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TRANSCRIPT
1. G500H SYSTEM ARRANGEMENT SHOWN IS APPLICABLE TO BELL 206L, 206L-1, 206L-3, AND 206L-4 MODEL ROTORCRAFT.2. DIMENSIONS ARE IN INCHES UNLESS OTHERWISE NOTED.
WL59.5
FS21
9.6
WL70.1
FS24
3.0
FS32
.8
WL37.6
WL21.7
FS38
.6
WL43.3
FS60
.4
FS17
2.8
WL54.7
FS0.
0
WL0.0
FS1.
0
FS62
.0
FS83
.0
21.0
GDU 620 DISPLAY[SHEET 3]
GDC 74H AIR DATA COMPUTER[SHEET 4]
GRS 77H AHRS SECONDARY LOCATION[SHEET 5]
GTP 59 OAT PROBE[SHEET 7]
GRS 77H AHRSPRIMARY LOCATION [SHEET 5]
GMU 44 MAGNETOMETERPRIMARY LOCATION [SHEET 6]
GMU 44 MAGNETOMETERSECONDARY LOCATION [SHEET 6]
FIGURE 3 (C4 SHEET 1)
G500H SYSTEM OVERVIEW - SIDE VIEWSCALE 1:40
FIGURE 1 (D4 SHEET 1)
G500H SYSTEM OVERVIEW - TOP VIEWSCALE 1:40
BL10.3LH
BL2.5LH
BL0.0
BL18.6LH
BL6.3RH
WIRE HARNESS[SHEET 8]
FIGURE 2 (B7 SHEET 1)
G500H SYSTEM OVERVIEW - FRONT VIEWSCALE 1:40
WL21.7
WL37.6
WL43.3
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
DATE ECO NO.DESCRIPTIONREVZONE
REVISIONS
A
B
C
D
8 7 6 5 4 3 2 1
CONFIDENTIALThis drawing and the specifications contained herein are the property of Garmin Ltd. or its subsidiaries and may not be reproduced or used in whole or in part as the basis for manufacture or sale of products
without written permission.
TOLERANCE(UNLESS NOTED OTHERWISE)
.X ± .100
.XX ± .010
.XXX ± .005HOLES ± .003
.X ± .25
.XX ± .13HOLES ± .08
ANGLES ± 0.5°
DRAWN
CHECKED
PROJ. MGR.
RELEASED BY
TITLE
SIZE
SCALE
DWG. NO.
PART NO.
REV.
8 7 6 5 4 3 2 1
A
B
C
D
ADB
02/28/2010MKD
02/23/2010SGSBELL 206L ROTORCRAFT
1:40
02/23/2010
190-01150-421 8
2
RK
DER REVIEW REQUIRED
02/23/2010
-----INITIAL RELEASE 02/23/201070689CHANGED GMU 44 SECONDARY LOCATION 03/31/2010
12
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
NONE
190-01150-422 8
2
ITEMPART NUMBER WEIGHT (LB)
ARM (IN) [2] MOMENT ARM (IN-LB) [2]011-01264-50 [5] 6.38 246.3GDU 620 (Unit Only)
1
GDC 74H (Unit Only)
38.6ARM (IN) [2] MOMENT ARM (IN-LB) [2]
40.26.3
LONGITUDINAL [3] LATERAL [4]
Table 1: Weight and Balance Bell 206L [1][2]
[1] A ROTORCRAFT WEIGHT AND BALANCE IS REQUIRED AFTER INSTALLATION OF THE G500H SYSTEM. REFER TO STC INSTALLATION MANUAL P/N 190-01150-06 FOR ADDITIONAL INFORMATION, INCLUDING OVERALL SIZE AND CENTER OF GRAVITY LOCATION OF ALL LRUs.
[2] ARM AND MOMENT VALUES LISTED IN THIS TABLE ARE FOR REFERENCE ONLY. THE ARM AND MOMENTS MUST BE VERIFIED FOR EVERY INSTALLATION.
[3] THE LONGITUDINAL ARM IS MEASURED IN TERMS OF THE FUSELAGE STATION (FS) NUMBER.[4] THE LATERAL ARM IS MEASURED IN TERMS OF THE BUTT LINE (BL). THE CENTERLINE OF THE HELICOPTER IS BL0.00. THE MOMENT ARMS TO
THE LEFT SIDE (LOOKING FORWARD) ARE NEGATIVE (-) AND THE MOMENT ARMS TO THE RIGHT SIDE ARE POSITIVE (+).[5] EITHER 011-01264-50 OR 011-01264-60 UNITS ARE ACCEPTABLE.[6] GRS 77H UNIT MAYBE INSTALLED UNDER EITHER PILOT OR CO-PILOT SEAT. CO-PILOT SEAT MOMENT ARM SHOWN.
011-00882-11 1.702
55.832.8 0.00.0
GRS 77H (Unit Only) [Primary Location] 011-00868-20
3
172.8 -28.8-10.3
011-01264-50 [5] 7.04 271.7GDU 620 (Installed with rack and connector) 38.6 44.46.3
GDC 74H (Installed with connector) 011-00882-11 1.92 63.032.8 0.00.02.80 483.8
GRS 77H (Installed with rack and connector) [Primary Location] 011-00868-20 172.8 -35.6-10.33.46 597.9
GMU 44 (Unit Only) [Primary Location] 011-00870-10
4
219.60.35 76.9GMU 44 (Installed with rack and connector) [Primary Location] 011-00870-10 219.60.50 109.8
0.00.00.00.0
GMU 44 (Unit Only) [Secondary Location] 011-00870-10 243.00.35 85.1GMU 44 (Installed with rack and connector) [Secondary Location] 011-00870-10 243.00.50 121.5
-0.9-2.5-1.3-2.5
GRS 77H (Unit Only) [Secondary Location] 011-00868-20 60.4 -52.1-18.6 [6]2.80 169.1GRS 77H (Installed with rack and connector) [Secondary Location] 011-00868-20 60.4 -64.4-18.6 [6]3.46 209.0
011-00978-00 -5 -- --GTP 59 (Installed with connector)
109
45678
301302
33002
100 FEET
180200
160
140120 100
4020
AIRSPEED
KNOTS 80
6010
2010
20
20
2010
10
63
N33
30
W 2421
S15
12
E
TURBINE
percent
010
20
30
40
5060 70
80
90
100
110120
HOOK LOADd.c. voltage
davtron
510 15
20
0
510 15
20
VERTICALSPEED
PER MIN100 FEET
UP
DN
5040
3020
10
0 100
9080
70
60
torque
percent
temp
13
5 6
7
89
turbout
gasproducer
010
20
30
40
5060
70
809090
chronometer
davtron
ENGOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
xmsnOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
fuel
qty
e
25 50
75
gals
load fuel
0
5
10
0
12
X10
P dc psi p
3
hobbsquartz
flight hours
min2
d.c.elec.
L R
BARO
V/S
ALT
CRS
HDG
ENT
CLR
MENU
DFLT
RNG
109
45678
301302
33002
100 FEET
180200
160
140120 100
4020
AIRSPEED
KNOTS 80
60
0
10
20
30
40
50607080
90
100
110
120
1
2
3
4
5
%RPMROTORRPM 100
R
HOOK LOADX 10
SetupUN-ZERO ZERO
load fuel
0
5
10
0
12
X10
P dc psi p
3D.C. VOLTAGE
DAVTRONM450
gasproducer
010
20
30
40
5060
70
809090
fuel
qty
e
25 50
75
gals
temp
13
5 6
7
89
turbout
ENGOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
xmsnOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
5040
3020
10
0 100
9080
70
60
torque
percent
chronometer
davtron
hobbsquartz
flight hours
D.C. VOLTAGE
DAVTRONM450
chronometer
davtron
109
45678
301302
33002
100 FEET
180200
160
140120 100
4020
AIRSPEED
KNOTS 80
6010
2010
20
20
2010
10
63
N33
30
W 2421
S15
12
E
TURBINE
percent
010
20
30
40
5060 70
80
90
100
110120
510 15
20
0
510 15
20
VERTICALSPEED
PER MIN100 FEET
UP
DN
5040
3020
10
0 100
9080
70
60
torque
percent
temp
13
5 6
7
89
turbout
gasproducer
010
20
30
40
5060
70
809090
chronometer
davtron
ENGOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
xmsnOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
fuel
qty
e
25 50
75
gals
load fuel
0
5
10
0
12
X10
P dc psi p
3
min2
d.c.elec.
L R
10
2010
20
20
2010
10
63
N33
30
W 2421
S15
12
E
109
45678
301302
33002
100 FEET
180200
160
140120 100
4020
AIRSPEED
KNOTS 80
60
63
N33
30
W 2421
S15
12
E
TURBINE
percent
010
20
30
40
5060 70
80
90
100
110120
5040
3020
10
0 100
9080
7060
torque
percent
temp
13
5 6
7
89
turbout
gasproducer
010
20
30
40
5060
70
809090
chronometer
davtron
ENGOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
xmsnOIL
0
5
10
15
0
5
10
15
X10
P PSI C T
fuel
qty
e
25 50
75
gals
load fuel
0
5
10
0
12
X10
P dc psi p
3
CDI OBS MSG FPL PROCVNAV
C
V
C
D
MENU
CLR
ENT
NAVDEFAULT
RNG
V
PUSHC/V
PUSHCRSR
VLOCCOM
VOLID
PUSH
SQPUSHVOL
PWR
GNS 530
CDI OBS MSG FPL PROCVNAV
C
V
C
D
MENU
CLR
ENT
NAVDEFAULT
RNG
V
PUSHC/V
PUSHCRSR
VLOCCOM
VOLID
PUSH
SQPUSHVOL
PWR
GNS 530
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
1:40
190-01150-423 8
2
FS0.
0
FS38
.6
WL0.0
WL43.3
FIGURE 4 [D6 SHEET 3]
GDU 620 LOCATION - SIDE VIEWSCALE 1:40
FIGURE 5 [D2 SHEET 3]
EXAMPLE - WIDE INSTRUMENT PANEL LAYOUT
SCALE 1:8ORIGINAL CONFIGURATION AND GDU 620 INSTALLED
FIGURE 6 [B2 SHEET 3]
EXAMPLE - INSTRUMENT PANEL LAYOUT
SCALE 1:8ORIGINAL CONFIGURATION AND GDU 620 INSTALLED
GDU 620 UNIT
SYS - AIRFRAME CONFIG (AIRSPEEDS):VS0 0
Table 2: System Configuration Settings
VS1 0VFE 0VNO 130
GLIDE 0
GDC - FILTERING TIME CONSTANTSGDU AIRSPEED
0.9000.600LOW
HIGH
GDU AIRSPEED TRANS TO
25 KTS20 KTSLOW
HIGH
GDU VERTICAL SPEED 1.35
VR 0VX 0VY 57VLE OFFVMCA OFFVYSE 100
VNE 130
1. LOCATE GDU 620 UNIT ON THE INSTRUMENT PANEL. REFER TO STC INSTALLATION MANUAL, P/N 190-01150-06 FOR UNIT MOUNTING CONSIDERATIONS, AND TO 190-01150-43 INSTALLATION, G500H SYSTEM, BELL 206L ROTORCRAFT DRAWING FOR DETAILS.
2. GDU 620 WEIGHT AND BALANCE VALUES LISTED IN TABLE 1 MUST BE ADJUSTED FOR ANY WEIGHT AND LOCATION CHANGES.3. GDU 620 UNIT MUST BE ELECTRICALLY BONDED TO ROTORCRAFT METALLIC STRUCTURE. REFER TO 190-01150-43 INSTALLATION, G500H
SYSTEM, BELL 206L ROTORCRAFT DRAWING FOR DETAILS.4. UPON COMPLETION OF THE G500H SYSTEM INSTALLATION, GDU 620 HAS TO BE CONFIGURED USING SYSTEM CONFIGURATION SETTINGS
DEFINED IN TABLE 2.5. DIMENSIONS ARE IN INCHES UNLESS OTHERWISE NOTED.
A
DETAIL A [B4 SHEET 3]
GDU 620 LOCATION DETAILSCALE 1:10
VNE (Power Off) 0
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
1:40
190-01150-424 8
2
FS0.
0
FS32
.8
WL0.0
WL37.6
B
1. LOCATE GDC 74H UNIT ON TOP OF SUPPORTING STRUCTURE FORWARD OF THE INSTRUMENT PANEL. REFER TO 190-01150-43 INSTALLATION, G500H SYSTEM, BELL 206L ROTORCRAFT DRAWING FOR DETAILS.
2. GDC 74H UNIT MUST BE ELECTRICALLY BONDED TO ROTORCRAFT METALLIC STRUCTURE.3. GDC 74H UNIT LOCATION REQUIRES FABRICATION OF A SUPPORT BRACKET. 4. GDC 74H WEIGHT AND BALANCE VALUES LISTED IN TABLE 1 MUST BE ADJUSTED FOR ANY WEIGHT AND LOCATION CHANGES.5. DIMENSIONS ARE IN INCHES UNLESS OTHERWISE NOTED.
GDC 74H UNIT
REF. ENGINE INSTRUMENTSHYDRAULIC FITTINGS
REF. INSTRUMENT PANEL SUPPORTSTRUCTURE/CENTER CONSOLE
FIGURE 7 [D6 SHEET 4]
GDC 74H LOCATION - SIDE VIEWSCALE 1:40
DETAIL B [B4 SHEET 4]
GDC 74H LOCATIONSCALE 1:10
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
1:40
190-01150-425 8
2
1. GRS 77H UNIT MUST BE ELECTRICALLY BONDED TO ROTORCRAFT METALLIC STRUCTURE.2. GRS 77H UNIT MUST BE MOUNTED RIGIDLY TO THE ROTORCRAFT PRIMARY STRUCTURE. REFER TO STC INSTALLATION MANUAL, P/N 190-01150-06 FOR UNIT
MOUNTING CONSIDERATIONS.3. PRIMARY GRS 77H UNIT LOCATION REQUIRES FABRICATION OF A SUPPORTING STRUCTURE. REFER TO 190-01150-43 INSTALLATION, G500H SYSTEM, BELL 206L
ROTORCRAFT DRAWING FOR DETAILS.4. SECONDARY GRS 77H UNIT LOCATION MAY REQUIRE FABRICATION OF AN ADAPTER BRACKET AND/OR INSTALLATION OF POTTED INSERTS PER BELL STRUCTURAL
REPAIR MANUAL BHT-206-SRM-1.5. GRS 77H WEIGHT AND BALANCE VALUES LISTED IN TABLE 1 MUST BE ADJUSTED FOR ANY WEIGHT AND LOCATION CHANGES.6. DIMENSIONS ARE IN INCHES UNLESS OTHERWISE NOTED.
FIGURE 8 [D5 SHEET 5]
GRS 77H LOCATION - SIDE VIEWSCALE 1:40
FS0.
0
FS60
.4
FS17
2.6
WL0.0
WL21.7
WL54.7
C
D
DETAIL C [B7 SHEET 5]
GRS 77H SECONDARY LOCATIONSCALE 1:12
DETAIL D [B2 SHEET 5]
GRS 77H PRIMARY LOCATIONSCALE 1:12
REF. FABRICATED BRACKET SUPPORTSTRUCTURE [MAY INCLUDE 115-00922-00 TOP BRACKETAND 115-00909-00 ANGLE BRACKET (2X), PARTS OF GRS 77H UNIVERSAL MOUNT,GARMIN P/N 011-01780-00]
FUSELAGE FRAMEFS167.33 REF.
FUSELAGE FRAMEFS179.66 REF.
GRS 77H UNIT
REF. CO-PILOT SEATSUPPORT STRUCTURE
GRS 77H UNIT
GRS 77H AHRSSECONDARY LOCATION
GRS 77H AHRSPRIMARY LOCATION
1. LOCATE GMU 44 UNIT CHOOSING PRIMARY OR SECONDARY LOCATION. REFER TO STC INSTALLATION MANUAL, P/N 190-01150-06 FOR UNIT MOUNTING CONSIDERATIONS. REFER TO 190-01150-43 INSTALLATION, G500H SYSTEM, BELL 206L ROTORCRAFT DRAWING FOR DETAILS.
2. GMU 44 UNIT MUST BE ELECTRICALLY BONDED TO ROTORCRAFT METALLIC STRUCTURE.3. PRIMARY GMU 44 UNIT LOCATION REQUIRES FABRICATION OF A SUPPORT BRACKET FOR ATTACHING GMU 44 UNIVERSAL MOUNT, GARMIN
P/N 011-01779-01.4. SECONDARY GMU 44 UNIT LOCATION REQUIRES FABRICATION OF A MOUNTING BRACKET. 5. GMU 44 WEIGHT AND BALANCE VALUES LISTED IN TABLE 1 MUST BE ADJUSTED FOR ANY WEIGHT AND LOCATION CHANGES.6. DIMENSIONS ARE IN INCHES UNLESS OTHERWISE NOTED.
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
1:40
190-01150-426 8
2
TAILBOOM FRAMEBS42.59 REF.
REF. GMU 44 MOUNTING BRACKET[FABRICATED]
REF. GMU 44 UNIT
FRAME FS 217.84 REF.
REF. GMU 44 UNIT
REF. GMU 44 MOUNTING PLATE[FABRICATED]
REF. GMU 44 UNIVERSAL MOUNTGARMIN P/N 011-01779-01
FS0.
0
FS21
9.6
FS24
3.0
WL0.0
WL20.6
WL59.5
WL70.1
GMU 44 MAGNETOMETERPRIMARY LOCATION
GMU 44 MAGNETOMETERSECONDARY LOCATION
FIGURE 9 [D5 SHEET 6]
GMU 44 INSTALLATION LOCATION
SCALE 1:40SIDE VIEW
EF
DETAIL E [B7 SHEET 6]
GMU 44 PRIMARY LOCATIONSCALE 1:10
DETAIL F [B3 SHEET 6]
GMU 44 SECONDARY LOCATIONSCALE 1:10
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
1:40
190-01150-427 8
2
FS0.
0
FS62
.0
FS83
.0
FS1.
0
WL0.021.0
G H
1. LOCATE GTP 59 OUTSIDE TEMPERATURE PROBE ON THE BOTTOM OF A ROTORCRAFT FUSELAGE. PROBE LOCATION MAY VARY WITHIN INDICATED AREA. GTP 59 SHOULD BE KEPT AWAY FROM HEAT SOURCES. REFER TO 190-01150-43 INSTALLATION, G500H SYSTEM, BELL 206 L ROTORCRAFT DRAWING FOR DETAILS.
2. GTP 59 TEMPERATURE PROBE MUST BE ELECTRICALLY BONDED. 3. GTP 59 TEMPERATURE PROBE LOCATION MAY REQUIRE FABRICATION OF A DOUBLER.4. DIMENSIONS ARE IN INCHES UNLESS OTHERWISE NOTED.
1 FIGURE 10 [D6 SHEET 7]
GTP 59 OAT PROBE LOCATION - SIDE VIEWSCALE 1:40
DETAIL G [B6 SHEET 7]
GTP 59 OAT PROBE - NEW INSTALLATIONSCALE 1:1
DETAIL H [B3 SHEET 7]
GTP 59 OAT PROBE - INSTALLATION IN COVER PLATESCALE 1:1
FS69.8 REF.
OAT PROBE SUPPORTDOUBLER
GTP 59 OAT PROBE
FS81.5 REF.
EXISTING ANTENNACOVER PLATE REF.
GTP 59 OAT PROBE
FIGURE 12 (B4 SHEET 8]
WIRE HARNESS ROUTING - SIDE VIEWSCALE: NONE
FIGURE 11 (B4 SHEET 8]
WIRE HARNESS ROUTING - TOP VIEWSCALE: NONE
NOTES:1. REFER TO 190-01150-43 INSTALLATION, G500H SYSTEM, BELL 206 L ROTORCRAFT DRAWING FOR DETAILS OF WIRE
HARNESS FABRICATION, ROUTING, AND INSTALLATION.
GTP 59 OAT PROBE TYP.GRS 77H AHRSSECONDARY LOCATION
GDU 620 DISPLAY
GDC 74H AIRDATA COMPUTER
GRS 77H AHRSPRIMARY LOCATIONREF: 005-W0222-00, P771
GMU 44 MAGNETOMETERPRIMARY LOCATION
GMU 44MAGNETOMETERSECONDARYLOCATION
OVERHEAD CB PANEL
GDC 74H AIR DATA COMPUTERREF: 005-W0222-00, P741
GMU 44 MAGNETOMETERSECONDARY LOCATIONREF: 005-W0222-00, P441
GDU 620 DISPLAYREF: 005-W0222-00,P6201, P6202, P6203
GRS 77H AHRS PRIMARY LOCATIONREF: 005-W0222-00, P771
GRS 77H AHRSSECONDARY LOCATIONREF: 005-W0222-00, P771
GTP 59 OAT PROBE TYP.REF: 005-W0222-00
GMU 44 MAGNETOMETERPRIMARY LOCATIONREF: 005-W0222-00, P441
GTP 59 OAT PROBEDISCONNECT JG01/PG01
(OPTIONAL)
FS 1
79.7
FS 1
67.3
FS 2
41.9
FS 0
.0
WL 0.0
FS 1
92.0
FS 2
04.9
FS 2
17.8 IND
FUEL
RIGHT
QTY
VALVE TEMP
ENG GOV
OVSP CONT IGNTR
ENGINE
START
PITOT DEFOG
& ATT HEAT BLOWER
OFF
BAT
O
GEN
HEAT
OFF
COLL LT
OFF
POS LT
OFF
ANTIOFF BRT
INST LT
FF
IND
GEN
FIELD
GEN
RESET
IND
ENG PAR
SEP PRG
AUX
RECP
PASS
MIKEHAND
CONTCUTPOWER
CARGOCABIN LT
ENC
TURN
ADCAHRS
SYSTEM
LDG INST COCKPITCAUTION
TOT
IND
BOOST
LEFT
XMSN
TEMP
ANTI-ICING
DIR GYRO PITOT DEFOG
& ATT HEAT BLOWER
OFF
BAT
O
GEN
VENT
HEATCOLL LT
OFF
POS LT
OFF
ANTIOFF BRT
INST LT
FF
IND
START
GEN
FIELD
GEN
RESET
INDPRESS
ENG
HOOK
HANDHOISTCABLEHOIST
INDCUTPOWER
HTR
OFF
AHRSPFD NAV COM
LIGHTS
HYDR
XPNDR AUDIO
ALT
R
OFSHT.
B
Garmin Ltd. or its subsidiariesc/o Garmin International, Inc.
1200 E. 151st StreetOlathe, Kansas 66062 U.S.A.
SIZE
SCALE
DWG. NO.
PART NO.
REV.
A
B
C
D
8 7 6 5 4 3 2 1
8 7 6 5 4 3 2 1
A
B
C
D
NONE
190-01150-428 8
2