IIN-D350-794
~ART
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AEROSPACE
DART AEROSPACE LTD.
1270 Aberdeen Street
Hawkesbury, ON, K6A 1K7
CANADA
Tel: 1 6136325200
Fax: 1 613 632 5246
e-mail: heli@dartaero.com
http://www.dartaero.com
INSTAllATION
INSTRUCTIONS
IIN-D350-794
Auxiliary Fuel Tank
AIRBUS AS 350 AND EC130 MODELS
CANADA
DEPARTMENT OF TRANSPORT
AIRCRAFT CERTIFICATION
BRANCH
DAO # 01-0-01
Prepared By:
M. Lee
esigner
Mechanic
BY:
' •
~
D. SHEPH
DATE:
CERT, NO.:
ISSUE NO.:
THIS OOCUMENT
Checked By:
H. Siemens
RD (DE # 02)
14.08.25
SH05-4
3
___
~~Signer
Released By:
D. Shepherd
Chief Engineer
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTO,
OR COPIED
Revision: G
Date: 14.08.20
DART AEROSPACE LTD.
IIN-D350-794
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Revision Record
Revision
A
B
C
Issue
Date
09.06.22
09.12.08
10.01.25
D
E
11.10.24
12.04.13
F
13.08.15
G
14.08.20
Description
New Issue
Changed placards from JCA to Dart part numbers.
Replace all remaining JCA part numbers with Dart part
numbers
Add D350-794-111/-141 and D130-794-121 Kits
Update weight & balance per DSI 9577, revise sections 3.8.2
and 3.9.3.
Update parts list to describe D4022-5 as part of the D4022041 pump assembly, ref. CAR13-80.
Incorperated DSI 9672
Revised section 1.0
Updated Weight & Balance and Parts List
 COPYRIGHT  2009 BY DART AEROSPACE LTD 
THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision: G
Date: 14.08.20
DART AEROSPACE LTD.
IIN-D350-794
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Table of Contents
1.0 INTRODUCTION ................................................................................................................................ 4 2.0 GENERAL NOTES ............................................................................................................................ 5 3.0 INSTALLATION PROCEDURE ......................................................................................................... 5 3.1 3.2 3.3 3.4 3.5 3.6 3.7 3.8 3.9 3.10 3.11 3.12 3.13 3.14 3.15 3.16 PREPARATION ............................................................................................................................... 5 FORWARD RESTRAINT BEAM INSTALLATION (EC 130 ONLY) ........................................................... 6 FORWARD FLOOR GUTTER (AS 350 AND EC 130) ......................................................................... 7 FUEL PUMP AND PIPE INSTALLATION (AS 350 AND EC 130) ......................................................... 10 LOCATING ANGLES (AS 350 ONLY) ............................................................................................. 11 LOCATING ANGLES (EC 130 ONLY) ............................................................................................. 11 TOP HOLD DOWN ANCHOR POINT (AS 350 AND EC 130) ............................................................. 14 VERTICAL RESTRAINT (AS 350 ONLY) ......................................................................................... 15 VERTICAL RESTRAINT (EC 130 ONLY) ......................................................................................... 17 FUEL TRANSFER HOSE (AS 350 AND EC 130) ............................................................................. 19 VENT SYSTEM (AS 350 AND EC 130) .......................................................................................... 20 SEALING LOCKER FLOOR (AS 350 AND EC 130) ......................................................................... 22 ELECTRICAL AND GAUGE INSTALLATION (AS 350 AND EC 130) .................................................... 23 FINAL INSTALLATION (AS 350 AND EC 130)................................................................................. 24 FUEL QUANTITY GAUGE SETUP (AS 350 AND EC 130)................................................................. 26 FUEL QUANTITY ERROR MESSAGES AND FAULT RESOLUTION (AS 350 AND EC 130) .................... 27 4.0 ELECTRICAL LOAD ....................................................................................................................... 32 5.0 WEIGHT AND BALANCE ............................................................................................................... 32 6.0 PARTS LIST .................................................................................................................................... 33  COPYRIGHT  2009 BY DART AEROSPACE LTD 
THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision: G
Date: 14.08.20
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IIN-D350-794
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1.0
INTRODUCTION
These instructions cover the installation of the Dart D350-794-011/-013/-111 and D130-794-021/-023/121 Aux Fuel Tank Kits for the Airbus AS 350 and EC130 series aircraft.
The D350-794-011 Aux Fuel Tank Kit provides the necessary parts to install the D350-794-041 auxiliary
fuel tank into the left side locker compartment of the AS 350 series aircraft.
(Superseded by D350-794-111 Tank Design)
The D130-794-021 Aux Fuel Tank Kit provides the parts necessary to install the D350-794-041 auxiliary
fuel tank into the left side locker compartment of the EC 130 B4 series aircraft.
(Superseded by D350-794-121 Tank Design)
The D350-794-111 Aux Fuel Tank Kit provides the necessary parts to install the D350-794-141 auxiliary
fuel tank into the left side locker compartment of the AS 350 series aircraft.
The D130-794-121 Aux Fuel Tank Kit provides the parts necessary to install the D350-794-141 auxiliary
fuel tank into the left side locker compartment of the EC 130 B4 series aircraft.
The D350-794-041 auxiliary fuel tank is the original flat bottomed tank assembly that is applicable to both
AS 350 and EC 130 models. The D350-794-141 auxiliary fuel tank is an improved version of the tank
that includes sediment bowls in the forward and aft ends for collecting water and debris from the fuel, but
is still compatible with AS 350 and EC 130 models. The installation procedure, maintenance instructions
and operating limitations and procedures are the same for the D350-794-041 and D350-794-141 tanks.
All kits provide extra fuel which can be transferred to the main aircraft fuel tank as desired by the pilot to
extend range and provide mission flexibility. The installation of the side locker auxiliary fuel tank kits are
shown in Figure 1.
Figure 1 – D350-794-041/-141 Auxiliary Fuel Tank
 COPYRIGHT  2009 BY DART AEROSPACE LTD 
THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision: G
Date: 14.08.20
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IIN-D350-794
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2.0 GENERAL NOTES
COMPATIBILITY
Compatibility of this installation with the aircraft is the responsibility of the installer. Ensure that this
installation does not conflict with a previous modification.
WORKMANSHIP
Unless otherwise stated, all workmanship should be to the standards set by the Aircraft Maintenance
Manual.
CONTINUING AIRWORTHINESS
This installation should be maintained in accordance with Instructions for Continued Airworthiness
ICA-D350-794.
FASTENER TORQUE
Fastener torques are as follows unless otherwise specified.
Table 1 – Fastener Torque
Size
8-32
3/16”
1/4”
5/16”
3/8”
Torque
12-15 in-lbs
1.4-1.7 N-m
20-25 in-lbs
2.3-2.8 N-m
50-70 in-lbs
5.6-7.9 N-m
100-140 in-lbs
11.3-15.8 N-m
160-190 in-lbs
18.1-21.5 N-m
ADDITIONAL DRAWINGS
These instructions should be used in conjunction with the following drawings:
- D350-794-001 (AS 350) Installation Drawing,
- D130-794-002 (EC 130) Installation Drawing,
- D350-794-901 Wiring Drawing
3.0 INSTALLATION PROCEDURE
3.1
Preparation
Refer to the Aircraft Maintenance Manual and proceed as follows;
3.1.1
Ensure all systems are turned off.
3.1.2
When disconnecting and/or removing equipment and panels, retain all hardware.
3.1.3
Disconnect the battery and ground the aircraft. Ensure that electrical power is not applied.
Provide access to left hand side locker, under belly and instrument console. Remove lower belly
cowling. Remove left side locker door. Remove shrouding around the fuel tank filler neck.
Remove the left hand side locker wall paneling.
3.1.4
If, on installation, a universal rivet head securing non-structural components is obstructing the
fitment, a countersunk rivet should be substituted for the existing rivet.
 COPYRIGHT  2009 BY DART AEROSPACE LTD 
THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision: G
Date: 14.08.20
DART AEROSPACE LTD.
IIN-D350-794
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3.2
Forward Restraint Beam Installation (EC 130 Only)
3.2.1
Install the forward restraint beam p/n D4005-3 with angles p/n D4005-5, D4005-7 and D4005-9 to
the forward bulkhead in the left hand side locker. Use solid or cherry rivets where specified on
drawing. See Figure 2A and 2B.
D4005-3
Figure 2A – Bottom Forward Restraint Beam
(EC 130 B4 Only)
D4005-3
Figure 2B – Top Forward Restraint Beam
(EC 130 B4 Only)
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
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IIN-D350-794
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3.3
Forward Floor Gutter (AS 350 and EC 130)
3.3.1
Place fuel tank in position and push forward. Mark forward edge.
3.3.2
Remove tank, locate and install forward floor gutter p/n D4005-041 with forward flange 0.2” (5
mm) forward of tank position. It is necessary to cut Ø0.625” (Ø15.9 mm) hole through the floor
for the AS 350 and through the existing rubber boot for the EC 130 B4 to allow drain tube to
protrude through locker floor.
3.3.3
Any rivet heads obstructing forward floor gutter should be converted to countersunk rivets to
allow gutter to sit flush. Use a 0.032” packer if necessary. Trim outer length of gutter to fit inside
locker door by 0.2” (5 mm) on the AS 350 models per drawing D350-794-001 Sheet 3. Trim
outer length of gutter to fit inside the raised flange of the locker edge on the EC 130 B4 models
per drawing D130-794-002 Sheet 3.
3.3.4
Use Pro-seal PR 1422 B1/2 sealant to seal all edges of forward floor gutter. See Figure 3A and
3B.
3.3.5
Cut a slot in side panel to go over the forward floor gutter.
D4005-041
Figure 3A – Forward Floor Gutter Installation
(AS 350)
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
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D4005-041
Figure 3B – Forward Floor Gutter
(EC 130 B4)
3.3.6
Install drain hose p/n D4063-1 with hose clamp p/n 2000-6s and attach per drawing D350-794001 Sheet 2 and D130-794-002 Sheet 2.
3.3.7
Allow drain hose to protrude below lower cowling by 2.36” (60 mm). Cut lower end of hose at 45°
facing away from airflow.
3.3.8
On EC 130 B4 models, use existing tooling hole in rib to install “P” clamp and cut Ø0.79” (20 mm)
hole in the rear edge of the cowling for the hose to pass through. See Figure 3C.
3.3.9
On AS 350 models, the hose passes to the rear of the cross tube and it is necessary to drill a
Ø0.79” (20 mm) hole in the transverse rib 4.53” (115 mm) out from the cabin structural beam and
0.59” (15 mm) up from the rib lower flange. See Figure 3D.
 COPYRIGHT  2009 BY DART AEROSPACE LTD 
THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
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Date: 14.08.20
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Figure 3C – Forward Drain Installation
(EC 130 B4)
Figure 3D – Forward Drain Installation
(AS 350)
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
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Date: 14.08.20
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3.4
Fuel Pump and Pipe Installation (AS 350 and EC 130)
3.4.1
Drill a Ø0.625” (Ø15.9 mm) hole 5.98” (152 mm) up and 1.69” (43 mm) forward of the side locker
rear bulkhead as shown in drawing D350-794-001 Sheet 4 (AS 350) and D130-794-002 Sheet 4
(EC 130). Install bulkhead fitting AN832-6D in hole. See Figure 4A.
3.4.2
Cut Ø1.57” (40 mm) hole in the removable side panel to go around bulkhead fitting. Panel is
reused when auxiliary tank is not in use.
3.4.3
The fuel pump is supplied as an assembly including mounting bracket p/n D4022-3 and wiring
loom.
3.4.4
Install fuel pump inlet tube p/n D4003-047 from bulkhead fitting to pump inlet to assist in
positioning fuel pump assembly per drawing D350-794-001 Sheet 4 (AS 350) and D130-794-002
Sheet 4 (EC 130).
3.4.5
Support the weight of the pump in a horizontal position and transfer drill 2x Ø0.191 (#11 drill,
Ø4.85 mm) holes from the fuel pump to the bulkhead per drawing D350-794-001 Sheet 4 (AS
350) and D130-794-002 Sheet 4 (EC 130). Mount fuel pump with 2x AN3-4A bolts, MS21042-3
nuts, and AN970-3 washers. The AN970-3 washers are installed on the aft side of the bulkhead.
3.4.6
Install fuel splash guard p/n D4008-043 over the fuel pump. See drawing D350-794-001 Sheet 4
(AS 350) and D130-794-002 Sheet 4 (EC 130) for details. Pickup on four anchor nuts with
AN525-10R6 screws.
Aux Fuel Pump
AN832-6D
Bulkhead Fitting
Cannon Plug
Figure 4A – Pump/Bulkhead Fitting Installation
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
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3.5
Locating Angles (AS 350 Only)
3.5.1
Reference drawing D350-794-001 Sheet 2 and 3. Place fuel tank in position. Push firmly
forward and inboard. Mark position of side restraint angle p/n D4004-041 and rear restraint
angle/gutter p/n D4005-1. Rear restraint angle needs to be trimmed off to fit inside locker door by
0.2” (5 mm). See Figures 5A and 5B.
3.5.2
Side restraint angle p/n D4004-041 is to be located 17.5” ± 0.4” (445 mm ± 10 mm) aft of the
forward bulkhead. Use angle as drilling template for holes.
3.5.3
Remove tank. Attach rear restraint angle/gutter p/n D4005-1 with eight (8) countersunk rivets,
use 0.032” packer as necessary. Attach side restraint angle with nine (9) CR3213-4 cherry rivets
and attach bottom strap attach bracket p/n D4004-5 with five (5) CR3213-5 cherry rivets which
pass through the lower restraint angle and locker floor per drawing D350-794-001 Sheet 3.
3.6
Locating Angles (EC 130 Only)
3.6.1
Reference drawing D130-794-002 Sheet 2 and 3. Place fuel tank in position. Push firmly
forward and inboard. Mark position of side restraint angle p/n D4004-043 and rear restraint
angle/gutter p/n D4005-1. Rear restraint angle needs to be trimmed to fit inside raised flange.
See Figure 6.
3.6.2
Side restraint angle p/n D4004-043 is to be located 17.5” ± 0.4” (445 mm ± 10 mm) aft of the
forward bulkhead.
3.6.3
When installing the side restraint angle it is necessary to pick up on the existing rivets in the floor
starting 17.5” (445 mm) from the forward wall. Two (2) of these rivets will need to be countersunk
to allow the bottom strap attach bracket to seat in position. Refer to drawing D130-794-002
Sheet 3.
3.6.4
Remove tank. Attach rear restraint angle/gutter p/n D4005-1 with eight (8) countersunk rivets,
use 0.032” packer as necessary.
3.6.5
Attach side restraint angle with ten (10) CR3213-4 cherry rivets and attach bottom strap attach
bracket p/n D4004-5 with five (5) CR3213-5 cherry rivets which pass through the lower restraint
angle and locker floor per drawing D130-794-002 Sheet 3.
 COPYRIGHT  2009 BY DART AEROSPACE LTD 
THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
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Date: 14.08.20
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D4005-1
Figure 5A – Rear Gutter Installation
(EC 130 Shown, AS 350 Similar)
D4004-041
D4004-5
Figure 5B – Lower Hold Down Point
(AS 350 Only)
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
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D4004-043
D4004-5
Figure 6 – Lower Tie Down Point
(EC 130 Only)
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3.7
Top Hold Down Anchor Point (AS 350 and EC 130)
3.7.1
Remove the tank.
3.7.2
Install the top strap bracket p/n D4004-11 with three (3) MS24694-S50 screws, MS21042-3 nuts
and NAS1149F0363P washers provided. The forward edge of the track to be 1.26” (32 mm) aft
of the transverse rib and 1.57” (40 mm) down from the deck skin. Refer to drawing D350-794001 Sheet 2 (AS 350) and D130-794-002 Sheet 2 (EC 130). See Figure 7.
D4004-11
Figure 7 – Top Hold Down Anchor Point
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3.8
Vertical Restraint (AS 350 Only)
3.8.1
With the tank removed, drill out a minimum of ten (10) rivets on existing bracket on transmission
deck at the base of the support tube from the cabin rear wall. Locate and rivet in top support
bracket p/n D4007-3 with four (4) MS20470AD4 rivets through existing rib and a minimum of
eight (8) MS20470AD5 rivets through the original bracket and top support bracket using vacated
rivet holes. Refer to drawing D350-794-001 Sheet 3. Refer to Figure 8A.
3.8.2
With tank in position and strapped in with strap p/n D4024-041, install top support bracket
assembly p/n D4006-041 by match drilling two (2) Ø0.25 (Ø6.4 mm) holes in existing rib
assembly. Ensure bracket assembly is held down hard on tank when drilling holes. Refer to
drawing D350-794-001 Sheet 2 and 3. See Figure 8B and 8C. Secure bracket using two (2)
AN4-5A bolts, MS21042-3 nuts and NAS1149F0363P washers. It is acceptable for the top
support bracket assembly p/n D4006-041 to contact the tank at the access covers location (-141
tank only).
D4007-3
Figure 8A – Top Support Bracket
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D4006-041
Figure 8B – Vertical Support Assembly
D4024-041
Figure 8C – Vertical Support Assembly
(With D4024-041 strap installed)
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3.9
Vertical Restraint (EC 130 Only)
3.9.1
With the tank removed, drill out a minimum of nine (9) rivets on existing bracket on transmission
deck at the base of the support tube from the cabin rear wall. Locate and rivet in top support
bracket p/n D4007-1 with four (4) MS20470AD4 rivets through existing rib and a minimum of
eight (8) MS20470AD5 rivets through the original bracket and top support bracket using vacated
rivet holes. Refer to drawing D130-794-002 Sheet 3. Refer to Figure 9A.
3.9.2
Installation will need to include packer p/n D4007-5. Holes will need to be added into packer by
installer to allow for lightening holes in flange rib.
3.9.3
With tank in position and strapped in with strap p/n D4024-041, install top support bracket
assembly p/n D4006-041 by match drilling two (2) Ø0.25 (Ø6.4 mm) in existing rib assembly.
Ensure bracket assembly is held down hard on tank when drilling holes. Refer to drawing D130794-002 Sheet 2 and 3. See Figure 9B and 9C. Secure bracket using two (2) AN4-6A bolts,
MS21042-3 nuts and NAS1149F0363P washers. It is acceptable for the top support bracket
assembly p/n D4006-041 to contact the tank at the access covers location (-141 tank only).
D4007-1
Figure 9A – Top Support Bracket
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D4006-041
Figure 9B – Vertical Support Assembly
D4024-041
Figure 9C – Vertical Support Assembly
(With D4024-041 strap installed)
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3.10
Fuel Transfer Hose (AS 350 and EC 130)
3.10.1 With the tank removed and the main fuel tank filler neck connecting hose and filter removed,
mark and drill Ø0.56 (Ø14.3 mm) hole 0.59” (15 mm) outboard from a line taken from the
removable side panel locker wall and in the center of the tank filler tube. Refer to drawing D350794-001 Sheet 5 (AS 350) and D130-794-002 Sheet 5 (EC 130). Refer to Figure 10.
Caution: Ensure that no swarf or filings enter the tank. If available, it would be better to
use a screw type hole punch that draws the excess material out.
3.10.2 Install D4001-3 bulkhead fitting with AN924-6D or AS5178D06 Nut and NAS1149D0963J washer
supplied. Use Pro-seal PR-1422 liberally around fitting.
3.10.3 Install supply hose p/n D4002-7 from fuel pump outlet to bulkhead fitting on main tank filler neck.
D4001-3
Figure 10 – Supply Fitting
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED
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3.11
Vent System (AS 350 and EC 130)
3.11.1 AS 350 – Install vent pipe p/n D4003-11 on lower side of aft cross tube 1.57” (40 mm) inboard of
saddle clamp and protruding 2.36” (60 mm) below lower cowling. Trim cowling to suit. Install
clamp p/n D4027-043 and attach to cross tube and inside of forward and aft beam per drawing
D350-794-001 Sheet 2 and 4. Refer to Figure 11A.
Note: Paint to be removed from under MS21919WDG-6 clamp to provide electrical bonding to
tube.
3.11.2 EC 130 – Install vent pipe p/n D4003-11 on rear side of aft cross tube and inboard of locker rear
panel. Install clamp and attach to cross tube per drawing D130-794-002 Sheet 2 and 4. Refer to
Figure 11B.
Note: Paint to be removed from under MS21919WDG-6 clamp to provide electrical bonding to
tube.
D4003-11
Figure 11A – Inboard Tank Vent
(AS 350)
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Date: 14.08.20
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D4003-11
Figure 11B – Tank Vent
(EC 130)
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3.12
Sealing Locker Floor (AS 350 and EC 130)
3.12.1 Modify rear floor cover panel by the addition of metal finishing strip p/n D4005-11 so as to seal
against existing structure per drawing D350-794-001 Sheet 3 and 4 (AS 350) and D130-794-002
Sheet 3 and 4 (EC 130).
3.12.2 Install four (4) anchor nuts on existing structure to hold modified cover panel.
3.12.3 Install 3 sealed anchor nuts and screws to locker floor to replace existing press clips holding rear
panel. Seal any other existing holes in side locker floor area with rivets or low profile head
screws.
3.12.4 Sealing to be done after pump power supply has been installed. In the lower rear corner of
locker trim off 3.94” (100 mm) of vertical and horizontal door seal rubber for ventilation.
3.12.5 Place Pro-seal PR 1422 sealant around all edges of floor and rear floor cover panel, ensuring
that the floor is a fluid proof installation. Refer to Figure 12.
D4002-5
D4005-11
Trim Seal
Sealant
Trim Seal
Figure 12 – Rear Cover Plate
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3.13
Electrical and Gauge Installation (AS 350 and EC 130)
3.13.1 Install cannon plug for fuel pump power supply under rear cover using MS35206-217 screws,
NAS1149FN416 washers and MS21044N04 nuts. Drill Ø0.63” (Ø15.9 mm) hole, 2.36” (60 mm)
up from locker floor and 2.91” (70 mm) forward of side locker rear bulkhead. Refer to drawing
D350-794-001 Sheet 4 (AS 350) and D130-794-002 Sheet 4 (EC 130). See Figure 13.
Cannon Plug
Figure 13 – Cannon Plug in Bulkhead
3.13.2 Install fuel gauge into existing instrument panel located in easy view of the pilot. The D4026-041
will fit any standard 2-1/4” aircraft instrument mounting hole. Place the instrument in the hole
from the rear of the panel and attach using the four (4) screws provided. If you need to replace
the screws, ensure that the threads of the replacement screws do not penetrate the instrument
more than ½” (12.7 mm). Screws that penetrate the instrument further will cause severe damage
to the instrument.
3.13.3 Install gauge master switch and placard in view of the pilot next to the fuel gauge. Refer to
drawing D350-794-001 Sheet 6 and D130-794-002 Sheet 6.
3.13.4 Install fuel transfer switch alongside the fuel gauge with placards supplied. (Alternately if
required, use D4290-1 (Airbus switch p/n DSQ201) installed in existing Honeywell panel)
3.13.5 Install fuses or circuit breaker and mark accordingly. Ensure that there is one spare fuse of each
rating or 50% spare fuses of each rating, whichever is greater.
3.13.6 Install two (2) grounding studs p/n AN525-832R6, NAS1149FN832P and MS21042-08. One is
installed on the auxiliary fuel tank and the other is installed on the existing structure above the
tank. Install the three bonding braids p/n D4009-041 with short ends secured to the aircraft
structure per drawing D350-794-001 Sheet 2 (AS 350) and D130-794-002 Sheet 2 (EC 130).
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,...----------------------------------------_._----_._--_.----------------------
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3.13.7
The vent tube and tank earth leads terminate at the vent tube clamp installed on the locker
sidewall.
3.13.8
Undertake a resistance check between ground points and aircraft ground. Maximum resistance is
0.006 ohms (0).
3.13.9
The electrical wire for sender unit routes through existing hole in top right hand corner fairing.
Notes:
1)
2)
3)
4)
THIS DOCUMENT
Electrical wiring for gauge and fuel pump to be carried out by an appropriately approved
person per drawing 0350-794-901.
Cable installations should be done according to standard aircraft practices outlined in
AC43.13-1 B Chapter 11, Paragraph 11-96 and follow existing looms.
All exposed wiring located inside the side locker and main fuel tank bays are to be
shrouded with vapor-proof heat shrink and sealed against the pump and at each end
using Pro-seal PR 1422 to provide a vapor-proof seal.
Fuel pump assembly is supplied with wiring loom sealed with heat shrink and sealed at
each end with Pro-seal PR 1422 .
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IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
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3.14
Final Installation (AS 350 and EC 130)
3.14.1
Restraints and Fuel Supply Hose
3.14.2
3.14.3
3.14.4
3.14.1.1
Reinstall tank
3.14.1.2
Install hold down strap pin 04024-041 and tighten by pulling down with 33 Ib (15 kg)
pressure on strap end.
3.14.1.3
Install vertical restraint support assembly with two (2) AN4-5A (AS 350) or two (2)
AN4-6A (EC 130) bolts, MS21 042-3 nuts and NAS1149F0363P washers.
3.14.1.4
Install hose pin 04002-5 from tank outlet to bulkhead fitting in compartment.
Fuel Orain Hose
3.14.2.1
Install fuel drain hoses pin 04002-041 and 04002-043 per drawing 0350-794-001
Sheet 2 (AS 350) and 0130-794-002 Sheet 2 (EC 130).
3.14.2.2
Install 04004-7 clip per drawing 0350-794-001 Sheet 2 (AS 350) and 0130-794-002
Sheet 2 (EC 130).
Vent Hose
3.14.3.1
AS 350 - Install vent hose pin 04063-3 or 306-8 to tank vent pipe pin 04003-049 and
vent pipe pin 04005-041 using 2000-8s hose clamps. Cut hose to suit length.
3.14.3.2
EC 130 - Install vent hose pin 04063-3 or 306-8 to tank vent pipe pin 04003-049 and
vent pipe pin 04003-11 using 2000-8s hose clamps. Cut hose to suit length.
Operational Check
3.14.4.1
Ensure all hoses are connected and secure. Undertake a final check of wiring.
3.14.4.2
Reverse cockpit placard to read calibrationlequivalent card.
3.14.4.3
Reconnect power to aircraft.
3.14.4.4
Fill auxiliary tank with 20 liters of fuel (Jet-A1).
3.14.4.5
Turn auxiliary pump "ON" briefly and verify operation.
3.14.4.6
Ensure main tank has sufficient capacity for an additional 20 liters of fuel.
3.14.4.7
Switch auxiliary pump "ON" and transfer all auxiliary fuel to main fuel tank.
3.14.4.8
Check for leaks and proper operation.
3.14.4.9
Orain auxiliary tank completely from sump drain(s) after check .
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IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
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3.14.5
Placard Placement
3.14.5.1
Install placards as described in Table 2.
Table 2 - Placard Placement
Part Number
03997-1
03997-3
03997-7
03997-9
03997-13
03997-15
03997-19
03997-25
Oescription
AS 350 capacity
EC 130 capacity
Aux fuel transfer pump
Aux fuel
On/Off
Check to see if side
locker tank is installed
Tank vent
AS 350 conversion chart
03997-27
EC 130 conversion chart
03997-31
Aux fuel on/off
03997-35
Aux fuel gauge
03997-37
6.3 A aux tank pump
03997-39
2.5 A aux tank gauge
03997-41
Auxiliary tank not fitted
Placement
Adjacent to auxiliary fuel tank fuel filler
Adjacent to auxiliary fuel tank fuel filler
Next to fuel transfer pump switch
On fuel gauge blanking plate
Around fuel pump on/off switch
Centrally located on the outside of the side
locker door.
On vent tube protruding from helicopter
On instrument panel adjacent to the fuel gauge
in placard holder
On instrument panel adjacent to the fuel gauge
in placard holder
Around the auxiliary fuel gauge on/off switch on
instrument panel
Adjacent to auxiliary fuel gauge on/off switch
on instrument panel
On 6.3 amp fuse/circuit breaker that connects
to auxiliary tank fuel pump
On 2.5 amp fuse/circuit breaker that connects
to auxiliary tank fuel qauqe
On back of 03997-25 for AS 350
On back of 03997-27 for EC 130
Qtv.
1
1
1
1
1
1
1
1
1
1
1
1
1
1
3.15
Fuel Quantity Gauge Setup (AS 350 and EC 130)
3.15.1
With the aircraft in level flight attitude, fill tank with four (4) liters of fuel. Run transfer pump until it
pumps air and allow 20 seconds for fuel to settle. This will leave unusable fuel in auxiliary tank.
3.15.2
Turn power off to the gauge and remove switch plate pin 04014-1.
3.15.3
Press and hold the LRS switch to the S position, and turn the power on without releasing the
switch from the S position. Hold the switch until Set- is displayed. Then release to the R position.
3.15.4
B ..I will appear (Brightness Control Selection). Move the LRS switch from the L to R to choose 1
or E (I internal dimming, E external dimming, using a rheostat type device). When choice has
been made push the LRS switch momentarily to the S position. This is done to the customer's
preference, refer to wiring diagram.
3.15.5
CAL- will appear followed by SurE. Move the switch from the R to the L and back to the R
position to enter the calibration mode.
3.15.6
S.n.n will appear (set up of sender configuration). Push the LRS switch to the S position and then
release it back to the R position. If S.n.r appears move the LRS switch from the L to R until S.n.n
appears. Then push the LRS switch to the S position and release back to the R position.
3.15.7
L.E.Ft will appear. Push the LRS switch to the L position and then to the R position .
=
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IS PRIVATE AND CONFIDENTiAL AND is SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
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3.15.8 L..O will appear on the fuel quantity gauge display. Press LRS switch momentarily to the S
position and back to the R position.
3.15.9 L..1 will appear. Add exactly 1 US gallon (3.79 liters) to the tank. Allow 20 seconds for the fuel
to settle. Push the LRS switch momentarily to the S position and back to the R position. L..2 will
appear.
3.15.10 Keep repeating step 3.15.9 until the maximum fuel quantity is reached; 35 US gallons (133 liters)
for AS350 models or 41 US gallons (156 liters) for EC130 models. When the final gallon is
added instead of pressing the LRS switch to the R position, push the LRS switch to the L and
then back to the R position.
3.15.11 SurE will appear. Push the LRS switch to the L position and then back to the R position.
3.15.12 r.t. will be displayed. Push the LRS switch to the S position momentarily. DonE will be displayed
for 2 seconds.
3.15.13 Calibration has been completed successfully.
3.15.14 Push the LRS switch to the L position and hold in place by installing the switch plate p/n D40141.
Note: If a mistake is made after step 3.15.9 is started, the process must be re-started at 3.15.1
3.16
Fuel Quantity Error Messages and Fault Resolution (AS 350 and EC 130)
3.16.1 During normal operations and the calibration process, the instrument continually monitors
operations to ensure that it operates in accordance with the necessary specifications.
3.16.2 While calibrating the instrument, a number of parameters must be met in order for the instrument
to be commissioned in an aircraft. This section will provide you with an identification of the error
messages as well as possible resolutions. In all cases error messages are displayed as
indicated in Figure 14 below.
Figure 14 – Typical Error Message Indication
(Error 9 shown, other error messages similar)
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Table 3 - Error Message and Fault Resolution
Error
1
Point of
Occurrence
Reserved
2
Reserved
3
LO or r ..O of
the calibration
process
4
5
Any time during
normal
operations or
calibration
LO or r..O of
the calibration
process
Resolution
Contact Aerospace Logic Inc. Technical Support Department. You should
never see this messaQe.
Contact Aerospace Logic Inc. Technical Support Department. You should
never see this messaQe.
Cause:
The fuel sender is not providing a valid indication of fuel for the zero fuel level.
To qualify for installation into a certified aircraft the fuel sender must provide a
valid zero fuel level indication to the instrument.
Resolution: (in order of probability)
1. If you have not added the unusable fuel to the tank, do so now and
return to the calibration process.
2. The fuel sender travel is not correctly set. Refer to the manufacturer
documentation and correct the problem.
3. The fuel sender is defective. Replace it with a new or re-built unit.
4. If the sender orientation is set in the n mode check:
a. for an open circuit condition between the instrument and the
sender;
b. that the sender is grounded;
c. that the resistance specification if the sender matches that of
the instrument.
The instrument has detected an internal failure. Contact Aerospace Logic Inc.
Technical Support Department for an RMA and shipment of a new instrument.
Cause:
The fuel sender is not providing a valid indication of fuel for zero fuel level. To
qualify for installation into a certified aircraft the fuel sender must provide a
valid zero fuel level indication to the instrument.
Resolution: (in order of probability)
1. If you have not added the unusable fuel to the tank, do so now and
return to the calibration process.
2. The fuel sender travel is not correctly set. Refer to the manufacturer
documentation and correct the problem.
3. The fuel sender is defective. Replace it with a new or re-built unit.
4. If the sender orientation is set in the r mode check:
a. for an open circuit condition between the instrument and the
sender;
b. that the sender is grounded;
c. that the resistance specification of the sender matches that of
the instrument.
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@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED TO ANY OTHER PERSON WITHOUT WRIITEN
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Date: 14.08.20
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Table 3 - Error Message and Fault Resolution
Error
6
Point of
Occurrence
Anytime after
LO or r ..O
Resolution
Cause:
The fuel sender output has not changed since the last calibration reading.
Resolution: (in order of probability)
1. Did you add one US gallon of fuel since the last calibration point? If
not, do so now and continue with the process.
2. The fuel sender did not move with the addition of fuel:
a. Is the fuel tank full? Go to Section 3 step 15 of FL-100-R
Operations and Installation Manual
b. Has the fuel sender reached the maximum point of travel?
If this point of travel is in agreement with the
i.
manufacturers stated travel, then go to Section 3 step 15
of FL-1 OO-ROperations and Installation Manual
If this point of travel is not in agreement with the
ii.
manufacturers stated travel, then either adjust the sender
or have it repaired.
3. If the fuel tank is not full, the sender has not reached the full point of
travel and the sender has moved with the addition of fuel, then the
sender may be defective. Add up to 2 gallons of fuel in y.. gallon
increments checking to see if the error is cleared at each point. If the
instrument allows progress to the next calibration step, proceed with
% gallon increments until the additional fuel quantity has been
compensated for.
If the error cannot be resolved within 2 gallons, the sender must be
repaired before continuing .
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LTD.
IS PRIVATE AND CONFIDENTIAL
AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITIEN
PERMISSION FROM DART AEROSPACE LTD.
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Date: 14.08.20
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Table 3- Error Message and Fault Resolution
Error
7
Point of
Occurrence
Anytime after
LO or r..O
Resolution
Cause:
The fuel sender output has changed in the opposite orientation to that
expected since the last calibration reading.
Resolution: (in order of probability)
1. Is the sender orientation set correctly?
See Section 3 Step 6 of the FL-100-R Operations and Installation
Manual.
2. Did you add one gallon of fuel since the last calibration point?
If not, do so now and continue with process.
3. Is the fuel tank full?
Go to Section 3 Step 15 of the FL-100-R Operations and Installation
Manual.
4. Has the fuel sender reached the maximum point of travel?
a. If this point of travel is in agreement with the manufacturers
stated travel go to Section 3 Step 15 of FL-100-R Operations
and Installation Manual
b. If this point of travel is not in agreement with the
manufacturers stated travel then either adjust the sender or
have it repaired.
5. If the fuel tank is not full, the sender has not reached the full point of
travel and the sender has moved with the addition of fuel, then the
sender may be defective. Add up to 2 gallons of fuel in 11.1 gallon
increments checking to see if the error is removed at each point. If
the instrument allows progress to the next calibration step, proceed
with % gallon increments until the additional fuel quantity has been
compensated for.
If the error cannot be resolved within 2 gallons, the sender must be
repaired before continuil"1Q.
THIS DOCUMENT
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
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Date: 14.08.20
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Table 3- Error Message and Fault Resolution
Error
8
Point of
Occurrence
Anytime after
LO or r..O
Resolution
Cause:
The fuel sender output exceeded the specified limits for the instrument.
Resolution: (in order of probability)
1. Check that you have the correct
Maximum Sender
Resistance
440
670
1090
3000
2.
3.
4.
9
When the
calibration
process is
ended
instrument model for your sender:
FL-100 Model
Reauired
FL-100-R 44)
FL-100-R 67)
FL-100-R 109)
FL-100-R
Is the fuel tank full? Go to Section 3 step 15 of FL-1 OO-ROperations
and Installation Manual
Has the fuel sender reached the maximum point of travel?
a. If this point of travel is in agreement with the manufacturers
stated travel, then go the Section 3 step 15 of FL-100-R
Operations and Installation Manual
b. If this point of travel is not in agreement with the
manufacturers stated travel, then either adjust the sender or
have it repaired.
If the fuel tank is not full, the sender has not reached the full point of
travel and the correct instrument model is being used, then the sender
is defective. The sender must be repaired before continuinq.
Cause:
The instrument must be calibrated for a minimum of 10 gallons of fuel.
Resolution:
Continue the calibration process until a minimum of 10 qallons is reached.
Technical support for Aerospace Logic Inc. FL-100-R instrument may be obtained from:
Aerospace Logic Inc.
3150 Ridgeway Drive, Unit #43
Mississauga, Ontario, Canada
L5L 5R5
Tel: 905-569-3887
Fax: 416-352-5854
Email: technical@aerospacelogic.com
www.aerospacelogic.com
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IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
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4.0
ELECTRICAL LOAD
The electrical load effect for each aircraft must be assessed as follows.
5.0
WEIGHT AND BALANCE
The following is the weight increase associated with the Aux Fuel Tank Installation.
the weight of any parts or material removed.
LATERAL
Moment
Be sure to subtract
LONGITUDINAL
Arm
Moment
Installation
Weight
Arm
0350-794-011 Auxiliary Fuel Tank
(AS350 models)
32.71b
14.8 kg
-22.0 in
-0.56 m
-719.4 in-Ib
-8.29 m-kg
126.0 in
3.20m
4120.2 in-Ib
47.4 m-kg
0350-794-013 Auxiliary Fuel Tank Provisions
(AS350 models)
5.51b
2.5 kg
-14.6 in
-0.37 m
-80.3 in-Ib
-0.93 m-kg
163.4 in
4.15 m
898.7 in-Ib
10.4 m-kg
0130-794-021 Auxiliary Fuel Tank
(EC130 models)
32.71b
14.8 kg
-23.6 in
-0.60 m
-771.7 in-Ib
-8.88 m-kg
126.0 in
3.20 m
4120.2 in-Ib
47.4 m-kg
0130-794-023 Auxiliary Fuel Tank Provisions
(EC130 models)
5.51b
2.5 kg
-16.1 in
-0.41 m
-88.6 in-Ib
-1.03 m-kg
163.4 in
4.15 m
898.7 in-Ib
10.4 m-kg
0350-794-111 Auxiliary Fuel Tank
(AS350 models)
44.61b
20.2 kg
-22.0 in
-0.56 m
-981.2 in-Ib
-11.3 m-kg
126.0 in
3.20 m
5619.6 in-Ib
64.6 m-kg
0130-794-121 Auxiliary Fuel Tank
(EC130 models)
44.61b
20.2 kg
-23.6 in
-0.60 m
-1052.6 in-Ib
-12.1 m-kg
126.0 in
3.20m
5619.6 in-Ib
64.6 m-kg
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6.0
Qty
-011
X
1
Qty
-013
PARTS LIST
Qty
-021
Qty
-023
Qty
-041
X
X
1
1
1
1
1
1
1
1
1
X
0350-794-041
1
D4055-041
D4022-041
D4023-3
D4002-5
D4003-047
D4002-7
JCAlM47-1-01A
A8150-B1-JCA
ER281
JCA-M47-2-13
JCA-M47-2-16
JCA-M47-2-25
D4002-041
D4002-043
MS20822-3D
AN832-6D
AN816-6D
AN924-6D
NAS 1149D0963J
MS20822-8D
AN815-6D
MS29512-06
D4022-3
AN3-4A
MS21 042-3
AN970-3
D4008-043
D4004-7
D4009-041
D4008-041
AN525-10R6
D4001-3
JCA-M47 -1-13
JCA-M47-1-16
1*
1
1
2
1
1
2
2
2
2
2
2
1
2
2
2
1
1
2
2
1
2
2
2
1
1
1
1
2
1
4
1
4
1
2
1
2
1
1
1
1
1
2
1
1
2
3
3
1
1
1
2
1
1
2
3
3
3
1
1
1
THIS DOCUMENT
1
1
Superseded
Part Numbers
0130-794-021
0130-794-023
X
1
1
Part Number
0350-794-011
0350-794-013
MS21919WDG-8
D4003-11
D4027-041
D4003-049
D4027-043
D4063-3
2000-8S
NAS43DD3-32N
MS35207-267
MS35207-264
NAS 1149D0332J
MS21 042-3
TBA28B
TY25MX
MS21919WDG-6
D4009-041
05-00021
JCA-M47-2-29
N3
JCA-M47-4-01
JCA-M47-2-26
AN832-6D-JCA
JCA-M47-2-21
JCA-M47-2-20
JCA-M47-2-17
JCA-M47-2-35
193-8
JCA-M47.-4-01
OescriDtion
AUXILIARY FUEL
AUXILIARY FUEL
(AS 350 SERIES)
AUXILIARY FUEL
AUXILIARY FUEL
(EC 130 SERIES)
TANK ASSEMBLY
TANK (AS 350 SERIES)
TANK PROVISIONS
TANK (EC 130 SERIES)
TANK PROVISIONS
FUEL TANK
FUEL TRANSFER PUMP ASSEMBLY
FUEL CAP
SUPPLY HOSE - FROM AUX TANK
FUEL PUMP INLET PIPE
SUPPLY HOSE - PUMP TO MAIN TANK
FILLER NECK
DRAIN HOSE ASSEMBLY - FRONT
DRAIN HOSE ASSEMBLY - REAR
UNION
BULKHEAD UNION
STRAIGHT FiniNG
NUT (ALTERNATE AS5178D06)
WASHER
90° FiniNG
UNION
ORING
FUEL PUMP MOUNTING BRACKET
BOLT
NUT
WASHER
FUEL PUMP SPLASH GUARD
HOSE CLIP
BONDING BRAID
AUXILIARY TANK FILLER SPLASH GUARD
SCREW
BULKHEAD FiniNG - MODIFIED
VENT ASSEMBLY PARTS
CLAMP
VENT PIPE - TANK
VENT CLAMP ASSEMBL Y
VENT PIPE - TANK
VENT CLAMP ASSEMBL Y
VENT HOSE
HOSE CLAMP
SPACER
SCREW
SCREW
WASHER
NUT
CABLE TIE FASTENER
TIE WRAP
CLAMP (RUBBER REMOVED)
BONDING BRAID ASSEMBLY
• COPYRIGHT
@2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL
AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTl:l.
OR COPIED
Revision: G
Date: 14.08.20
DART AEROSPACE LTD.
IIN-D350-794
Page 34 of 38
Qty
-011
Qty
-013
Qty
-021
Qty
-023
Qty
-041
Part Number
1
1
1
3
3
3
1
1
1
1
2
2
1
1
1
3
3
3
1
1
1
1
2
2
D4005-1
D4004-11
D4004-5
MS24694-S50
MS21 042-3
NAS 1149F0363P
D4024-041
D4004-041
D4007-3
D4006-041
AN4-5A
NAS 1149F0463P
1
1
1
1
1
1
1
3
1
4
7
1
1
1
1
1
1
1
3
1
4
7
D4005-041
D4063-1
MS21919WDG-9
MS35207-264
NAS 1149D0332J
MS21 042-3
2000-6S
NAS1474-08
D4005-11
MS21059-L08
AN525-832R6
1
1
D4290-9
1
1
D4290-11
1
1
1
1
1
1
MS35058-23
D4290-29
D4290-27
1
1
4
4
4
1
1
1
4
4
4
1
1
1
D4290-25
D4025-1
MS35206-217
NAS 1149FN416P
MS21044N04
D4290-33
D4290-23
D4290-15
1
1
D4290-17
5
5
D4290-35
5
5
D4290-31
1
1
2
2
1
1
2
2
D4009-041
D4026-041
AN525-832R6
NAS 1149FN832P
1"
THIS DOCUMENT
Superseded
Part Numbers
JCA-M4 7-2-03
JCA-M47-2-11
JCA-M47-2-23
JCA/ASSO/MIN
JCA-M47-2-19
JCA-M47-2-18
JCA-M47-2-01
JCA-M47-2-22
193-6
JCA-M47-2-12
D8-603
(AL 1. HA23-6U3)
D1-205
(AL 1. HA21-2U5)
107-964
107-978
(ALT. 105-5465)
107-943
VDO-M47-JCA
143-207
143-208
143-204
(ALT. 973-1482)
143-203
(ALT. 973-1490)
143-219
(ALT. 977-3800)
143-217
(ALT. 977-3797)
JCA-M47-4-01
FL-100-R-JCA
Description
Restraint Assembly Parts
REAR RESTRAINT ANGLE/GUTIER
TOP STRAPATIACH
BRACKET
BOTIOM STRAP ATI ACH BRACKET
SCREW
NUT
WASHER
ANCRA RESTRAINT STRAP
SIDE RESTRAINT ANGLE
TOP SUPPORT BRACKET
TANK TOP SUPPORT ASSEMBLY
BOLT
WASHER
LOCKER PREPARATION PARTS
FORWARD FLOOR GUTIER
DRAIN HOSE
CLAMP
SCREW
WASHER
NUT
HOSE CLAMP
SEALED CAPTIVE ANCHOR NUT
FINISHING STRIP
ANCHOR NUT
SCREW
ELECTRICAL PARTS
6.3A ECF FUSE
2.5A ECF FUSE
SWITCH
CONNECTOR RECEPTACLE
CONNECTOR BACKSHELL
CONNECTOR PLUG
FUEL QUANTITY SENDER
SCREW
WASHER
NUT
PLUG
RECEPTACLE
RECEPTACLE HOUSING
PLUG HOUSING
CRIMP PIN
CRIMP SOCKET
BONDING BRAID ASSEMBLY
FUEL GAUGE
SCREW - GROUND STUD
WASHER
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
OR COPIED
Revision: G
Date: 14.08.20
DART AEROSPACE
IIN-D350-794
LTD.
Page 35 of 38
Qty
-011
Qty
-013
2
1
1**
Qty
-021
1
1
Qty
-023
2
1
1**
Qty
-041
Superseded
Part Numbers
444-2556
3775628
(ALT. 100-6847)
Description
NUT
GAUGE MASTER SWITCH
THERMAL SWITCH (125°C) - FARNELL
GENERAL
PLACARD HOLDER
BLANK CAP
1
1
AN5800-1
AN929-6D
3
3
3
1
1
MS35207-264
NAS 1149D0332J
MS21 042-3
D4027-041
D4004-043
1
4
1
1
1
2
1
D4005-5
D4005-7
D4005-9
D4007-1
D4005-3
AN4-6A
D4007-5
JCA-M47-2-06
JCA-M47-2-07
JCA-M47-2-08
JCA-M47-2-02
JCA-M47-2-05
JCA-M47-2-24
ADDITIONAL EC 130 PARTS
SCREW
WASHER
NUT
VENT CLAMP ASSEMBLY
SIDE RESTRAINT ANGLE AND TIE DOWN
POINT
ANGLE
ANGLE
ANGLE
TOP SUPPORT BRACKET
FORWARD RESTRAINT BEAM
BOLT
PACKER
D3997-1
D3997-3
D3997-5
D3997-7
D3997-9
D3997-11
D3997-13
D3997-15
D3997-17
D3997-19
D3997-21
D3997-23
D3997-25
D3997-27
D3997-29
D3997-31
D3997-33
D3997-35
D3997-37
D3997-39
D3997-41
D3997-43
JCA-M47-P1
JCA-M47-P2
JCA-M47-P3
JCA-M47-P4
JCA-M47-P5
JCA-M47-P6
JCA-M47-P7
JCA-M47-P8
JCA-M47-P9
JCA-M47-P10
JCA-M47-P13
JCA-M47-P14
JCA-M47-P15
JCA-M47-P16
JCA-M47 -P17
JCA-M47-P18
JCA-M47-P19
JCA-M47-P20
JCA-M47-P21
JCA-M47-P22
JCA-M47-P23
JCA-M47-P24
PLACARDS
FUEL QUANTITY - AS 350 MODELS
FUEL QUANTITY - EC 130 B4 MODEL
AUX FUEL DRAIN
AUX FUEL TRANSFER PUMP
AUX FUEL
WEIGHT AND BALANCE
ON/OFF
CHECK LOCKER TANK
STOWAGE PROHIBITED
TANK VENT
SWITCH FIXED
AUX FUEL
CONVERSION CHART - AS 350 MODELS
CONVERSION CHART - EC 130 B4 MODEL
DO NOT OVERFILL WARNING
ON/OFF
AUX GAUGE FACE
AUX FUEL GAUGE
6.3 A CIRCUIT BREAKER
2.5A CIRCUIT BREAKER
AUX TANK NOT FinED
EARTH
1
1
2*
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1*
1*
1
1*
1
1
1
1
1
1
Part Number
MS21 042-08
D4290-7
D4022-5
1
1
1
1
1
1
1*
JCA-M47-2-20
JCA-M47-2-04
* - item included as part of 04055-041 tank assembly
** - item included as part of 04022-041 pump assembly
THIS DOCUMENT
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTO.
OR COPIED
Revision: G
Date: 14.08.20
DART AEROSPACE LTD.
IIN-D350-794
Page 36 of 38
Qty
-111
X
1
Qty
-013
Qty
-121
Qty
-023
Qty
-141
X
X
1
1
1
1
1
1
1
1
1
1
X
0350-794-141
1
D4464-041
D4022-041
D4023-3
D4002-5
D4003-047
D4002-7
1*
1
1
2
1
1
2
2
2
2
2
2
1
2
2
2
1
1
2
2
1
2
2
2
1
1
1
1
2
1
4
1
4
1
2
1
2
1
1
1
1
1
2
1
1
2
3
3
1
1
1
2
1
1
2
3
3
3
1
1
1
THIS DOCUMENT
1
1
Superseded
Part Numbers
0130-794-121
0130-794-023
X
1
Part Number
0350-794-111
0350-794-013
D4002-041
D4002-043
MS20822-3D
AN832-6D
AN816-6D
AN924-6D
NAS 1149D0963J
MS20822-8D
AN815-6D
MS29512-06
D4022-3
AN3-4A
MS21 042-3
AN970-3
D4008-043
D4004-7
D4009-041
D4008-041
AN525-10R6
D4001-3
MS21919WDG-8
D4003-11
D4027-041
D4003-049
D4027-043
D4063-3
2000-8S
NAS43DD3-32N
MS35207-267
MS35207-264
NAS 1149D0332J
MS21 042-3
TBA28B
TY25MX
MS21919WDG-6
D4009-041
A8150-B 1-JCA
JCA-M47-2-13
JCA-M47-2-16
JCA-M47-2-25
JCA-M47-1-13
JCA-M47-1-16
05-00021
JCA-M47-2-29
N3
JCA-M47-4-01
JCA-M47-2-26
AN832-6D-JCA
JCA-M47-2-21
JCA-M47-2-20
JCA-M47-2-17
JCA-M47-2-35
193-8
JCA-M47-4-01
Oescription
AUXILIARY FUEL
AUXILIARY FUEL
(AS 350 SERIES)
AUXILIARY FUEL
AUXILIARY FUEL
(EC 130 SERIES)
TANK ASSEMBLY
TANK (AS 350 SERIES)
TANK PROVISIONS
TANK (EC 130 SERIES)
TANK PROVISIONS
TANK ASSEMBLY
FUEL TRANSFER PUMP ASSEMBLY
FUEL CAP
SUPPLY HOSE - FROM AUX TANK
FUEL PUMP INLET PIPE
SUPPLY HOSE - PUMP TO MAIN TANK
FILLER NECK
DRAIN HOSE ASSEMBLY - FRONT
DRAIN HOSE ASSEMBLY - REAR
UNION
BULKHEAD UNION
STRAIGHT FiniNG
NUT (ALTERNATE AS5178D06)
WASHER
90° FiniNG
UNION
ORING
FUEL PUMP MOUNTING BRACKET
BOLT
NUT
WASHER
FUEL PUMP SPLASH GUARD
HOSE CLIP
BONDING BRAID
AUXILIARY TANK FILLER SPLASH GUARD
SCREW
BULKHEAD FiniNG - MODIFIED
VENT ASSEMBLY PARTS
CLAMP
VENT PIPE - TANK
VENT CLAMP ASSEMBLY
VENT PIPE - TANK
VENT CLAMP ASSEMBLY
VENT HOSE
HOSE CLAMP
SPACER
SCREW
SCREW
WASHER
NUT
CABLE TIE FASTENER
TIE WRAP
CLAMP (RUBBER REMOVED)
BONDING BRAID ASSEMBLY
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
OR COPIED
Revision: G
Date: 14.08.20
IIN-D350-794
DART AEROSPACE LTD.
Page 37 of 38
Qty
Qty
Qty
Qty
Qty
.111
-013
.121
-023
-141
Part Number
Superseded
Part Numbers
JCA-M47-2-03
JCA-M47-2-11
JCA-M47-2-23
1
1
1
3
3
3
1
1
1
1
2
2
1
1
1
3
3
3
1
1
1
1
2
2
D4005-1
D4004-11
D4004-5
MS24694-S50
MS21 042-3
NAS 1149F0363P
D4024-041
D4004-041
D4007-3
D4006-041
AN4-5A
NAS 1149F0463P
1
1
1
1
1
1
1
3
1
4
7
1
1
1
1
1
1
1
3
1
4
7
D4005-041
D4063-1
MS21919WDG-9
MS35207-264
NAS1149D0332J
MS21 042-3
2000-6S
NAS1474-08
D4005-11
MS21059-L08
AN525-832R6
JCA-M47-2-22
193-6
1
1
D4290-9
1
1
D4290-11
D8-603
CALT. HA23-6U3)
D1-205
CAL1. HA21-2U5)
1
1
1
1
1
1
MS35058-23
D4290-29
D4290-27
1
1
4
4
4
1
1
1
4
4
4
1
1
1
D4290-25
D4025-5
MS35206-217
NAS 1149FN416P
MS21044N04
D4290-33
D4290-23
D4290-15
1
1
D4290-17
5
5
D4290-35
5
5
D4290-31
1
1
2
2
1
1
2
2
D4009-041
D4026-041
AN525-832R6
NAS1149FN832P
1*
THIS DOCUMENT
JCA/ASSO/MIN
JCA-M47-2-19
JCA-M47-2-18
JCA-M47-2-01
JCA-M47-2-12
107-964
107-978
CAL1. 105-5465)
107-943
143-207
143-208
143-204
CALT. 973-1482)
143-203
CAL1. 973-1490)
143-219
(ALT. 977-3800\
143-217
CALT. 977-3797)
JCA-M47-4-01
FL-100-R-JCA
Description
Restraint Assemblv Parts
REAR RESTRAINT ANGLE/GUTIER
TOP STRAP ATIACH BRACKET
BOTIOM STRAP ATIACH BRACKET
SCREW
NUT
WASHER
ANCRA RESTRAINT STRAP
SIDE RESTRAINT ANGLE
TOP SUPPORT BRACKET
TANK TOP SUPPORT ASSEMBLY
BOLT
WASHER
LOCKER PREPARATION PARTS
FORWARD FLOOR GUTIER
DRAIN HOSE
CLAMP
SCREW
WASHER
NUT
HOSE CLAMP
SEALED CAPTIVE ANCHOR NUT
FINISHING STRIP
ANCHOR NUT
SCREW
Electrical Parts
6.3A ECF FUSE
2.5A ECF FUSE
SWITCH
CONNECTOR RECEPTACLE
CONNECTOR BACKS HELL
CONNECTOR PLUG
FUEL QUANTITY SENDER
SCREW
WASHER
NUT
PLUG
RECEPTACLE
RECEPTACLE HOUSING
PLUG HOUSING
CRIMP PIN
CRIMP SOCKET
BONDING BRAID ASSEMBLY
FUEL GAUGE
SCREW - GROUND STUD
WASHER
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL
AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTO.
OR COPIED
Revision: G
Date: 14.08.20
DART AEROSPACE
IIN-D350-794
LTD.
Page 38 of 38
Qty
-111
Qty
-013
2
1
1**
Qty
-121
1
1
Qty
-023
2
1
1**
Qty
-141
1
1
1*
Superseded
Part Numbers
444-2556
3775628
(ALT. 100-6847)
Description
NUT
GAUGE MASTER SWITCH
THERMAL SWITCH (125°C) - FARNELL
GENERAL
PLACARD HOLDER
BLANK CAP
CUSHION
AN5800-1
AN929-6D
D4968-1
3
3
3
1
1
MS35207-264
NAS 1149D0332J
MS21 042-3
D4027-041
D4004-043
1
4
1
1
1
2
1
D4005-5
D4005-7
D4005-9
D4007-1
D4005-3
AN4~6A
D4007-5
JCA-M47-2-06
JCA-M47-2-07
JCA-M47-2-08
JCA-M47-2-02
JCA-M47-2-05
JCA-M47-2-24
ADDITIONAL EC 130 PARTS
SCREW
WASHER
NUT
VENT CLAMP ASSEMBL Y
SIDE RESTRAINT ANGLE AND TIE DOWN
POINT
ANGLE
ANGLE
ANGLE
TOP SUPPORT BRACKET
FORWARD RESTRAINT BEAM
BOLT
PACKER
D3997-1
D3997-3
D3997-5
D3997-7
D3997-9
D3997-11
D3997-13
D3997-15
D3997-17
D3997-19
D3997-21
D3997-23
D3997-25
D3997-27
D3997-29
D3997-31
D3997-33
D3997-35
03997-37
03997-39
03997-41
03997-43
JCA-M47-P1
JCA-M47-P2
JCA-M47-P3
JCA-M47-P4
JCA-M47-P5
JCA-M47-P6
JCA-M47-P7
JCA-M47-P8
JCA-M47-P9
JCA-M47 -P1 0
JCA-M4 7-P13
JCA-M47-P14
JCA-M4 7-P15
JCA-M4 7-P16
JCA-M47-P17
JCA-M47 -P18
JCA-M4 7-P19
JCA-M47-P20
JCA-M47-P21
JCA-M47-P22
JCA-M47-P23
JCA-M47-P24
PLACARDS
FUEL QUANTITY - AS 350 MODELS
FUEL QUANTITY - EC 130 B4 MODEL
AUX FUEL DRAIN
AUX FUEL TRANSFER PUMP
AUX FUEL
WEIGHT AND BALANCE
ON/OFF
CHECK LOCKER TANK
STOWAGE PROHIBITED
TANK VENT
SWITCH FIXED
AUX FUEL
CONVERSION CHART - AS 350 MODELS
CONVERSION CHART - EC 130 B4 MODEL
DO NOT OVERFILL WARNING
ON/OFF
AUX GAUGE FACE
AUX FUEL GAUGE
6.3 A CIRCUIT BREAKER
2.5A CIRCUIT BREAKER
AUX TANK NOT FITTEO
EARTH
1
1
2*
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1*
1*
1
1*
1
1
1
1
1
1
Part Number
MS21 042-08
D4290-7
D4022-5
1
1
1
1
1
1
1*
JCA-M47-2-20
JCA-M47-2-04
* - items included as part of 04464-041 tank assembly
** - items included as part of 04022-041 pump assembly
THIS DOCUMENT
• COPYRIGHT
@ 2009 BY DART AEROSPACE
LTD.
IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE
OR COMMUNICATED
TO ANY OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
OR COPIED
Revision: G
Date: 14.08.20