BRM Aero BRISTELL B23 Technical specifications

Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
I
Date of Issue: 15.04.2021
The technical content of this document is approved under the authority of the DOA ref. EASA. 21J.411
BRISTELL B23
AIRCRAFT FLIGHT MANUAL

AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
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Date of Issue: 15.04.2021
INTENTIONALLY LEFT BLANK

AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
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Date of Issue: 15.04.2021
Model: BRISTELL B23
Serial No: …………….
Registration: ………………
Document No.: ADXC-73-001-AFM
Date of Issue: 15.04.2021
For approval reference of pages identified as “Approved page” refer to
Section 0.1 record of revisions
This aircraft must be operated in compliance with information and
limitations contained herein.
This document must be available on-board of the aircraft permanently in a
form acceptable for the NAA.

AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
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Date of Issue: 15.04.2021
Contact Data for Occurrences
BRM AERO s.r.o.
Letecká 255
686 04 Kunovice
Czech republic
Tel.: [phone]
Mail: [email protected]m
www.bristell.com
Aircraft Design Certification GmbH
Reichensteinstrasse 48
69151 Neckargemünd
Germany
Tel.: [phone]
Mail: [email protected]
www.aircraftdc.de

AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
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Date of Issue: 15.04.2021
SECTION 0
0 TECHNICAL INFORMATION
0.1 Record of revisions................................................0-1
0.2 List of Effective Pages...........................................0-2
0.3 Table of Contents...................................................0-5
0.4 Symbols, Abbreviations, Terminology.................0-6

AIRCRAFT FLIGHT
MANUAL
BRISTELL B23
Document No.: ADXC-73-001-AFM
Non-approved page
Revision: A2
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Date of Issue: 15.04.2021
0.1 Record of revisions
Any revision of the present manual, except actual weighing data, must be
recorded in the following table and in case of approved Sections
endorsed by the Agency.
The new or amended text in the revised pages will be indicated by a
black vertical line in the left hand margin, and the Revision No. and the
date will be shown on the bottom left hand side of the page.
Issue
Affected
Pages
Date
Change/Reason
Approval
Reference
A
all
07.10.20
First issue
EASA.A.642
A1
I
1-8
2-16
5-11…5-13
6-11…6-13
11.01.21
Change of Cover picture
Correction of typo
typo correction in fuel filler placard
Clarification of performance graph axis
label, correction of typo
Removal SN column
EASA.A.642
A2
ALL
Several
2-17
6-4, 6-5
7-37
9-2
Editorial update:
(on all instances, see change bar)
- AEPS and fire extinguisher “if installed”
- Refinement procedures
- Typo(s), spelling see change bar
- Battery type
- Wording improvements / unification /
abbreviations / formatting
Added note for indication above 45liter
Clarifications W&B section
update of lat./long. limitation ESI-500
Update of list of potential supplements
ADxC-DC-
73-016

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AIRCRAFT FLIGHT
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Document No.: ADXC-73-001-AFM
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Date of Issue: 15.04.2021
0.3 Table of Contents
Sections:
0 Technical Information ................................................................0-0
1 General.......................................................................................1-0
2 Limitations..................................................................................2-0
3 Emergency procedures ..............................................................3-0
4 Normal procedures ....................................................................4-0
5 Performance...............................................................................5-0
6 Weight and balance ...................................................................6-0
7 Aeroplane and system description.............................................7-0
8 Aeroplane handling, servicing and maintenance.......................8-0
9 Supplements ..............................................................................9-0

AIRCRAFT FLIGHT
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Document No.: ADXC-73-001-AFM
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Date of Issue: 15.04.2021
0.4 Symbols, Abbreviations, Terminology
AEPS Aircraft emergency parachute system
AGL Above ground level
C.G. Centre of gravity
CHT Cylinder head temperature
EASA European Union Aviation Safety Agency
EGT Exhaust gas temperature
EIS Engine indication system (used to describe the physical unit
collecting engine sensor data)
ELT Emergency location transmitter
EMS Engine monitoring system (used to describe the pilot interface and
indication)
ISA International standard Atmosphere
LHS Left hand side
MAC Mean aerodynamic chord
MACLE Distance of MAC to Datum
MCP Maximum continuous power
MFD Multifunction display
MLG Main landing gear
MTOP Maximum take-off power
MTOW Maximum take-off weight
NAV/COM Combined VOR navigation and communication radio unit
NLG Nose landing gear
OAT Outside air temperature
PED Personal electronic device
PFD Primary flight display
RHS Right hand side
ROC Rate of climb
RPM Revolutions per minute (used synonym with engine speed, not
synonym with propeller speed)
SL Sea level
TOW Take-off weight
VOR Very high frequency (VHF) omnidirectional radio range
WOT Wide open Throttle
XPDR Transponder

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Speeds:
CAS Calibrated airspeed
EAS Equivalent airspeed
IAS Indicated airspeed
TAS True airspeed
VADesign manoeuvring speed
VFE Maximum speed with flaps extended
VHMaximum level flight speed
VNE Never exceed speed
VNO Maximum structural cruising speed
VSStall speed
VS0 Stell speed in landing configuration
VXSpeed for best angle of climb
VYSpeed for best rate of climb
NOTE
For all practical purposes for this airplane EAS=CAS.

AIRCRAFT FLIGHT
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Document No.: ADXC-73-001-AFM
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Revision: A2
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Date of Issue: 15.04.2021
SECTION 1
1 GENERAL
1.1 Introduction ............................................................1-1
1.2 Certification basis..................................................1-1
1.3 Warnings, cautions and notes ..............................1-2
1.3.1 AFM warnings, cautions and notes.................................1-2
1.3.2 Pilot warnings, cautions and advisory lights....................1-3
1.4 Descriptive data......................................................1-8
1.4.1 Dimensions External.......................................................1-9
1.4.2 Dimensions Internal........................................................1-9
1.5 Three-view drawing..............................................1-10

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Document No.: ADXC-73-001-AFM
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Revision: A2
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Date of Issue: 15.04.2021
1.1 Introduction
The aeroplane Flight Manual has been prepared to provide pilots and
operators with information for the safe and efficient operation of this very
light aeroplane.
This manual includes the information required to be supplied to the pilot
according to the certification basis
It also contains supplemental data supplied by the aeroplane
manufacturer.
1.2 Certification basis
This type of aircraft has been approved by the European Union Aviation
Safety Agency in accordance with
•CS-23 Amdt. 5
•CS-ACNS, issue 2
and the
Type Certificate No. : EASA.A.642
has been issued on (date): 07.10.2020
Category of Airworthiness: Normal
Noise Certification Basis: ICAO Annex 16, Volume I, Chapter 10
(10.4b)
Type Certificate No. : TCDSN EASA.A.642
The determined noise emission value according ICAO Annex 16 Chapter
10 Vol. 1. is 69.2dB(A).

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1.3 Warnings, cautions and notes
1.3.1 AFM warnings, cautions and notes
The following definitions apply to warnings, cautions and notes used in
the flight manual.
WARNING
Means that the non-observation of the corresponding procedure leads to
an immediate or important degradation of the flight safety.
CAUTION
Means that the non-observation of the corresponding procedure leads to
a minor or to a more or less long term degradation of the flight safety.
NOTE
Draws the attention to any special item not directly related to safety but
which is important or unusual.

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1.3.2 Pilot warnings, cautions and advisory lights
The colour coding for pilot indications follows the aviation standard:
-RED: immediate danger, immediate pilot action
-AMBER: condition acceptable only for limited time
-GREEN: normal operation
-Any other: Information
The following table gives an overview of implication and required
procedures to react and interpret the indications.
Light
Display
Condition
Implication/ Procedure
RED,
EMS
master
warning
Cylinder Head
Temp.:
max. limit exceeded
AFM 4.4.9 Climb:
Reduce climb angle / increase
airspeed
Exhaust Gas
Temp.:
max. limit exceeded
AFM 4.4.11 Descent:
Reduce RPM
Oil Temperature:
max. limit exceeded
AFM 4.4.9 Climb:
Reduce climb angle / increase
airspeed
Oil Pressure:
min. limit exceeded
AFM 3.8.3 Loss of oil
pressure:
1. Reduce engine power
setting to the minimum
necessary
2. Check oil temperature; if
high:
- reduce oil temp
if temperature decrease does
not result in improvement:
- land as soon as practical
CHT
EGT
OIL
TEMP
OIL PRESS

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Light
Display
Condition
Implication/ Procedure
cont...
RED,
EMS
master
warning
Oil Pressure:
max. limit exceeded
AFM 3.8.4 High oil pressure:
1. Reduce engine power
setting to the minimum
necessary
2. engine RPM (propeller)
- reduce <5000
3. Speed
- 67 KIAS
4. Land as soon as practical
3.6.2
AFM 4.4.3 Engine starting:
Oil pressure with a cold engine
could be high. A maximum of
7bar is acceptable
Manifold Pressure:
max. limit exceeded
Reduce power / Throttle
Note: exceedance physically only
possible in very high ambient
pressure condition (ambient press
> 1050hPa), sensor failure should
be considered.
Fuel Pressure:
min. limit exceeded
Transient fuel pressure below
0.15bar acceptable for
maximum 5sec
Switch fuel pump ON
Fuel Pressure:
max. limit exceeded
Switch fuel pump OFF
Switch fuel tank (L/R)
Reduce RPM
Engine Speed
(RPM):
max. limit exceeded
Reduce RPM (propeller)
Reduce Throttle (power)
Fuel Quantity:
Less than unusable
fuel amount in
respective tank
Switch fuel tank
Land as soon as practical
Prepare for precautionary
landing Chapter 3.6.2
FUEL PRESS
RPM
OIL PRESS
MAN PRESS
FUEL PRESS
FUEL L
FUEL R

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Light
Display
Condition
Implication/ Procedure
cont...
RED,
EMS
master
warning
Electric system
voltage
below 8 Volt
Check ALT1/ALT2 ON
Check AMP positive (charging
the system)
USB power - remove load
switch off all non-essential
electrical equipment
see AFM 3.8.5 Alternator
failure / use of back-up battery
3.8.6 Bus system failure
Electric system
voltage above 15
Volt
Reduce engine RPM (propeller
and power)
Alt1 switch –OFF (if not
sufficient)
Alt2 switch –OFF (if not
sufficient)
See AFM 3.8.7 Overvoltage
Battery current
below -20A
(discharge)
If positive charge (Amps)
cannot be maintained on one
alternator: Consider use of
back-up battery see 3.8.5
- Land as soon as practical
Battery current
above +25A
(charge)
MASTER Switch OFF
AMB.
EMS
master
caution
Oil Temperature:
min. caution limit
exceeded
Engine starting:
Engine speed <2500 RPM
Cruise
Increase power / reduce RPM
Fuel Quantity:
Less than 10liter in
respective tank
Switch tank (L/R)
Check flight planning
AMPS
VOLTS
VOLTS
AMPS
OIL TEMP
FUEL L
FUEL R

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Light
Display
Condition
Implication/ Procedure
cont...
AMB.
EMS
master
caution
Electric system
voltage below 11
Volt
Check ALT1/ALT2 ON
Check AMP positive (charging
the system)
USB power - remove load
switch off all non-essential
electrical equipment
Battery current
below -10 Amp
(discharge)
Observe; if continuous:
Check ALT1/ALT2 ON
Check AMP positive (charging
the system)
USB power - remove load
switch off all non-essential
electrical equipment
Battery current
above +10Amp
(charge)
Observe; if continuous:
MASTER Switch OFF
Alternator 1 does
not deliver
Switch ALT 1 ON,
Check ALT 1 and ALT 1 CTRL
CB
If the caution indication
persists: ALT 1 OFF
Alternator 2 does
not deliver
Switch ALT 2 ON,
Check ALT 2 and ALT 2 CTRL
CB
If the caution indication
persists: ALT 2 OFF
Back Up Batt supply
insufficient (below
11 Volt)
Check system voltage, if low
consider 3.8.5 Alternator
failure / use of back-up battery
BACKUP BATT
VOLTS
AMPS
AMPS
ALT 1
ALT 2

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Light
Display
Condition
Implication/ Procedure
AMB.
LOW
FUEL
Left
N/A
Usable fuel
remaining less than
6 liter in left tank
This system is electrically
independent of the fuel QTY
indication. In case of
conflicting information landing
is advised as soon as practical
AMB.
LOW
FUEL
Right
N/A
Usable fuel
remaining less than
6 liter in right tank
This system is electrically
independent of the fuel QTY
indication. In case of
conflicting information landing
is advised as soon as practical
GRE.,
Fuel
pump
ON
N/A
El. Fuel pump is
switched on
is triggered by the power
supply to the electric pump –
actual pump function of
pressure built up must be
checked using the fuel
pressure indication
GRE.,
Land.
light
ON
N/A
Landing light or
WIG/WAG is
switched ON
is triggered by the landing light
power supply in both,
WIG/WAG and ON mode
GRE.
Pitot
Heat
ON
N/A
Pitot Heat is
switched ON
is triggered by the power
supply to the heating element
–it does not sense actual
current or temperature built up.
This must be checked in pre-
flight inspection.
BLUE
Ext.
Power
ON
N/A
External Power
supply connected
is triggered by the connected
external power
Set park break / use wheel
chocks
Never taxi with the External
power light illuminated