FAA Approved Supplementary Airplane Flight Manual II Morrow

II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
FAA Approved Supplementary Airplane Flight Manual
II Morrow Apollo SL50 GPS/SL60 GPS-Comm
Airplane Make: ..................... Partenavia
Airplane Model: .................... P68 Series
Airplane Serial No.: .............. ________
Registration No.: ................... ________
This Supplementary Flight Manual must be attached to or with the Regsitro
Aeronautica Italiano (R.A.I.) approved Flight Manual when the Apollo SL50
GPS/SL60 GPS-COMM is installed in accordance with STC SA00420SE.
The information contained herein supplements the basic Regsitro Aeronautica
Italiano (R.A.I.) approved Airplane Flight Manual only in those areas listed
herein. For limitations, procedures, and performance information not contained in
this document, consult the basic Airplane Flight Manual.
FAA Approved
Date: MAR 31 1997
Page 1 of 16
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
2345 Turner Rd. SE
Salem, OR 97302
Revision Log
Rev
Date
-
03/17/97
Page 2 of 16
Description
Initial release. Word 6.0
EN
By
RMG
FAA
Approval
Lester H Berven
Date
03/31/97
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
TABLE OF CONTENTS
1. GENERAL................................................................................................................................................................. 4
1.1 APOLLO SL50 GPS/SL60 GPS-COMM DESCRIPTION .............................................................................................. 4
1.1.1 SL50.................................................................................................................................................................. 4
1.1.2 SL60.................................................................................................................................................................. 5
1.2 OPERATION ................................................................................................................................................................ 5
2. LIMITATIONS ......................................................................................................................................................... 5
3. EMERGENCY/ABNORMAL PROCEDURES...................................................................................................... 7
3.1 EMERGENCY PROCEDURES ......................................................................................................................................... 7
3.2 ABNORMAL PROCEDURES .......................................................................................................................................... 7
4. NORMAL PROCEDURES ...................................................................................................................................... 7
4.1 GENERAL ................................................................................................................................................................... 7
4.2 SYSTEM ANNUNCIATORS ........................................................................................................................................... 7
4.3 SYSTEM SWITCHES/CONTROLS .................................................................................................................................. 8
4.4 PILOT’S DISPLAY ....................................................................................................................................................... 8
4.5 HSI / AUTOPILOT COUPLED OPERATION - NAV SOURCE SELECTION .......................................................................... 9
4.6 COMM SOURCE SELECTION........................................................................................................................................ 9
4.7 TO/FROM “OBS” SELECTION .................................................................................................................................... 9
4.8 RAIM........................................................................................................................................................................ 9
4.8.1 Enroute RAIM (2.0 nm.).................................................................................................................................... 9
4.8.2 Terminal RAIM (1.0 nm.) ............................................................................................................................... 10
4.9 PARALLEL TRACK .................................................................................................................................................... 10
4.10 AIRSPACE ALERTS............................................................................................................................................ 10
5. PERFORMANCE ................................................................................................................................................... 10
6. WEIGHT AND BALANCE.................................................................................................................................... 10
7. SYSTEM DESCRIPTION ...................................................................................................................................... 10
7.1 APOLLO SL50 GPS/SL60 GPS-COMM SYSTEM COMPONENTS.............................................................................. 12
7.1.1 Apollo SL50/SL60.......................................................................................................................................... 12
7.1.2 Apollo SL50.................................................................................................................................................... 12
7.1.3 Apollo SL60.................................................................................................................................................... 12
7.1.4 Circuit Protection............................................................................................................................................ 12
7.2 NAVIGATION SOURCE SELECTION ............................................................................................................................ 13
7.3 COMM SOURCE SELECTION...................................................................................................................................... 13
7.4 APOLLO SL50 GPS/SL60 GPS-COMM OPERATION ............................................................................................... 13
7.4.1 Basic Navigation Data .................................................................................................................................... 13
7.4.2 Viewing Messages .......................................................................................................................................... 13
7.4.3 Direct To - ...................................................................................................................................................... 13
7.4.4 Basic Communication Functions ..................................................................................................................... 14
LIST OF ILLUSTRATIONS
FIGURE 1 - APOLLO SL50 ................................................................................................................................................ 4
FIGURE 2 - APOLLO SL60 ................................................................................................................................................ 5
FIGURE 3 APOLLO SL50 GPS/SL60 GPS-COMM ANNUNCIATORS ............................................................................... 8
FIGURE 4 SL50/SL60 NAVIGATION SYSTEM BLOCK DIAGRAM ..................................................................................... 11
FIGURE 5 SL60 COMMUNICATIONS SYSTEM BLOCK DIAGRAM...................................................................................... 11
FIGURE 6 - APOLLO SL50 KEYS/CONTROLS .................................................................................................................. 12
FIGURE 7 - APOLLO SL60 KEYS/CONTROLS .................................................................................................................. 12
FAA Approved
Date: MAR 31 1997
Page 3 of 16
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
2345 Turner Rd. SE
Salem, OR 97302
1. GENERAL
1.1 APOLLO SL50 GPS/SL60 GPS-COMM DESCRIPTION
The Apollo SL50 GPS is a TSO-C129 CLASS A2 GPS. It provides for connection to an
external annunciator/switch array. The Apollo SL50 GPS can drive a dedicated display such
as a CDI/HSI, or it can be coupled to a shared HSI/CDI and autopilot system using
navigation source selectors and annunciators. The Apollo SL50 GPS is authorized for
IFR/VFR enroute oceanic and remote, enroute domestic, and terminal operation.
The Apollo SL60 contains all navigation functionality of the SL50 and additionally contains
VHF airband communications capability with a Mean Time Between Failures (MTBF) for
the communications function predicted to be far in excess of 1000 hours. The VHF
communication function provides a minimum of 8 Watts of transmit capability.
1.1.1 SL50
The SL50 is a TSO C129 CLASS A2 supplemental navigation system. It interfaces
to a non-numeric display (CDI/HSI) and annunciators. It is powered through the
aircraft circuit breaker panel and the avionics switches.
Figure 1 - Apollo SL50
Page 4 of 16
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
1.1.2 SL60
The SL60 contains the SL50 functionality. In addition it contains airband VHF
communications and NOAA weather channel reception capability.
It contains all the interfaces for both the navigation and communications
functions. The Comm transceiver function and the GPS function are powered
through separate circuits. These are both through the aircraft circuit breaker panel
and the avionics master switches.
Figure 2 - Apollo SL60
1.2 OPERATION
Provided the Apollo SL50 GPS/SL60 GPS-COMM is receiving adequate useable signals, it
has been demonstrated capable of and has been shown to meet the accuracy specifications
of:
a) VFR/IFR enroute oceanic and remote, enroute domestic, and terminal operation using
GPS within the U.S. National Airspace System and the North Atlantic Minimum
Navigation Performance Specification (MNPS) Airspace using the WGS-84 (or NAD 83)
coordinate reference datum in accordance with the criteria of AC 20-138, AC 91-49, and
AC 120-33.
b) The Apollo SL60 additionally provides VHF airband communications capability
meeting the requirements of AC 20-67b, Airborne VHF Communications Installations.
2. LIMITATIONS
1. User Manual
The information contained in the User’s Guide, Apollo SL50 GPS Receiver, Apollo SL60
GPS Receiver and VHF Comm Transceiver Manual, II Morrow P/N 560-0955-01 (or later
approved revision) must be immediately available to the flight crew whenever IFR
navigation and/or communication is predicated on the Apollo SL50 GPS/SL60 GPS-COMM
system.
FAA Approved
Date: MAR 31 1997
Page 5 of 16
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
2345 Turner Rd. SE
Salem, OR 97302
2. System Software (IFR)
The System must utilize the software version listed below (or later FAA approved versions).
Versions can be displayed in the System mode on the SL50 GPS/SL60 GPS-COMM front
panel.
• Apollo SL50 GPS/SL60 GPS Nav Software
Ver 1.0
• GPS Sensor Software
Ver 2.1
• Apollo SL60 only Comm Software
Ver 1.2
3. Data Base (IFR)
IFR enroute and terminal navigation is prohibited unless the pilot verifies the currency of the
data base or verifies each selected waypoint for accuracy by reference to current approved
data.
4. Alternate Navigation System
The aircraft must have other approved navigation equipment installed and operational
appropriate to the route of flight.
5. Alternate Communications System
When an Apollo SL60 is installed, for IFR communications, the aircraft must have another
independent communication systems having a minimum Mean Time Between Failures
(MTBF) of 1000 hours.
6. Magnetic Variation
a) The magnetic variation (MagVar) correction is not available in the Apollo SL50
GPS/SL60 GPS-COMM above 73 degrees North or below 73 degrees South latitude.
All bearing and track information is computed and displayed relative to true north in
these polar regions.
b) If the “Using Manual MAG VAR” message is generated by the Apollo SL50
GPS/SL60 GPS-COMM, the Pilot/Crew must verify or set the manual magnetic
variation to the appropriate value.
7. Annunciated Messages (IFR)
All annunciated messages, indicated by the MSG annunciator, must be viewed and
acknowledged by the pilot/crew.
8. Display/Annunciators/Indicators (IFR)
Prior to IFR flight, the SL50 GPS/SL60 GPS-COMM display and all annunciators and
CDI/HSI indicators must be checked for proper operation. (Note: The SL50 GPS/SL60 GPSCOMM automatically sequences through a series of start-up tests that include operational
checks of the display, annunciators, flags, and CDI/HSI indicators.)
9. Non-Navigation Information
All non-navigation information displayed by the SL50 GPS/SL60 GPS-COMM, such as
timer/clock and waypoint information (frequencies, runways, etc.) is advisory information
only.
Page 6 of 16
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
10. Foreign Airspace
FAA approval of the Apollo SL50 GPS/SL60 GPS-COMM does not necessarily constitute
approval for use in foreign airspace.
3. EMERGENCY/ABNORMAL PROCEDURES
3.1 EMERGENCY PROCEDURES
No change. Refer to approved Airplane Flight Manual.
3.2 ABNORMAL PROCEDURES
1. Invalid Nav Data
If the Apollo SL50 GPS/SL60 GPS-COMM navigation information is not available or is
invalid (flagged), utilize remaining operational navigation equipment as required.
2. RAIM Not Available
If a “RAIM Not Available” message is displayed, continue to navigate using the GPS
equipment or revert to an alternate means of navigation appropriate to the route and phase
of flight. When continuing to use GPS navigation, position must be verified every 15 minutes
using visual reference or another IFR-approved navigation system.
4. NORMAL PROCEDURES
4.1 GENERAL
The normal operating procedures for the Apollo SL50 GPS/SL60 GPS-COMM are outlined
in the Apollo SL50 GPS/SL60 GPS-COMM User’s Manual listed under Limitation 1.
4.2 SYSTEM ANNUNCIATORS
The Apollo SL50 GPS/SL60 GPS-COMM is connected to two annunciators in an array of
six annunciators located in the upper left of the aircraft instrument panel. The annunciators
are illustrated in Figure 3. The brightness of the annunciators is controlled by a toggle switch
labeled “Day/Night” located directly above the annunciators. These annunciators are shared
by the Apollo 2001 NMS (NMC2). When the Apollo SL50/SL60 is selected as the
navigation source, only the MSG, and PTK annunciators are connected. The GPS,
APPRCH, and ACTIVE annunciators and the OBS/HLD annunciator/switch are used only
when the Apollo 2001 is selected as the navigation source. The OBS/HLD annunciator
switch is optional for the Apollo SL50/SL60 and is not used in this installation. The function
of the six annunciators is as follows:
a) MSG (amber)
The MSG annunciator is illuminated to indicate messages are still active. The annunciator
flashes to indicate a new message that has not been viewed.
b) GPS (amber) N/A
Used only by multi-sensor navigation systems which include GPS. The GPS annunciator is
illuminated when GPS is not available or not in use. (Not used by the Apollo SL50/SL60).
c) PTK (blue)
The PTK annunciator is illuminated when parallel track offset is in use.
FAA Approved
Date: MAR 31 1997
Page 7 of 16
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
2345 Turner Rd. SE
Salem, OR 97302
d) OBS/HLD (blue) N/A
The OBS/HLD annunciator is illuminated to indicate waypoint sequencing is on hold.
Waypoint sequencing hold can be enabled/disabled by pressing the waypoint
sequencing/hold annunciator button. (Not used by the SL50/SL60 in this installation).
e) APPRCH (blue) N/A
Used only for systems with GPS approach capability. (Not used by the Apollo SL50/SL60).
f) ACTIVE (green) N/A
Used only for systems with GPS approach capability. (Not used by the Apollo SL50/SL60).
Hold push button
MSG
WPT SEQ
APPRCH
GPS PTK
OBS/HLD
ACTIVE
Figure 3 Apollo SL50 GPS/SL60 GPS-COMM Annunciators
4.3 SYSTEM SWITCHES/CONTROLS
The switches and controls for the SL50 GPS/SL60 GPS-COMM system include the
navigation source selector switches (described in section 4.5), and the controls on the front
panel of the SL50 GPS/SL60 GPS-COMM (described in the Apollo SL50 GPS/SL60 GPSCOMM User’s Manual).
4.4 PILOT’S DISPLAY
a) The primary navigation display for the SL50 GPS/SL60 GPS-COMM is the HSI
located in the pilot’s primary instrument scan area as are the system annunciators.
Cross-track deviation, to/from indication, and validity are displayed on the HSI. Valid
flag outputs are provided for the cross-track deviation.
b) Messages and all other available information as described in the Apollo SL50
GPS/SL60 GPS-COMM operating manual such as distance to waypoint, groundspeed,
time to waypoint, and waypoint and flightplan information is available on the Apollo
SL50 GPS/SL60 GPS-COMM front panel.
Page 8 of 16
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
4.5 HSI / AUTOPILOT COUPLED OPERATION - NAV SOURCE SELECTION
The installation allows for pilot selection of the navigation source for coupling to the
HSI / autopilot. The available sources that can be selected are:
• NAV1
• SL50/SL60
• NMC 2
The procedure for selecting the navigation source is as follows.
a) To select NAV1
Press the switch labeled “AUX NAV / NAV1” so that “NAV1” is illuminated.
b) To select SL50 GPS/SL60 GPS-COMM
Press the switch labeled “AUX NAV / NAV1” so that “AUX NAV” is illuminated and press
the switch labeled “SL50-SL60 / NMC 2” so that “SL50 / SL60” is illuminated.
c) To select NMC 2
Press the switch labeled “AUX NAV / NAV1” so that “AUX NAV” is illuminated and press
the switch labeled “SL50-SL60 / NMC 2” so that “NMC 2” is illuminated.
When an SL50 GPS/SL60 GPS-COMM is selected as the HSI navigation source, the HSI
course pointer must be manually turned to the desired track as indicated by the Apollo SL50
GPS/SL60 GPS-COMM. For autopilot operation, refer to the autopilot operator’s manual.
4.6 COMM SOURCE SELECTION
The SL60 is selected as the active communications radio by selecting Comm 1 on the
existing audio panel.
4.7 TO/FROM “OBS” SELECTION
When waypoint sequencing is suspended a desired course to or from the active waypoint
can be selected by pressing the Direct-to key twice, entering the course with the large and
small knobs, and pressing enter. Selecting a desired “OBS” to/from course when sequencing
is not suspended, will automatically suspend sequencing.
4.8 RAIM
RAIM stands for Receiver Autonomous Integrity Monitor. It provides a method whereby
the receiver can provide an integrity check, using more satellites than are needed for a
position solution. This integrity check protects you from position errors caused by failed
satellites or bad GPS satellite data. RAIM is based on an allowed limit of horizontal position
difference called the RAIM alarm limit. Two different RAIM limits are used in the Apollo
SL50 GPS/SL60 GPS-COMM corresponding to the phase of flight:
4.8.1 Enroute RAIM (2.0 nm.)
Enroute RAIM alarm limit is 2.0 nm. During the enroute phase of flight a RAIM alarm will
mean that an error of 2.0 nm. or greater, caused by bad satellite data, has been detected.
FAA Approved
Date: MAR 31 1997
Page 9 of 16
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
2345 Turner Rd. SE
Salem, OR 97302
4.8.2 Terminal RAIM (1.0 nm.)
Terminal RAIM alarm limit of 1.0 nm is automatically provided by the Apollo SL50
GPS/SL60 GPS-COMM when you are within 30 nm. radial distance of your departure or
destination airport as contained in the active flight plan.
4.9 PARALLEL TRACK
When the parallel track feature (PTK) is activated, navigation is predicated on a course
offset from the parent route by the selected parallel track distance. The PTK annunciator
will be continuously on when the PTK feature is active. All navigation data, such as bearing
and distance to active waypoint, is calculated and displayed relative to the “phantom” active
waypoint parallel to the actual waypoint. Use of the Direct-to feature or entering a desired
“OBS” course relative to the active waypoint automatically cancels PTK and extinguishes
the PTK annunciator.
4.10 AIRSPACE ALERTS
Airspace alerts [set under System Mode - Navigation Info] should be set to “OFF” for IFR
operations to prevent unnecessary airspace alert messages.
5. PERFORMANCE
No change. Refer to the approved Airplane Flight Manual.
6. WEIGHT AND BALANCE
Refer to the current aircraft weight and balance information.
7. SYSTEM DESCRIPTION
The Apollo SL50 GPS/SL60 GPS-COMM is a TSO C129 GPS navigation system. The
SL60 is also a TSO C37d, C38d and C128 VHF Airband Communications system. The SL50
GPS/SL60 GPS-COMM system is installed using the guidelines of AC 20-138 for the GPS
navigation functions and AC 20-67b for the communications functions The SL50 GPS/SL60
GPS-COMM system is illustrated in Figure 4 SL50/SL60 Navigation System Block Diagram
(GPS navigation) and in Figure 5 SL60 Communications System Block Diagram (Comm
functions).
Page 10 of 16
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
CDI
NAV
Autopilot
L/R, GS,
& Flags
HSI
Switching
Relay
SL50/60
CDI, VDI, & Flags
Switching
Relay
NMC2
SL50/60
NAV1
NMC2
Aux
Nav
Annunciators
Source Selector
Switches/Annunciators
Figure 4 SL50/SL60 Navigation System Block Diagram
A p o llo S L 6 0
A u d io o u t, m o d u la tio n & tr a n s m i t k e y in
A u d io P a n el
Figure 5 SL60 Communications System Block Diagram
FAA Approved
Date: MAR 31 1997
Page 11 of 16
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
2345 Turner Rd. SE
Salem, OR 97302
7.1 APOLLO SL50 GPS/SL60 GPS-COMM SYSTEM COMPONENTS
7.1.1 Apollo SL50/SL60
The Apollo SL50 GPS/SL60 GPS-COMM) is the main control, display, and navigation
computer for the Apollo SL50 GPS/SL60 GPS-COMM system. The SL50 GPS/SL60 GPSCOMM also includes outputs and drivers for connection to external CDI/HSI indicators,
autopilots, and system annunciators. The database for the SL50 GPS/SL60 GPS-COMM is
contained on an internal database which can be updated from a Personal Computer (PC).
Data is available on the standard ARINC 28-day update cycle.
7.1.2 Apollo SL50
The Apollo SL50 is a TSO C129 CLASS A2 GPS navigation system.
Figure 6 - Apollo SL50 Keys/Controls
7.1.3 Apollo SL60
The Apollo SL60 contains the same buttons, knobs and display as the Apollo SL50 GPS;
however, the key labeled NRST on the Apollo SL50 is labeled with a double-ended arrow on
the SL60 and is used to “flip-flop” the active and standby communications frequency. The
nearest function on the SL60 is reached through a top level page under NAV mode or in a
short-cut method by pressing MSG twice. The key labeled WPT on the SL50 is labeled
COM on the SL60 and is used to select and display the Comm functions. The WPT function
on the SL60 is available from a top-level page under SYS mode. The knob in the lower-left
corner of the SL60 functions both as the power switch (as it also does on the SL50) and as
the VHF airband radio audio volume control.
Figure 7 - Apollo SL60 Keys/Controls
7.1.4 Circuit Protection
Circuit breakers for SL50 GPS/SL60 GPS-COMM navigation and communication functions
are located in the circuit breaker panel to the left of the pilot and can be pulled or reset
Page 12 of 16
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
during flight. The circuit breaker for the navigation functions is labeled SL50/SL60. The
circuit breaker for the communications function is labeled Comm 1.
7.2 NAVIGATION SOURCE SELECTION
The Apollo SL50 GPS/SL60 GPS-COMM system is connected to the aircraft HSI indicator
and autopilot systems using switching relays and source selection switches. The navigation
source selection connections are illustrated in Figure 4 SL50/SL60 Navigation System Block
Diagram. The procedure for selecting the navigation source is included in section 4.5 on page
8.
7.3 COMM SOURCE SELECTION
The SL60 is selected as the communications source by selecting COM 1 on the existing
audio panel.
7.4 APOLLO SL50 GPS/SL60 GPS-COMM OPERATION
This section highlights several of the basic operational features of the Apollo SL50
GPS/SL60 GPS-COMM. Refer to the user manual listed in Limitation 1 for complete
operating instructions.
7.4.1 Basic Navigation Data
The basic navigation data can be selected on the SL50 GPS/SL60 GPS-COMM display by
pressing the NAV button (twice), then rotating the SMALL knob to view the navigation pages.
The basic navigation data available includes:
• Bearing and distance to the next waypoint
• Cross track error bar graph and numeric display
• Ground speed and track angle
• ETE (estimated time enroute) to the next waypoint
7.4.2 Viewing Messages
To view messages, press the MSG button, rotate the LARGE knob to select “new” or “old”
messages, and rotate the SMALL knob to view the messages.
The MSG annunciator is illuminated when there are active messages, flashing when there are
new messages. “Old” messages are those messages that have already been viewed as a
“new” message.
7.4.3 Direct To a) Waypoint Entry
To enter a waypoint as the next waypoint, press the DIRECT-TO button, rotate the
SMALL knobs to select the desired waypoint, and press ENT.
LARGE
and
b) “OBS” Entry
To enter a bearing to or from the active “To” waypoint, press the DIRECT-TO button twice,
rotate the LARGE and SMALL knobs to select the desired course, and press ENT. If waypoint
sequencing was not already suspended (OBS/HLD annunciator illuminated), entering a
FAA Approved
Date: MAR 31 1997
Page 13 of 16
Airplane Flight Manual Supplement
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March 17, 1997
Part #: 560-1006-00
II Morrow Inc.
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Salem, OR 97302
to/from bearing will automatically suspend sequencing and the OBS/HLD annunciator will
illuminate.
Note: When you cross a waypoint the first time when sequencing is suspended, a message
will be generated to remind you to enter the desired inbound course for your hold. This
message will ask you to press ENT to enter your inbound course or any other key to ignore
the message. Pressing ENT when this message is displayed will result in displaying the
course entry page, just as if you had pressed Direct-To button twice.
7.4.4 Basic Communication Functions
a) Comm functions
To select the comm function display on the SL60 press the button labeled Comm. Pressing
Comm again, when in the Comm mode will activate the standby frequency monitor and an
‘M’ will be displayed by the standby frequency. The standby frequency will be monitored
by the audio output, with a slightly reduced volume and audio quality, unless there is activity
on the active frequency.
b) Flip Flop Key
Pressing the flip flop key will transfer the standby frequency to the active frequency and
vice-versa.
c) Standby Frequency Selection
The standby frequency may be selected by using the large and small knobs. The standby
frequency may also be selected from “stacks” of available frequencies for waypoints, lastused list, user-stored list, weather channels, and the emergency channel (121.50). Refer to
the user’s manual listed in Limitation 1., for details.
d) Optional
The Apollo SL60 may optionally connected to an external frequency flip-flop switch which
duplicates the function of the flip-flop key. It may also provide internal 2-place intercom
capability when installed in aircraft without existing intercom systems. These features are
not used for this installation.
Page 14 of 16
FAA Approved
Date: MAR 31 1997
II Morrow Inc.
2345 Turner Rd SE
Salem, OR 97302
Airplane Flight Manual Supplement
for II Morrow Apollo SL50/SL60
March 17, 1997
Part #: 560-1006-00
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FAA Approved
Date: MAR 31 1997
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FAA Approved
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