CEAPR DR400/135CDI User manual

PILOT’S OPERATING HANDBOOK
SUPPLEMENT
DR400/135CDI
Document n° 1001639GB
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Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Issue 3 –July 2014 Page i
Pilot´s Operating Handbook
Supplement
for the
DR400/120D
DR400/140B
DR400/180R
DR400/200R
DR400/RP
Equipped with TAE 125 Installation
TYPE ................................DR 400
MODEL No.......................
SERIAL No.......................
REGISTER No. ................
This supplement must be attached to the EASA approved Pilot´s
Operating Handbook of the DR400/120D, DR400/140B, DR400/180R,
DR400/200R or DR400/RP when the TAE 125-01 or TAE 125-02-99
installation has been installed in accordance with EASA.A.S.01380 or
EASA STC 10014219.
The information contained in this supplement supersedes or adds 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
STC 10014219.
Doc.Nr.: 1001639GB
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Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Page - ii Issue 3 - July 2014
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Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Issue 3 –July 2014 Page iii
APPROVAL
Issue 2:
The content of approved sections 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.
Issue 3:
The content of approved sections is approved by EASA, transfer of STC
10014219. C.E.A.P.R is TC holder.
LOG OF REVISIONS
Issue/
Rev.
Section
Description
Approval
D
at
e
Endorsed
2/1
2
New fuel,
new gearbox oil
M
ar
c
h
1
6
2
0
1
2
Revision No. 1 to AFM
supplement ref 60-0310-
60022 is approved under
the authority of DOA ref.
EASA.21J.010.
Date: March 16 ,2012
Office of Airworthiness
4
Procedures updated
3/0
all
Change of TC holder
Initial issue C.E.A.P.R
Numbering of CEAPR
documents
J
ul
y
2
0
1
4
EASA STC 10014219
transfer
The parts of the text which changed are marked with a vertical line on
the margin of the page.
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Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Page - iv Issue 3 - July 2014
LIST OF EFFECTIVE SECTIONS
Section
Issue/ Revision
Date
0
3/0
July 2014
1
3/0
July 2014
2
3/0
July 2014
3
3/0
July 2014
4
3/0
July 2014
5
3/0
July 2014
6
3/0
July 2014
7
3/0
July 2014
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DR400/180R, DR400/200R, DR400/RP
Issue 3 –July 2014 Page v
TABLE OF CONTENTS
APPROVAL.............................................................................................. iii
LOG OF REVISIONS............................................................................... iii
LIST OF EFFECTIVE SECTIONS........................................................... iii
ABBREVIATIONS....................................................................................xi
SECTION 0
GENERAL
CONVENTIONS IN THIS HANDBOOK.................................................0-1
FOR DR400 AIRCRAFT FROM SERIAL NUMBER 2500 AND UP......0-1
UPDATE AND REVISION OF THE MANUAL.......................................0-1
SECTION 1
DESCRIPTION
OVERALL DIMENSIONS ......................................................................1-1
ENGINE .................................................................................................1-1
PROPELLER..........................................................................................1-2
NOISE LIMITATION...............................................................................1-2
ELECTRICAL SYSTEM.........................................................................1-3
FADEC-RESET......................................................................................1-6
FUELS, OILS and LIQUIDS...................................................................1-6
ENGINE OIL...........................................................................................1-7
FUEL SYSTEM......................................................................................1-7
OPTIONAL EXTENDED RANGE TANK ...............................................1-8
INSTRUMENT PANEL.........................................................................1-11
HEATING AND VENTILATION............................................................1-20
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Page - vi Issue 3 - July 2014
SECTION 2
LIMITATIONS
APPROVED OPERATION....................................................................2-1
MAXIMUM ALTITUDE...........................................................................2-1
FLIGHT LOAD FACTOR LIMITS AT MAXIMUM WEIGHT ..................2-2
MAXIMUM AUTHORIZED WEIGHTS ..................................................2-2
WEIGHT AND BALANCE .....................................................................2-2
LOAD PLANNING .................................................................................2-3
ENGINE OPERATING LIMITS..............................................................2-3
ENGINE INSTRUMENT MARKINGS ...................................................2-6
GROUNDING (EARTHING) BEFORE AND DURING FUELING.........2-6
PERMISSIBLE FUEL GRADES............................................................2-7
MAXIMUM FUEL QUANTITIES............................................................2-7
PERMISSIBLE OIL GRADES ...............................................................2-7
PERMISSIBLE COOLING LIQUID .......................................................2-8
LOAD LIMITS........................................................................................2-8
OPERATIONAL LIMITATIONS IN THE “U” CATEGORY ....................2-8
PLACARDS...........................................................................................2-9
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SECTION 3
EMERGENCY PROCEDURES
ENGINE FAILURE OR LOSS OF POWER...........................................3-2
During takeoff roll...................................................................................3-2
Immediately after takeoff .......................................................................3-2
During flight............................................................................................3-3
LANDING WITHOUT ENGINE POWER ...............................................3-4
Restart after engine failure ....................................................................3-5
FADEC malfunction in flight...................................................................3-6
ENGINE SHUT-DOWN IN FLIGHT.......................................................3-8
FIRE.......................................................................................................3-9
Engine fire on the ground, during starting .............................................3-9
Engine fire in flight ................................................................................3-9
Electrical fire ........................................................................................3-10
ROUGH ENGINE OPERATION ..........................................................3-11
Oil pressure too low .............................................................................3-11
Oil temperature too high ......................................................................3-12
Coolant temperature too high ..............................................................3-12
“Cool level” light illuminates.................................................................3-13
Gearbox temperature too high.............................................................3-13
Fuel temperature too low.....................................................................3-13
Propeller RPM too high........................................................................3-14
Fluctuations in propeller RPM..............................................................3-14
ICING ...................................................................................................3-14
ELECTRICAL POWER SUPPLY MALFUNCTION .............................3-16
If the “ALT” light is lit or the ammeter shows battery discharge during
normal engine operation for more than 5 minutes...............................3-17
INADVERTENT SPIN..........................................................................3-18
LOSS OF ELEVATOR CONTROL ......................................................3-18
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Page - viii Issue 3 –July 2014
SECTION 4
NORMAL PROCEDURES
NORMAL OPERATING SPEEDS.........................................................4-1
Best rate of climb speed........................................................................4-1
Maximum operating speed in turbulent air............................................4-1
Never Exceed speed.............................................................................4-1
Maximum speed....................................................................................4-1
Landing speed, final approach..............................................................4-1
PRE-FLIGHT INSPECTION..................................................................4-2
CABIN INTERIOR CHECK BEFORE START-UP................................4-5
STARTING THE ENGINE.....................................................................4-6
AFTER ENGINE START.......................................................................4-7
FADEC BACKUP BATTERY TEST ......................................................4-7
WARM UP .............................................................................................4-8
TAXIING................................................................................................4-8
BEFORE TAKEOFF..............................................................................4-8
TAKEOFF............................................................................................4-11
Short takeoff .......................................................................................4-11
Crosswind takeoff................................................................................4-11
CLIMB..................................................................................................4-12
Normal climb (flaps up) .......................................................................4-12
CRUISE...............................................................................................4-12
DESCENT ...........................................................................................4-13
Approach or downwind........................................................................4-13
Final.....................................................................................................4-13
LANDING.............................................................................................4-14
Short landing .......................................................................................4-14
Overshoot procedure...........................................................................4-14
AFTER LANDING................................................................................4-14
ENGINE SHUT-DOWN.......................................................................4-14
After the engine stops .........................................................................4-14
PARKING BRAKE USE ......................................................................4-15
Brake on..............................................................................................4-15
Brake off..............................................................................................4-15
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Issue 3 –July 2014 Page ix
SECTION 5
PERFORMANCE
AIRSPEED INSTALLATION CALIBARTION.........................................5-1
STALL SPEEDS ....................................................................................5-1
TAKEOFF PERFORMANCE .................................................................5-2
Takeoff distance, 1100 kg......................................................................5-3
Takeoff distance, 1000 kg......................................................................5-4
CLIMB PERFORMANCE.......................................................................5-5
Climb speeds .........................................................................................5-5
Rate of climb, Flaps retracted, 1100 kg.................................................5-6
Rate of climb, Flaps retracted, 1000 kg.................................................5-7
Time, fuel and distance to climb, Flaps retracted, 1100kg....................5-8
Time, fuel and distance to climb, Flaps retracted, 1000kg....................5-9
Maximum angle of climb in takeoff position.........................................5-10
Glide performance ...............................................................................5-10
CRUISE PERFORMANCE ..................................................................5-11
At maximum take-off weight, 1100 kg .................................................5-12
At take-off weight 980 kg .....................................................................5-15
LANDING PERFORMANCE................................................................5-18
SECTION 6
WEIGHT AND BALANCE
USE OF WEIGHT AND BALANCE DIAGRAM .....................................6-3
Example of loading problem (dashed line on the diagram)...................6-3
SECTION 7
SUPPLEMENTS
No supplements
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DR400/180R, DR400/200R, DR400/RP
Page -x Issue 3 - July 2014
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Supplement POH DR400/120D, DR400/140B,
DR400/180R, DR400/200R, DR400/RP
Issue 3 –July 2014 Page xi
ABBREVIATIONS
TAE Thielert Aircraft Engines GmbH, developing and
manufacturing company of the Centurion 2.0 S engine, (since
July 2013, Technify Motors GmbH).
FADEC Full Authority Digital Engine Control
CED 125 Compact Engine Display. Multifunctional instrument for
indication of engine data of the TAE 125-01 and TAE 125-02-
99 engine.
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DR400/180R, DR400/200R, DR400/RP
Page -xii Issue 3 –July 2014
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DR400/180R, DR400/200R, DR400/RP
Issue 3 –July 2014 Page 0 - 1
SECTION 0
GENERAL
CONVENTION IN THIS HANDBOOK
This manual contains the following convention and warnings. They
should be strictly followed to rule out personal injury, property damage,
and 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.
FOR DR400 AIRCRAFT FROM SERIAL NUMBER 2500 AND UP
This supplement is valid if the TAE 125-01 or TAE 125-02-99 aircraft
engine is installed.
UPDATE AND REVISION OF THE MANUAL
▲WARNING: A safe operation is only assured with an up to date POH
supplement.
Note: The document number of this POH supplement is
published on the cover sheet of this supplement.
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DR400/180R, DR400/200R, DR400/RP
Page 0 - 2 Issue 3 –July 2014
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DR400/180R, DR400/200R, DR400/RP
Issue 3 –July 2014 Page 1 - 1
SECTION 1
DESCRIPTION
OVERALL DIMENSIONS
Wing span................................................................ (28 ft 7.3 in) 8.72 m
Overall length...............................................................(23 ft 8 in) 7.20 m
Overall height........................................................... (7 ft 3.79 in) 2.23 m
Propeller ground clearance...............................................(9.5 in) 0.26 m
ENGINE
Engine manufacturer...........................................Technify Motors GmbH
Engine models ........................................TAE 125-01 or TAE 125-02-99
The TAE 125-02-99 is the successor of the TAE 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 engine variants are liquid cooled in-line four-stroke 4-cylinder
engines 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 operate for a very limited
time on FADEC backup battery power (TAE 125-02-99
installation).
Therefore, it is important to pay attention to indications of
alternator failure.
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Page 1 - 2 Issue 3 –July 2014
Due to the specific characteristic of the TAE 125 engine, all of the
information from the original DR400 flight manual recognized by EASA
are no longer valid with the 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.........................................................................................1.87m
Type................................................................................Constant Speed
NOISE LIMITATION
In compliance with the regulation ICAO, annex 16, Volume I, Part II,
Chapter X, the maximum acceptable noise level for the DR400/120D,
DR400/140B, DR400/180R, DR400/200R, DR400/RP at a certified max.
take-off weight of 980 kg (2161 lb) is 78.4 dB(A).
For the TAE 125-01 installation:
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with "Akrapovic type for TAE 125" muffler, is 70.9 dB(A).
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with no installed muffler, is 74.4 dB(A).
For the TAE 125-02-99 installation:
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with "Akrapovic type for TAE 125" muffler, is 70.2 dB(A).
The noise level determined under the conditions of the abovementioned
regulation, with the MT Propeller MTV-6-A/187-129 propeller together
with “Langer LA 44” muffler, is 69.1 dB(A).
ELECTRICAL SYSTEM
The electrical system of the TAE 125 installation differs from the previous
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Issue 3 –July 2014 Page 1 - 3
installation and is equipped with the following operating and display
elements:
1. Rocker Switch "Battery"
The battery must be switched ON in normal operation.
2. The circuit breaker below the Rocker Switch "Battery" disables the
alternator. The alternator can be left ON always.
3. Key Switch "Starter"
This switch controls the starter motor only.
4. Voltmeter
5. Warning lamp "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 lamp always illuminates when the “Engine Master” (“IGN” resp.)
is switched on without revolution and extinguished immediately after
starting the engine.
6. Switch "Engine Master"
The Engine Master switch controls the two redundant FADEC
components, and the back-up alternator excitation battery, with three
independent contacts. It is protected against unintentional switching with
a pull-to-actuate mechanism and a guard. The alternator excitation
battery is used to ensure that the alternator continues to function in any
circumstances even if the main battery fails.
7. 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.
8. FADEC Backup Battery (TAE 125-02-99 installation)
The backup battery ensures power supply to A-FADEC only when supply
from main battery and alternator is interrupted. This allows continued
engine operation for limited time only.
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Page 1 - 4 Issue 3 –July 2014
STARTER
PITOT HEAT
(optional)
ALTERNATOR
BATTERY
EXTERNAL POWER
PLUG
SWITCH TYPE
CIRCUIT BREAKER
TRIP FREE
CIRCUIT BREAKER
SWITCH
PUSH
BUTTON
WARNING
LIGHT
FADEC
PULLTO
FORCEB
ENGINEMASTER
ALTERNATOR
BATTERY
TEST
START
(key)
GLOW
CED
COMPACTENGINEDISPLAY
TEST/ ACK TURNINDICATOR
VOLTMETER
STROBE
LIGHT
NAVIGATION
LIGHT
TAXI
LIGHT
LANDING
LIGHT
ELECT.
PUMP
FUEL
TEMPERATURE
PITOT
HEAT
DIMMERS
AVIONICS
STALLWARNING
FUELGAUGE
ANNUNCIATORPANEL
FUEL
TEMPERATURE
ICE ZONE
ELECTRONICSINTERNATIONAL
C
RDO & inst.
Cabin
Figure 1-1 Simplified block diagram
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