Garmin GNS 530 User manual

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 1 15 Mar 2002 OÄM 40-117 Page 9 - A21 - 1
0.1 RECORD OF REVISIONS
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Page(s) Date of
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Approval Date of
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Date Inserted Signature
1OÄM 40-117
WX 500
09-A21-1, 9-A21-2,
9-A21-3, 9-A21-4
15-Mar-2002
79-A21-33, 9-A21-34

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 1 15 Mar 2002 OÄM 40-117 Page 9 - A21 - 2
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GNS 530
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DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 1 15 Mar 2002 OÄM 40-117 Page 9 - A21 - 4
0.3 TABLE OF CONTENTS
Page
1. GENERAL ...............................................9-A21-5
2. OPERATING LIMITATIONS ..................................9-A21-5
3. EMERGENCY PROCEDURES ...............................9-A21-8
4A. NORMAL OPERATING PROCEDURES ........................9-A21-9
4B. ABNORMAL OPERATING PROCEDURES .....................9-A21-10
5. PERFORMANCE .........................................9-A21-11
6. MASS AND BALANCE .....................................9-A21-11
7. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ..........9-A21-11
8. AIRPLANE HANDLING, CARE AND MAINTENANCE .............9-A21-34|

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 5
1. GENERAL
This Supplement supplies the information necessary for the efficient operation of the
airplane when the COM/NAV/GPS GNS 530 is installed. The information contained
within this Supplement is to be used in conjunction with the complete AFM.
This Supplement is a permanent part of this AFM and must remain in this AFM at all
times when the GNS 530 is installed.
Refer to Section 7.14 for approved modes of operation (i. e. BRNAV, MNPS) of the
GNS 530´s GPS receiver.
2. LIMITATIONS
A. The GNS 530 Pilot's Guide, dated April 2000 or later appropriate revision must
be immediately available to the flight crew whenever navigation is predicated on
the use of the system.
B. The GNS 530 must utilize the following or later approved software versions:
Sub-System Software Version
Main 2.00
GPS 2.00
COMM 1.22
VOR/LOC 1.25
G/S 2.00

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 6
The Main software version is displayed on the GNS 530 self test page immediately
after turn-on for 5 seconds. The remaining system software versions can be verified
on the AUX group sub-page 2, 'SOFTWARE/DATABASE VER'.
C. IFR en route and terminal navigation predicated upon the GNS 530’s GPS
Receiver 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.
D. Instrument approach navigation predicated upon the GNS 530’s GPS Receiver
must be accomplished in accordance with approved instrument approach
procedures that are retrieved from the GPS equipment data base. The GPS
equipment database must incorporate the current update cycle.
(1) Instrument approaches utilizing the GPS receiver must be conducted in
the approach mode and Receiver Autonomous Integrity Monitoring
(RAIM) must be available at the Final Approach Fix.
(2) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other
type of approach not approved for GPS overlay with the GNS 530’s GPS
receiver is not authorized.
(3) Use of the GNS 530 VOR/ILS receiver to fly approaches not approved
for GPS requires VOR/ILS navigation data to be present on the external
indicator.

DA 40 AFM Supplement A21
GNS 530
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(4) When an alternate airport is required by the applicable operating rules,
it must be served by an approach based on other than GPS or Loran-C
navigation, the aircraft must have the operational equipment capable of
using that navigation aid, and the required navigation aid must be
operational.
(5) VNAV information may be utilized for advisory information only. Use of
VNAV information for Instrument Approach Procedures does not
guarantee Step-Down Fix altitude protection, or arrival at approach
minimums in normal position to land.
E. If not previously defined, the following default settings must be made in the
'SETUP 1' menu of the GNS 530 prior to operation (refer to Pilot's Guide for
procedure if necessary):
(1) dis, spd: nm, kt (sets navigation units to 'nautical miles' and 'knots')
(2) alt, vs: ft, fpm (sets altitude units to 'feet' and 'feet per minute')
(3) map datum: WGS 84 (sets map datum to WGS-84, see note below)
(4) posn: hddd°mm.mmm' (sets navigation grid units to decimal minutes)
(5) fuel: gl (sets fuel units to gallons)

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 8
NOTE
In some areas datums other than WGS-84 may be used. If
the GNS 530 is authorized for use by the appropriate
Airworthiness authority, the required geodetic datum must
be set in the GNS 530 prior to its use for navigation.
F. The accuracy of the data base information is only assured if it is used before the
end of the effectivity period. Use of out of date data base information is done
entirely at the user´s own risk.
3. EMERGENCY PROCEDURES
A. If GNS 530 navigation information is not available or invalid, utilize remaining
operational navigation equipment as required.
B. If 'RAIM POSITION WARNING' message is displayed the system will flag and no
longer provide GPS based navigational guidance. The crew should revert to the
GNS 530 VOR/ILS receiver or an alternate means of navigation other than the
GNS 530’s GPS Receiver.
C. If 'RAIM IS NOT AVAILABLE' message is displayed in the en route, terminal, or
initial approach phase of flight, continue to navigate using the GPS equipment or
revert to an alternate means of navigation other than the GNS 530’s GPS
receiver appropriate to the route and phase of flight. When continuing to use
GPS navigation, position must be verified every 15 minutes using the GNS 530’s
VOR/ILS receiver or another IFR-approved navigation system.

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 9
D. If 'RAIM IS NOT AVAILABLE' message is displayed while on the final approach
segment, GPS based navigation will continue for up to 5 minutes with approach
CDI sensitivity (0.3 nautical miles). After 5 minutes the system will flag and no
longer provide course guidance with approach sensitivity. Missed approach
course guidance may still be available with 1 nautical mile CDI sensitivity by
executing the missed approach.
E. In an in-flight emergency, depressing and holding the Comm transfer button for 2
seconds will select the emergency frequency of 121.500 MHz into the 'Active'
frequency window.
F. If GNS 530 Communication is inoperative, utilize remaining operational COMM
equipment (if installed) or follow standard communication failure procedure by
using Transponder Code 7600 and appropriate flight procedures.
4A. NORMAL PROCEDURES
DETAILED OPERATING PROCEDURES
Normal operating procedures are described in the GNS 530 Pilot's Guide, dated April
2000 or later appropriate revision.
PILOT'S DISPLAY
The GNS 530 System data will appear on the Pilot’s HSI. The source of data is either
GPS or VLOC as annunciated on the display above the CDI-key.

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GNS 530
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AUTOPILOT COUPLED OPERATION
Coupling of the GNS 530 System steering information to the autopilot can be
accomplished by engaging the autopilot in the NAV or APR mode. When the autopilot
system is using course information supplied by the GNS 530 System, the course
pointer on the HSI must be manually set to the desired track (DTK) indicated by the
GNS 530. For detailed autopilot operational instructions, refer to the JAA Approved
Flight Manual Supplement for the autopilot.
CROSSFILL OPERATIONS
For dual GNC 500 Product Series or GNC 500/GNC 400 Product Series installations,
crossfill capabilities exist between the number one and number two Systems. Refer to
the GNS 530 Pilot’s Guide for detailed crossfill operating instructions.
AUTOMATIC LOCALIZER COURSE CAPTURE
By default, the GNS 530 automatic localizer course capture feature is enabled. This
feature provides a method for system navigation data present on the external
indicators to be switched automatically from GPS guidance to localizer / glide slope
guidance as the aircraft approaches the localizer course inbound to the final approach
fix. If an offset from the final approach course is being flown, it is possible that the
automatic switch from GPS course guidance to localizer / glide slope course guidance
will not occur. It is the pilot’s responsibility to ensure correct system navigation data is
present on the external indicator before continuing a localizer based approach beyond
the final approach fix. Refer to the GNS 530 Pilot’s Guide for detailed operating
instructions.
4B. ABNORMAL PROCEDURES
No change.

DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 11
5. PERFORMANCE
No change.
6. MASS AND BALANCE
Upon removal or installation of the GNS 530 the change of empty mass and
corresponding center of gravity of the airplane must be recorded according to Chapter
6 of the Airplane Flight Manual.
7. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS
7.14 AVIONICS
The GNS 530 System is a fully integrated, panel mounted instrument, which contains
a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning
System (GPS) Navigation computer. The system consists of a GPS antenna, GPS
Receiver, VHF VOR/LOC/GS antenna, VOR/ILS receiver, VHF COMM antenna and a
VHF Communications Transceiver. The primary function of the VHF Communication
portion of the equipment is to facilitate communication with Air Traffic Control. The
primary function of the VOR/ILS Receiver portion of the equipment is to receive and
demodulate VOR, Localizer, and Glide Slope signals. The primary function of the GPS
portion of the system is to acquire signals from the GPS system satellites, recover
orbital data, make range and Doppler measurements, and process this information in
real-time to obtain the user's position, velocity, and time.

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GNS 530
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Provided the GNS 530’s GPS receiver is receiving adequate usable signals, it has
been demonstrated capable of and has been shown to meet the accuracy
specifications for:
SVFR/IFR enroute, terminal, and non-precision instrument approach (GPS, Loran-
C, VOR, VOR-DME, TACAN, NDB, NDB-DME, RNAV) operation in accordance
with AC 20-138.
SOne of the approved sensors, for a single or dual GNS 530 installation, for North
Atlantic Minimum Navigation Performance Specification (MNPS) Airspace in
accordance with AC 91-49 and AC 120-33.
SThe system meets RNP5 airspace (BRNAV) requirements of AC 90-96 and in
accordance with AC 20-138, and JAA AMJ 20X2 Leaflet 2 Revision 1, provided it
is receiving usable navigation information from the GPS receiver.
Navigation is accomplished using the WGS-84 (NAD-83) coordinate reference datum.
Navigation data is based upon use of only the Global Positioning System (GPS)
operated by the United States of America.

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GNS 530
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KEY AND KNOB FUNCTIONS
The key and knob descriptions on the next pages provide a general overview of the
primary function(s) for each knob.
LEFT-HAND KEYS AND KNOBS
1. The small left knob (PUSH C/V) is used to tune the kilohertz (kHz) value of the
standby frequency for the communications transceiver (COM) or the VLOC
receiver, whichever is currently selected by the tuning cursor. Press this knob
momentarily to toggle the tuning cursor between the COM and VLOC frequency
fields.

DA 40 AFM Supplement A21
GNS 530
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2. The large left knob (COM/VLOC) is used to tune the megahertz (MHz) value of
the standby frequency for the communications transceiver (COM) or the
VOR/Localizer receiver, whichever is currently selected by the tuning cursor.
3 The VLOC volume knob controls audio volume for the selected VOR/Localizer
frequency. Press momentarily to enable/disable the ident tone.
4. The VLOC flip-flop key is used to swap the active and standby VLOC frequencies
(i.e., make the selected standby frequency active).
5. The COM power/volume knob controls unit power and communications radio
volume. Press momentarily to disable automatic squelch control.
6. The COM flip-flop key is used to swap the active and standby COM frequencies.
Press and hold to select emergency channel (121.500 MHz).
RIGHT-HAND KEYS AND KNOBS
7. The range key allows you to select the desired map scale. Use the up arrow side
of the key to zoom out to a larger area, or the down arrow side to zoom in to a
smaller area.
8. The direct-to key provides access to the direct-to function, which allows you to
enter a destination waypoint and establishes a direct course to the selected
destination.

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GNS 530
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9. The menu key displays a context-sensitivity list of options. This options list allows
you to access additional features or make settings changes which relate to the
currently displayed page.
10. The clear key is used to erase information or cancel an entry. Press and hold this
key to immediately display the Default Navigation Page, regardless of which page
is currently being displayed.
11. The enter key is used to approve an operation or complete data entry. It is also
used to confirm information, such as the Database Page during power on.
12. The small right knob (PUSH CRSR) is used to select between the various pages
within one of the groups listed below. Press this knob momentarily to display the
on-screen cursor. The cursor allows you to enter data and/or make a selection
from a list of options.
13. The large right knob (GPS) is used to select between the various page groups:
NAV, WPT, AUX, or NRST. With the on-screen cursor enabled, the large right
knob allows you to move the cursor about the page.
BOTTOM ROW KEYS
14. The procedures key allows you to select approaches, departures and arrivals
from your flight plan. When using a flight plan, available procedures for your
departure and/or arrival airport are offered automatically. Otherwise, you may
select the desired airport, then the desired procedure.

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GNS 530
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15. The vertical navigation key allows you to create a three-dimensional profile which
guides you to a final (target) altitude at a specified location.
16. The flight plan key allows you to create, edit, activate and invert flight plans, as
well as access approaches, departures and arrivals. A closest point to flight plan
feature is also available from the flight plan key.
17. The message key is used to view system messages and to alert you to important
warnings and requirements.
18. The OBS key is used to select manual or automatic sequencing of waypoints.
Pressing this key selects OBS mode, which will retain the current 'active to'
waypoint as your navigation reference even after passing the waypoint (i.e.,
prevents sequencing to the next waypoint). Pressing the OBS key again will return
to normal operation, with automatic sequencing of waypoints. Whenever OBS
mode is selected, you may set the desired course to/from a waypoint using the
OBS Page, or an external OBS selector on your HSI.
19. The CDI key is used to toggle which navigation source (GPS or VLOC) provides
output to the HSI.

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GNS 530
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OPERATION
POWERING UP THE GNS 530
The GNS 530´s power and COM volume are controlled using the COM power/volume
knob (5) at the top left corner of the unit. Rotating it clockwise will turn unit power on
and increase the COM radio volume. After turning the unit on, a 'welcome page' will be
displayed while the unit performs a self test, followed by a 'land data page'.
The database confirmation page will appear next, which shows the current database
information on the NavData card (with the valid operating dates, cycle number and
database type indicated). The database is updated every 28 days, and must be
current for approved instrument approach operations. Information on database
subscriptions is available inside your GNS 530 package.
To acknowledge the database information, press the ENT-key.
Once the database has been acknowledged, the instrument panel self-test page will
appear. To ensure that the GNS 530 and any connected instruments are working
properly, check for the following indications on your HSI and external annunciators:
•Course deviation - half left /
no flag
•TO/FROM flag - TO
•All external annunciators - on
•Glideslope - half up / no flag
The instrument panel self-test page indicates the currently selected OBS course, fuel
capacity ('CAP'), fuel on board ('FOB') and fuel flow ('FF'). The fuel capacity, fuel on
board and fuel flow are entered manually.

DA 40 AFM Supplement A21
GNS 530
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To enter fuel capacity, fuel on board and fuel flow figures:
1. Rotate the large right knob (13) to select the 'CAP'-, 'FOB'- or 'FF'-
field
2. Rotate the small (12) and large (13) right knobs to enter the desired
figure, then press ENT.
The instrument panel self-test page includes selections to set fuel on board ('FOB') to
full capacity and access the checklist page. This allows you to quickly set fuel to full
limits and display any checklists you have entered, such as start up or takeoff
checklists.
To set fuel on board to full:
1. Rotate the large right knob (13) to highlight 'Set Full Fuel?'.
2. Press ENT and verify that fuel on board ('FOB') now matches the fuel
capacity ('CAP') figure. Fuel on board will now be reduced, over time,
based on the fuel flow ('FF') figure.
To view the checklists page:
1. Rotate the large right knob (13) to highlight 'Go To Checklists?' and
press ENT.
2. Rotate the large right knob (13) to select the desired checklist, then
follow the steps on page 142 of the GNS 530 Pilot´s Guide to execute
each step in the selected checklist.

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GNS 530
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3. Once you complete the desired checklist(s), press the small right knob
(12) to return to the checklists page. Press the small right knob (12)
again to return to normal operation on the satellite status or map
pages.
Once you have verified instrument operation with the instrument panel self-test page
displayed, rotate the large right knob (13) to highlight 'OK?' and press the ENT key.
ACQUIRING SATELLITES & VIEWING MESSAGES
The satellite status page will appear as the GNS 530 will begin to collect satellite
information. An 'Acquiring' status will be displayed on the satellite status page, and the
signal strength of any satellites received will appear as 'bar graph' readings. This is a
good indication that you are receiving signals and a position fix will be determined.
Following the first-time use of your GNS 530, the time required for a position fix will
vary - usually from one to two minutes.
If the unit can only obtain enough satellites for 2D navigation (no altitude), the unit will
use the altitude provided by the altitude encoder.
If the GNS 530 has not been operated for a period of six months or more, it may have
to 'Search the Sky' to collect new data. This means the unit is acquiring satellite data
to establish almanac and satellite orbit information, which can take 5 to 10 minutes.
The satellite status page will display a 'Searching Sky' status, and the message
annunciator (MSG), above the MSG key, will also flash to alert you of a system
message, 'Searching the Sky'.
To view a system message, press MSG.