Butler National Corporation AFM Supplement For G700 TXi in

One Aero Plaza Learjet 35, 35A (C21A), 36, 36A

New Century, KS 66031

FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT

G700 TXi in LEARJET 35, 35A (C-21A), 36, 36A Aircraft

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Registration No. _________

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Serial No. _________
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This supplement must be attached to the FAA approved Airplane Flight Manual when the
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airplane is configured with the Garmin G700 TXi System installed in accordance with
Supplemental Type Certificate ___________.
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The information contained herein supplements or supersedes the information of the basic
Airplane Flight Manual only in those areas listed herein. For limitations, procedures, and
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performance information not contained in this supplement, consult the basic Airplane Flight
Manual.
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FAA Approved: ______________________

Kent S. Lund, Manager
Central Flight Test Section
Federal Aviation Administration
Wichita, KS

Date:

Document No. 05707100

Issue: 0
Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

TABLE OF CONTENTS
SECTION 0 – SYSTEMS DESCRIPTION ...................................................................................3
EFFECTIVITY .......................................................................................................................................... 3
DEFINITIONS .......................................................................................................................................... 4
PILOT’S GUIDE ....................................................................................................................................... 5
MODIFICATION OVERVIEW .................................................................................................................. 5
GDU 1060 Display ................................................................................................................................... 6
GCU 485 controller .................................................................................................................................. 8
GI 275 Standby Instrument ...................................................................................................................... 9
POWER.................................................................................................................................................... 9
SECTION I – LIMITATIONS .....................................................................................................10
COCKPIT REFERENCE & PILOT’S GUIDE ......................................................................................... 10
SYSTEM SOFTWARE REQUIREMENTS............................................................................................. 10
MOVING MAP ........................................................................................................................................ 10
AHRS OPERATIONAL DATA ................................................................................................................ 10
MAGNETIC VARIATION OPERATIONAL AREA .................................................................................. 10

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AHRS NORMAL OPERATING MODE .................................................................................................. 10
AIRSPEED LIMITATIONS AND INDICATOR MARKINGS ................................................................... 11

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SYNTHETIC VISION TECHNOLOGY ................................................................................................... 11
TERRAIN-FLTA ..................................................................................................................................... 11

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TRAFFIC DISPLAY (OPTIONAL) .......................................................................................................... 11
KINDS OF OPERATIONS ..................................................................................................................... 12
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TAWS-A FUNCTIONS (OPTIONAL) ..................................................................................................... 12
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SECTION II – NORMAL PROCEDURES..................................................................................13
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POWER ON ........................................................................................................................................... 13
BEFORE TAKEOFF............................................................................................................................... 13
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AUTOPILOT/FLIGHT DIRECTOR INTERFACE ................................................................................... 13

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Coupling the Autopilot/Flight Director .................................................................................................... 14

SECTION III – EMERGENCY PROCEDURES .........................................................................19
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TAWS-A WARNINGS (IF OPTIONAL TAWS IS EQUIPPED)............................................................... 19

SECTION IV – ABNORMAL PROCEDURES ...........................................................................20
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ABNORMAL INDICATIONS................................................................................................................... 21
Heading Failure ...................................................................................................................................... 21
AHRS Failure ......................................................................................................................................... 21
Air Data Computer (ADC) Failure .......................................................................................................... 21
LOSS OF ELECTRICAL POWER ......................................................................................................... 21
ALERT ANNUNCIATIONS..................................................................................................................... 21
TAWS-A Cautions (If Optional TAWS is Equipped) .............................................................................. 22
TAWS-A Inhibit (GTN 750Xi Only) ......................................................................................................... 24
GPWS Inhibit (GTN 750Xi Only) ............................................................................................................ 24
Flap Override Inhibit (GTN 750Xi Only) ................................................................................................. 24
Glideslope Deviation Inhibit (GTN 750Xi Only)...................................................................................... 25
SECTION V – PERFORMANCE ...............................................................................................26
SECTION VI – SUPPLEMENTS ...............................................................................................26
SECTION VII – WEIGHT AND BALANCE DATA .....................................................................26

Manufacturer’s Data Section Page 2 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

SECTION 0 – SYSTEMS DESCRIPTION

EFFECTIVITY
This Flight Manual Supplement is applicable to Learjet Model 35, 35A (C21A), 36 and 36A
aircraft with the Garmin G700 TXi System including the GDU 1060 Primary Flight Display
(PFD)/Multi-Function Display (MFD) that replaces traditional flight instruments when installed
with the FC-530 or FC-535 autopilots.
The following Garmin equipment is added:
• Two (2) federated GDU 1060 - 10.6” control display units providing the functions of
PFD/MFD and the optional GCU 485 pedestal-mounted controllers
• Two (2) federated GDC 7400 RVSM-compliant air data computer systems
• Two (2) federated GRS 79 Attitude Heading Reference System (AHRS) with alternative
option for two (2) federated GRS 7800 attitude heading reference systems including two

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(2) GMU 44 remote-mounted magnetometers; two (2) new GTP 59 temperature probes;
two (2) GAD 43e digital to analog controllers; and one (1) GI 275 standby instrument for
display of attitude, altitude and airspeed.

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The information contained herein supplements the information in the basic FAA Approved
Airplane Flight Manual. For limitations, procedures and performance information not contained
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in this supplement, consult the basic FAA Approved Airplane Flight Manual or applicable FAA
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Approved Airplane Flight Manual Supplement.
The engine instruments and fuel indicators are retained, in the same locations as the original
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installation, and are not modified in any way. All other flight instruments are replaced by the
Garmin GDU 1060 displays, which provide both Primary Flight Display (PFD) and Multifunction
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Display (MFD) capabilities.

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Manufacturer’s Data Section Page 3 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

DEFINITIONS
The following terminology is used within this document:
ADAHRS Air Data Attitude Heading Reference System
ADC Air Data Computer
CDI Course Deviation Indicator
DME Distance Measuring Equipment
FLTA Forward-looking Terrain Alerting
GCU Garmin Control Unit
GNSS Global Navigation Satellite System
GPS Global Positioning System
GTN Garmin GNSS Navigator including the GTN 750Xi, 750, 650Xi or 650
HDG Heading
HSI Horizontal Situation Indicator

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IAP Instrument Approach Procedure
IAS Indicated Airspeed

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IFR Instrument Flight Rules

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ILS Instrument Landing System
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LNAV Lateral Navigation
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LNAV/VNAV Lateral Navigation with Vertical Navigation
L/VNAV Lateral/Vertical Navigation
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LOC Localizer
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LP+V Localizer Performance with Advisory Vertical Guidance

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LP Localizer Performance
LPV Localizer Performance with Vertical Guidance
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LRU Line Replaceable Unit

MFD Multi-function Display
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OBS Omnibearing Select

PFD Primary Flight Display
RF Leg Radius-to-Fix Leg of a Charted Instrument Procedure
RNAV Area Navigation
RNP Required Navigational Performance
SBAS Satellite Based Augmentation System
SD Secure Digital
TAWS Terrain Awareness and Warning System
TSO Technical Standard Order
VMC Visual Meteorological Conditions
VOR VHF Omnidirectional Range
VS Vertical Speed

Manufacturer’s Data Section Page 4 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

NOTE
References to specific technical standard orders, advisory circulars, operational
rules, and other guidance material are based on information current at time of
publication. Changes to these documents can occur over time. Pilots are
responsible for ensuring compliance with all operational requirements.

PILOT’S GUIDE
The G500(H)/G600/G700 TXi Pilot's Guide, part number 190-01717-10, Rev. B or later
applicable revision, contains detailed information regarding the G700 TXi system description,
control, and function.

MODIFICATION OVERVIEW
The equipment installed by this modification is shown in the block diagram below. The equipment
enclosed in the box is installed by pre-requisite STC ST01926WI. Reference to the GTN shall
mean the GTN 750Xi, 750, 650Xi or 650.

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Figure 1 - G700 TXi System Block Diagram

Manufacturer’s Data Section Page 5 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

The primary components/sensors for the Garmin G700 TXi system are listed in the following
table.
Table 1 G700 TXI System Equipment
Description Make/Model QTY
10.6” Control Display Unit with PFD/MFD GDU 1060 2
Air Data Computer (RVSM Compliant) GDC 7400 2
Attitude Heading Reference System GRS 7800 2
Option GRS 79
Remote-mount Magnetometer GMU 44 2
Remote-mount Temperature Probe GTP 59 2
Remote Control and Display Unit GCU 485 0 or 2
Analog to Digital Convertor GAD 43e 2
Standby Instrument (Attitude, Altimeter and Airspeed Indicator) GI 275 1

GDU 1060 Display

The GDU 1060 is a 10.6-inch LCD panel mount control and display unit. The GDU 1060 can be

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configured as a PFD/MFD. There are two GDU 1060 displays installed to the instrument panel.

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The GDU 1060 PFD function replaces traditional analog instruments by displaying: 1. Attitude; 2.
Airspeed; 3. Altitude; 4. Vertical speed (including TCAS Resolution Advisory Information); 5.

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Heading; 6. HSI; 7. lateral/vertical deviation; 8. Alerts; 9. GNSS/SBAS navigation information; 11.
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Radar altimeter; 12. Temperature; and 13. Time.
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GDU 1060 MFD function provides the following MFD displays: 1. Moving map; 2. Weather; 3.
Traffic; 4. Terrain; 5. Flight plan; 6. Charts; 7. Waypoint information; 8. System information; and
9. Alerts
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Figure 2 - GDU 1060 Display

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One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

An example of typical indications is shown below.

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Figure 3 - Typical GDU 1060 Bugs and Controls
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ALT/HDG knob: The ALT/HDG knob allows the pilot to set the selected altitude or heading bug
on the G700 TXi. The outer knob changes the selected altitude bug. The inner knob sets the
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value of the heading bug. The inner knob can also be pushed to sync the HDG bug to the
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currently selected heading.

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BARO knob: The BARO knob allows the pilot to set the selected barometric pressure. The knob
controls the Barometric pressure setting to aid in altitude calibration. When the knob is pressed,
the Barometric setting will revert to Standard.
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IAS/VS knob: The IAS/VS knob allows the pilot to set the selected indicated airspeed (IAS) or
vertical speed (VS). The outer knob changes the selected IAS bug on the PFD and the inner
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knob changes the value of the selected vertical speed. Pushing the inner knob will sync the VS
bug to the value of the currently selected vertical speed for selected autopilots.
CDI button: Changes the NAV source for the Course Deviation Indicator (CDI).
Database Cards
The G700 TXi utilizes several databases. Database titles display in yellow if expired or in
question (Note: the G700 TXi receives the calendar date from the GPS, but only after acquiring a
position fix). Database cycle information is displayed at power up on the MFD screen, but more
detailed information is available on the AUX pages. Internal database validation prevents
incorrect data from being displayed.
The upper Secure Digital (SD) data card slot is typically vacant as it is used for software
maintenance and navigational database updates. The lower data card slot should contain a data
card with the system’s terrain / obstacle information and optional data including Safe Taxi,
FliteCharts and ChartView electronic charts (if installed).

Manufacturer’s Data Section Page 7 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

The terrain databases are updated periodically and have no expiration date. Coverage of the
airport terrain database is worldwide.
The obstacle database (optional) contains data for obstacles, such as towers, that pose a
potential hazard to aircraft. Obstacles 200 feet and higher are included in the obstacle database.
It is very important to note that not all obstacles are necessarily charted and therefore may not
be contained in the obstacle database. Coverage of the obstacle database includes the United
States and Europe. This database is updated on a 56-day cycle.
The Garmin SafeTaxi database (optional) contains detailed airport diagrams for selected
airports. These diagrams aid in following ground control instructions by accurately displaying the
aircraft position on the map in relation to taxiways, ramps, runways, terminals, and services. This
database is updated on a 56-day cycle.
The Garmin FliteCharts database (optional) contains procedure charts for the coverage area
purchased. This database is updated on a 28-day cycle. If not updated within 180 days of the
expiration date, FliteCharts will no longer function.
The Jeppesen ChartView electronic charts database (optional) contains procedure charts for the

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coverage area purchased. An own-ship position icon will be displayed on these charts. This
database is updated on a 14-day cycle. If not updated within 70 days of the expiration date,

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ChartView will no longer function.

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The airport directory database (optional) contains detailed information on landing facilities, such
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as operating hours, services available, and transportation/lodging resources. Airport directory
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information may be available from multiple sources and coverage areas. This database is
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updated on a 56-day cycle.
GCU 485 controller
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The GCU 485 is a remote controller for the GDU 1060 PFD. The GCU 485 allows for direct pilot
interaction with various PFD settings, without the need for the pilot to use the touchscreen or
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dual-concentric knob controls on the GDU. The GCU is internally lit and incorporates a photocell
in the bezel to drive lighting levels.
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Figure 4 - GCU 485 Remote Control Unit

ALT/HDG knob: The ALT/HDG knob allows the pilot to set the selected altitude or heading bug
on the G700 TXi. The outer knob changes the selected altitude bug. The inner knob sets the
value of the heading bug. The inner knob can also be pushed to sync the HDG bug to the
currently selected heading.
BARO knob: The BARO knob allows the pilot to set the selected barometric pressure. The knob
controls the Barometric pressure setting to aid in altitude calibration. When the knob is pressed,
the Barometric setting will revert to Standard.
IAS/VS knob: The IAS/VS knob allows the pilot to set bugs for indicated airspeed (IAS) or
vertical speed (VS). The outer knob changes the selected IAS bug on the PFD and the inner

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

knob changes the value of the vertical speed. Pushing the inner knob will sync the VS bug to the
value of the currently selected vertical speed. The IAS and VS bugs are not connected to the
autopilot.
CDI button: Changes the NAV source for the Course Deviation Indicator (CDI).
GI 275 Standby Instrument
The GI 275 standby instrument provides an independent display for standby attitude, altimeter
and airspeed information. The optional heading function of the GI 275 is not included in this
installation. The GI 275 is powered by the left Essential A buss and the GI 275 has an internal
back-up battery.

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Figure 5 - GI 275 Standby Indicator
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POWER
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The following circuit breakers provide power to the dual G700 TXi equipment:
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• DC Power to the GDU 1060 PFD/MFD units is provided through 5-amp DC circuit breakers
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labeled GDU 1 and GDU 2 on the respective #1 and #2 Essential A Buss.

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• AC Power to the #1 (Pilot’s) GDU 1060 PFD/MFD unit is provided through 2-amp AC circuit
breaker labeled GDU 1 on the #1 side 26V AC Buss.
• Power to the GDC 7400 ADC units is provided through 5-amp DC circuit breakers labeled
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ADC 1 and ADC 2 on the respective #1 and #2 Essential A Buss.

• Power to the GRS 79 AHRS units (if installed) is provided through 3-amp DC circuit
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breakers labeled AHRS 1 and AHRS 2 on the respective #1 and #2 Essential A Buss.
• Power to the GRS 7800 AHRS units (if installed) is provided through 5-amp DC circuit
breakers labeled AHRS 1 and AHRS 2 on the respective #1 and #2 Essential A Buss.
• DC Power for the GAD 43E adapter is provided through 3-amp DC circuit breaker labeled
GAD 43E on the #1 Essential A Buss.
• AC Power for the GAD 43E adapter is provided through 2-amp AC circuit breaker labeled
GAD 43E on the #1 26V AC Buss.
• Power to the GCU 485 display control units is provided through 1-amp DC circuit breakers
labeled GCU 1 and GCU 2 on the respective #1 and #2 Essential A Buss
• Power for the air data ADM adapter is provided through 1-amp DC circuit breaker labeled
ADM on the #1 Essential A Buss.
• Power to the air data digital adapters for the autopilot is provided through 2-amp DC circuit
breakers labeled DDA 1 and DDA 2 on the respective #1 and #2 Essential A Buss.

Manufacturer’s Data Section Page 9 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

SECTION I – LIMITATIONS
COCKPIT REFERENCE & PILOT’S GUIDE
The Garmin G500(H)/G700 TXi/G700 TXi Pilot’s Guide P/N 190-01717-10, Revision N or later
appropriate revision must be immediately available to the flight crew.

SYSTEM SOFTWARE REQUIREMENTS

The G700 TXi system must utilize the following software versions or later for this AFMS revision
to be applicable:
Table 2 - Software Versions
Component Software Version
GDU 1060 PFD / MFD 3.12

MOVING MAP

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The only approved source of course guidance is the HSI display on the PFD. The moving map
on the MFD and the HSI map are advisory in nature and is not approved for course guidance.

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The moving map on the MFD must be cross checked for correctness against the PFD HSI,

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published charts, or other approved sources of navigation information.
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AHRS OPERATIONAL DATA
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The AHRS used in the G700 TXi is limited in its operational area: IFR Operations are prohibited
north of 72°N and south of 70°S latitudes unless the GRS 7800 is installed. In addition, IFR
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operations are prohibited in the following four regions:

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1) North of 65° North latitude between longitude 75° W and 120° W

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2) North of 70° North latitude between longitude 70° W and 128° W

3) North of 70° North latitude between longitude 85° E and 114° E
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4) South of 55° South latitude between longitude 120° E and 165° E

If the GRS 7800 AHRS is installed, IFR Operations are prohibited north of 84°N and south of
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70°S latitudes in addition to the four prohibitions immediately above.

Loss of the G700 TXi heading and attitude may occur near the poles, but this will not affect the
GPS track or standby attitude indicator.

MAGNETIC VARIATION OPERATIONAL AREA

IFR operations are prohibited in areas where the magnetic variation is greater than 99.9 degrees
East or West.

AHRS NORMAL OPERATING MODE

The Attitude and Heading Reference System integrity monitoring features require the availability
of GPS and Air Data. Although the attitude will remain valid if one of these systems becomes
inoperative, IFR flight is not authorized unless both integrity systems are fully operational. The
G700 TXi monitors these integrity systems automatically and will alert the pilot when the AHRS is
not receiving GPS or Air Data. Note: In dual GPS installations, only one GPS needs to be
available for IFR use.
Manufacturer’s Data Section Page 10 of 26 Document No. 05707100
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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

AIRSPEED LIMITATIONS AND INDICATOR MARKINGS

The original type design approved airspeed limitations remain in effect. The airspeed limitations
imposed by the AFM/POH, standby airspeed indicator and/or airspeed limitation placards must
be observed.
The G700 TXI airspeed tape displays red/white striping to indicate the maximum allowable
airspeed (VNE/VMO/MMO). This maximum allowable airspeed display is configured to indicate the
appropriate maximum allowable airspeed for the airplane, including variations for altitude or
Mach number.
The G700 TXI airspeed tape displays a red low-speed awareness band at the lower range of the
airspeed tape. This low-speed awareness band is configured to a fixed value. It does not indicate
an actual or calculated stall speed and does not adjust with variations in aircraft weight or other
factors.
All other G700 TXI airspeed tape indications are configured to indicate the original type design
limitations. The G700 TXI airspeed tape does not adjust these additional markings (including

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VNO, landing gear, or flap speed limitations) for variations with aircraft weight, altitude, or other
factors.

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SYNTHETIC VISION TECHNOLOGY

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The use of the synthetic vision display elements alone for aircraft control without reference to the
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G700 TXI primary flight instruments or the aircraft standby instruments is prohibited.
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TERRAIN-FLTA
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The G700 TXi is configured for Forward Looking Terrain Avoidance (FLTA). Aircraft maneuvers
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and navigation must not be predicated upon the use of the terrain display. Terrain-FLTA alerts
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are advisory only and are not equivalent to warnings provided by TAWS.

TRAFFIC DISPLAY (OPTIONAL)

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Traffic may be displayed on the G700 TXi System provided by an existing TAS, TCAS I or TCAS
II system. Use of traffic display as the sole basis for maneuvering to avoid traffic is prohibited.
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One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

KINDS OF OPERATIONS
Unless placarded as limited to VFR only operations, G700 TXi equipment installed in an
appropriately certified aircraft is approved for Day and Night / VFR and IFR operations in
accordance with 14 Code of Federal Regulations Part 91, Part 121, and Part 135 when
appropriately maintained.
The table below lists the minimum fully functional G700 TXi System elements required for IFR
flight operations. For IFR flight, a fully functional G700 TXi system should not generate system
alerts, which indicate faults within the system or any interfaced equipment.
Equipment Number installed VFR IFR
Primary/Multi Flight Display (GDU 1060) 2 1a** 1
Garmin GPS/SBAS Navigator (GTN) 2* - 1
Attitude / Heading Unit (GRS 79 AHRS***) 2 - 1
Air data computer 2 1a** 1
(GDC 7400 ADC)
Magnetometer (GMU 44) 2 - 1

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Standby Attitude Indicator (GI 275) 1 - 1
Standby Airspeed Indicator (GI 275) 1 1b 1

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Standby Altimeter (GI 275) 1 1b 1

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Magnetic Compass 1* 1 1
*Existing equipment
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**For VFR operations under 14 CFR Part 91, the aircraft must have one source of
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altitude and airspeed information. This may be from either the PFD or the standby
instruments. (i.e. all “1a” items or all “1b” items from the table above).
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*GRS 7800 installation is an optional alternative to the GRS 79 AHRS.

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TAWS-A FUNCTIONS (OPTIONAL)

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NOTE
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The Terrain Display is intended to serve as a situational awareness tool only. It may
not provide the accuracy and/or fidelity on which to solely base decisions and plan
maneuvers to avoid terrain or obstacles.
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• Flight crews are authorized to deviate from their current ATC clearance to
the extent necessary to comply with TAWS warnings. Navigation must not
be predicated on the use of the TAWS-A Information
• TAWS-A shall be inhibited when landing at an airport that is not included in
the airport database.

Manufacturer’s Data Section Page 12 of 26 Document No. 05707100

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One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

SECTION II – NORMAL PROCEDURES

Refer to the GTN Xi Series Pilot’s Guide (190-01717-10) for normal operating procedures. This
includes all GNSS operations, VHF communication and navigation, traffic, terrain, transponder
operation, weather radar display and Multi-Function Display information.

POWER ON
1. Database ................................................................ REVIEW EFFECTIVE DATES
2. G700 TXi Self-Test .......................................VERIFY OUTPUTS TO BOTH PFDs
3. GTN Self-Test ..............................................VERIFY OUTPUTS TO BOTH PFDs

BEFORE TAKEOFF
1. System Messages and Annunciators ..............................................CONSIDERED

AUTOPILOT/FLIGHT DIRECTOR INTERFACE

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Only the data displayed on the pilot’s (left) PFD can be coupled to the autopilot/flight director.

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When coupled to the VLOC navigation source (VLOC selected as the #1 PFD CDI source and
NAV selected as the autopilot/flight director mode), the autopilot/flight director uses analog

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course deviation data. The pilot must set the PFD HSI course pointer.
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When coupled to the ILS navigation source (VLOC selected as the #1 PFD CDI source and NAV
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with GS selected as the autopilot/flight director mode), the autopilot/flight director uses analog
course and glideslope deviation data. The pilot must set the PFD HSI course pointer.
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When coupled to the GNSS navigation source (GPS selected as the #1 PFD CDI source, GPSS
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selected on the PFD HDG/GPSS Switch and HDG selected as the autopilot/flight director mode),
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the autopilot/flight director uses roll steering to track the desired track and will lead course
changes and fly RF legs, arcing procedures, procedure turns, and holding patterns. The PFD
course pointer is automatically set to the desired track in the LEG mode. In OBS mode
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operations, the pilot must manually set the course pointer on the PFD.
For detailed autopilot/flight director operating instructions, refer to the FAA Approved Airplane
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Flight Manual and appropriate Airplane Flight Manual Supplement.

NOTE
The autopilot/flight director does not interface to PFD selected vertical speed control or
PFD selected airspeed control.
NOTE
The Autopilot Altitude Preselect mode is set using the PFD selected altitude control for
altitude value, and Altitude Preselect mode is armed using the autopilot controller SEL
button in the glareshield autopilot controller.

Manufacturer’s Data Section Page 13 of 26 Document No. 05707100

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One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

NOTE
The autopilot/flight director will automatically default to the wings lateral level mode as
indicated by the “LVL” annunciation on the autopilot/flight director controller from the NAV
mode whenever any one or more of the following signals is received by the autopilot/flight
director:
• Transition from roll steering to analog course deviation data
• CDI source is changed on the #1 PFD or GTN
• Roll steering mode on the #1 GTN is changed to approach mode
• Transition to missed approach
• Reaching the last point in a flight plan or on a missed-approach procedure
(decision point of whether or not to hold) without selecting “Unsuspend”
• #1 GTN navigation data is invalid
• Roll steering information is invalid
The pilot must anticipate the mode changes of the autopilot/flight director. In the event

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the autopilot or flight director does not perform the operation intended by the pilot,
immediately disconnect the autopilot and flight director and manually fly the airplane.

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Confirm autopilot/flight director mode selection after any change to the #1 GTN mode and before
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each segment of an instrument procedure.
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Coupling the Autopilot/Flight Director
NOTE
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• The autopilot/flight director can only be coupled to the data displayed on the
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pilot’s (left) PFD.

R FID

• When the pilot’s (left) PFD navigation source selection is changed, the
autopilot/flight director mode may change. Confirm autopilot/flight
director/mode selection after changing the navigation source displayed on the
FO ON

pilot’s (left) PFD.

• Phase of flight annunciations are provided at the bottom of the GTN display
C

indicating the current mode of flight.

Enroute and terminal using RNAV (GNSS) navigation:
GTN Mode: Active Leg Desired Track ...................................................CONFIRM
#1 PFD HDG/GPSS Switch ............................................. VERIFY/SELECT GPSS
#1 PFD CDI Selection ..................................................................... SELECT GPS
Autopilot/flight director Lateral Mode .......... SELECT HDG/ENGAGE (as desired)
Autopilot/flight director Vertical Mode ...............................................AS DESIRED

Manufacturer’s Data Section Page 14 of 26 Document No. 05707100

(Non-FAA Approved) Issue: 0
Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

Enroute, terminal and approach using VOR or localizer navigation:

#1 PFD HDG/GPSS Switch ...............................................VERIFY/SELECT HDG
#1 PFD CDI Selection .................................................................. SELECT VLOC
Course Pointer Selection ................... SET/CONFIRM VOR RADIAL/LOCALIZER
Autopilot/flight director Lateral Mode ........... SELECT NAV/ENGAGE (as desired)
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
ILS approach:
If on radar vectors:
#1 PFD HDG/GPSS Switch ...............................................VERIFY/SELECT HDG
#1 PFD CDI Selection .................................................................. SELECT VLOC
Course Pointer Selection .......................................... SET LOCALIZER COURSE
Autopilot/flight director Lateral Mode ............................. SELECT HDG/ARM NAV
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
When established on the localizer course:
Autopilot/flight director Lateral Mode ................................. CONFIRM NAV CAPT

LY
Glideslope Data ............................................................... CONFIRM AVAILABLE
Autopilot/flight director Vertical Mode ............................................... SELECT G/S

N
If using GNSS navigation to final approach course:

O
Prior to intercepting the final approach course:
E
GTN Mode: Active Leg Desired Track ...................................................CONFIRM
EN L
ER TIA

#1 PFD CDI Selection ..................................................................... SELECT GPS

C
#1 PFD HDG/GPSS Switch ............................................. VERIFY/SELECT GPSS
#1 PFD Heading Bug Selection ..................... SELECT INBOUND LOC COURSE
EF N

Autopilot/flight director Lateral Mode .............................................. SELECT HDG

R E

Autopilot/flight director Vertical Mode ...............................................AS DESIRED

Course Pointer Selection – Each Leg ............................................ CONFIRM/SET
R FID

When established on the localizer course inbound (flash of CDI soft key on PFD#1):
FO ON

#1 PFD CDI Selection .................................................................. SELECT VLOC

Course Pointer Selection ..................................... VERIFY LOCALIZER COURSE
Autopilot/flight director Lateral Mode ............................................... SELECT NAV
C

Glideslope Data ............................................................... CONFIRM AVAILABLE

Autopilot/flight director Vertical Mode ............................................... SELECT G/S

Manufacturer’s Data Section Page 15 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

Localizer Back Course approach:

If on radar vectors:
#1 PFD HDG/GPSS Switch ...............................................VERIFY/SELECT HDG
#1 PFD CDI Selection .................................................................. SELECT VLOC
Course Pointer Selection ....................................... SET to front course inbound
Autopilot/flight director Lateral Mode ............. SELECT HDG/ARM NAV and REV
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
When established on the localizer back course:
Autopilot/flight director Lateral Mode ................. CONFIRM NAV CAPT and REV
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
If using GNSS navigation to final approach course:
Prior to intercepting the final approach course:
GTN Mode: Active Leg Desired Track ...................................................CONFIRM
#1 PFD CDI Selection ..................................................................... SELECT GPS
#1 PFD HDG/GPSS Switch ............................................. VERIFY/SELECT GPSS

LY
#1 EHSI/HSI Heading Bug Selection ......................SELECT INBOUND COURSE
Autopilot/flight director Lateral Mode .............................................. SELECT HDG

N
Autopilot/flight director Vertical Mode ...............................................AS DESIRED

O
Once established on the localizer back course inbound (flash of CDI soft key on PFD#1):
E
EN L
#1 PFD CDI Selection .................................................................. SELECT VLOC
ER TIA
C
Course Pointer Selection ...................................... VERIFY front course inbound
Autopilot/flight director .................................................... SELECT NAV AND REV
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
EF N

RNAV (GPS) approach without vertical guidance (LNAV, LP):

R E

If on radar vectors:
R FID

#1 PFD HDG/GPSS Switch ...............................................VERIFY/SELECT HDG

#1 PFD CDI Selection ..................................................................... SELECT GPS
FO ON

Autopilot/flight director Lateral Mode .............................................. SELECT HDG

Autopilot/flight director Vertical Mode ...............................................AS DESIRED
When intercepting the final course, the CDI is active and GTN in approach mode:
C

#1 PFD HDG/GPSS Switch .......................................................... SELECT GPSS

Autopilot/flight director Lateral Mode ............................................... VERIFY HDG
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
If using GNSS navigation:
Prior to intercepting the final approach course:
# GTN Mode: Active Leg Desired Track ................................................CONFIRM
#1 PFD CDI Selection ..................................................................... SELECT GPS
1 PFD HDG/GPSS Switch ...............................................VERIFY/SELECT GPSS
#1 EHSI/HSI Heading Bug Selection ......................SELECT INBOUND COURSE
Autopilot/flight director Lateral Mode .............................................. SELECT HDG
Autopilot/flight director Vertical Mode ...............................................AS DESIRED
Course Pointer Selection – Each Leg ....................................................CONFIRM
When established on the final approach course and GTN in approach mode:
Autopilot/flight director Lateral Mode ................................................VERIFY HDG

Manufacturer’s Data Section Page 16 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

Autopilot/flight director Vertical Mode ...............................................AS DESIRED

NOTE
The autopilot/flight director uses the HDG channel for GPS Steering (GPSS) when GPSS
is selected on the G700 TXi HDG/GPSS button. The HDG mode must be re-selected
when using radar vectors to couple autopilot/flight director GPSS lateral deviation data
when the G700 TXi is switched from HDG to GPSS.
The autopilot/flight director must be in HDG mode with GPSS selected on the G700 TXi
HDG/GPSS switch to prevent autopilot/flight director reversion to the wings-level lateral
mode.
RNAV (GPS) approach with vertical guidance (LPV, LP+V, LNAV+V, L/VNAV):
If on radar vectors:
#1 PFD HDG/GPSS Switch ...............................................VERIFY/SELECT HDG
#1 PFD CDI Selection ..................................................................... SELECT GPS
Autopilot/flight director Lateral Mode .............................................. SELECT HDG
Autopilot/flight director Vertical Mode ...............................................AS DESIRED

LY
When intercepting the final course, the CDI is active and GTN in approach mode:

N
#1 PFD HDG/GPSS Switch .......................................................... SELECT GPSS

O
Vertical Deviation Information .......................................... CONFIRM AVAILABLE
Autopilot/flight director Lateral Mode ............................................ CONFIRM HDG
E
EN L
Vertical Deviation Information .......................................... CONFIRM AVAILABLE
ER TIA
C
Autopilot/flight director Vertical Mode ............................................... SELECT G/S
If using GNSS navigation:
EF N

Prior to intercepting the final approach course:

R E

GTN Mode: Active Leg Desired Track ...................................................CONFIRM

R FID

#1 PFD CDI Selection ..................................................................... SELECT GPS

#1 PFD HDG/GPSS Switch .......................................................... SELECT GPSS
Autopilot/flight director Lateral Mode .............................................. SELECT HDG
FO ON

Autopilot/flight director Vertical Mode ...............................................AS DESIRED

Course Pointer Selection – Each Leg ....................................................CONFIRM
C

When intercepting the final course, the CDI is active and GTN in approach mode:
Vertical Deviation Information .......................................... CONFIRM AVAILABLE
Autopilot/flight director Lateral Mode ............................................ CONFIRM HDG
Vertical Deviation Information .......................................... CONFIRM AVAILABLE
Autopilot/flight director Vertical Mode ............................................... SELECT G/S
NOTE
The autopilot/flight director must be in HDG mode with GPSS selected on the G700 TXi
HDG/GPSS switch to prevent autopilot/flight director reversion to the wings-level lateral
mode.

Manufacturer’s Data Section Page 17 of 26 Document No. 05707100

(Non-FAA Approved) Issue: 0
Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

Missed Approach:
Autopilot ......................................................................................... DISCONNECT
If GNSS guidance to the missed approach holding point is desired:
#1 PFD HDG/GPSS Switch .......................................................... SELECT GPSS
GTN Mode: Activate GPS Missed Approach............................................ SELECT
#1 PFD CDI Selection .................................................... VERIFY/SELECT GPS 1
GTN GPS Waypoint Sequencing ..................................................... UNSUSPEND
GTN Mode: Active Leg Desired Track ...................................................CONFIRM
Autopilot/flight director ............................................................................ ENGAGE
Autopilot/flight director Lateral Mode .............................................. SELECT HDG
Autopilot/flight director Vertical Mode ...............................................AS DESIRED

LY
N
O
E
EN L
ER TIA
C
EF N
R E
R FID
FO ON
C

Manufacturer’s Data Section Page 18 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

SECTION III – EMERGENCY PROCEDURES

TAWS-A Warnings (If Optional TAWS is Equipped)
GDU 1060 PFD: PULL UP
GTN: PULL UP or Pop-Up Alert and Aural Alert (see following table)
Autopilot .................................................................................................... DISCONNECT
Aircraft Controls.................................................... INITIATE MAXIMUM POWER CLIMB*
Airspeed ...................................................................... BEST ANGLE OF CLIMB SPEED
NOTE
Only vertical maneuvers are recommended, unless either operating in visual
meteorological conditions (VMC), or the flight crew determines, based on all
available information, that turning in addition to the vertical escape maneuver is the
safest course of action, or both.
After Warning Ceases:

LY
Altitude ........................................................... CLIMB AND MAINTAIN SAFE ALTITUDE
Advise ATC of Altitude Deviation, if appropriate.

N
GTN TAWS-A WARNINGS

O
ALERT TYPE ANNUNCIATION POP-UP ALERT (GTN) AURAL MESSAGE
(Except TAWS-A Page)
E
EN L
Reduced Required PULL UP “Terrain, Terrain; Pull Up, Pull Up”
ER TIA

Terrain Clearance Or
C
Or
Warning (RTC) “Terrain Ahead, Pull Up; Terrain
Ahead, Pull Up”
Imminent Terrain “Terrain, Terrain; Pull Up, Pull Up”
EF N

Impact Warning (ITI) Or Or

R E

“Terrain Ahead, Pull Up; Terrain

Ahead, Pull Up”
R FID

Reduced Required “Obstacle, Obstacle; Pull Up, Pull

Obstacle Clearance Or Up” Or
Warning (ROC) “Obstacle Ahead, Pull Up;
FO ON

Obstacle Ahead, Pull Up”

Imminent Obstacle “Obstacle, Obstacle; Pull Up, Pull
Impact Warning (IOI) Or Up” Or
C

“Obstacle Ahead, Pull Up;

Obstacle Ahead, Pull Up”
Excessive Descent PULL UP “<whoop>
Rate Warning (EDR) <whoop> Pull Up”
Excessive Closure PULL UP “<whoop>
Rate Warning (ECR) <whoop> Pull Up”

Manufacturer’s Data Section Page 19 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

SECTION IV – ABNORMAL PROCEDURES

These procedures supersede those presented as markings or placards or documented in the
aircraft’s FAA approved Airplane Flight Manual as a result of the installation of the G700 TXi
PFD/MFD system. All other emergency procedures remain in effect.
1. If primary flight information (Attitude, Heading, Altitude or Airspeed) on the Pilot’s (#1)
PFD is not available or appears invalid, AHRS or air data information may be transferred
from the Co-pilot’s (#2) AHRS or (#2) air data computer to the Pilot’s (#1) PFD.
2. The Attitude, Heading and Reference System (AHRS) requires at least one GPS or air
data input to function properly. In the unlikely event that GPS data and air data is not
received by the AHRS, the system will subsequently lose attitude and heading and the
pilot will be required to use the standby instrumentation. In this instance, the PFD will not
provide Attitude, Heading, Altitude, or Airspeed information.
3. If navigation information on the PFD/MFD (HSI, RMI, WPT bearing and distance
information, or Moving Map Data) is not available or appears invalid, select an alternate

LY
data source (via CDI key or 1-2 key – the Co-pilot’s (#2) GTN data may be transferred to
the Pilot’s (#1) PFD) or utilize the data directly from the navigation equipment as required.

N
4. The synthetic vision display of terrain uses several data sources to correctly display

O
terrain (GPS, terrain database, attitude information, etc.). If any of these data sources
become unreliable or unavailable, the display of synthetic terrain will automatically revert
E
EN L
to the non-SVT PFD display of blue over brown. Additionally, if during the course of
ER TIA
C
normal operations there is any discrepancy between actual terrain around the aircraft and
terrain shown on the SVT display, the display of synthetic vision should be manually
turned off.
EF N
R E

5. If GPS position information from the selected GPS/SBAS navigation source is not valid
due to an inability to track GPS, the own-ship icon on the MFD is removed and “NO GPS
R FID

POSITION” text is overlaid on the MFD moving map. The system will annunciate a loss of
integrity, “LOI” on the HSI. The LOI annunciation will be colored yellow and the HSI
FO ON

needle will flag. The pilot should select an alternate navigation source (via CDI key or 1-2
key). Pressing the CDI soft key will change the HSI navigation source. If GPS navigation
is subsequently restored, the MFD moving map will display the own-ship icon, and the
C

HSI navigation source may be selected to GPS; at that time the “LOI” annunciation will be
removed.

Manufacturer’s Data Section Page 20 of 26 Document No. 05707100

(Non-FAA Approved) Issue: 0
Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

Abnormal Indications
Heading Failure
“HDG FAIL” annunciates when there is an AHRS heading data failure. If the magnetometer fails,
the HSI compass card indicates GPS track. The numeric heading value turns magenta to
indicate GPS track is displayed.
If both the magnetometer and GPS units fail:
• HSI reverts to a non-directional CDI
• Numeric heading display is removed
• Use the selected course control to manually control OBS
AHRS Failure
A failure of the Attitude and Heading Reference System (AHRS) is indicated by a removal of the
sky/ground presentation, a red X on the attitude display, and “HDG FAIL” is shown on the PFD
below the airspeed tape. Rate-of-turn information (heading trend vector) will not be available.

LY
1. Switch to the other AHRS source, if available.
2. Use Standby Attitude Indicator and standby compass

N
3. Seek VFR conditions or land as soon as practical

O
Air Data Computer (ADC) Failure
E
EN L
Complete loss of the Air Data Computer is indicated by a red X and yellow text over the
ER TIA
C
airspeed, altimeter, vertical speed, TAS and OAT displays. Some derived functions, such as true
airspeed and wind calculations, will also be lost. If valid GPS data is available, the PFD will
automatically revert to display GPS calculated altitude relative to mean sea level. This GPS
EF N

altitude is displayed above the altitude tape.

R E

1. Switch to the other air data source, if available

R FID

2. Use Standby Airspeed Indicator and Altimeter

3. Seek VFR conditions or land as soon as practical
FO ON

LOSS OF ELECTRICAL POWER

C

In the event of a total loss of electrical power, the G700 TXi system will cease to operate and the
pilot must utilize the standby instruments to fly the aircraft.

ALERT ANNUNCIATIONS
Alert annunciations are abbreviated messages that indicate an alerted function or mode. The
color of the annunciation depends on the alert type.
• Warnings display in white text on red background
• Cautions display in black text on amber background
• Function or mode specific advisories display in black text on white background

Manufacturer’s Data Section Page 21 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

When an alert is triggered, the annunciation flashes by alternating text and background colors. It
turns solid after five seconds. All annunciations remain active (solid) until the condition is
resolved or no longer a threat.
TAWS-A Cautions (If Optional TAWS is Equipped)
GDU 1060 PFD and GTN: Alert Type Caution (See Table Below)
Autopilot .................................................................................................... DISCONNECT
Aircraft Controls..... VERIFY AIRCRAFT FLIGHT PATH AND CORRECT, IF REQUIRED
Stop descending or initiate either a climb or a turn, or both as necessary, based on analysis of all
available instruments and information.
NOTE
If the amber TER N/A or TER FAIL status annunciator is displayed, the system will
no longer provide TAWS alerting or display relative terrain and obstacle elevations.
The crew must maintain compliance with procedures that ensure minimum terrain
and obstacle separation.

LY
POP-UP ALERT
G700 TXi Display (GTN) AURAL
ALERT TYPE ANNUNCIATION (Except TAWS-A Page) MESSAGE

N
“Caution, Terrain;

O
Caution, Terrain”*
Reduced Required Terrain Clearance
TERRAIN Or Or
Caution (RTC)
E
EN L
“Terrain Ahead;
Terrain Ahead”
ER TIA
C
“Caution, Terrain;
Caution, Terrain”
Imminent Terrain Impact Caution (ITI) TERRAIN Or Or
EF N

“Terrain Ahead;
R E

Terrain Ahead”
“Caution,
R FID

Obstacle;
Caution,
Reduced Required Obstacle Clearance
OBSTCL Or Obstacle”*
Caution (ROC)
FO ON

Or
“Obstacle Ahead;
Obstacle Ahead”
C

“Obstacle Ahead;
Obstacle Ahead”*
Or
Imminent Obstacle Impact Caution (IOI) OBSTCL Or “Caution,
Obstacle;
Caution,
Obstacle”
“Too Low,
Premature Descent Alert Caution (PDA) TERRAIN
Terrain”
Excessive Descent Rate Caution (EDR) TERRAIN “Sink Rate”
Excessive Closure Rate Caution (ECR) TERRAIN “Terrain, Terrain”
“Don’t Sink”*
Or
Negative Climb Rate Caution (NCR) TERRAIN Or
“Too Low,
Terrain”
Flight Into Terrain High Speed Caution “Too Low,
TERRAIN
(FIT) Terrain”
Flight Into Terrain Gear Caution (FIT) TERRAIN “Too Low, Gear”
Flight Into Terrain Flaps Caution (FIT) TERRAIN “Too Low, Flaps”

Manufacturer’s Data Section Page 22 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

POP-UP ALERT
G700 TXi Display (GTN) AURAL
ALERT TYPE ANNUNCIATION (Except TAWS-A Page) MESSAGE
“Too Low,
Flight Into Terrain Takeoff Caution (FIT) TERRAIN
Terrain”
Glide Slope Deviation Caution (GSD) GLIDESLOPE “Glideslope”
TAWS Not
TAWS N/A TAWS N/A N/A
Available
“TAWS System
TAWS System Test Fail TAWS FAIL N/A
Failure”
Incorrect TAWS configuration, invalid
“TAWS System
/missing terrain, airport, or obstacle TAWS FAIL* N/A
Failure”
database, or TAWS audio fault
“TAWS Not
No GPS position TAWS N/A N/A
Available”
GPS position unavailable/degraded, “TAWS Not
TAWS N/A N/A
outside of terrain database coverage Available”
Incorrect TAWS configuration, radar
“GPWS System
altimeter unavailable, GPS position GPWS FAIL N/A
Failure”
unavailable/ degraded, TAWS audio fault

LY
GPWS Not Available.
Incorrect TAWS configuration, radar

N
altimeter unavailable, GPS position GPWS N/A N/A None
unavailable/ degraded, TAWS audio

O
fault.
*VCO alerts are not issued if both TAWS and GPWS systems have failed or are not available
E
EN L
ER TIA
C
EF N
R E
R FID
FO ON
C

Manufacturer’s Data Section Page 23 of 26 Document No. 05707100

(Non-FAA Approved) Issue: 0
Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

TAWS-A Inhibit (GTN 750Xi Only)

The TAWS Forward Looking Terrain Avoidance (FLTA) and Premature Descent Alerts (PDA)
functions may be inhibited to prevent alerting, if desired. Only the PDA and FLTA alerts are
disabled in the inhibit mode. After cycling power, TAWS-A will no longer be inhibited. information.
To Inhibit TAWS-A
HOME Key ............................................................................................................PRESS
Terrain Key ........................................................................................................... TOUCH
Menu Key ............................................................................................................. TOUCH
TAWS Inhibit ........................................................................................................ TOUCH
NOTE
A green bar in the key indicates the TAWS is inhibited.
To Enable TAWS-A (if inhibited)
TAWS Inhibit ........................................................................................................ TOUCH
GPWS Inhibit (GTN 750Xi Only)

LY
EDR, ECR, FIT, and NCR aural and visual alerts can be manually inhibited as a group.

N
Discretion should be used when inhibiting alerts and the GPWS system should be enabled when
appropriate. When these alerts are inhibited, the alert annunciation “GPWS INH” is shown on the

O
TAWS-A Page annunciation window.
E
EN L
To Inhibit GPWS
ER TIA
C
HOME Key ............................................................................................................PRESS
Terrain Key ........................................................................................................... TOUCH
EF N

Menu Key ............................................................................................................. TOUCH

GPWS Inhibit ........................................................................................................ TOUCH
R E

NOTE
R FID

A green bar in the key indicates the GPWS functions are inhibited.
To Enable GPWS (if inhibited)
FO ON

GPWS Inhibit ........................................................................................................ TOUCH

Flap Override Inhibit (GTN 750Xi Only)
C

To reduce nuisance FIT alerts on approaches where flap extension is not desired (or is
intentionally delayed), the pilot may override FIT alerting based on the flap position, while all
other FIT alerting remains in effect.
To Inhibit Flaps-Based Flight Into Terrain Alerting
HOME Key ............................................................................................................PRESS
Terrain Key ........................................................................................................... TOUCH
Menu Key ............................................................................................................. TOUCH
Flap Override........................................................................................................ TOUCH
NOTE
A green bar in the key indicates the Flaps-Based Flight Into Terrain Alerting is
inhibited.

Manufacturer’s Data Section Page 24 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

To Enable GPWS (if inhibited)

Flap Override......................................................................................................... TOUCH
Glideslope Deviation Inhibit (GTN 750Xi Only)
GSD alerts are inhibited independent from all other FLTA, PDA, and GPWS alerts.
NOTE
The Glideslope (G/S) Inhibit function should be activated when flying a localizer
backcourse approach to prevents nuisance GSD alerts.
NOTE
The G/S Inhibit function will only be active for a single approach and the inhibit
function will not remain active for subsequent approaches. When G/S alerts are
inhibited, they are only inhibited for a single approach. To inhibit G/S alerts on the
next approach, the G/S Inhibit function must be activated again between the first
and second approaches.
To Inhibit Glideslope Deviation (GSD) Alerts

LY
HOME Key ............................................................................................................. PRESS

N
Terrain Key ............................................................................................................ TOUCH
Menu Key .............................................................................................................. TOUCH

O
G/S Inhibit ............................................................................................................. TOUCH
E
EN L
NOTE
ER TIA
C
A green bar in the key indicates the Glideslope Deviation Alerts are inhibited.
To Enable Glideslope Deviation Alerts
EF N

G/S Inhibit ............................................................................................................. TOUCH

R E
R FID
FO ON
C

Manufacturer’s Data Section Page 25 of 26 Document No. 05707100

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Butler National Corporation AFM Supplement For
One Aero Plaza Learjet 35, 35A (C21A), 36, 36A
New Century, KS 66031

SECTION V – PERFORMANCE
No change.

SECTION VI – SUPPLEMENTS
No change.

SECTION VII – WEIGHT AND BALANCE DATA

Refer to current weight and balance data. The Garmin G700 TXi System is considered a
permanent modification and the basic aircraft weight and balance shall be updated when the
system is installed.

LY
N
O
E
EN L
ER TIA
C
EF N
R E
R FID
FO ON
C

Manufacturer’s Data Section Page 26 of 26 Document No. 05707100

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