Sandel SA4550 Manual

82050-PG-ERR-F1 SANDEL SA4550 PG ERRATA PAGE 1 OF 2
SA4550
Pilot’s Guide Effectivity and Errata
Insert this update ahead of the cover page of the above referenced Pilot’s
Guide.
Date:
Effectivity:
Errata:
06-NOV-2013
SA4550 Software Version 1.09
Pilots Guide 82050-PG-F
With the exception of the
superseding information contained
in this document, operation of the
SA4550 is as described in the
SA4550 Pilot’s Guide referenced
above.
82050-PG-ERR-F1 SANDEL SA4550 PG ERRATA PAGE 2 OF 2
1) Page 2-8: added description of Radar Altimeter test.
CONTROL FEATURE
FUNCTION OPERATION
Radar Altimeter Test:
Used to test radar
altimeter system. If a
radar altimeter system is
not installed or remote
test function is not
enabled, the message
“Function Not Installed”
will appear when [RA
TEST] is pressed.
Depress [RA TEST]
button and observe
radar altimeter display
for proper indications.
See AFM for proper
radar altimeter test
display indications. For
installations using a
digital 429 radar
altimeter, the text “RAD
ALT” in the radar
altimeter window of the
display will be replaced
with “RA TEST” in
amber while the system
is under test.
RADAR
ALTIMETER
TEST

SA4550
Primary Attitude Display
Pilot’s Guide
82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE II
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82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE III
Pilot information
Publication Date: 29-SEP-2012
This guide provides information on the use and operation of the
SA4550 Primary Attitude Display.
Information in this manual is current as of publication or revision
date. Specifications and operational details are subject to change
without notice at the discretion of Sandel Avionics, Inc.
Copyright
Copyright 2012 Sandel Avionics, Inc.
May be covered by one or more US and foreign patents, including:
US Patent Nos. 6,259,378, 6,670,892, 6,507,288, 6,750,788,
6,972,695, and 7,187,304. Australia Patent No. 750,651. China
Patent No. 1211639C. Israel Patent Nos. 135,174, 153,460, and
155,983. All rights reserved. No part of this manual may be
reproduced, stored or distributed without written permission of
Sandel Avionics, Inc. Additional copies of this manual are available
from:
Sandel Avionics, Inc.
2401 Dogwood Way
Vista, CA 92081
Tel: [phone]
Fax: [phone]
www.sandel.com
82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE IV
Revision notice
The “Effectivity, Errata, and Revision History” allow the use of this
Pilot Guide with a specific software release and specifically lists the
software to which this Pilot’s Guide applies and corrects any errors
or omissions that may exist in this revision of the Pilot’s Guide.
Document number 82010-PG-ERR, Effectivity, Revision History,
and Errata” can be found on page x of this Pilot’s Guide.
Operational and legal issues
The information displayed on the SA4550 is generated by external
equipment. It is the pilot’s responsibility to ensure the correct
configuration and use of the external equipment. The SA4550 is
subject to all legal and operational limitations of the equipment
supplying data to it. Always refer to your approved Aircraft Flight
Manual Supplement for operation and limitations on the use of
installed equipment.
Note: Because aircraft vary in their installed equipment, it is
important to note that what is displayed on the SA4550 may vary
depending on the presence or absence of equipment.

82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE V
Approvals
The FAA has approved the SA4550 under the following TSOs:
C3d: Turn and Slip Instruments
C4c: Bank and Pitch Instruments
C34e: ILS Glideslope Receiving Equipment
C36e: Airborne ILS Localizer Receiving Equipment
C52b: Flight Director Equipment
C113: Airborne Multipurpose Electronic Displays
The following RTCA certification levels also apply to this product:
DO-160E: Environmental (Categories listed in Chapter 4)
DO-178B: Software Level A and C
DO-254: Hardware Level A and C
Limitations
Category I Approaches Only.
Installation of the SA4550 in a type-certificated aircraft must be
performed in accordance with the Sandel SA4550 Installation
Manual, document number 82010-IM (applicable revision).
82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE VI
Conventions Used in This Manual
The name of a button or control is placed within square brackets
when the button is described in text. For example, “…press the [M]
selection button to …”
This manual uses terms, which should be familiar to aviation-
minded readers, such as “Attitude” and “Flight Director”. Terms,
which are specific to the SA4550, will be placed in the glossary.

82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE VII
Table of Contents
Pilot information iii
Copyright iii
Revision notice iv
Operational and legal issues iv
Approvals v
Limitations v
Conventions Used in This Manual vi
Table of Figures ix
Effectivity, Revision History, and Errata x
CHAPTER 1 WELCOME TO THE SA4550 1-1
Introduction 1-1
CHAPTER 2 OPERATION 2-1
Power-On Self Test 2-1
SA4550 Control and Display Layout 2-3
DC Power LED 2-5
FD Mode Select 2-5
Attitude Test 2-6
Radar Altimeter Test 2-8
Mini-USB Port 2-8
MINS 2-9
Display Brightness 2-9
DISPLAY DESCRIPTION 2-10
DISPLAY FEATURES 2-11
Roll Scale 2-11
Sky Pointer 2-11
Pitch Scale 2-12
Flight Director Command Bars (Single Cue) 2-13
Own Aircraft Symbol (Single Cue) 2-13
Flight Director Command Bars (Dual Cue) 2-14
Own Aircraft Symbol (Dual Cue) 2-14
Fast/Slow Indicator 2-15
Glideslope Deviation Indicator 2-16
Localizer Deviation Indicator 2-17
Slip/Skid Indicator 2-18
Radar Altimeter Display 2-19
82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE VIII
Red Chevrons 2-20
Red Chevrons 2-21
ANNUNCIATOR DESCRIPTION 2-22
ANNUNCIATORS 2-23
Go Around 2-23
Radar Altitude Minimums 2-23
APFD Altitude Hold Mode 2-23
APFD Vertical NAV Mode 2-23
APFD Vertical Speed Mode 2-24
APFD Approach Mode 2-24
APFD Heading Mode 2-24
APFD NAV Mode 2-24
APFD Localizer Mode 2-24
APFD Glideslope 2-25
APFD Back Course 2-25
APFD Speed Mode 2-25
APFD RNAV Mode 2-25
FLAGS 2-26
Attitude Failure / Message Flag 2-26
Flight Director Computer Flag 2-27
Localizer Flag 2-28
Glideslope Failure Flag 2-28
Fast/Slow Flag 2-28
Function Not Installed Flag 2-28
ERROR INDICATIONS 2-29
CRC Error 2-29
Fatal Error 2-29
Data Color Coding 2-30
CHAPTER 3 TECHNICAL SPECIFICATIONS 3-1
CHAPTER 4 GLOSSARY 4-1
CHAPTER 5 AVIONICS ACRONYMS/ABBREVIATIONS 5-1

82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE IX
Table of Figures
Figure 2-1 Introduction Screen ................................................................ 2-1
Figure 2-2 SA4550 Display with Flags ...................................................... 2-2
Figure 2-3 SA4550 Single Cue FD ........................................................... 2-3
Figure 2-4 SA4550 Dual Cue FD Differences ........................................... 2-4
Figure 2-5 ATT Test.................................................................................. 2-7
Figure 2-6 SA4550 Primary Attitude Display........................................... 2-10
Figure 2-7 Annunciator Locations ........................................................... 2-22
82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE X
Effectivity, Revision History, and Errata
Date: 29-SEP-2012
Revision: F
Applies to: SA4550 Software 1.08
With the exception of the superseding information contained in this
section, operation of the SA4550 is as described in the SA4550
Pilot’s Guide referenced above.
Revision History
Revision Date Comments
F 28-SEP-2012
Release for 1.08 software.
Page 2-8: Added description of
radar altimeter test.
E 01-MAR-2011 Effectivity updated for 1.07 software
D1 11-NOV-2008 Effectivity updated for 1.06 software
D 15-JUL-2008
Release for 1.05 software
Page 2-22: New annun. added.
Page 2-23: MDA annun. added.
Page 2-25: RNAV annun..added.
Page 3-1: New part number added.
Chapter 5.: Added abbreviations.
C 27-FEB-2008
Release for 1.04 software,
Update page 2-8 “Function Not
Installed” message.
Update physical characteristics
(chapter 3)

82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE XI
B2 17-OCT-2007
Page x: Effectivity updated for
software 1.03.
No operational changes.
B1 22-AUG-2007
Page x: Effectivity updated for
software 1.02; Document number
reference added; Errata updated for
incorrect page reference.
No operational changes.
B 18-JUN-2007 New Format
A 07-MAY-2007 Initial Release
No errata applicable to this release.
82010-PG, REV. F SANDEL SA4550 PILOT’S GUIDE XII
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Welcome to the SA4550
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 1-1
CHAPTER 1 WELCOME TO THE SA4550
Introduction
The SA4550 Primary Attitude Display is a high performance
electronic ADI that can be used in new installations or as a
upgrade for electromechanical ADIs. It features a high
resolution, high brightness, and long life LED backlit display.
The SA4550 accepts pitch and roll input from the aircraft
Vertical Gyro to display attitude.
The SA4550 incorporates standard ADI features such as flight
director command bars and a glideslope/localizer deviation
scale, along with a fast/slow indicator, Radar Altitude/ Mins
and mode annunciations. A pilot-selectable single-cue/dual-
cue display option is also available.
The SA4550 typically displays data from the following sources:
Vertical Gyro
Navigation Receiver (ILS)
Radar Altimeter
Angle of Attack System
Flight Computer
Welcome to the SA4550
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 1-2
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Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-1
CHAPTER 2 OPERATION
Power-On Self Test
On initial power-up, a short introduction screen will be
displayed during the power on self test which includes the
software version.
It is normal for the self test screen to flash off once during
the sequence
Figure 2-1 Introduction Screen
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-2
After display of the power-up self test, the SA4550 will
immediately start normal operation.
Since it is typically powered by the aircraft main bus, it is
likely that the initial display will be flagged until after
engine start and avionics are switched on.
The display with no inputs available will look like this:
Figure 2-2 SA4550 Display with Flags

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-3
SA4550 Control and Display Layout
Figure 2-3 SA4550 Single Cue FD
Knob
NORM: Sets MINS alert
altitude
PULL: Ad
j
usts Bri
g
htness
Radalt
Test
Button
Glide Slope
Indicator
and Scale
Roll Scale
Annunciators
(highlight shown for
ALT and HDG)
Sky Pointer
Flight Director
Command Bar
Fast-Slow
Indicator
MINS alert
altitude
Airplane
Symbol
Pitch Scale
Horizon Line
Localizer
indicator
and
Zero Bank Index
Zero Pitch
Reference
Slip Skid
Indicator
Power-On
Indicator Attitude
Test
Button
Mini USB
Port
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-4
Figure 2-4 SA4550 Dual Cue FD Differences
Flight
Director
Pitch
Command
Airplane
Symbol
FD Mode
Button
Flight
Director Roll
Command
Note: in this
illustration LOC,
GS, and RADALT
are not shown for
clarity

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-5
The following describes each control.
CONTROL FEATURE
FUNCTION OPERATION
DC Power LED
Indicates the presence of
DC power.
Indicator only. No pilot
interaction required.
FD Mode Select
Toggles between the
Single Cue and Dual Cue
Flight Director Mode (If
enabled during
installation)
Depress button to
alternate Flight Director
presentation.
POWER ON
LED
FLIGHT
DIRECTOR
MODE
SELECTOR
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-6
CONTROL FEATURE
FUNCTION OPERATION
Attitude Test
Performs display self-
test.
Perform this test prior to
each flight.
NOTE: ATT TEST may
also operate the APFD
self-test which will cause
the on-screen
annunciators to
illuminate.
Depress [ATT TEST]
button and observe
display. A successful
display test will cause
the display to indicate a
10° roll to the left, a 10°
pitch up and full right
deflection of the slip skid
ball indicator. The red
ATTITUDE flag will
display with the words
“Att Test” directly below.
The words RED,
GREEN, and BLUE will
display in their
respective colors. The
display will go blank
after [ATT TEST] button
is held for 5 seconds.
If the display does not
test properly or if any of
the colors are visibly
incorrect do not fly
aircraft using the
SA4550. Maintenance is
required.
ATTITUDE
TEST
BUTTON

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-7
Figure 2-5 ATT Test
Press and hold
[ATT TEST]
button to
perform display
test.
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-8
CONTROL FEATURE
FUNCTION OPERATION
Radar Altimeter Test:
Used to test radar
altimeter system. If a
radar altimeter system is
not installed or remote
test function is not
enabled, the message
“Function Not Installed”
will appear when [RA
TEST] is pressed.
Depress [RA TEST]
button and observe
radar altimeter display
for proper indications.
See AFM for proper
radar altimeter test
display indications. For
installations using a
digital 429 radar
altimeter, the text “RAD
ALT” in the radar
altimeter window of the
display will be replaced
with “RA TEST” in
amber while the system
is under test.
CONTROL FEATURE
FUNCTION OPERATION
Mini-USB Port:
Used for updating
internal software.
Maintenance function
only.
MINI USB PORT
RADAR
ALTIMETER
TEST

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-9
CONTROL FEATURE
FUNCTION OPERATION
MINS: (IN) Used for
setting a minimum
radar altitude in the MIN
window. If [MINS] knob
is rotated in an aircraft
without a radar
altimeter system
installed or configured,
the message “Function
Not Installed” will
appear.
Rotate to set desired
radar altitude in the MIN
window:
MIN window will not
display in aircraft that do
not have a radar altimeter
system configured for
display on the SA4550.
Display Brightness:
(OUT) Used for
manually adjusting
display brightness
Pull knob out and rotate
to manually adjust
display brightness.
Brightness setting (0-
100) will appear on
screen when an
adjustment is made:
MINS / DISPLAY
BRIGHTNESS
CONTROL
KNOB
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-10
DISPLAY DESCRIPTION
The display utilizes a standard blue-above-brown
attitude depiction to depict Pitch and Roll, as directed by
the aircraft Vertical Gyro. The airplane symbol
references the aircraft’s current attitude.
If tuned, the localizer and glideslope deviations are
shown fed from the VHF NAV receiver.
The flight director command bars provide pitch and roll
guidance from the flight computer.
A slip/skid indicator is provided operated from an internal
accelerometer.
Desired radar altitude minimums can be set in the MIN
window and current radar altitude (AGL) is displayed in
the RAD ALT window using information from the radar
altimeter (if equipped – see AFM).
Ref Approach speed deviation is shown using
information from the angle of attack system.
The flight director mode annunciations displayed are
dependent on equipment installation – see AFM.
Figure 2-6 SA4550 Primary Attitude Display
Unit on right is configured without a radar altimeter.

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-11
DISPLAY FEATURES
FUNCTION OPERATION
Roll Scale – Indicates
aircraft roll attitude in
degrees from 0° to 60°
left or right of level. Scale
is marked at 10°, 20°,
30°, 45°, and 60°
increments.
Sky Pointer – Moves in
accordance with the
aircraft roll attitude.
Always points up.
Utilize normally
45 DEGREES
30 DEGREES
SKY POINTER
ROLL SCALE
60 DEGREES
0 DEGREES
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-12
DISPLAY FEATURES
FUNCTION OPERATION
Pitch Scale – Indicates
aircraft pitch attitude in
degrees from 0° to 90°
above or below level
pitch attitude. Scale is
marked in increments of
2.5° with short lines 2.5°
and 5° increments and
longer lines at 10°
increments. There are
numerical markings at
10° increments. Pitch
attitudes below zero are
preceded by a minus
sign.
Utilize normally
SINGLE CUE PITCH
REFERENCE POINT
PITCH SCALE
DUAL CUE PITCH
REFERENCE POINT

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-13
DISPLAY FEATURES
FUNCTION OPERATION
Flight Director
Command Bars (Single
Cue) –
Supplies combined
pitch/roll guidance from
the flight computer.
Own Aircraft Symbol
(Single Cue) –
Represents the aircraft
pitch and roll attitude
relative to the pitch scale
and sky/ground.
Fly the aircraft to center
the own-aircraft symbol
into the command bars.
FLIGHT DIRECTOR COMMAND
BARS – SINGLE CUE
OWN AIRCRAFT
SYMBOL
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-14
DISPLAY FEATURES
FUNCTION OPERATION
Flight Director
Command Bars (Dual
Cue) Supplies split
pitch/roll guidance from
the flight computer.
Own Aircraft Symbol
(Dual Cue) – Represents
the aircraft pitch and roll
attitude relative to the
pitch scale and
sky/ground.
Fly the aircraft to center
the cross-pointer on the
nose of the symbolic
aircraft.
Note: The split-cue
presentation can
provide guidance in one
direction without the
other. For instance, if
Alt Hold is selected on
the flight computer
without a lateral mode,
vertical guidance is
presented without lateral
guidance.
OWN AIRCRAFT
SYMBOL
FLIGHT DIRECTOR
COMMAND BARS – DUAL
CUE

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-15
DISPLAY FEATURES
FUNCTION OPERATION
Fast/Slow Indicator - (if
equipped) is driven by
the angle of attack
system and displays the
aircraft speed relative to
the optimum approach
speed.
If the aircraft speed is
too fast the magenta
index circle will move
toward the “F” on the
scale. An appropriate
speed decrease should
be made. If the aircraft
speed is too slow, the
magenta index circle will
move toward the “S” on
the scale. An
appropriate speed
increase should be
made. The indications
on the Fast/Slow
indicator are secondary
and should be
crosschecked with
airspeed.
FAST/SLOW
INDICATOR
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-16
DISPLAY FEATURES
FUNCTION OPERATION
Glideslope Deviation
Indicator - Indicates the
deviation of the ILS
glideslope.
The magenta pointer will
move up or down,
indicating the direction
the aircraft should fly to
return to on-course.
When VHF NAV is not
tuned to ILS, this
indicator will not appear.
GLIDESLOPE
DEVIATION
INDICATOR

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-17
DISPLAY FEATURES
FUNCTION OPERATION
Localizer Deviation
Indicator – Indicates the
deviation of the aircraft
with respect to the
localizer
The magenta pointer will
move left or right,
indicating the direction
the aircraft should fly to
stay on course.
When VHF NAV is not
tuned to ILS, this
indicator will not appear.
NOTE: This is a
standard localizer, and
is not an expanded-
scale localizer.
LOCALIZER DEVIATION
INDICATOR
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-18
DISPLAY FEATURES
FUNCTION OPERATION
Slip/Skid Indicator –
Shows turn coordination
from lateral body
acceleration.
Center the ball to
produce coordinated
flight.
This ball is centered if
the aircraft is parked
level.
SLIP/SKID
INDICATOR

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-19
DISPLAY FEATURES
FUNCTION OPERATION
Radar Altimeter Display
- Shows current radar
altimeter altitude in 5’
increments below 200’
and 10’ increments
above 200’.
Blanks if above the
maximum Radar Altitude
of 2000’ or 2500’
depending on
make/model of Radar
Altimeter.
Shows all dashes if the
RA is invalid.
The RAD ALT window
will not appear in aircraft
that do not have a radar
altimeter system
configured for display on
the SA4550.
RADAR
ALTITUDE
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-20
DISPLAY FEATURES
FUNCTION OPERATION
Red Chevrons
Points to the level flight
attitude
Alerts the pilot that a
potentially hazardous
nose low pitch attitude
exists.
The upward pointing red
chevrons appear any
time the pitch attitude
exceeds -20°. Automatic
decluttering of the
display will occur prior to
this unusual attitude
indication. Appropriate
unusual attitude
recovery techniques
should be used when
this display appears.

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-21
DISPLAY FEATURE
FUNCTION OPERATION
Red Chevrons
Points to the level flight
attitude.
Alerts the pilot that a
potentially hazardous
nose high pitch attitude
exists.
The downward pointing
red chevrons appear
any time the pitch
attitude exceeds +30°.
Automatic decluttering
of the display will occur
prior to this unusual
attitude indication.
Appropriate unusual
attitude recovery
techniques should be
used when this display
appears.
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-22
ANNUNCIATOR DESCRIPTION
The SA4550 annunciators appear in fixed locations.
Certain locations are shared by difference annunciators
which normally will not be on at the same time – for
instance VRT and ALT are mutually exclusive.
When a properly equipped aircraft has a GPS WAAS
approach selected and is on the approach, one of the
following GPS WAAS approach annunciators will
display: LP, LPV, L NAV, LVNAV.
When an annunciation changes state a green highlight
box will display around the text for 5-7 seconds
During flight computer self test (or If a malfunction
occurs during normal operation) two annunciators which
share one location may activate simultaneously. In this
case the text message will toggle once a second.
Figure 2-7 Annunciator Locations

Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-23
ANNUNCIATORS
DESCRIPTION
(See Aircraft Flight
Manual for
Operational Details)
Go Around
Go Around mode has
been selected.
Radar Altitude
Minimums
Radar altitude has
reached the desired
radar altitude preset in
the MIN window.
Minimum Descent
Altitude
Aircraft altitude has
reached the desired
minimum descent
altitude set externally
(with an altitude
alerter).
APFD Altitude Hold
Mode
Altitude Hold mode is
engaged.
APFD Vertical NAV
Mode
Vertical NAV mode is
engaged.
Operation
82010-PG, REV. F Sandel SA4550 Pilot’s Guide 2-24
ANNUNCIATORS
DESCRIPTION
(See Flight Manual
for Operational
Details)
APFD Vertical Speed
Mode
Vertical speed mode is
engaged or Altitude
capture has occurred
APFD Approach
Mode
Appears when VOR or
LOC approach capture
occurs.
APFD Heading Mode
Heading mode is
engaged.
APFD NAV Mode
VOR/GPS/RNAV track
mode is engaged.
APFD Localizer Mode
Localizer capture has
occurred.