to be

performed without any failure. In case the
engine shuts down or the FADEC lights are
flashing, take off is prohibited. This applies
even if the engine seems to run without
failure after the test.
Note: If the test button is released before the self

test is over, the FADEC immediately
switches over to normal operation.
Note: While switching from one FADEC to

another, it is normal to hear and feel a
momentary surge in the engine.
(9) Thrust Lever - FULL FORWARD, load display min. 94%,

RPM 2240 - 2300
Page 4-9
Issue 3
(11) Engine Instruments and Ammeter - CHECK

(12) Suction gage - CHECK
(13) Wing Flaps - SET for Take-off ( 0° or 10°).
(15) Strobe Lights - AS DESIRED
(16) Radios and Avionics - ON and SET
(17) Autopilot (if installed) - OFF
(18) Air Conditioning (if installed) - OFF
(19) Thrust Lever Friction Control - ADJUS
(20) Brakes - RELEASE
TAKE-OFF
NORMAL TAKEOFF
(1) Wing Flaps - 0° or 10°
(2) Thrust Lever - FULL FORWARD
(3) Elevator Control - LIFT NOSE WHEEL at 55 KIAS.
(4) Climb Speed - 65 to 80 KIAS
SHORT FIELD TAKEOFF

(1) Wing Flaps - 10°
(2) Brakes - APPLY
(4) Brakes - RELEASE
(5) Airplane Attitude - SLIGHTLY TAIL LOW
(6) Elevator Control - LIFT NOSE WHEEL at 44 KIAS
(7) Climb Speed - 58 KIAS (until all obstacles are cleared)
AFTER TAKEOFF
(1) Altitude about 300 ft, Airspeed more than 65 KIAS - Wing
Flaps - RETRACT
Page 4-10
Issue 3
CLIMB
(1) Airspeed - 70 to 85 KIAS.
Note: If a maximum performance climb is

necessary, use speeds shown in the
"Maximum Rate Of Climb" chart in Section
5. In case that Oil Temperature and/or
Coolant Temperature are approaching the
upper limit, continue at a lower climb angle
for better cooling if possible.

selector valve is installed it is
recommended to select the BOTH position.
The fuel temperatures have to be
monitored.
Page 4-11
Issue 3
CRUISE
(1) Power - maximum load 100% (maximum continuous pow-
er), 75% or less is recommended.
(2) Elevator trim and Rudder trim (if installed) - ADJUST
(3) Compliance with Limits for Oil Pressure, Oil Temperature,
Coolant Temperature and Gearbox Temperature (CED 125
and Caution light) - MONITOR constantly
(4) Fuel Quantity and Temperature (Display and LOW LEVEL
warning lights) - MONITOR.
Whenever possible, the airplane should be flown with the
fuel selector in the BOTH position to empty and heat both
fuel tanks evenly. However, operation in the LEFT or
RIGHT position may be desirable to correct a fuel quantity
imbalance or during periods of intentional uncoordinated
flight maneuvres. During prolonged operation with the fuel
selector in either the LEFT or RIGHT position the fuel
balance and temperatures should be closely monitored.
CAUTION: Do not use any fuel tank below the

minimum permissible fuel temperature!

CAUTION With ¼ tank or less prolonged or

uncoordinated flight is prohibited when
operating on either the left or right tank.
(5) FADEC and Alternator Warning Lights - MONITOR
Page 4-12
Issue 3
DESCENT
(1) Fuel Selector Valve - SELECT BOTH position (if installed)
or SET to tank with sufficient fuel quantity (LEFT or RIGHT)
recommended to select the BOTH position.
The fuel temperatures have to be
monitored.
(2) Power - AS DESIRED
BEFORE LANDING
(1) Pilot and Passenger Seat Backs - MOST UPRIGHT POSI-
TION
(2) Seats and Seat Belts - SECURED and LOCKED
(3) Fuel Selector Valve - SELECT BOTH position (if installed)
or SET to tank with sufficient fuel quantity (LEFT or RIGHT)
recommended to select the BOTH
position.The fuel temperatures have to be
monitored.
(5) Landing / Taxi Lights - ON
(6) Autopilot (if installed) - OFF
(7) Air Conditioning (if installed) - OFF
Page 4-13
Issue 3
LANDING
NORMAL LANDING
(1) Airspeed - 69 to 80 KIAS (wing flaps UP)
(2) Wing Flaps - AS REQUIRED (0°-10° below 110 KIAS; 10°-
Full below 85 KIAS)
(3) Airspeed in Final Approach:
- wing flaps 20°: 63 KIAS
- wing flaps 30°: 60 KIAS
(4) Touchdown - MAIN WHEELS FIRST
(5) Landing Roll - LOWER NOSE WHEEL GENTLY
(6) Brakes - MINIMUM REQUIRED
SHORT FIELD LANDING

(1) Airspeed - 69 to 80 KIAS (Flaps UP)
(2) Wing Flaps - 30°
(3) Airspeed in the Final Approach - 60 KIAS (until flare)
(4) Power - REDUCE to idle after clearing obstacles.
(5) Touchdown - MAIN WHEELS FIRST
(6) Brakes - APPLY HEAVILY
(7) Wing Flaps - RETRACT
BALKED LANDING
(2) Wing Flaps - RETRACT TO 20° (immediately after Thrust
Lever FULL FORWARD)
(3) Climb Speed - 58 KIAS
(4) Wing Flaps - 10° (until all obstacles are cleared)
(5) Wing Flaps - RETRACT after reaching a safe altitude and
65 KIAS
Page 4-14
Issue 3
AFTER LANDING
(1) Wing Flaps - RETRACT
SECURING AIRPLANE
(3) Avionics Power Switch, Electrical Equipment, Autopilot (if
installed) - OFF
(4) Main Bus switch - OFF
(5) "Engine Master" ("IGN" resp.) - OFF
(6) Switch Battery - OFF
(7) Control Lock - INSTALL
(8) Fuel Selector Valve - LEFT or RIGHT (to prevent
crossfeeding between tanks)
Page 4-15
Issue 3
AMPLIFIED PROCEDURES
STARTING ENGINE
The TAE 125 is a direct Diesel injection engine with common-

rail technology and a turbocharger. It is controlled automatically
by the FADEC, which makes a proper performance of the
FADEC test important for safe flight operation.
All information relating to the engine are compiled in the CED
125 multifunction instrument.
Potentiometers within the Thrust Lever transmit the load value
selected by the pilot to the FADEC.
With the Engine Master ("IGN" resp.) in position ON the glow
relay is triggered by the FADEC and the Glow Plugs are
supplied with electrical power, in position OFF the Injection
Valves are not supplied by the FADEC and stay closed.
The switch/push button "Starter" controls the Starter.
EXTERNAL POWER
External power may be used to charge the battery or for

maintenance purposes. To charge the battery with external
power the battery switch must be ON.
When using an External Power Source, the Battery Switch must
be in the OFF position before connecting the External Power
Source to the airplane receptacle.
It is not allowed to start up the engine using external power. If

starting the engine is not possible using battery power, the
condition of the battery must be verified before flight.
Page 4-16
Issue 3
TAXIING
When taxiing, it is important that speed and use of brakes be

held to a minimum and that all controls be utilized (Refer to
Figure 4-2, Taxiing Diagram) to maintain directional control and
balance.
The Alternate Air Door Control should be always pushed for
ground operation to ensure that no unfiltered air is sucked in.
Taxiing over loose gravel or cinders should be done at low
engine speed to avoid abrasion and stone damage to the
propeller tips.
BEFORE TAKE-OFF
WARM UP
To warm up the engine, operate the engine for about 2 minutes

at 890 RPM.
Let the engine run at propeller RPM of 1,400 to ensure normal
operation of the TAE 125 until it reaches an Engine Oil
Temperature of 50°C (green range) and a Coolant Temperature
of 60°C (green range).
MAGNETO CHECK
N/A since this is a Diesel engine.
ALTERNATOR CHECK
Prior to flights where verification of proper alternator and

alternator control unit operation is essential (such as night and
instrument flights), a positive verification can be made by
loading the electrical system momentarily (3 to 5 seconds) with
the landing light or by operating the wing flaps during the engine
runup (20% load). The ammeter will remain within a needle
width of zero if the alternator and alternator control unit are
operating properly.
Page 4-17
Issue 3
BATTERY CHECK
If there is doubt regarding the battery conditions or functionality

the battery has to be checked after warm-up as follows:
Switch-off the alternator while the engine is running (battery

remains "ON").
Perform a 10 sec. engine run. The voltmeter must remain in the

green range. If not, the battery has to be charged or, if
necessary, exchanged.
After this test the alternator has to be switched on again.
TAKE-OFF
POWER CHECK
It is important to check full load engine operation early in the

takeoff roll. Any signs of rough engine operation or sluggish
engine acceleration is good cause for discontinuing the take-off.
If this occurs, you are justified in making a thorough full load
static runup before another take-off is attempted.
After full load is applied, adjust the Thrust Lever Friction Control
to prevent the Thrust Lever from creeping back from a
maximum power position. Similar friction lock adjustments
should be made as required in other flight conditions to maintain
a fixed Thrust Lever setting.
WING FLAP SETTINGS
Flap deflections greater than 10° are not approved for normal
and short field takeoffs. Using 10° wing flaps reduces the
ground roll and total distance over a 15 m obstacle by
approximately 10%.
Page 4-18
Issue 3
CLIMB
Normal climbs are performed with flaps up and full load and at
speeds 5 to 10 knots higher than best rate-of-climb speeds for
the best combination of engine cooling, climb speed and
visibility. The speed for best climb is about 70 KIAS/ . If an
obstruction dictates the use of a steep climb angle, climb at 62
KIAS and flaps up.
Note: Climbs at low speeds should be of short

duration to improve engine cooling.
CRUISE
As guidance for calculation of the optimum altitude and power
setting for a given flight use the tables in chapter 5. Observe the
various rates of consumption with Diesel or Jet A-1-operation.
LANDING
NORMAL LANDING
Remarks in Pilot´s Operating Handbook concerning carburetor

pre-heating are N/A
BALKED LANDING
In a balked landing (go around) climb, reduce the flap setting to
20° immediately after full power is applied. If obstacles must be
cleared during the go-around climb, reduce wing flap setting to
10°and maintain a safe airspeed until the obstacles are cleared.
After clearing any obstacles, the flaps may be retracted as the
airplane accelerates to the normal flaps up climb speed.
CARBURETOR ICING
N/A since this is a Diesel engine.
FLIGHT IN HEAVY RAIN

N/A since no special procedures are necessary for heavy rain.
Page 4-19
Issue 3
COLD WEATHER OPERATION

Special attention should be paid to operation of the aircraft and
the fuel system in winter or before any flight at low
temperatures. Correct preflight draining of the fuel system is
particularly important and will prevent the accumulation of
water.
The following limitations for cold weather operation are
established due to temperature. “Operating limits“.
(Refer Section 2 "Limitations" also)
Minimum permissible Minimum permissible

Fuel fuel temperature in the fuel temperature in the
fuel tank before Take-off fuel tank during the flight
JET A-1,
JET-A,
Fuel No.3
JP-8 -30° -35°
JP8+100
TS-1 (only
C2.0)
Diesel greater than 0° -5°
Figure 4-1a Minimum fuel temperature limits in the fuel tank
WARNING: The fuel temperature of the fuel tank not in

use should be observed if it is intended for
later use.
WARNING: The following applies to Diesel and JET fuel

mixtures in the tank:
As soon as the proportion of Diesel in the
tank is more than 10% Diesel, the fuel
temperature limits have to be observed for
Diesel operation. If there is uncertainty
about the type of fuel in the tank, the
assumption should be made that it is
Diesel.
Page 4-20
Issue 3
Note: lt is advisable to refuel before each flight and

to enter the type of fuel filled and the
additives used in the log-book of the
airplane.
Cold weather often causes conditions which require special

care during airplane operations. Even small accumulations of
frost, ice or snow must be removed, particularly from wing, tail
and all control surfaces to assure satisfactory flight performance
and handling. Also, control surfaces must be free of any internal
accumulations of ice or snow.
If snow or slush covers the take-off surface, allowance must be

made for take-off distances which will be increasingly extended
as snow or slush depth increases. The depth and consistency
of this cover can, in fact, prevent take-off in many instances.
Cold weather starting procedures are the same as the normal

starting procedures. Use caution to prevent inadvertent forward
movement of the airplane during starting when parked on snow
or ice.
Page 4-21
Issue 3
HOT WEATHER OPERATION

Engine temperatures may rise into the
yellow range and activate the "Caution" Light when operating in
hot weather or longer climbouts at low speed. This warning
gives the pilot the opportunity to keep the engine from possibly
overheating by doing the following:
i) decrease rate of climb
ii) increase airspeed
iii) reduce power, if the engine temperatures ap-
proach the red range.
Should the seldom case occur that the fuel temperature is rising
into the yellow or red range, switch to the other tank or to the
BOTH position, if installed.
Page 4-22
Issue 3
SECTION 5
PERFORMANCE
SAMPLE PROBLEM
The following sample flight problem utilizes information from the
various tables and diagrams of this section to determine the
predicted performance data for a typical flight.
Assume the following information has already been determined:
AIRPLANE CONFIGURATION
Takeoff Weight............................... 1043 kg
Usable Fuel ................................... 127.4 l (33.6 US gal)
TAKEOFF CONDITIONS
Field Pressure Altitude................... 1000 ft
Temperature .................................. 28°C ( ISA +15°C)
Wind Component along Runway ... 12 Knot Headwind
Field Length ................................... 1067 m (3500 ft)
CRUISE CONDITIONS
Total Distance ................................ 841 km (400 NM)

Pressure Altitude............................ 6000 ft
Temperature .................................. 23°C (ISA + 20°C)
Expected Wind Enroute ................. 10 Knot Headwind
LANDING CONDITIONS
Field Pressure Altitude................... 2000 ft

Temperature .................................. 25°C
Field Length ................................... 914 m (3000 ft)
Page 5-1
Issue 2
GROUND ROLL AND TAKE-OFF

The ground roll and take-off distance chart, Figure 5-1e (Ground
Roll and Take-off Distance), should be consulted, keeping in
mind that distances shown are based on the short field
technique. Conservative distances can be established by
reading the chart at the next higher value of weight, temperature
and altitude. For example, in this particular sample problem, the
takeoff distance information presented for a weight of 1043 kg,
pressure altitude of 1000 ft and a temperature of 30°C should
be used and results in the following:
Ground Roll..........................................................283 m (927 ft)
Total Distance to clear a 15 m obstacle.............547 m (1793 ft)
These distances are well within the available takeoff field length.
However, a correction for the effect of wind may be made based
on Note 2 of the takeoff chart. The correction for a 12 Knot
Headwind is:
12 Kt
x 10 % = 13 % (Decrease)
9 Kt
This results in the following distances, corrected for wind:
Ground Roll, zero wind ....................................... 283 m (927 ft)

Decrease at 12 Knot Headwind (283m x 13%)= - 37 m (121 ft)
Corrected Ground Roll ........................................ 246 m (806 ft)
Total Distance to clear a 15 m obstacle,

zero wind.......................................................... 547 m (1793 ft)
Decrease at 12 Knot Headwind (547 m x 13%)= - 71 m (233 ft)
Corrected Total Distance to clear a ................ 476 m (1560 ft)
15 m obstacle
Page 5-2
Issue 2
CRUISE
The cruising altitude should be selected based on a
consideration of trip length, winds aloft and the airplanes
performance. A typical cruising altitude and the expected wind
enroute have been given for this sample problem. However, the
power setting selection for cruise must be determined based on
several considerations. These include the cruise performance
characteristics presented in Figures 5-4. Considerable fuel
savings and longer range result when lower power settings are
used.
Figure 5-4a shows a range of 589 NM at zero wind, a power
setting of 70% and altitude of 6000 ft.
With an expected headwind of 10 Knot at 6,000 ft altitude the
range has to be corrected as follows:
Range at zero wind (standard tanks) ....................... 589 NM
Reduction due to Headwind........... (5.5 h x 10 Knots) = - 55NM
Corrected Range...................................................... 534 NM
This shows that the flight can be performed at a power setting

of approximately 70% with full tanks without an intermediate fuel
stop.
Figure 5-4a is based on ISA conditions. For a temperature of

20°C above ISA temperature, according to Note 3, true
airspeed and maximum range are increased by 2 %.
The following values most nearly correspond to the planned
altitude and expected temperature conditions. Engine Power
setting chosen is 70%.
The resultants are:

Engine Power:.....................................................................70%
True Airspeed: .......................................... 102 kt + 2% = 104 kt
Fuel Consumption in cruise: ................... 18.6 l/h (4.9 US gal/h)
Page 5-3
Issue 2
FUEL REQUIRED
The total fuel requirement for the flight may be estimated using
the performance information in Figures 5-3 and 5-4. For this
sample problem, Figure 5-3a shows that a climb from 1000 ft to
6,000 ft requires 3.9 l (1.0 US gal) of fuel. The corresponding
distance during the climb is 10.3 NM. These values are for a
standard temperature and are sufficiently accurate for most
flight planning purposes.
However, a further correction for the effect of temperature may
be made as noted in Note 2 of the climb chart in Figure 5-3. An
effect of 10°C above the standard temperature is to increase
time and distance by 10%.
In this case, assuming a temperature 20°C above standard, the
correction would be:
20 °C
x 10 % = 20 % (Increase)
10 °C
:
With this factor included, the fuel estimate would be calculated

as follows:
Fuel to climb, standard temperature:
3.9 l (1.0 US gal)
Increase due to non-standard temperature:
3.9 l (1.0 US gal) x 20.0% = 0.8 l (0.2 US gal)
Corrected fuel to climb:
4.7 l (1.2 US gal)
Using a similar procedure for the distance to climb results in
12.4 NM.
Page 5-4
Issue 2
The resultant cruise distance is:

Total Distance .......................................................... 400.0 NM
Climbout Distance.................................................... - 12.4 NM
Cruise Distance........................................................ 387.6 NM
With an expected 10 Knot headwind, the ground speed for

cruise is predicted to be:
104 Knot
- 10 Knot
94 Knot
Therefore, the time required for the cruise portion of the trip is:
387.6 NM
= 4.1 hrs
94 Kt
The fuel required for cruise is:

4.1 h x 18.6 l/h = 76.2 l (20.1 US gal)
The total estimated fuel required is as follows:

Engine Start, Taxi and Takeoff ........... 4.0 l (1.1 US gal)
Climb................................................... + 4.7 l (1.2 US gal)
Cruise.................................................. + 76.2 l (20.1 US gal)
Total fuel required ............................... 84.9 l (22.4 US gal)
This gives with full tanks a reserve of:
127.4 l (33.6 US gal)
- 84.9 l (22.4 US gal)
42.5 l (11.2 US gal)
Once the flight is underway, ground speed checks will provide a

more accurate basis for estimating the time enroute and the
corresponding fuel required.
LANDING DISTANCE
Refer to Pilot´s Operating Handbook
Page 5-5
Issue 2
GROUND ROLL AND TAKE-OFF DISTANCE

at 907 kg (2000 lbs)
SHORT FIELD TAKE-OFFS

Conditions:
Take-off weight 907 kg (2000 lbs)
Flaps 10°
Full Power Prior to Brake Release
Paved, level, dry runway
Zero Wind
Lift Off: ...........................................................44 KIAS/ 51 mph
Speed at 15 m / 50 ft: .....................................50 KIAS/ 58 mph
Notes:
1. Short field technique
2. Decrease distances 10% for each 9 Knot headwind. For
operation with tailwinds up to 10 Knot increase distances by
10% for each 2 Knot.
3. For operation on dry, grass runway, increase distances by
15% of the "ground roll" figure.
4. Consider additionals for wet grass runway, softened ground
or snow.
Page 5-6
Issue 2
PRESS Ground Roll and Take-Off Distance [m]

ALT Outside Air Temperature [°C]
[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 129 149 159 170 183 201 224
0
50 ft (15 m) 249 288 308 329 355 389 436
Gnd Roll 138 160 171 182 196 215 240
1000
50 ft (15 m) 267 308 330 353 380 417 467
Gnd Roll 148 171 183 196 211 230 257
2000
50 ft (15 m) 286 331 354 378 407 447 500
Gnd Roll 159 183 196 210 226 247 275
3000
50 ft (15 m) 307 354 379 405 437 479 536
Gnd Roll 170 197 211 225 242 265 295
4000
50 ft (15 m) 329 380 407 435 468 514 576
Gnd Roll 183 211 226 242 260 285 317
5000
50 ft (15 m) 353 408 437 467 503 552 618
Gnd Roll 196 227 243 259 279 306 341
6000
50 ft (15 m) 379 438 469 501 540 593 663
Gnd Roll 218 251 269 287 309 339 377
7000
50 ft (15 m) 421 486 520 556 599 657 736
Gnd Roll 241 279 298 319 343 375 418
8000
50 ft (15 m) 467 539 577 617 665 729 816
Gnd Roll 268 309 331 354 381 417 464
9000
50 ft (15 m) 519 600 641 685 739 810 907
Gnd Roll 298 344 368 393 423 463 516
10000
50 ft (15 m) 577 667 714 763 822 902 1010
Figure 5-1a Ground Roll and Take-Off Distance [m] at take-off

weight 907 kg (2000 lbs)
Page 5-7
Issue 2
PRESS Ground Roll and Take-Off Distance [ft]

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 423 489 523 559 601 658 733
0
50 ft (15 m) 817 944 1010 1079 1163 1276 1429
Gnd Roll 453 524 560 599 644 705 786
1000
50 ft (15 m) 875 1011 1082 1156 1246 1367 1531
Gnd Roll 486 561 600 642 691 756 842
2000
50 ft (15 m) 938 1084 1160 1239 1336 1466 1641
Gnd Roll 521 602 644 688 741 810 903
3000
50 ft (15 m) 1006 1163 1244 1329 1432 1572 1759
Gnd Roll 559 646 691 738 795 870 969
4000
50 ft (15 m) 1080 1247 1334 1426 1537 1686 1888
Gnd Roll 600 693 741 792 853 933 1040
5000
50 ft (15 m) 1159 1339 1432 1531 1649 1810 2026
Gnd Roll 644 744 796 851 916 1002 1117
6000
50 ft (15 m) 1244 1438 1538 1644 1771 1944 2176
Gnd Roll 713 824 882 942 1015 1110 1237
7000
50 ft (15 m) 1380 1594 1705 1823 1964 2155 2413
Gnd Roll 791 914 978 1045 1125 1231 1372
8000
50 ft (15 m) 1531 1769 1893 2023 2180 2392 2678
Gnd Roll 878 1015 1086 1160 1249 1367 1523
9000
50 ft (15 m) 1702 1966 2103 2248 2422 2658 2976
Gnd Roll 976 1128 1207 1290 1388 1519 1693
10000
50 ft (15 m) 1894 2188 2340 2501 2695 2958 3311
Figure 5-1b Ground Roll and Take-Off Distance [ft] at take-off weight
907 kg (2000 lbs)
Page 5-8
Issue 2

at 953 kg (2100 lbs)

Conditions:
Flaps 10°
Zero Wind
Lift Off: ...........................................................44 KIAS/ 51 mph
Notes:
or snow.
Page 5-9
Issue 2

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 146 169 181 193 208 228 254
0
50 ft (15 m) 283 327 350 374 403 442 495
Gnd Roll 157 181 194 207 223 244 272
1000
50 ft (15 m) 303 350 375 400 431 473 530
Gnd Roll 168 194 208 222 239 262 292
2000
50 ft (15 m) 325 375 402 429 462 507 568
Gnd Roll 180 208 223 238 256 281 313
3000
50 ft (15 m) 348 403 431 460 496 544 609
Gnd Roll 193 224 239 256 275 301 335
4000
50 ft (15 m) 374 432 462 494 532 584 654
Gnd Roll 208 240 257 274 295 323 360
5000
50 ft (15 m) 401 464 496 530 571 627 702
Gnd Roll 223 258 276 295 317 347 387
6000
50 ft (15 m) 431 498 533 569 613 673 754
Gnd Roll 247 285 305 326 351 384 428
7000
50 ft (15 m) 478 552 590 631 680 746 835
Gnd Roll 274 316 339 362 390 426 475
8000
50 ft (15 m) 530 613 655 700 755 828 927
Gnd Roll 304 351 376 402 432 473 527
9000
50 ft (15 m) 589 681 728 778 839 920 1030
Gnd Roll 338 391 418 446 481 526 586
10000
50 ft (15 m) 656 758 810 866 933 1024 1147
Figure 5-1c Ground Roll and Take-Off Distance [m] at take-off

Page 5-10
Issue 2

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 480 555 594 635 683 748 833
0
50 ft (15 m) 928 1072 1147 1226 1321 1450 1623
Gnd Roll 515 595 636 680 732 801 892
1000
50 ft (15 m) 994 1149 1229 1313 1415 1553 1739
Gnd Roll 552 637 682 729 784 858 956
2000
50 ft (15 m) 1066 1231 1317 1408 1517 1665 1863
Gnd Roll 591 683 731 781 841 920 1026
3000
50 ft (15 m) 1143 1320 1412 1509 1627 1785 1998
Gnd Roll 635 733 784 838 902 988 1100
4000
50 ft (15 m) 1226 1417 1515 1619 1745 1915 2144
Gnd Roll 681 787 842 900 969 1060 1181
5000
50 ft (15 m) 1316 1521 1627 1738 1873 2056 2301
Gnd Roll 732 845 904 966 1040 1139 1269
6000
50 ft (15 m) 1413 1633 1747 1867 2012 2208 2472
Gnd Roll 810 936 1002 1070 1152 1261 1405
7000
50 ft (15 m) 1567 1811 1937 2070 2230 2448 2740
Gnd Roll 898 1038 1111 1187 1278 1398 1558
8000
50 ft (15 m) 1739 2010 2150 2297 2476 2717 3041
Gnd Roll 997 1152 1233 1318 1418 1552 1730
9000
50 ft (15 m) 1933 2233 2389 2553 2751 3019 3380
Gnd Roll 1109 1281 1370 1465 1577 1725 1922
10000
50 ft (15 m) 2151 2485 2658 2841 3061 3359 3761
Figure 5-1d Ground Roll and Take-Off Distance [ft] at take-off weight
953 kg (2100 lbs)
Page 5-11
Issue 2

at 1043 kg (2300 lbs)

Conditions:
Flaps 10°
Zero Wind
Lift Off: ...........................................................48 KIAS/ 55 mph
Notes:
or snow.
Page 5-12
Issue 2

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 186 214 229 245 264 289 322
0
50 ft (15 m) 359 414 443 474 510 560 627
Gnd Roll 199 230 246 263 283 309 345
1000
50 ft (15 m) 384 444 475 507 547 600 672
Gnd Roll 213 246 263 281 303 332 369
2000
50 ft (15 m) 412 476 509 544 586 643 720
Gnd Roll 228 264 282 302 325 356 396
3000
50 ft (15 m) 441 510 546 583 628 690 772
Gnd Roll 245 283 303 324 349 382 425
4000
50 ft (15 m) 474 547 585 626 674 740 828
Gnd Roll 263 304 325 348 374 410 456
5000
50 ft (15 m) 508 587 628 672 724 794 889
Gnd Roll 283 327 349 373 402 440 490
6000
50 ft (15 m) 546 631 675 721 777 853 955
Gnd Roll 313 362 387 413 445 487 543
7000
50 ft (15 m) 605 699 748 800 862 946 1059
Gnd Roll 347 401 429 458 494 540 602
8000
50 ft (15 m) 672 776 830 888 956 1050 1175
Gnd Roll 385 445 476 509 548 600 668
9000
50 ft (15 m) 747 863 923 986 1063 1166 1306
Gnd Roll 428 495 529 566 609 667 743
10000
50 ft (15 m) 831 960 1027 1097 1183 1298 1453
Figure 5-1e Ground Roll and Take-Off Distance [m] at take-off

Page 5-13
Issue 2

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 609 703 752 804 866 947 1055
0
50 ft (15 m) 1176 1359 1453 1553 1674 1837 2056
Gnd Roll 652 753 806 861 927 1015 1131
1000
50 ft (15 m) 1260 1456 1557 1664 1793 1968 2203
Gnd Roll 699 808 864 923 994 1088 1212
2000
50 ft (15 m) 1350 1560 1669 1784 1922 2109 2361
Gnd Roll 749 866 926 990 1066 1166 1300
3000
50 ft (15 m) 1448 1673 1790 1913 2061 2262 2532
Gnd Roll 804 929 994 1062 1143 1251 1394
4000
50 ft (15 m) 1554 1795 1920 2052 2211 2427 2717
Gnd Roll 863 997 1067 1140 1227 1343 1497
5000
50 ft (15 m) 1668 1927 2061 2203 2374 2605 2916
Gnd Roll 927 1071 1146 1225 1318 1443 1607
6000
50 ft (15 m) 1791 2069 2213 2366 2549 2797 3132
Gnd Roll 1027 1186 1269 1356 1460 1598 1780
7000
50 ft (15 m) 1986 2294 2454 2623 2826 3101 3472
Gnd Roll 1138 1315 1407 1504 1619 1772 1974
8000
50 ft (15 m) 2204 2546 2724 2911 3137 3442 3854
Gnd Roll 1264 1460 1562 1670 1797 1967 2192
9000
50 ft (15 m) 2449 2830 3027 3235 3486 3826 4283
Gnd Roll 1405 1623 1736 1856 1998 2186 2436
10000
50 ft (15 m) 2725 3149 3368 3600 3879 4257 4765
Figure 5-1f Ground Roll and Take-Off Distance [ft] at take-off weight
1043 kg (2300 lbs)
Page 5-14
Issue 2
GROUND ROLL AND TAKE-OFF DISTANCE at 1089 kg

(2400 lbs) (Cessna 172P only)

Conditions:
Flaps 10°
Zero Wind
Lift Off: ...........................................................48 KIAS/ 55 mph
Notes:
or snow.
Page 5-15
Issue 2

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 207 239 256 274 295 323 359
0
50 ft (15 m) 400 463 495 529 570 625 700
Gnd Roll 222 257 274 293 316 346 385
1000
50 ft (15 m) 429 496 530 567 611 670 750
Gnd Roll 238 275 294 314 338 370 413
2000
50 ft (15 m) 460 531 568 607 654 718 804
Gnd Roll 255 295 315 337 363 397 443
3000
50 ft (15 m) 493 570 609 651 702 770 862
Gnd Roll 274 316 338 362 389 426 475
4000
50 ft (15 m) 529 611 654 699 753 826 925
Gnd Roll 294 340 363 388 418 457 510
5000
50 ft (15 m) 568 656 702 750 808 887 993
Gnd Roll 316 365 390 417 449 491 547
6000
50 ft (15 m) 610 705 754 806 868 953 1066
Gnd Roll 350 404 432 462 497 544 606
7000
50 ft (15 m) 676 781 836 893 962 1056 1182
Gnd Roll 388 448 479 512 551 603 672
8000
50 ft (15 m) 750 867 927 991 1068 1172 1312
Gnd Roll 430 497 532 568 612 670 746
9000
50 ft (15 m) 834 964 1031 1102 1187 1303 1458
Gnd Roll 478 553 591 632 680 744 829
10000
50 ft (15 m) 928 1072 1147 1226 1321 1449 1623
Figure 5-1g Ground Roll and Take-Off Distance [m] at take-off

weight 1089 kg (2400 lbs) (Cessna 172P only)
Page 5-16
Issue 2

[ft] --- -20°C 0°C 10°C 20°C 30°C 40°C 50°C
Gnd Roll 680 785 840 898 967 1058 1179
0
50 ft (15 m) 1313 1517 1623 1735 1869 2051 2297
Gnd Roll 728 841 900 962 1036 1133 1263
1000
50 ft (15 m) 1407 1626 1739 1858 2003 2198 2460
Gnd Roll 781 902 965 1031 1110 1215 1354
2000
50 ft (15 m) 1508 1742 1864 1992 2146 2356 2637
Gnd Roll 837 967 1035 1106 1190 1303 1451
3000
50 ft (15 m) 1617 1869 1999 2136 2302 2526 2828
Gnd Roll 898 1038 1110 1186 1277 1398 1557
4000
50 ft (15 m) 1735 2005 2144 2292 2470 2710 3034
Gnd Roll 964 1114 1192 1273 1371 1500 1672
5000
50 ft (15 m) 1862 2152 2302 2460 2651 2909 3257
Gnd Roll 1035 1196 1280 1368 1472 1611 1795
6000
50 ft (15 m) 2000 2311 2472 2642 2847 3124 3498
Gnd Roll 1147 1325 1417 1515 1631 1785 1988
7000
50 ft (15 m) 2218 2562 2741 2929 3156 3464 3878
Gnd Roll 1271 1469 1572 1680 1808 1979 2205
8000
50 ft (15 m) 2461 2844 3042 3251 3503 3845 4304
Gnd Roll 1412 1631 1745 1865 2007 2197 2448
9000
50 ft (15 m) 2735 3160 3381 3613 3893 4273 4783
Gnd Roll 1569 1813 1939 2073 2231 2442 2721
10000
50 ft (15 m) 3043 3517 3762 4020 4332 4754 5322
Figure 5-1h Ground Roll and Take-Off Distance [ft] at take-off weight
1089 kg (2400 lbs) (Cessna 172P only)
Page 5-17
Issue 2
MAXIMUM RATE-OF-CLIMB at 1043 kg (2300 lbs)

Conditions:
Climb speed vy = 70 KIAS/ 81 mph
Flaps Up
Full Power
Notes:
1. For operation in air colder than this table provides, use
coldest data shown.
2. For operation in air warmer than this table provides, use
extreme caution.
PRESS Climb Rate of Climb [ft/min]
ALT speed Outside Air Temperature [°C]
[FT] [KIAS] -20°C 0°C +20°C +40°C +50°C
0 70 684 665 647 542 433
1000 70 675 656 638 532 422
2000 70 666 646 628 522 412
3000 70 656 636 618 511 401
4000 70 647 626 607 500 390
5000 70 637 616 596 489 379
6000 70 626 605 585 478 367
7000 70 592 570 550 444 335
8000 70 558 536 515 410 303
9000 70 523 500 479 376 271
10000 70 488 465 443 341 238
11000 70 453 429 407 306 205
12000 70 417 393 371 271 171
13000 70 381 357 334 236 138
14000 70 345 320 296 200 103
15000 70 308 283 259 163 69
16000 70 271 245 221 126 34
17000 70 234 207 182 89 -2
18000 70 196 169 143 51 -38
Figure 5-2a Maximum Rate of Climb at take-off weight 1043 kg
(2300 lbs)
Page 5-18
Issue 2
MAXIMUM RATE-OF-CLIMB at 1089 kg (2400 lbs)

(Cessna 172P only)
Conditions:
Flaps Up, Full Power
Notes:
1. For operation in air colder than this table provides, use
coldest data shown.
2. For operation in air warmer than this table provides, use
extreme caution.
PRESS Climb Rate of Climb [ft/min]
ALT speed Outside Air Temperature [°C]
[FT] [KIAS] -20°C 0°C +20°C +40°C +50°C
0 70 625 605 587 485 379
1000 70 615 595 577 475 369
2000 70 606 586 567 464 358
3000 70 596 575 556 453 347
4000 70 586 565 546 442 336
5000 70 576 554 535 431 324
6000 70 565 543 523 419 312
7000 70 532 510 489 386 281
8000 70 498 476 454 353 250
9000 70 464 441 420 319 218
10000 70 430 406 384 285 186
11000 70 395 371 349 251 153
12000 70 361 336 313 216 120
13000 70 325 300 277 181 87
14000 70 290 264 240 146 53
15000 70 254 228 203 110 19
16000 70 217 191 166 74 -16
17000 70 181 153 128 37 -51
18000 70 143 116 90 0 -86
Figure 5-2b Maximum Rate of Climb at take-off weight
1089 kg (2400 lbs) (Cessna 172P only)
Page 5-19
Issue 2
TIME, FUEL AND DISTANCE TO CLIMB at 1043 KG (2300 lbs)

Conditions:
Flaps Up
Full Power
Standard Temperature (ISA)
Notes :
1. Add 4 l (1.1 US gal) of fuel for engine start, taxi and takeoff
allowance.
2. Increase time and distance by 10% for 10°C above standard
temperature.
3. Distances shown are based on zero wind.
4. Time, distance and fuel required are only valid from the point
where the airplane climbs at vy = 70 KIAS.
Page 5-20
Issue 2
Press.
OAT Vy ROC Time Distance Fuel used
Alt.
[US
[ft] [°C] [KIAS] [FPM] [MIN] [NM] [l]
Gal]
0 15 70 653 0.0 0.0 0.0 0.0
1000 13 70 645 1.5 1.8 0.8 0.2
2000 11 70 637 3.1 3.7 1.5 0.4
3000 9 70 629 4.7 5.7 2.3 0.6
4000 7 70 621 6.3 7.7 3.1 0.8
5000 5 70 612 7.9 9.9 3.9 1.0
6000 3 70 603 9.5 12.1 4.7 1.2
7000 1 70 571 11.3 14.5 5.4 1.4
8000 -1 70 538 13.1 17.1 6.1 1.6
9000 -3 70 505 15.0 20.0 6.8 1.8
10000 -5 70 472 17.0 23.0 7.5 2.0
11000 -7 70 439 19.2 26.4 8.2 2.2
12000 -9 70 405 21.6 30.2 8.9 2.3
13000 -11 70 371 24.2 34.3 9.6 2.5
14000 -13 70 337 27.0 39.0 10.4 2.7
15000 -15 70 303 30.1 44.2 11.2 3.0
16000 -17 70 268 33.6 50.2 12.0 3.2
17000 -19 70 233 37.6 57.1 13.0 3.4
18000 -21 70 198 42.2 65.2 14.0 3.7
Figure 5-3a Time, Fuel and Distance to Climb at 1043 kg (2300 lbs)
Page 5-21
Issue 2
TIME, FUEL AND DISTANCE TO CLIMB at 1089 KG

(Cessna 172P only)
Conditions:
Flaps Up
Full Power
Standard Temperature (ISA)
Notes :
1. Add 4 l (1.1 US gal) of fuel for engine start, taxi and takeoff
allowance.
2. Increase time and distance by 10% for 10°C above standard
temperature.
3. Distances shown are based on zero wind.
4. Time, distance and fuel required are only valid from the point
where the airplane climbs at vy = 70 KIAS.
Page 5-22
Issue 2
Press. Distanc
OAT Vy ROC Time Fuel used
Alt. e
[US
[ft] [°C] [KIAS] [FPM] [MIN] [NM] [l]
Gal]
0 15 70 593 0.0 0.0 0.0 0.0
1000 13 70 585 1.7 2.0 0.8 0.2
2000 11 70 576 3.4 4.1 1.7 0.4
3000 9 70 568 5.2 6.3 2.5 0.7
4000 7 70 560 6.9 8.6 3.4 0.9
5000 5 70 551 8.7 11.0 4.3 1.1
6000 3 70 542 10.6 13.5 5.2 1.4
7000 1 70 510 12.5 16.1 6.0 1.6
8000 -1 70 478 14.5 19.0 6.7 1.8
9000 -3 70 446 16.7 22.2 7.5 2.0
10000 -5 70 414 19.0 25.7 8.3 2.2
11000 -7 70 381 21.5 29.6 9.1 2.4
12000 -9 70 348 24.2 33.9 10.0 2.6
13000 -11 70 315 27.3 38.8 10.9 2.9
14000 -13 70 282 30.6 44.2 11.8 3.1
15000 -15 70 248 34.4 50.5 12.8 3.4
16000 -17 70 214 38.7 57.8 13.9 3.7
17000 -19 70 180 43.8 66.5 15.1 4.0
18000 -21 70 146 49.9 77.1 16.6 4.4
Figure 5-3b Time, Fuel and Distance to Climb at 1089 kg (2400 lbs)
(Cessna 172P only)
Page 5-23
Issue 2
CRUISE PERFORMANCE, RANGE AND ENDURANCE

with standard tanks at 1043 kg (2300 lbs)
Conditions:
Flaps Up
Zero wind
Notes:
1. Endurance information is based on standard tanks with
127.4 l (33.6 US gal) usable fuel.
2. The table assumes 4 l for startup and taxi; time, fuel and
distance to climb and 45 min. reserve.
3. Increase true airspeed (KTAS) and maximum range (NM) by
1% per 10°C above ISA temperature.
4. Cruise Power above 85% not recommended. For economic
cruise set load 70% or less.
Page 5-24
Issue 2
Endu-
Press.
Load Speed Fuel Flow Distance rance
Alt.
Time
[ft] [%] [KTAS] [mph] [l/h] [US Gal/h] [NM] [Hrs]
SL 100 115 132 29.5 7.8 394 3.4
SL 90 110 126 25.3 6.7 453 4.1
SL 80 104 120 21.7 5.7 514 4.9
SL 70 98 113 18.6 4.9 576 5.9
SL 60 91 104 15.8 4.2 641 7.1
SL 50 82 95 13.0 3.4 720 8.7
2000 100 117 134 29.5 7.8 399 3.3

2000 90 111 128 25.3 6.7 457 4.0
2000 80 106 122 21.7 5.7 518 4.8
2000 70 99 114 18.6 4.9 580 5.8
2000 60 92 106 15.8 4.2 645 6.9
2000 50 83 96 13.0 3.4 723 8.6
4000 100 119 137 29.5 7.8 403 3.2

4000 90 113 130 25.3 6.7 462 3.9
4000 80 107 124 21.7 5.7 523 4.7
4000 70 101 116 18.6 4.9 585 5.6
4000 60 93 107 15.8 4.2 649 6.8
4000 50 84 97 13.0 3.4 726 8.4
6000 100 121 139 29.5 7.8 407 3.1

6000 90 115 133 25.3 6.7 466 3.8
6000 80 109 126 21.7 5.7 527 4.6
6000 70 102 118 18.6 4.9 589 5.5
6000 60 95 109 15.8 4.2 653 6.6
6000 50 85 98 13.0 3.4 728 8.2
8000 90 117 135 25.3 6.7 471 3.7

8000 80 111 128 21.7 5.7 532 4.4
8000 70 104 120 18.6 4.9 593 5.3
8000 60 96 111 15.8 4.2 656 6.4
8000 50 86 99 13.0 3.4 730 8.0
Page 5-25
Issue 2
Endu-
Press.
Alt.
Time
10000 90 119 137 25.3 6.7 475 3.5
10000 80 113 130 21.7 5.7 536 4.3
10000 70 106 122 18.6 4.9 598 5.2
10000 60 97 112 15.8 4.2 660 6.3
10000 50 87 101 13.0 3.4 731 7.8
12000 80 115 132 21.7 5.7 541 4.1

12000 70 107 124 18.6 4.9 602 5.0
12000 60 99 114 15.8 4.2 663 6.1
12000 50 88 102 13.0 3.4 731 7.6
14000 80 117 134 21.7 5.7 545 3.9

14000 70 109 126 18.6 4.9 606 4.8
14000 60 100 115 15.8 4.2 666 5.9
14000 50 89 102 13.0 3.4 730 7.4
Figure 5-4a Cruise Performance, Range and Endurance with

standard tanks, at 1043 kg (2300 lbs)
Page 5-26
Issue 2

with long-range tanks (Cessna 172N) at 1043 kg (2300 lbs)
Conditions:
Flaps Up
Zero wind
Notes:
1. Endurance information is based on long-range tanks with
Page 5-27
Issue 2
Endu-
Press.
Alt.
Time
SL 100 115 132 29.5 7.8 516 4.5
SL 90 110 126 25.3 6.7 588 5.4
SL 80 104 120 21.7 5.7 663 6.4
SL 70 98 113 18.6 4.9 740 7.6
SL 60 91 104 15.8 4.2 820 9.0
SL 50 82 95 13.0 3.4 918 11.1
2000 100 117 134 29.5 7.8 522 4.4

2000 90 111 128 25.3 6.7 595 5.2
2000 80 106 122 21.7 5.7 670 6.3
2000 70 99 114 18.6 4.9 747 7.4
2000 60 92 106 15.8 4.2 827 8.9
2000 50 83 96 13.0 3.4 923 11.0
4000 100 119 137 29.5 7.8 529 4.3

4000 90 113 130 25.3 6.7 601 5.1
4000 80 107 124 21.7 5.7 677 6.1
4000 70 101 116 18.6 4.9 754 7.3
4000 60 93 107 15.8 4.2 833 8.7
4000 50 84 97 13.0 3.4 928 10.8
6000 100 121 139 29.5 7.8 535 4.2

6000 90 115 133 25.3 6.7 608 5.0
6000 80 109 126 21.7 5.7 684 6.0
6000 70 102 118 18.6 4.9 761 7.2
6000 60 95 109 15.8 4.2 840 8.6
6000 50 85 98 13.0 3.4 933 10.6
8000 90 117 135 25.3 6.7 615 4.9

8000 80 111 128 21.7 5.7 691 5.9
8000 70 104 120 18.6 4.9 768 7.0
8000 60 96 111 15.8 4.2 846 8.4
8000 50 86 99 13.0 3.4 937 10.4
Page 5-28
Issue 2
Endu-
Press.
Alt.
Time
10000 90 119 137 25.3 6.7 622 4.8
10000 80 113 130 21.7 5.7 699 5.7
10000 70 106 122 18.6 4.9 775 6.8
10000 60 97 112 15.8 4.2 852 8.2
10000 50 87 101 13.0 3.4 940 10.2
12000 80 115 132 21.7 5.7 706 5.6

12000 70 107 124 18.6 4.9 782 6.7
12000 60 99 114 15.8 4.2 858 8.1
12000 50 88 102 13.0 3.4 943 10.0
14000 80 117 134 21.7 5.7 713 5.4

14000 70 109 126 18.6 4.9 789 6.5
14000 60 100 115 15.8 4.2 863 7.8
14000 50 89 102 13.0 3.4 944 9.8
Figure 5-4b Cruise Performance, Range and Endurance

with long-range tanks, at 1043 kg (2300 lbs)
Page 5-29
Issue 2

with standard tanks at 1089 kg (2400 lbs)
(Cessna 172P)
Conditions:
Flaps Up
Zero wind
Notes:
1. Endurance information is based on standard tanks with
Page 5-30
Issue 2
Endu-
Press.
Alt.
Time
SL 100 114 131 29.5 7.8 392 3.4
SL 90 109 125 25.3 6.7 449 4.1
SL 80 103 119 21.7 5.7 509 4.9
SL 70 97 112 18.6 4.9 570 5.9
SL 60 90 103 15.8 4.2 633 7.1
SL 50 81 93 13.0 3.4 708 8.7
2000 100 116 133 29.5 7.8 396 3.3

2000 90 111 127 25.3 6.7 453 4.0
2000 80 105 121 21.7 5.7 513 4.8
2000 70 98 113 18.6 4.9 574 5.7
2000 60 91 105 15.8 4.2 636 6.9
2000 50 82 94 13.0 3.4 710 8.6
4000 100 118 136 29.5 7.8 399 3.2

4000 90 112 129 25.3 6.7 457 3.9
4000 80 107 123 21.7 5.7 517 4.7
4000 70 100 115 18.6 4.9 578 5.6
4000 60 92 106 15.8 4.2 639 6.7
4000 50 83 95 13.0 3.4 711 8.4
6000 100 120 138 29.5 7.8 403 3.1

6000 90 114 132 25.3 6.7 461 3.7
6000 80 108 125 21.7 5.7 521 4.5
6000 70 101 117 18.6 4.9 581 5.4
6000 60 93 108 15.8 4.2 642 6.6
6000 50 84 96 13.0 3.4 711 8.2
8000 90 116 134 25.3 6.7 465 3.6

8000 80 110 127 21.7 5.7 525 4.4
8000 70 103 118 18.6 4.9 584 5.3
8000 60 95 109 15.8 4.2 644 6.4
8000 50 85 97 13.0 3.4 711 8.0
Page 5-31
Issue 2
Endu-
Press.
Alt.
Time
10000 90 118 136 25.3 6.7 469 3.5
10000 80 112 129 21.7 5.7 529 4.2
10000 70 105 120 18.6 4.9 588 5.1
10000 60 96 110 15.8 4.2 646 6.2
10000 50 85 98 13.0 3.4 710 7.7
12000 80 114 131 21.7 5.7 532 4.0

12000 70 106 122 18.6 4.9 590 4.9
12000 60 97 112 15.8 4.2 648 6.0
12000 50 86 99 13.0 3.4 708 7.5
14000 80 115 133 21.7 5.7 536 3.8

14000 70 108 124 18.6 4.9 593 4.7
14000 60 98 113 15.8 4.2 649 5.7
14000 50 87 100 13.0 3.4 704 7.2
Figure 5-4c Cruise Performance, Range and Endurance

with standard tanks, Cessna 172P at 1089 kg (2400 lbs)
Page 5-32
Issue 2

with long-range tanks at 1089 kg (2400 lbs)
(Cessna 172P)
Conditions:
Flaps Up
Zero wind
Notes:
1. Endurance information is based on long-range tanks with
Page 5-33
Issue 2
Endu-
Press.
Alt.
Time
SL 100 114 131 29.5 7.8 512 4.5
SL 90 109 125 25.3 6.7 584 5.4
SL 80 103 119 21.7 5.7 658 6.4
SL 70 97 112 18.6 4.9 733 7.6
SL 60 90 103 15.8 4.2 810 9.0
SL 50 81 93 13.0 3.4 903 11.1
2000 100 116 133 29.5 7.8 518 4.4

2000 90 111 127 25.3 6.7 590 5.2
2000 80 105 121 21.7 5.7 664 6.2
2000 70 98 113 18.6 4.9 739 7.4
2000 60 91 105 15.8 4.2 816 8.9
2000 50 82 94 13.0 3.4 906 11.0
4000 100 118 136 29.5 7.8 524 4.3

4000 90 112 129 25.3 6.7 596 5.1
4000 80 107 123 21.7 5.7 671 6.1
4000 70 100 115 18.6 4.9 745 7.3
4000 60 92 106 15.8 4.2 821 8.7
4000 50 83 95 13.0 3.4 910 10.8
6000 100 120 138 29.5 7.8 530 4.1

6000 90 114 132 25.3 6.7 602 5.0
6000 80 108 125 21.7 5.7 677 6.0
6000 70 101 117 18.6 4.9 751 7.1
6000 60 93 108 15.8 4.2 827 8.5
6000 50 84 96 13.0 3.4 912 10.6
8000 90 116 134 25.3 6.7 609 4.8

8000 80 110 127 21.7 5.7 683 5.8
8000 70 103 118 18.6 4.9 757 6.9
8000 60 95 109 15.8 4.2 831 8.3
8000 50 85 97 13.0 3.4 914 10.4
Page 5-34
Issue 2
Endu-
Press.
Alt.
Time
10000 90 118 136 25.3 6.7 615 4.7
10000 80 112 129 21.7 5.7 689 5.6
10000 70 105 120 18.6 4.9 763 6.8
10000 60 96 110 15.8 4.2 836 8.1
10000 50 85 98 13.0 3.4 915 10.1
12000 80 114 131 21.7 5.7 696 5.5

12000 70 106 122 18.6 4.9 768 6.6
12000 60 97 112 15.8 4.2 840 7.9
12000 50 86 99 13.0 3.4 914 9.9
14000 80 115 133 21.7 5.7 702 5.3

14000 70 108 124 18.6 4.9 774 6.3
14000 60 98 113 15.8 4.2 843 7.7
14000 50 87 100 13.0 3.4 912 9.6
Figure 5-4d Cruise Performance, Range and Endurance with

long-range tanks, Cessna 172P at 1089 kg (2400 lbs)
Page 5-35
Issue 2

with Integraltanks at 1089 kg (2400 lbs) (Cessna 172P)
Conditions:
Flaps Up
Zero wind
Notes:
1. Endurance information is based on integral tanks with 196.8 l
(52 US gal) usable fuel.
Page 5-36
Issue 2
Endu-
Press.
Alt.
Time
SL 100 114 131 29.5 7.8 660 5.8
SL 90 109 125 25.3 6.7 748 6.9
SL 80 103 119 21.7 5.7 840 8.1
SL 70 97 112 18.6 4.9 932 9.6
SL 60 90 103 15.8 4.2 1027 11.5
SL 50 81 93 13.0 3.4 1141 14.1
2000 100 116 133 29.5 7.8 668 5.7

2000 90 111 127 25.3 6.7 757 6.7
2000 80 105 121 21.7 5.7 849 8.0
2000 70 98 113 18.6 4.9 941 9.5
2000 60 91 105 15.8 4.2 1036 11.3
2000 50 82 94 13.0 3.4 1147 13.9
4000 100 118 136 29.5 7.8 677 5.6

4000 90 112 129 25.3 6.7 766 6.6
4000 80 107 123 21.7 5.7 858 7.9
4000 70 100 115 18.6 4.9 950 9.3
4000 60 92 106 15.8 4.2 1044 11.1
4000 50 83 95 13.0 3.4 1153 13.7
6000 100 120 138 29.5 7.8 685 5.4

6000 90 114 132 25.3 6.7 775 6.5
6000 80 108 125 21.7 5.7 867 7.7
6000 70 101 117 18.6 4.9 959 9.2
6000 60 93 108 15.8 4.2 1053 10.9
6000 50 84 96 13.0 3.4 1158 13.5
8000 90 116 134 25.3 6.7 784 6.3

8000 80 110 127 21.7 5.7 877 7.6
8000 70 103 118 18.6 4.9 969 9.0
8000 60 95 109 15.8 4.2 1061 10.8
8000 50 85 97 13.0 3.4 1162 13.3
Page 5-37
Issue 2
Endu-
Press.
Alt.
Time
10000 90 118 136 25.3 6.7 793 6.2
10000 80 112 129 21.7 5.7 886 7.4
10000 70 105 120 18.6 4.9 978 8.8
10000 60 96 110 15.8 4.2 1068 10.6
10000 50 85 98 13.0 3.4 1165 13.1
12000 80 114 131 21.7 5.7 896 7.2

12000 70 106 122 18.6 4.9 986 8.6
12000 60 97 112 15.8 4.2 1075 10.3
12000 50 86 99 13.0 3.4 1167 12.8
14000 80 115 133 21.7 5.7 905 7.0

14000 70 108 124 18.6 4.9 995 8.4
14000 60 98 113 15.8 4.2 1081 10.1
14000 50 87 100 13.0 3.4 1166 12.5
Figure 5-4e Cruise Performance, Range and Endurance

with Integraltanks, Cessna 172P at 1089 kg (2400 lbs)
Page 5-38
Issue 2
Figure 5-5 Density Altitude Chart
Page 5-39
Issue 2
Figure 5-6 Engine Power Over Altitude
Page 5-40
Issue 2
SECTION 6
HANDLING ON GROUND
& MAINTENANCE
WARNING: Do not start the engine in any case when
filling levels are below the corresponding
minimum marking.
CAUTION: Normally, a refill of coolant or gearbox oil

between service intervals is not necessary.
In case of low coolant or gearbox oil levels,
inform the maintenance company
immediately.
ENGINE OIL
Both TAE 125 engine variants are filled with 4.5 - 6 l engine oil
(refer to section 1 of this supplement for specification).
A dip stick is used to check the oil level. It is accessible by a flap
on the upper right-hand side of the engine cowling.Notice that
on warm engines 5 minutes after engine shut-off there are 80%
of the entire engine oil in the oil pan and therefore visible o the
oil dip stick. On warm engines oil should be added if the oil dip
stick shows oil levels below 50%. After 30 minutes the real oil
level is visible on the dip stick.
The drain screw is located on the lower left-hand outside of the
oil pan, the oil filter is on the upper left-hand side of the housing.
The oil system has to be checked for sealing after the first 5
operating hours (visual inspection).
Checks and changes of oil and oil filter have to be performed
regularly according to the engine Operation and Maintenance
Manual. See OM 02-01 for the TAE 125-01 engine or OM-02-02
for the TAE 125-02 engine.The Supplement of the Aircraft
Maintenance Manual has to be considered as well. See AMM-
20-01 for the TAE 125-01 engine or AMM-20-02 for the TAE
125-02 engine.
Page 6-1
Issue
GEARBOX OIL
To ensure the necessary propeller speed, tboth TAE 125
variants are equipped with a reduction gearbox filled with
gearbox oil. (refer to section 1 of this supplement for
specification)The level can be checked through a viewing glass
on the lower leading edge of the gearbox. To do so open the
flap on the left front side of the engine cowling.
The drain screw is located at the lowest point of the gearbox. A
filter is installed upstream of the pump, as well as microfilter in
the Constant Speed Unit. Check the gearbox for sealing after
the first 5 hours of operation (visual inspection). Regular
checks as well as oil and filter changes have to be performed in
according with the engine Operation and Maintenance Manual.
See, see OM-02-01 for the TAE 125-01 engine or OM-02-02
for the TAE 125-02 engine.
The Supplement of the Aircraft Maintenance Manual has to be
considered as well. See AMM-20-01 for the TAE 125-01 engine
or AMM-20-02 for the TAE 125-02 engine.
WARNING: It is not allowed to start the engine with low

gearbox oil level.
CAUTION: Between scheduled maintenance topping

up gearbox oil should not be necessary. If
low gearbox oil level is detected, inform
your service centre immediately.
Page 6-2
Issue 3
FUEL
Both TAE 125 can be operated with kerosene (Jet A-1, Jet A,
Fuel No. 3, JP-8, TS-1 (only C2.0)) or Diesel fuel.
Due to the higher specific density of engine fuel or Diesel in
comparison to aviation gasoline (AVGAS) the permissible
capacity for standard tanks was reduced as mentioned in
Section 1.
Appropriate placards are attached near the fuel filler
connections.
For temperature limitations refer to Section 2 "Limitations" and
Section 4 "Normal Operation".
It is recommended to refuel before each flight and to enter the

type of fuel into the log-book.
COOLANT
To cool the engine a liquid cooling system was installed with a
water/approved radiator protection mixture at a ratio of 1:1.
A heat exchanger for cabin heating is part of the cooling system.
Check the cooling system for sealing after the first 5 hours of
operation (visual inspection).
The coolant has to be changed in accordance with the engine
Operation and Maintenance Manual. See OM-02-01 for the TAE
125-01 engine or OM-02-02 for the TAE 125-02 engine.
The Supplement of the Aircraft Maintenance Manual has to be
considered as well. See AMM-20-01 for the TAE 125-01 engine
or AMM-20-02 for the TAE 125-02 engine.
WARNING: It is not allowed to start the engine with low

coolant level.
CAUTION: Between scheduled maintenance topping-

up coolant should not be necessary. If low
coolant level is detected, inform your
service centre immediately.
Page 6-3
Issue
CAUTION. The water has to satisfy the following

requirements:
1. visual appearance: colorless, clear and
no deposits allowed
2. pH-value: 6.5 to 8.5
3. maximum water hardness: 2.7 mmol/l
4. maximum hydrogen carbonate
concentration: 100 mg/l
5. maximum chloride concentration:
100 mg/l
6. maximum sulfate concentration:
100 mg/l
Note: The freezing point of the coolant is -36°C.
Note: The waterworks also provide information.

In general, tap water may be diluted with
distilled water. Pure distilled water may not
be used to mix with approved radiator
protection.
Page 6-4
Issue 3
SECTION 7
WEIGHT & BALANCE
Item Weight x Arm = Moment

(kg) (m) (mkp)
Empty Weight
plus Engine Oil

-0.31
(6 l to 0.9 kg/l)
plus Gearbox Oil
-0.69
(1 l to 0.9 kg/l)
plus unusable fuel
standard tanks 1.17
(11.4 l to 0.84 kg/l)
long-range tanks
1.17
(15.0 l to 0.84 kg/l)
integral tanks
1.17
(22.8 l to 0.84 kg/l)
plus Coolant
-0.26
(4 l to 1.0 kg/l)
Changes in Equipment
Basic Empty Weight
Figure 7-1 Calculating the Basic Empty Weight
Page 7-1
Issue 3
Revision 1, Sept. 2011
Your aircraft
Mass Moment
kg mkp
1. Basic Empty Weight:
Use the values for your airplane
with the present equipment.
Unusable fuel, engine oil, gearbox
oil and coolant are included.
2. Usable Fuel (at 0.84 kg/l),
Standard tanks (127.4 l max.)
Long-range tanks (158.6 l max.)
Integral tanks (196.8 l max.)
Calculation of the loaded condition
3. Pilot and Front Passenger

(Station 0.86 to 1.17 m)
4. Rear Passenger
5. *Baggage Area 1 or Passenger
on the children‘s seat
(Station 2.08 to 2.74; max.54kg)
6. *Baggage Area 2
(Station 2.74 to 3.61; max. 23kg)
7. Ramp Weight and Moment
8. Fuel allowance for engine start,
taxi and runup
9. Take-off Weight and Moment
(Subtract Step 8 from Step 7)
10.Locate this point in the weight
and balance envelope in the
original POH.
Check if its within the envelope.
*Maximum allowable combinded
weight capacity for Baggage Areas 1
and 2 is 54 kg.
Figure 7-2 Calculating Weight and Moment
Page 7-2
Issue 3
Figure 7-3 Load Moment
Page 7-3
Issue 3
This page has been intentionally left blank
Page 7-4
Issue 3
SECTION 8
SPECIAL EQUIPMENT
EQUIPMENT LIST
CARBURETOR AIR TEMPERATURE GAGE
N/A
QUICK OIL DRAIN VALVE

N/A
Page 8-1
Issue 3
Revision -, July 2010
This page has been intentionally left blank
Page 8-2
Issue 3
Revision -, July 2010
SECTION 9
SUPPLEMENTS
TABLE OF CONTENTS
No supplement
Page 9-1
Issue 3
Page 9-2
Issue 3

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Thielert Aircraft Engines GmbH Tel.

This supplement must be attached to the EASA approved

The information contained in this supplement supersede or add

This supplement Pilot‘s Operating Handbook is approved with

3/0 all new Issue 23.08.2010 EASA AFM

3/1 1 New oil, editorial changes April 14, 2011

3/2 1 New gearbox oil, Sept. 22, EASA AFM

2 New gearbox oil,

5 Flight performance with

3/3 1 New fuel, new gearbox oil March 16,

3/4 1 New gearbox oil March 11,

2 New gearbox oil

LIST OF APPLICABLE CHAPTERS

The content of this POH supplement is developed on basis of

LOG OF REVISIONS......................................................page iii

LIST OF APPLICABLE CHAPTERS.............................. page vi

GENERAL REMARK ..................................................... page vi

TABLE OF CONTENTS ................................................page vii

CONVERSION TABLES ...............................................page viii

ABBREVIATIONS ..........................................................page xii

Foot pound [ft.lb] [ft.lb] / 7.2331 = [kpm]

TAE Thielert Aircraft Engines GmbH, developing

FADEC Full Authority Digital Engine Control

CED 125 Compact Engine Display

AED 125 Auxiliary Engine Display

This manual contains following conventions and warnings.

WARNING: Non-compliance with these safety rules

CAUTION: Non-compliance with these special notes

Note: Information added for a better

UPDATE AND REVISION OF THE MANUAL

WARNING: A safe operation is only assured with an up

Note: The TAE-No of this POH supplement is

The TAE 125-02-99 is the successor of the 125-01. Both engine

Due to this specific characteristic, all of the information from the

FUELS and LIQUIDS

CAUTION: Normally it is not necessary to fill the cooling

Note: The freezing point of the coolant is -36°C.

Figure 1-1 Example of Instrument panel with TAE 125 installation

13. "Alt. Air Door" Alternate Air Door

51. AED 125 SR with indication of Fuel Flow, Fuel Temperature,

Figure 1-2 Lightpanel

FUEL SYSTEM (Left, Right)

FUEL SYSTEM (Left, Right)

CAUTION: In flight conditions with downward pointing

Fuel selector &

Fuel tank left Fuel tank right

Fuel tank ventilation line

Fuel tank temperature indication

Low fuel warning

Figure 1-3a Scheme of the Fuel System (Left, Right)

FUEL SYSTEM (Left, Right, Both)

FUEL SYSTEM (Left, Right, Both)

CAUTION In turbulent air it is strongly recommended

Figure 1-3b Scheme of the Fuel System (Left, Right, Both)

Note The handling of the fuel selector positions

1. Switch "Main Bus"

2. Circuit Breaker (Switch resp.) "Alternator"

4. Push Button (Switch resp.) "Starter"

&/2#%" !,4%2.!4/2 )NST0ANEL

&/2#%" !,4%2.!4/2 )NST0ANEL