Garmin | G500 TXi | Garmin G500 TXi AFMS TBM 700/850 G600 TXi RVSM

Garmin G500 TXi AFMS TBM 700/850 G600 TXi RVSM
Rev
1
Section
All
2
2,3,4,7
LOG OF REVISIONS
Description
FAA Approval
Complete Supplement
Erik Frisk
ODA STC Unit Administrator
Garmin International, Inc.
ODA-240087-CE
Date: 11/17/2017
Updated procedures to include
applicable data for replacement of the
KFC275/325 with the GFC600 AFCS.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
See Page 1
190-01717-B4 Rev. 2
Page 2 of 20
TABLE OF CONTENTS
SECTION 1. GENERAL................................................................................... 4
1.1
1.2
1.3
APPLICABILITY ..................................................................................... 4
RVSM GROUP AIRWORTHINESS APPROVAL ........................................ 4
DEFINITIONS ......................................................................................... 4
SECTION 2. LIMITATIONS ........................................................................... 6
2.1
2.2
2.3
2.4
OPERATIONS ......................................................................................... 6
STATIC PORTS....................................................................................... 6
AIR DATA SOURCE ............................................................................... 6
REQUIRED EQUIPMENT ......................................................................... 6
SECTION 3. EMERGENCY PROCEDURES ................................................ 7
3.1
3.2
EMERGENCY PROCEDURES ................................................................... 7
ABNORMAL PROCEDURES................................................................... 12
SECTION 4. NORMAL PROCEDURES ...................................................... 14
4.1
4.2
4.3
PREFLIGHT INSPECTION ...................................................................... 14
BEFORE TAKEOFF ............................................................................... 14
CRUISE ............................................................................................... 14
SECTION 5. PERFORMANCE ..................................................................... 15
SECTION 6. WEIGHT AND BALANCE ..................................................... 15
SECTION 7. DESCRIPTION ......................................................................... 16
7.1
7.2
7.3
7.4
SYSTEM DESCRIPTION ........................................................................ 16
PITOT-STATIC SYSTEM ....................................................................... 18
TRANSPONDER ALTITUDE SOURCES ................................................... 19
AUTOMATIC ALTITUDE CONTROL SYSTEM ........................................ 19
SECTION 8. HANDLING, SERVICING AND MAINTENANCE ............. 20
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 3 of 20
Section 1. GENERAL
1.1 Applicability
This supplement applies to TBM 700/850 aircraft which have been modified for
Reduced Vertical Separation Minimum (RVSM) operations in accordance with
Supplemental Type Certificate SA02571SE. It applies to TBM 700/850 aircraft
which have been modified in accordance with Appendix G of the G500/G600
TXi Part 23 AML STC Installation Manual, 190-01717-B3.
For general limitations, procedures and performance information on the G600
TXi system refer to the G600 TXi AFMS (Garmin part number 190-01717-B2).
NOTE
The basic G500/600 TXi AFMS includes limitations and
procedures for the altitude preselector.
1.2 RVSM Group Airworthiness Approval
Aircraft equipped with this modification have been evaluated in accordance with
14 CFR Part 91, Appendix G, “Operations in Reduced Vertical Separation
Minimum (RVSM) Airspace,” and FAA Advisory Circular 91-85B,
“Authorization of Aircraft and Operators for Flight in Reduced Vertical
Separation Minimum Airspace,” and are qualified for RVSM operations as a
group aircraft. This finding does not constitute approval to conduct RVSM
operations. Additional approval to conduct RVSM operations may be required
by the local aviation authority.
1.3
Definitions
The following acronyms are used within this document:
ADC:
AFM:
AFMS:
AHRS:
GPS:
ICAO:
LCD:
MEL:
OAT:
PFD:
PIT:
Air Data Computer
Aircraft Flight Manual
Aircraft Flight Manual Supplement
Attitude Heading and Reference System
Global Positioning System
International Civil Aviation Organization
Liquid-Crystal Display
Minimum Equipment List
Outside Air Temperature
Primary Flight Display
Autopilot pitch hold mode
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 4 of 20
MFD:
POH:
RVSM:
SSEC:
TAS:
Multi-Function Display
Pilot Operating Handbook
Reduced Vertical Separation Minimum
Static Source Error Correction
True Air Speed
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 5 of 20
Section 2. LIMITATIONS
2.1 Operations
Reduced Vertical Separation Minimum (RVSM) airworthiness approval is met
pending airplane compliance with the G600 TXi Installation Manual.
Airworthiness Approval alone does not authorize flight into airspace for which
an RVSM Operational Approval is required by an ICAO Regional Navigation
Agreement.
NOTE
Only the configurations approved in Appendix G of the G600
TXi Installation Manual is compliant with TBM 700 operation
in RVSM airspace.
2.2 Static Ports
RVSM operations are not permitted if the static ports are damaged or if there is
damage or surface irregularities within the RVSM critical area.
NOTE
The RVSM critical area encompasses approximately 18 inches
forward and 8 inches above/below/aft of the static ports. If
damage or surface irregularities are suspected to be within this
area, consult maintenance personnel.
2.3 Air Data Source
During normal operations, the Pilot PFD must be set to receive air data from
ADC 1 which can be selected from the PFD; (Menu→Sensors→ADC1).
Selection of the ADC 2 source is only permitted during system testing and
emergency procedures. When ADC 2 is selected as the source of air data:
• A white ON ADC2 will appear on the PFD
• True Airspeed and Outside Air Temperature data will be unavailable if
an AM250 is installed as ADC 2
2.4 Required Equipment
The equipment listed below must be operational in addition to the equipment
specified in the basic G600 TXi AFMS before conducting RVSM flight
operations:
•
•
•
•
•
Co-Pilot altitude display
Air Data Source #2 (ADC 2)
Automatic Altitude Hold System
Audio panel (aural altitude alerter functions only)
One (1) transponder with altitude reporting function
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 6 of 20
Section 3. EMERGENCY PROCEDURES
3.1
Emergency Procedures
NOTE
The ADC failure procedures in this AFMS supersede the ADC
failure procedure in the basic G600 TXi AFMS.
3.1.1 ADC 1 Failure
ADC 1 failure is indicated by:
• Red X over airspeed and altitude tapes
• Yellow X over vertical speed
• TAS and OAT displays are dashed
Wind calculations will be unavailable. If valid GPS data is available, the PFD
will automatically display GPS altitude relative to mean sea level above the
altitude tape. Autopilot modes requiring air data which has failed may be
unavailable.
1.
Monitor Co-Pilot altimeter to maintain assigned altitude.
standby airspeed indicator for airspeed reference.
Refer to
2.
Select ADC 2 as the air data source by selecting ADC 2 on the PFD
display (Menu→Sensors→ADC2).
When ADC 2 data is displayed on the PFD, the PFD may be used for
altitude, airspeed, and vertical speed references. The PFD altitude
alerter function will be restored. All autopilot functionality will be
restored. TAS, OAT, and wind calculations will be unavailable if ADC
2 is a AM-250.
3.
Execute RVSM contingency procedures for the following:
• Loss of one primary altimetry system.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 7 of 20
3.1.2 ADC 2 Failure
3.1.2.1 AM-250 as ADC 2
AM-250 failure is indicated as blank, “----,” or “FAIL” text in place of the
normal altitude readout on the AM-250 LCD. Automatic altitude control mode
will be inoperative if equipped with a KFC 275/325.
1.
Deselect ALT mode on the autopilot and maintain assigned altitude
manually or in conjunction with other autopilot modes by reference to
the PFD altimeter.
2.
Verify transponder source selection is ADC 1.
NOTE
If Transponder #1 is inoperative (per MEL), operate Transponder
#2 (if installed) without altitude reporting.
3.
Execute RVSM contingency procedures for the following:
• Loss of one primary altimetry system.
• Loss of all automatic altitude hold systems.
• Loss of altitude reporting (if Transponder #1 is inoperative).
3.1.2.2 GSU 75B or GDC 74B as ADC 2
GSU 75B/GDC74B failure is indicated by:
• Red X over airspeed and altitude tapes on Co-Pilot side
• Yellow X over vertical speed on Co-Pilot side
• TAS and OAT displays are dashed on Co-Pilot side
• White inverse video “IAS & ALT” on Pilot side
1.
Maintain assigned altitude with reference to Pilot side PFD altimeter.
2.
Select ADC 1 as the air data source by selecting ADC 1 on the Co-Pilot
PFD display (Menu→Sensors→ADC1).
3.
Execute RVSM contingency procedures for the following:
• Loss of one primary altimetry system.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 8 of 20
3.1.3 ADC 1 and ADC 2 Failure
ADC 1 and ADC 2 failures are indicated as described in procedures 3.1.1 and
3.1.2.
1.
Disconnect autopilot or select PIT and maintain assigned altitude
manually or in conjunction with the autopilot by reference to the
standby altimeter.
2.
Execute RVSM contingency procedures for the following:
• Loss of all primary altimetry systems.
• Loss of all automatic altitude hold systems.
• Loss of altitude alerting.
• Loss of altitude reporting.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 9 of 20
3.1.4 Difference in Primary Altimeters
If the primary altimeters (Pilot PFD and AM-250 or Co-Pilot PFD) differ by 200
feet or more, attempt to identify the incorrect primary altimeter.
WARNING
The standby altimeter uses the same static source as the ADC
2. The standby altimeter does not have static source error
correction applied and will therefore differ slightly from the
primary altimeters during normal operation. Do not use the
standby altimeter as the only means of determining the
incorrect altimeter.
1.
Verify all altimeters (both primary altimeters and standby) are set to the
correct altimeter setting (e.g 29.92 inHg).
2.
Attempt to identify the incorrect primary altimeter:
If the Pilot PFD altimeter (ADC 1) is determined to be incorrect:
• Perform procedure 3.1.1, ADC 1 Failure.
If the AM-250 or Co-Pilot PFD altimeter (ADC 2) is determined to be
incorrect:
• Perform procedure 3.1.2, ADC 2 Failure.
If unable to determine which primary altimeter is incorrect:
• Perform procedure 3.1.3, ADC 1 and ADC 2 Failure
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 10 of 20
3.1.5 PFD Failure (RVSM considerations)
WARNING
This procedure is to be performed in addition to the
PFD 1 Failure procedure in the basic G600 TXi AFMS. This
procedure only addresses RVSM considerations for PFD
failure.
In addition to the loss of flight instruments, PFD failure will result in the loss of
altitude alerting and Transponder #1 altitude reporting.
1.
Monitor AM-250 or Co-Pilot PFD altimeter to maintain assigned
altitude (using autopilot or manual control).
2.
Select Transponder #2 (if installed).
NOTE
If Transponder #2 is not installed or inoperative (per MEL),
continue to operate Transponder #1 without altitude reporting
(stop altitude squawk).
3.
Execute RVSM contingency procedures for the following:
• Loss of one primary altimetry system.
• Loss of altitude alerting.
• Loss of altitude reporting (if Transponder #2 is not installed or
inoperative).
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 11 of 20
3.2
Abnormal Procedures
3.2.1 Loss of Altitude Reporting
If loss of transponder altitude reporting is suspected or reported:
1.
Select other transponder for operation (if installed and operative).
If other transponder is not installed or inoperative (per MEL):
2.
Continue to operate installed/operative transponder without
altitude reporting (stop altitude squawk).
3.
Execute appropriate RVSM contingency procedure for loss of
altitude reporting.
3.2.2 Loss of Automatic Altitude Hold
If the autopilot altitude hold mode fails for any reason (e.g loss of attitude, servo
failure, or trim failure):
1.
Maintain assigned altitude manually or in conjunction with other
operative autopilot modes using available primary or standby
altimeters.
2.
Execute appropriate RVSM contingency procedure for loss of all
automatic altitude hold systems.
3.2.3 Loss of Altitude Alerting
NOTE
This procedure applies to loss of altitude alerting due to an
inability to select the desired altitude or loss of altitude alert
tones. Refer to PFD or ADC failure procedures for other
failure scenarios.
1.
Engage autopilot altitude hold mode at assigned altitude.
2.
Monitor primary altimeters while maintaining assigned altitude.
3.
Execute appropriate RVSM contingency procedure for loss of altitude
alerting.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 12 of 20
3.2.4 Difference Between Captured Altitude and Selected Altitude
1.
Verify all altimeters (both primary altimeters and standby) are set to
correct altimeter setting (e.g. 29.92 inHg).
2.
Refer to altitude trimming procedure in the TBM 700 AFM section
4.5.26 if equipped with KFC 275/325 autopilot system.
3.
If a difference in indicated altitude between the primary altimeters is
greater than 200 ft, or if the altitude trim procedure is ineffective at
restoring the aircraft to the selected altitude perform procedure 3.1.4
and/or 3.2.2 as appropriate.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 13 of 20
Section 4. NORMAL PROCEDURES
The normal procedures in this section are for RVSM flight operations and are in
addition to all other normal procedures specified in the basic AFM/POH or
applicable supplements.
4.1
Preflight Inspection
1. Visually inspect the static ports and the RVSM critical region for
damage or surface irregularities.
4.2
Before Takeoff
1. Select ADC 2 using the PFD (Menu→Sensors→ADC2).
a. Verify that PFD altitude matches AM-250 or Co-Pilot PFD
altitude.
b. Verify that PFD airspeed and vertical speed tapes are
indicating correctly (approximately zero).
4.3
2.
Select ADC 1 using the PFD (Menu→Sensors→ADC1).
3.
Check both primary altimeters and standby altimeter.
a. With all altimeters using the same altimeter setting, the
difference between the highest and lowest altimeter must not
exceed 80 feet.
Cruise
1. Set PFD altitude alerter to assigned altitude.
2.
Engage automatic altitude hold mode.
a. Refer to autopilot AFMS and basic G600 TXi AFMS for
autopilot and altitude preselect procedures.
3.
Cross-check altimeters.
a. Verify altimeter settings (e.g 29.92 inHg).
b. Note differences between primary and standby altimeters in
accordance with RVSM procedures.
NOTE
Difference between primary altimeters must be less than 200
feet.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 14 of 20
Section 5. PERFORMANCE
No change.
Section 6. WEIGHT AND BALANCE
No change.
AFMS, TBM 700/850 G600 TXi RVSM
FAA APPROVED
190-01717-B4 Rev. 2
Page 15 of 20
Section 7. DESCRIPTION
7.1 System Description
7.1.1 System Description: RVSM Architecture 1
Architecture 1 RVSM configuration consists of the following equipment:
•
•
•
•
•
•
•
GDU 700 or GDU 1060 Primary Flight Display (PFD)
GDC 74B or GSU 75B Air Data Computer (ADC 1)
GAD 43e adapter
AM-250 altimeter / air data computer (ADC 2)
KFC 275/325 autopilot system
Transponder 1
Transponder 2 (optional)
STANDBY
ALTIMETER
ALTITUDE
XPNDR 1
PILOT PFD GDU 700/1060
ADC 2
STANDBY
AIRSPEED
CO-PILOT
ALTIMETER
AM-250
ALTITUDE
XPNDR 2
(OPTIONAL)
ADC 1
GSU 75B/GDC 74B
ALT PRESELECT
SIGNALS
GAD 43e
ALT HOLD
OSCILLATOR
VS & ALT CAPTURE
ALT HOLD ENGAGE
KCP 220
AIR DATA &
ACCELERATIONS
TXi STC Equipment
Existing Equipment
KDC 222
Figure 7-1- RVSM Equipment Block Diagram: Arch. 1
7.1.2 System Description: Architecture 2
Architecture 2 RVSM configuration consists of the following equipment:
•
•
•
•
•
•
GDU 700 or GDU 1060 Primary Flight Display (PFD)
GDC 74B or GSU 75B Air Data Computer (ADC 1)
AM-250 altimeter / air data computer (ADC 2)
GFC 600 AFCS autopilot system
Transponder 1
Transponder 2 (optional)
AFMS, TBM 700/850 G600 TXi RVSM
190-01717-B4 Rev. 2
Page 16 of 20
STANDBY
ALTIMETER
PILOT PFD GDU 700/1060
ADC 2
STANDBY
AIRSPEED
CO-PILOT
ALTIMETER
AM-250
ALTITUDE
XPNDR 2
(OPTIONAL)
ALTITUDE
ADC 1
XPNDR 1
GSU 75B/GDC 74B
AIR DATA
& MODE ANNUN.
TXi STC Equipment
Existing Equipment
Other STC
Equipment
GMC 605
GSA 87 SERVOS
Figure 7-2: RVSM Equipment Block Diagram: Arch. 2
7.1.3 System Description: Architecture 3
Architecture 3 RVSM configuration consists of the following equipment:
•
•
•
•
•
•
•
GDU 700 or GDU 1060 Primary Flight Display (PFD) Pilot side
GSU 75B Air Data Computer (ADC 1)
GDU 700 or GDU 1060 Primary Flight Display (PFD) Co-Pilot Side
GSU 75B or GDC 74B Air Data Computer (ADC 2)
GFC 600 AFCS autopilot system
Transponder 1
Transponder 2 (optional)
AFMS, TBM 700/850 G600 TXi RVSM
190-01717-B4 Rev. 2
Page 17 of 20
STANDBY
ALTIMETER
PILOT PFD GDU 700/1060
HSDB
CROSSFILL
CO-PILOT PFD GDU 700/1060
STANDBY
AIRSPEED
ADC 1
ALTITUDE
GSU 75B
XPNDR 1
ALTITUDE
ADC 2
XPNDR 2
(OPTIONAL)
GSU 75B/GDC 74B
AIR DATA
& MODE ANNUN.
TXi STC Equipment
GMC 605
Existing Equipment
Other STC
Equipment
GSA 87 SERVOS
Figure 7-3: RVSM Equipment Block Diagram: Arch. 3
7.2 Pitot-Static System
The pitot-static instruments that are part of this RVSM configuration are
connected to the sources specified in the Table 2.
Table 2 – Pitot-Static System Connectivity
Instrument
Pitot Source
ADC 1 (GDC 74B or
Pitot 1
GSU 75B)
ADC 2 (AM-250) or
Pitot 2
ADC 2 (GSU 75B/GDC
74B)
Pilot’s Standby Altimeter
N/A
Pilot’s Standby Airspeed
Pitot 2
* Source is selected by the emergency static valve
Static Source
Static 1 / Emergency*
Static 2
Static 2
Static 2
The GSU 75B or GDC 74B, and the AM-250 have been modified with static
source error correction (SSEC) data at the time of installation. This data
corrects the pitot-static system for residual errors in the system. The standby
altimeter connected to Static 2 has not been corrected with SSEC.
Sources for other instruments are unchanged by this modification.
AFMS, TBM 700/850 G600 TXi RVSM
190-01717-B4 Rev. 2
Page 18 of 20
7.3 Transponder Altitude Sources
Transponder #1 receives altitude data from the G600 TXi PFD and will report
the pressure altitude from the source that is displayed on the PFD. In normal
operations, Transponder #1 will report the pressure altitude from ADC 1. If
ADC 2 is selected for display on the PFD, then Transponder #1 will report the
pressure altitude from ADC 2.
Transponder #2 (if installed) receives altitude data from the AM-250 (ADC 2) or
the Co-Pilot PFD if equipped. Transponder #2 will always report the pressure
altitude from ADC 2 if ADC 2 is an AM 250. If the aircraft is equipped with a
Co-Pilot PFD, Transponder #2 will report the pressure altitude from ADC 2. If
ADC 1 is selected for display on the Co-Pilot’s PFD, then Transponder #2 will
report the pressure altitude from ADC 1.
7.4 Automatic Altitude Control System
7.4.1 Aircraft Equipped with KFC 275/325
Automatic altitude control of the aircraft is performed by the retained KFC
275/325 autopilot and its associated components. The installation of the G600
TXi system replaces the KAS-297C altitude selector and the mechanical gyros
with the GDU 700P/1060 display, GSU 75B ADAHRS or GDC 74B ADC, and
the GAD 43e adapter. The GAD 43e adapter collects information from the
GDU 700P/1060 about altitude and vertical speed and transmits appropriate
information to the KCP-220 flight computer allowing altitude preselect and
capture to operate normally with digital ADC information from the GSU 75B or
GDC 74B. Upon reaching the selected altitude, the KCP-220 receives the
appropriate oscillator signal from the AM-250 RVSM certified altimeter on the
co-pilot side. The GAD 43e adapter cannot emulate the oscillator signal of the
AM-250. For this reason, an AM-250 (ADC 2) failure will render the automatic
altitude hold function of the autopilot inoperative.
7.4.2 Aircraft Equipped with GFC 600 AFCS
Automatic altitude control of the aircraft is performed by the GFC 600 AFCS
autopilot and its associated components. The GMC 605 mode controller receives
current altitude and rate information from the Pilot PFD over HSDB.
AFMS, TBM 700/850 G600 TXi RVSM
190-01717-B4 Rev. 2
Page 19 of 20
Section 8. HANDLING, SERVICING AND MAINTENANCE
Instructions for Continued Airworthiness are contained in Garmin document
number 190-01717-B1, Rev. 1 or later.
AFMS, TBM 700/850 G600 TXi RVSM
190-01717-B4 Rev. 2
Page 20 of 20
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