ICA-D350-794-Rev8

DART AEROSPACE LTD.

ICA-D350-794

Page 2 of 46

REVISION RECORD

Revision No. Issue

Date

Description

0 09.06.17 Issue

1 09.12.08 Changed placards from

JCA to DART part numbers.

2 10.01.25 Replace all remaining JCA part numbers with Dart part numbers

3

4

5

6

7

8

11.11.03 Add D350-794-111 Aux

Tank Kit, D130-794-121

Aux Tank Kit and D350-

794-141 Tank Assembly;

Add Sections 28.10, 28.11 and Chapter 98

12.04.13 Update weight & balance per DSI 9577. Add section

28.7 and 28.8. Update 5.2.3 and 5.6.5. Add Figure 28-3.

Update parts list.

12.08.21 Updated Wiring Diagrams

13.08.15 Update parts list to describe

D4022-5 as part of the

D4022-041 pump assembly, ref CAR13-80.

14.07.30 Updated Figure 28-2/-3 per

DSI 9663. Update Figure

11-21 per DSI 9673.

Incorporated DSI 9672.

Updated Weight and

Balance.

15.06.05 Updated Figure 28-2

Date Inserted Inserted By

 COPYRIGHT

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2015 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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ICA-D350-794

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LIST OF EFFECTIVE PAGES

REVISION RECORD

LIST OF EFFECTIVE PAGES

TABLE OF CONTENTS

CHAPTER 0 – INTRODUCTION

CHAPTER 0 – INTRODUCTION

CHAPTER 4 – AIRWORTHINESS LIMITATIONS

CHAPTER 5 – INSPECTION REQUIREMENTS



CHAPTER 11 – PLACARDS





CHAPTER 28 – FUEL SYSTEMS





























CHAPTER 98 - WIRING DIAGRAMS

CHAPTER 98 - WIRING DIAGRAMS

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ICA-D350-794

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TABLE OF CONTENTS

CHAPTER 0 – INTRODUCTION (00-00-00) ................................................................................................ 5

0.1

0.2

SCOPE 5

ARRANGEMENT ............................................................................................................................ 5

0.3

0.4

0.5

DISTRIBUTION .............................................................................................................................. 5

COMPATIBILITY ............................................................................................................................ 5

SYSTEM DESCRIPTION ............................................................................................................... 6

CHAPTER 4 – AIRWORTHINESS LIMITATIONS (04-00-00) ...................................................................... 7

CHAPTER 5 – INSPECTION REQUIREMENTS (05-00-00) ........................................................................ 8

5.1

5.2

5.3

5.4

5.5

5.6

5.7

DAILY INSPECTION....................................................................................................................... 8

ANNUAL/100 HOUR INSPECTION ................................................................................................ 8

24 MONTH/600 HOUR INSPECTION ............................................................................................ 9

3000 HOUR INSPECTION ........................................................................................................... 10

12 YEAR INSPECTION ................................................................................................................ 10

FUEL LEAKAGE INSPECTION .................................................................................................... 10

SERVICABILITY INSPECTION .................................................................................................... 10

CHAPTER 11 – PLACARDS (11-00-00) ..................................................................................................... 11

11.1

REQUIRED PLACARDS .............................................................................................................. 11

CHAPTER 28 – FUEL SYSTEM (28-00-00) ............................................................................................... 16

28.1

28.2

28.3

28.4

28.5

28.6

28.7

28.8

28.9

AUXILIARY FUEL TANK REMOVAL ............................................................................................ 16

AUXILIARY FUEL TANK RE-INSTALLATION .............................................................................. 16

AUXILIARY FUEL TANK LONG TERM STORAGE ...................................................................... 17

FUEL QUANTITY GAUGE CALIBRATION ................................................................................... 17

FUEL QUANTITY GAUGE ERROR MESSAGES AND FAULT RESOLUTION............................ 18

D350-794-141 TANK ASSEMBLY ................................................................................................ 23

28.10

28.11

28.12

28.13

ACCESS PANEL REMOVAL ........................................................................................................ 24

ACCESS PANEL RE-INSTALLATION.......................................................................................... 24

CUSHION REMOVAL AND INSTALLATION ................................................................................ 25

ELECTRICAL LOAD ..................................................................................................................... 25

WEIGHT

PARTS

AND BALANCE ............................................................................................................. 25

LIST ................................................................................................................................. 26

28.14

AS350 INSTALLATION ................................................................................................................ 33

EC130 INSTALLATION ................................................................................................................ 39

CHAPTER 98 – WIRING DIAGRAMS (98-00-00) ...................................................................................... 45

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CHAPTER 0 – INTRODUCTION (00-00-00)

0.1 SCOPE

This manual provides the requirements set forth in Appendix A of FAR Part 27 for the Instructions for

Continued Airworthiness of the Dart D350-794 and D130-794 Auxiliary Fuel Tank kits when installed in the

Airbus AS 350-B/B1/B2/B3/BA/D and EC 130 B4 model aircraft. These Instructions for Continued

Airworthiness are to be referred to for inspection and maintenance when the Auxiliary Fuel Tank Kits are installed on, removed from, or in service on the rotorcraft.

0.2 ARRANGEMENT

The manual is arranged in ATA-100 format. This manual is only applicable to Airbus AS 350-

B/B1/B2/B3/BA/D and EC 130 B4 model rotorcraft modified with the installation of the Dart D350-794 and

D130-794 Auxiliary Fuel Tank kits.

There are no abbreviations, acronyms, or symbolization which are not common to the aviation industry in this manual.

Units of measurement are expressed in Imperial and metric values and all torque values are standard values for the specified fastener combinations as defined in FAA AC 43.13, unless otherwise specified in this document.

No other Instructions for Continued Airworthiness for any product or appliance is inferred or addressed herein.

0.3 DISTRIBUTION

Any changes in the content or revision level of this document will be made available to any owner/operator in the internet at www.dartaero.com

Additionally, any changes will be sent to the Transport Canada. All changes will be recorded in the Record of Revisions page at the front of this manual.

0.4 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.

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ICA-D350-794

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DESCRIPTION

These instructions cover the installation of the Dart D350-794 and D130-794 Auxiliary Fuel Tank Kits for the Airbus AS 350 and EC 130 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.

Both 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 auxiliary fuel tank kits are shown in

Figure 0-1

.

Figure 0-1 – D350-794/D130-794 Auxiliary Fuel Tank Installation

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DART AEROSPACE LTD. ICA-D350-794

Page 7 of 46

CHAPTER 4 – AIRWORTHINESS LIMITATIONS (04-00-00)

The Airworthiness Limitations section is approved by the Minister and specifies maintenance required by any applicable airworthiness or operating rule unless an alternative program has been approved by the Minister.

No airworthiness limitations associated with this type design change.

CHAPTER 4 – AIRWORTHINESS LIMITATIONS (04-00-00)

FOR FAA CUSTOMERS

The Airworthiness Limitations section is FAA approved and specifies inspections and other maintenance required under Sections 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.

No airworthiness limitations associated with this type design change.

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

CHAPTER 5 – INSPECTION REQUIREMENTS (05-00-00)

INSPECTION

(To be performed before the first flight of the day)

5.1.1 Check tank for security, leaks and correct operation. Check restraint webbing is correctly tensioned to 33 lbs (15 kg) on strap end.

5.2 ANNUAL/100 HOUR INSPECTION

(To be performed every 100 hours or 12 months, to coincide with the airframe inspection or if damage is found on the daily inspection)

Note: For the convenience of scheduling maintenance, the tolerance for scheduled inspection intervals is ±10% (±10 hours or ±1 month). In each case, the subsequent interval will be adjusted to re-establish the original schedule. When an inspection is done more than 10% early, subsequent inspections will be advanced as required not to exceed the maximum tolerance. Concurrence and final approval of the inspection interval tolerance by the governing civil aviation authority is the responsibility of the owner/operator.

5.2.1 Check the Auxiliary tank restraint for tightness, chafing and wear.

5.2.2 Drain tank and remove from aircraft per Section 28.1. Note that the D350-794-041 aux tank cannot be completely drained when installed in aircraft. Tank must be removed for complete draining.

5.2.3 Carry out internal examination of fuel tank for cleanliness, debris, corrosion and fungal growth.

Clean tank of contaminants if found. No corrosion or other damage permitted. On the D350-794-

141 tanks used in the D350-794-111 and D130-794-121 kits, it is acceptable to remove the covers for improved access per Section 28.7, perform the inspection, and re-install the covers per Section

28.8.

5.2.4 Inspect the D4968-3, D4404-3/-5 Cushion(s) installed on the side of the tank. If they become chafed or damaged during service they may be removed and replaced per section 28.9.

5.2.5 Inspect outer surface of tank for corrosion, cracking and other damage. Visually inspect tank welds for condition. If fuel leakage is suspected perform fuel leakage inspection per Section 5.6.

5.2.6 Inspect auxiliary tank restraint angles and attach hardware for condition. Retouch primer/paint as necessary and replace worn or damaged hardware as required.

5.2.7 Inspect all fuel transfer hoses and lines for condition. Damaged, corroded, chafed or worn hoses and lines are to be replaced.

5.2.8 Inspect condition of auxiliary tank transfer fitting in main fuel tank filler neck. Ensure fitting is secure, filler neck is undamaged and sealant is intact.

5.2.9 Check tank vent and auxiliary drain lines for blockages, dirt and debris. Ensure tank vent is clear.

Clean lines of any blockages, dirt or debris with fuel. Check condition and security of vent and drain lines.

5.2.10 Reinstall tank and hoses per Section 28.2. Check all hose fittings and connectors for security and tightness.

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5.2.11 Inspect auxiliary tank transfer pump and fittings for security and any signs of weeping fuel.

Retighten fittings as required. No fuel weep allowed.

5.2.12 Inspect auxiliary tank transfer pump wiring conduit, fuel quantity sender wiring conduit and grounding straps for condition, chafing and security. Ensure wiring conduit terminations at pump body are fully sealed against vapor ingress. Renew seal using PR1422 or equivalent if required.

NOTE:

Resistance across the bonding jumper is required to be 0.01 ohms or less.

5.2.13 Fill tank with nominally 10L of Jet A1 fuel. Disconnect aux fuel transfer fitting from main tank filler neck and place the free end of the transfer hose into a graduated container. Operate auxiliary tank transfer pump and pump fuel into the container. Once a continuous flow is achieved record the amount of time required to transfer a known quantity of fuel. Transfer rate is to be 3 liters per minute or more.

5.2.14 Reconnect transfer hose fitting to main tank filler neck and tighten. Transfer remaining fuel to main tank and check system for leaks per 5.6.

5.3 24 MONTH/600 HOUR INSPECTION

(To be performed every 600 hours or 24 months, to coincide with the airframe inspection or if damage is found on the daily inspection)

Note: For the convenience of scheduling maintenance, the tolerance for scheduled inspection intervals is ±10% (±60 hours or ±2 month). In each case, the subsequent interval will be adjusted to re-establish the original schedule. When an inspection is done more than 10% early, subsequent inspections will be advanced as required not to exceed the maximum tolerance. Concurrence and final approval of the inspection interval tolerance by the governing civil aviation authority is the responsibility of the owner/operator.

5.3.1 Carry out steps 5.2.1 to 5.2.10 of the Annual/100 Hour Inspection.

5.3.2 Undertake a close visual inspection of the pump body and fittings for damage and corrosion.

Inspect pump body for signs of weeping fuel. If the pump is faulty, damaged or weeping, replace with a new pump or return to an approved overhaul workshop.

5.3.3 Check pump output pressure. Disconnect the supply hose at aircraft fuel tank filler neck and install stop valve. Run the pump into a container with valve open until a steady fuel flow is obtained.

Close the valve and check gauge for a pressure reading of above 4 psi. Do not keep the valve closed for more than 30 seconds. Ensure pump does not weep fuel during test.

5.3.4 Check condition of thermal switch mounting on pump body and electrical connections. If switch requires re-mounting, clean contact surfaces of all existing adhesive and mount switch using

Metalset A4 or equivalent metal filled adhesive.

5.3.5 Visually inspect transfer pump mounting holes on aircraft bulkhead for cracking.

5.3.6 Carry out fuel calibration as per Section 28.4.

5.3.7 Ensure all placards are properly installed per Chapter 11 of this ICA.

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5.4 3000 HOUR INSPECTION

5.4.1 Replace or overhaul auxiliary tank transfer pump. Overhaul may be performed by an approved overhaul facility.

5.5 12 YEAR INSPECTION

5.5.1 Replace all flexible lines.

5.6 FUEL LEAKAGE INSPECTION

5.6.1 Remove auxiliary tank from aircraft per Section 28.1 and drain remaining fuel from tank.

5.6.2 Install blanking covers and plates over vent and outlet connections.

5.6.3 Using appropriate shop equipment (regulator, lines, fittings etc.) pressurize the tank to 5 psi.

5.6.4 Visually check the tank for evidence of leakage. Apply a soap/water solution to suspected leakage areas and watch for bubbles.

5.6.5 If leak is confirmed, repair by TIG weld per MIL-STD-2219 or AMS D17.1.2001 using AWS 4043A filler rod or 5356 filler rod. Prepare surfaces for welding per AC 43.13-1B Chapter 4 Paragraph 4-

74. Alternately, repair leak by applying Proseal 890 to the suspected area from the inside of the tank (-141 tank only).

5.6.6 Repeat steps 5.6.3 – 5.6.5 to confirm effectiveness of repair.

5.7.1 Check for dents or scratches and general cleanliness.

5.7.2 Check security of the plumbing.

5.7.3 Check that blanks are installed in supply and vent hoses.

5.7.4 Check tank internally for contamination. If contamination present, then the tank must be thoroughly cleaned and all contaminants removed.

5.7.5 Check placards are legible and in good condition and applicable to the helicopter being used.

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CHAPTER 11 – PLACARDS (11-00-00)

The following placards are required when the D350-794/D130-794 Auxiliary Fuel Tank Kit is installed.

Placards are to be installed where indicated.

Figure 11-1 – D3997-1 (Fuel Quantity AS350 Models)

(Install adjacent to auxiliary fuel tank filler)

Figure 11-2 – D3997-3 (Fuel Quantity EC 130 B4 Models)


Figure 11-3 – D3997-5 (Aux Drain)

(Install adjacent to auxiliary fuel tank drain)

Figure 11-4 – D3997-7 (Pump Switch)

(Install adjacent to pump switch on instrument panel – if installed)

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Figure 11-5 – D3997-9 (Switch Panel)

(Install in aircraft switch panel)

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Figure 11-6 – D3997-11 (Weight and Balance)

(Install on tank outboard surface)

Figure 11-7 – D3997-13 (Switch On/Off)

(Install around fuel pump on/off switch (if fitted))

Figure 11-8 – D3997-15 (Locker Door)

(Install on baggage locker outer surface below release button)

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Figure 11-9 – D3997-17 (Stowage Warning)

(Install on tank outboard surface)

Figure 11-10 – D3997-19 (Tank Vent)

(Install on all tank exterior vent tubes)

Figure 11-11 – D3997-21 (Switch Fixed)

(Install on aux. fuel gauge switch plate)

Figure 11-12 – D3997-23 (Aux Fuel)

(Install on aux fuel gauge)

AUX TANK

MAX 129L USABLE

D3997-25

US GAL LITERS

34

30

129

114

25

20

15

10

5

95

76

57

38

19

0 0

Figure 11-13 – D3997-25 (Conversion AS 350)

(Install next to aux fuel gauge)

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AUX TANK

MAX 152L USABLE

D3997-25

US GAL LITERS

40

35

152

133

30

25

20

15

114

95

76

57

10

5

0

38

19

0

Figure 11-14 – D3997-27 (Conversion EC130B4)

(Install next to aux fuel gauge)

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Figure 11-15 – D3997-29 (Do Not Overfill Warning)


Figure 11-16 – D3997-31 (Aux Fuel Gauge Switch On/Off)

(Install around auxiliary fuel gauge on/off switch on instrument panel)

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Figure 11-17 – D3997-33 (Aux Fuel Gauge Face)

(Install on auxiliary fuel gauge cover)

Figure 11-18 – D3997-35 (Aux Fuel Gauge Switch)

(Install adjacent to auxiliary fuel gauge on/off switch on instrument panel)

Figure 11-19 – D3997-37 (Circuit Breaker (6.3A))

(Install adjacent to circuit breaker installation)

Figure 11-20 – D3997-39 (Circuit Breaker (2.5A))

(Install adjacent to circuit breaker installation)

Figure 11-21 – D3997-41 (Aux Fuel Tank Not Fitted)

(Install on back of D3997-25 for AS350 and on back of D3997-27 for EC130)

Figure 11-22 – D3997-43 (Tank Earth)

(Install on auxiliary fuel earth point)

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CHAPTER 28 – FUEL SYSTEM (28-00-00)

28.1 AUXILIARY FUEL TANK REMOVAL

Following initial installation as per Installation Instructions IIN-D350-794, the auxiliary fuel tank can be easily removed depending on operational requirements. An appropriately approved person certified to carry out maintenance should perform this task.

28.1.1 Drain or transfer all fuel. Note: The D350-794-041 tank cannot be completely drained when installed in aircraft. Some fuel will remain in tank during removal process. Drain remaining fuel when tank is removed. Disconnect the fuel sender lead and the two bonding leads. Open Auxiliary Tank circuit breakers and secure open using a zip tie under the head. Alternatively, remove fuse from the fuse holder if applicable.

28.1.2 Disconnect fuel supply line. Install an AN929-6D blanking cap to supply bulkhead and a plastic blank to supply hose.

28.1.3 Disconnect vent hose at lower rear vent pipe and install plastic blank on hose.

28.1.4 Remove fuel vent from top of tank and install plastic blank.

28.1.5 Remove hold down strap.

28.1.6 Remove vertical support bracket assembly.

28.1.7 Remove tank.

28.1.8 Install rear half of back panel and fairing around fuel filler tube.

28.1.9 Reverse Aux Fuel Gauge Conversion Placard adjacent to Auxiliary Fuel Tank Gauge to read “AUX

FUEL TANK NOT FITTED”.

28.1.10 Endorse appropriate documentation.

28.2 AUXILIARY FUEL TANK RE-INSTALLATION

Following initial installation as per Installation Instructions IIN-D350-794, the auxiliary fuel tank can be easily re-installed depending on operational requirements. An appropriately approved person certified to carry out maintenance should perform this task. The following torques apply to installation of fasteners when the auxiliary fuel tank is re-installed.

Table 28-1 – Fastener Torque

Size Torque

8-32 12-15 in-lbs 1.4-1.7 N-m

3/16”

1/4”

20-25 in-lbs

50-70 in-lbs

2.3-2.8 N-m

5.6-7.9 N-m

5/16”

3/8”

28.2.1 Remove any items from the locker.

100-140 in-lbs 11.3-15.8 N-m

160-190 in-lbs 18.1-21.5 N-m

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28.2.2 Remove cargo net.

28.2.3 Remove any floor protection.

28.2.4 Remove fairing from fuel filler tube and rear half of sidewall panel.

28.2.5 Perform Serviceability Inspection per Section 5.7

28.2.6 Tape fuel drain hoses up out of the way.

28.2.7 Slide tank carefully into position allowing vent pipe fitting to enter first.

28.2.8 Firmly push tank forward and inboard to sit down in retaining angles.

28.2.9 Install hold down strap.

28.2.10 Install vertical support bracket assembly p/n D4006-041 with two AN4-5A bolts and washers on the

AS 350. Use two AN4-6A bolts on the EC 130.

28.2.11 Clip drain hoses in position.

28.2.12 Remove blanking cap from fuel supply bulkhead fitting and supply hose. Install supply hose.

28.2.13 Install vent pipe to top of tank.

28.2.14 Connect vent hose to vent top pipe and lower vent tube.

28.2.15 Connect bonding leads and fuel sender wire.

NOTE:

Resistance across the bonding jumper is required to be 0.01 ohms or less.

28.2.16 Close Aux Fuel Tank circuit breakers and check operation of fuel transfer pump and fuel gauge.

28.2.17 Check Flight Manual for Auxiliary Fuel Tank Supplement Number: FMS-D350-794 (AS350), or

FMS-D130-794 (EC130B4).

28.2.18 Reverse “AUX FUEL TANK NOT FITTED” placard to show fuel gauge conversion chart.

28.2.19 Endorse appropriate documentation.

28.3 AUXILIARY FUEL TANK LONG TERM STORAGE

28.3.1 Tank should be kept in a clean, dry environment.

28.3.2 Flush tank every 12 months with 3 liters of fresh fuel.

28.4 FUEL QUANTITY GAUGE CALIBRATION

28.4.1 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.

28.4.2 Turn power off to the gauge and remove switch plate p/n D4014-1.

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28.4.3 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.

28.4.4 B..I will appear (Brightness Control Selection). Move the LRS switch from the L to R to choose I 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.

28.4.5 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.

28.4.6 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.

28.4.7 L.E.Ft will appear. Push the LRS switch to the L position and then to the R position.

28.4.8 L..O will appear on the fuel quantity gauge display. Press LRS switch momentarily to the S position and back to the R position.

28.4.9 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.

28.4.10 Keep repeating step 28.4.9 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.

28.4.11 SurE will appear. Push the LRS switch to the L position and then back to the R position.

28.4.12 r.t. will be displayed. Push the LRS switch to the S position momentarily. DonE will be displayed for 2 seconds.

28.4.13 Calibration has been completed successfully.

28.4.14 Push the LRS switch to the L position and hold in place by installing the switch plate p/n D4014-1.

Note: If a mistake is made after step 28.4.9 is started, the process must be re-started at 28.4.1

28.5 FUEL QUANTITY GAUGE ERROR MESSAGES AND FAULT RESOLUTION

28.5.1 During normal operations and the calibration process the instrument continually monitors operations to ensure that it operates in accordance with the necessary specifications.

28.5.2 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 28-1 below.

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1

2

3

Figure 28-1 – Error Message Indication

Table 28-2 – Error Message and Fault Resolution

Reserved

of Resolution

Occurrence

Reserved Contact Aerospace Logic Inc. Technical Support Department. You should never see this message.

Contact Aerospace Logic Inc. Technical Support Department. You should never see this message.

L..0

or r..0 of the calibration process during normal operations or calibration

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.

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5


of Resolution

Occurrence

L..0

or r..0 of the calibration process

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:


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. after

L..0

or r..0

Cause:

The fuel sender output has not changed since the last calibration reading.

Resolution:


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? i. If this point of travel is in agreement with the manufacturers stated travel, then go to Section 3 step 15 of FL-100-R Operations and Installation

Manual ii. If this point of travel is not in agreement with the 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 ¼ 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 ¾ 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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of Resolution

Occurrence

L..0

or r..0

Cause:

The fuel sender output has changed in the opposite orientation to that expected since the last calibration reading.

Resolution:


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 ¼ 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 ¾ 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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of Resolution

Occurrence

after

L..0

or r..0

Cause:

The fuel sender output exceeded the specified limits for the instrument.

Resolution:


1. Check that you have the correct instrument model for your sender:

Maximum Sender FL-100 Model

Resistance Required

44 Ω FL-100-R(44)

67 Ω FL-100-R(67)

109 Ω FL-100-R(109)

300 Ω FL-100-R

2. Is the fuel tank full? Go to Section 3 step 15 of FL-100-R

Operations and Installation Manual

3. 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.

4. 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 continuing. the calibration process is ended

Cause:

The instrument must be calibrated for a minimum of 10 gallons of fuel.

Resolution:

Continue the calibration process until a minimum of 10 gallons is reached.

Technical Support for the 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: [email protected]

www.aerospacelogic.com

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28.6 D350-794-141 TANK ASSEMBLY

The floor support may be removed from the D350-794-141 tank using Figure 28-2A/2B as a reference.

Figure 28-2A – Floor Support Installation (At CHG 005 or earlier)

Figure 28-2B – Floor Support Installation (At CHG 006 or later)

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28.7 ACCESS PANEL REMOVAL

28.7.1 Remove tank from the aircraft per Section 28.1.

28.7.2 Remove qty (8) AN3-5A bolts and qty (8) NAS1149D0363J washers from each D4577-041/-3/-5

Access Panels as required (see Figure 28-3).

28.7.3 Break the layer of sealant between the access panel and the tank and remove access panel.

Ensure that the tank and access panel finish is not damaged during this process.

28.8 ACCESS PANEL RE-INSTALLATION

28.8.1 Install D4577-041/-03/-5 Access Panels wet with Proseal 890. Install each panel with qty (8) AN3-

5A bolts and qty (8) NAS1149D0363J washers. Allow Proseal 890 to cure per manufacturer’s recommendations.

28.8.2 Perform the fuel leakage inspection per Section 5.6.

28.8.3 Reinstall tank in the aircraft per Section 28.2.2

Figure 28-3 – Access Panel Locations

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28.9 CUSHION REMOVAL AND INSTALLATION

28.9.1 Remove the D4968-3 or D4404-3/-5 Cushion(s) installed on the side of the tank and clean the residual adhesive off of the tank surface using an approved solvent.

28.9.2 Replace the cushion(s) with (qty 1) D4968-1 Cushion by applying a thin, uniform layer of contact cement (3M 1300/1301 Scotchgrip Adhesive) to the back of the cushion, then firmly press it into position on the side of the tank allowing approximately 1 inch of clearance around the edge of the tank. Trim to fit if required.

28.10 ELECTRICAL LOAD

The electrical load effect for each aircraft must be assessed as follows.

Component Load

Fuel Pump

Fuel Gauge

Fuel Sender

Total Installation

3.00 Amps

0.45 Amps

0.13 Amps

3.58 Amps = 100 Watts

28.11 WEIGHT AND BALANCE

The following is the weight increase associated with the Auxiliary Fuel Tank Kits. Be sure to subtract the weight of any parts or material removed.

Installation Weight Arm

LATERAL LONGITUDINAL

Moment Arm Moment

D350-794-011

Auxiliary Fuel Tank Installation

(AS350 models)

32.7 lb

14.8 kg

-22.0 in

-0.56 m

-719.4 in-lb

-8.29 m-kg

126.0 in

3.20 m

4120.2 in-lb

47.4 m-kg

D350-794-013

Auxiliary Fuel Tank Provisions

(AS350 models)

D130-794-021

Auxiliary Fuel Tank Installation

(EC130 models)

D130-794-023

Auxiliary Fuel Tank Provisions

(EC130 models)

D350-794-111

Auxiliary Fuel Tank

(AS350 models)

D130-794-121

Auxiliary Fuel Tank

(EC130 models)

5.5 lb

2.5 kg

32.7 lb

14.8 kg

5.5 lb

2.5 kg

44.6 lb

20.2 kg

44.6 lb

20.2 kg

-14.6 in

-0.37 m

-23.6 in

-0.60 m

-80.3 in-lb

-0.93 m-kg

-771.7 in-lb

-8.88 m-kg

-16.1 in

-0.41 m

-22.0 in

-0.56 m

-88.6 in-lb

-1.03 m-kg

-981.2 in-lb

-11.3 m-kg

-23.6 in

-0.60 m

-1052.6 in-lb

-12.1 m-kg

163.4 in

4.15 m

126.0 in

3.20 m

163.4 in

4.15 m

126.0 in

3.20 m

126.0 in

3.20 m

898.7 in-lb

10.4 m-kg

4120.2 in-lb

47.4 m-kg

898.7 in-lb

10.4 m-kg

5619.6 in-lb

64.6 m-kg

5619.6 in-lb

64.6 m-kg

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28.12 PARTS LIST

Qty Qty Qty Qty Qty

-011 -013 -021 -023 -041 Part

1 X D350-794-013

Superseded

Part Numbers Description

AUXILIARY FUEL TANK (AS 350 SERIES)

AUXILIARY FUEL TANK PROVISIONS

(AS 350 SERIES)

AUXILIARY FUEL TANK (EC 130 SERIES)


(EC 130 SERIES)

1 JCA/M47-1-01A

1

1

1

1

1

1

1

1

1

1

D4022-041

D4002-5

D4003-047

D4002-7

D4002-041

D4002-043

A8150-B1-JCA

ER281

JCA-M47-2-13

JCA-M47-2-16

JCA-M47-2-25

JCA-M47-1-13

JCA-M47-1-16

FUEL TRANSFER PUMP ASSEMBLY

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

1 1

1

2 2 AN924-6D NUT (ALTERNATE AS5178D06)

WASHER

2 2

1 1 D4022-3 05-00021

2 2

1 1 D4008-043 JCA-M47-2-29

UNION

ORING

FUEL PUMP MOUNTING BRACKET

BOLT

NUT

WASHER

FUEL PUMP SPLASH GUARD ASSEMBLY

N3

2 JCA-M47-4-01

1 D4008-041 JCA-M47-2-26

1 1 D4001-3 AN832-6D-JCA

AUXILIARY TANK FILLER SPLASH GUARD

SCREW

BULKHEAD FITTING – MODIFIED

VENT ASSEMBLY PARTS

CLAMP

1 1 D4003-11 JCA-M47-2-21 VENT PIPE – TANK

1 JCA-M47-2-20


1 1 JCA-M47-2-35

193-8

SPACER

SCREW

SCREW

WASHER

NUT 3 3

1 1 MS21919WDG-6 CLAMP (RUBBER REMOVED)

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-011 -013 -021 -023 -041 Part

Superseded


1 1 JCA-M47-4-01

1

1

1

1

1

1

D4005-1

D4004-11

D4004-5

3 3

JCA-M47-2-03

JCA-M47-2-11

JCA-M47-2-23

BONDING BRAID ASSEMBLY

RESTRAINT ASSEMBLY PARTS

1

1

1

1

1

1

D4024-041

D4004-041

D4007-3

1 1

JCA/ASSO/MIN ANCRA RESTRAINT STRAP

JCA-M47-2-19 SIDE RESTRAINT ANGLE

JCA-M47-2-18

JCA-M47-2-01

TOP SUPPORT BRACKET

TANK TOP SUPPORT ASSEMBLY

BOLT

WASHER

1 1 D4005-041 JCA-M47-2-22

193-6

LOCKER PREPARATION PARTS

FORWARD FLOOR GUTTER

1 1

3 3 NAS1474-08

REAR RESTRAINT ANGLE/GUTTER

TOP STRAP ATTACH BRACKET

BOTTOM STRAP ATTACH BRACKET

SCREW

NUT

WASHER

CLAMP

SCREW

WASHER

NUT

SEALED CAPTIVE ANCHOR NUT

SCREW

D8-603

(ALT. HA23-6U3)

D1-205

(ALT. HA21-2U5)

ELECTRICAL PARTS

6.3A ECF FUSE

2.5A ECF FUSE

SWITCH

107-964

107-978

(ALT. 105-5465)

107-943

VDO-M47-JCA

CONNECTOR BACKSHELL

1* D4025-1

143-207

143-208

143-204

(ALT. 973-1482)

143-203

(ALT. 973-1490)

143-219

(ALT. 977-3800)

143-217

(ALT. 977-3797)

1 1 JCA-M47-4-01

FUEL QUANTITY SENDER

SCREW

WASHER

NUT

PLUG

RECEPTACLE

RECEPTACLE HOUSING

PLUG HOUSING

CRIMP PIN

CRIMP SOCKET


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-011 -013 -021 -023 -041 Part

Superseded


1

2

1

1

2

1

D4026-041

AN525-832R6

D4290-7

1** 1** D4022-5

FL-100-R-JCA

444-2556

3775628

(ALT. 100-6847)

FUEL GAUGE ASSEMBLY

SCREW – GROUND STUD

WASHER

NUT

GAUGE MASTER SWITCH

THERMAL SWITCH (125°C) – FARNELL

GENERAL

1 1

ADDITIONAL EC 130 PARTS

SCREW

WASHER

NUT

1 JCA-M47-2-20

1 D4004-043 JCA-M47-2-04 SIDE RESTRAIN ANGLE AND TIE DOWN

POINT

1

1

D4007-1

D4005-3

JCA-M47-2-02

JCA-M47-2-05

TOP SUPPORT BRACKET

FORWARD RESTRAINT BEAM

BOLT

1

1

1

1

D3997-1

D3997-3

2* D3997-5

D3997-7

JCA-M47-P1

JCA-M47-P2

JCA-M47-P3

JCA-M47-P4

PLACARDS

FUEL QUANTITY – AS 350 MODELS

FUEL QUANTITY – EC 130 B4 MODEL

AUX FUEL DRAIN

AUX FUEL TRANSFER PUMP

1* JCA-M47-P6 WEIGHT

JCA-M47-P7 ON/OFF

1 1 D3997-15 JCA-M47-P8 CHECK LOCKER TANK

1* PROHIBITED

1

1

D3997-25

D3997-27

1* D3997-29

JCA-M47-P15

JCA-M47-P16

JCA-M47-P17

CONVERSION CHART – AS 350 MODELS

CONVERSION CHART – EC 130 B4 MODEL

DO NOT OVERFILL WARNING

JCA-M47-P18 ON/OFF

JCA-M47-P20

JCA-M47-P21

AUX FUEL GAUGE

6.3 A CIRCUIT BREAKER

1

1

1

1

D3997-35

D3997-37

1 1 D3997-41 JCA-M47-P23 AUX TANK NOT FITTED

1* EARTH

* - items included as part of D4055-041 tank assembly

** - items included as part of D4022-041 pump assembly

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1 X D350-794-013

Superseded

Part Numbers

1

1

1

1 1

1

1

1

1

1* D4577-041

1* D4577-1

1* D4577-3

1* D4023-3

5* AN3H5A

4* MS21042L3

4* AN3-6A

32* NAS1149D0363J

5* NAS1149D0332J

1

1

D4464-041

D4022-041

D4002-5

D4003-047

D4002-7

D4002-041

D4002-043

A8150-B1-JCA

JCA-M47-2-13

JCA-M47-2-16

JCA-M47-2-25

JCA-M47-1-13

JCA-M47-1-16

1 1

2 2 AN924-6D

Description

AUXILIARY FUEL TANK (AS 350 SERIES)


(AS 350 SERIES)

AUXILIARY FUEL TANK (EC 130 SERIES)


(EC 130 SERIES)

TANK ASSEMBLY

FUEL TRANSFER PUMP ASSEMBLY

FWD ACCESS PANEL ASSEMBLY

REAR ACCESS PANEL

MIDDLE ACCESS PANEL

FUEL CAP

BOLT

NUT

BOLT

WASHER

WASHER

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

2 2

1 1 D4022-3 05-00021

1 1

1

D4008-043

D4008-041

JCA-M47-2-29

N3

JCA-M47-2-26

1

1

1

1

D4001-3

D4003-11

AN832-6D-JCA

JCA-M47-2-21

NUT (ALTERNATE AS5178D06)

WASHER

UNION

ORING

FUEL PUMP MOUNTING BRACKET

BOLT

NUT

WASHER

FUEL PUMP SPLASH GUARD

AUXILIARY TANK FILLER SPLASH GUARD

SCREW

BULKHEAD FITTING – MODIFIED

VENT ASSEMBLY PARTS

CLAMP

VENT PIPE – TANK


193-8

SPACER

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Qty Qty Qty Qty Qty Superseded


SCREW

SCREW

WASHER

NUT

1 1

1

1

1

MS21919WDG-6

D4005-1

D4004-11

D4004-5

1

CLAMP (RUBBER REMOVED)


1

1

1

1

1

1

1

1

1

D4024-041

D4004-041

D4007-3

JCA-M47-2-03

JCA-M47-2-11

JCA-M47-2-23

JCA/ASSO/MIN

JCA-M47-2-19

JCA-M47-2-18

RESTRAINT ASSEMBLY PARTS

REAR RESTRAINT ANGLE/GUTTER

TOP STRAP ATTACH BRACKET

BOTTOM STRAP ATTACH BRACKET

SCREW

NUT

WASHER

ANCRA RESTRAINT STRAP

SIDE RESTRAINT ANGLE

TOP SUPPORT BRACKET

TANK TOP SUPPORT ASSEMBLY

BOLT

WASHER

1 1 D4005-041 JCA-M47-2-22

193-6

LOCKER PREPARATION PARTS

FORWARD FLOOR GUTTER

CLAMP

SCREW

WASHER

NUT

3 3 NAS1474-08 SEALED CAPTIVE ANCHOR NUT

1 1 STRIP

1 1

1 1

1 1

D8-603

(ALT. HA23-6U3)

D1-205

(ALT. HA21-2U5)

107-964

107-978

(ALT. 105-5465)

1 1 107-943

1* D4025-5

SCREW

ELECTRICAL PARTS

6.3A ECF FUSE

2.5A ECF FUSE

SWITCH

CONNECTOR BACKSHELL

1 1

1 1

143-207

143-208

FUEL QUANTITY SENDER

SCREW

WASHER

NUT

PLUG

RECEPTACLE

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Part Numbers

1 1 143-204

(ALT. 973-1482)

1 1 143-203

(ALT. 973-1490)

5 5 143-219

(ALT. 977-3800)

5 5 143-217

(ALT. 977-3797)

2

1

AN525-832R6

1** 1** D4022-5

444-2556

3775628

(Alt. 100-6847)

1 1

1 1

2

1

1

D4290-7

D4004-043 JCA-M47-2-04

Description

RECEPTACLE HOUSING

PLUG HOUSING

CRIMP PIN

CRIMP SOCKET


SCREW – GROUND STUD

WASHER

NUT

GAUGE MASTER SWITCH

THERMAL SWITCH (125°C) – FARNELL

GENERAL

CUSHION

ADDITIONAL EC 130 PARTS

SCREW

WASHER

NUT

SIDE RESTRAINT ANGLE AND TIE DOWN

POINT

1

1

D4007-1

D4005-3

JCA-M47-2-02

JCA-M47-2-05

TOP SUPPORT BRACKET

FORWARD RESTRAINT BEAM

BOLT

1

1

1

1

D3997-1

D3997-3

2* D3997-5

D3997-7

JCA-M47-P1

JCA-M47-P2

JCA-M47-P3

JCA-M47-P4

PLACARDS

FUEL QUANTITY – AS 350 MODELS

FUEL QUANTITY – EC 130 B4 MODEL

AUX FUEL DRAIN

AUX FUEL TRANSFER PUMP

1* JCA-M47-P6 WEIGHT

1 1 JCA-M47-P7 ON/OFF

1 1 D3997-15 JCA-M47-P8 CHECK LOCKER TANK

1* PROHIBITED

1 1 VENT

1 1 FIXED

1 1 FUEL

1 D3997-25 JCA-M47-P15 CONVERSION CHART – AS 350 MODELS

1

1*

D3997-27

D3997-29

JCA-M47-P16

JCA-M47-P17

CONVERSION CHART – EC 130 B4 MODEL

DO NOT OVERFILL WARNING

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1 1 JCA-M47-P18 ON/OFF

1 1 JCA-M47-P19 AUX

1 1 D3997-35 JCA-M47-P20 AUX FUEL GAUGE

1 1 D3997-37 JCA-M47-P21 6.3 A CIRCUIT BREAKER

1 1 JCA-M47-P22 2.5A

1 1 D3997-41 JCA-M47-P23 AUX TANK NOT FITTED

1* JCA-M47-P24 EARTH

* - items included as part of D4464-041 tank assembly

** - items included as part of D4022-041 pump assembly

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28.13 AS350 INSTALLATION

ICA-D350-794

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28.14 EC130 INSTALLATION

ICA-D350-794

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CHAPTER 98 – WIRING DIAGRAMS (98-00-00)

ICA-D350-794

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ICA-D350-794-Rev8

Figure 0-1 – D350-794/D130-794 Auxiliary Fuel Tank Installation

Figure 11-1 – D3997-1 (Fuel Quantity AS350 Models)

(Install adjacent to auxiliary fuel tank filler)

Figure 11-2 – D3997-3 (Fuel Quantity EC 130 B4 Models)

(Install adjacent to auxiliary fuel tank filler)

Figure 11-3 – D3997-5 (Aux Drain)

(Install adjacent to auxiliary fuel tank drain)

Figure 11-4 – D3997-7 (Pump Switch)

(Install adjacent to pump switch on instrument panel – if installed)

Figure 11-5 – D3997-9 (Switch Panel)

(Install in aircraft switch panel)

Figure 11-6 – D3997-11 (Weight and Balance)

(Install on tank outboard surface)

Figure 11-7 – D3997-13 (Switch On/Off)

(Install around fuel pump on/off switch (if fitted))

Figure 11-8 – D3997-15 (Locker Door)

(Install on baggage locker outer surface below release button)

Figure 11-9 – D3997-17 (Stowage Warning)

(Install on tank outboard surface)

Figure 11-10 – D3997-19 (Tank Vent)

(Install on all tank exterior vent tubes)

Figure 11-11 – D3997-21 (Switch Fixed)

(Install on aux. fuel gauge switch plate)

Figure 11-12 – D3997-23 (Aux Fuel)

(Install on aux fuel gauge)

Figure 11-13 – D3997-25 (Conversion AS 350)

(Install next to aux fuel gauge)

Figure 11-14 – D3997-27 (Conversion EC130B4)

(Install next to aux fuel gauge)

Figure 11-15 – D3997-29 (Do Not Overfill Warning)

(Install adjacent to auxiliary fuel tank filler)

Figure 11-16 – D3997-31 (Aux Fuel Gauge Switch On/Off)

(Install around auxiliary fuel gauge on/off switch on instrument panel)

Figure 11-17 – D3997-33 (Aux Fuel Gauge Face)

(Install on auxiliary fuel gauge cover)

Figure 11-18 – D3997-35 (Aux Fuel Gauge Switch)

(Install adjacent to auxiliary fuel gauge on/off switch on instrument panel)

Figure 11-19 – D3997-37 (Circuit Breaker (6.3A))

(Install adjacent to circuit breaker installation)

Figure 11-20 – D3997-39 (Circuit Breaker (2.5A))

(Install adjacent to circuit breaker installation)

Figure 11-21 – D3997-41 (Aux Fuel Tank Not Fitted)

(Install on back of D3997-25 for AS350 and on back of D3997-27 for EC130)

Figure 11-22 – D3997-43 (Tank Earth)

(Install on auxiliary fuel earth point)

Table 28-1 – Fastener Torque

Figure 28-1 – Error Message Indication

Figure 28-2A – Floor Support Installation (At CHG 005 or earlier)

Figure 28-2B – Floor Support Installation (At CHG 006 or later)

Figure 28-3 – Access Panel Locations

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