# ASB No. EC155-53A031

Revision 0 2011-05-03

. Approved under EASA DOA No. 21J.056. Page 1/33

Revision 1 2011-09-21 This document is available on the Internet: www.eurocopter.com/techpub 

### Civil versions: B, B1

Military versions: F, Fi, Fs, K



# ALERT SERVICE BULLETIN

SUBJECT : FUSELAGE

Draining tank box area

Corresponds to modifications 0745C96, 0753C98,

365A084485.00



### Revision No. Date of issue

Revision 0 2011-05-03

Revision 1 2011-09-21



### Summary :

Modification to draining system of tank boxes.

For aircraft equipped with emergency buoyancy FP (Fixed Parts), this modification consists of:

- canceling one drain plug per fuel tank compartment in order to make drain possible (except for center tanks),

- creating a new drain point for each RH and LH center tank compartment,

- installing self-sealing drain valves replacing previously-removed drain plug s or on newly-performed drains, in

order to guarantee compartment sealing in case of ditching.

For aircraft not equipped with emergency buoyancy FP, this modification consists of:

- canceling one drain plug per fuel tank compartment in order to make drain possible.



### Reason for last revision :

- For aircraft equipped with emergency buoyancy FP:

. propose a new operational procedure to create new drain points without disassembling center tanks.

- Take into account customer feedback.



### Compliance :

Compliance with this Alert Service Bulletin is mandatory. For the attention of

# ASB No. EC155-53A031

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### 1. PLANNING INFORMATION

CAUTION

THE INFORMATION AND INSTRUCTIONS IN THIS

SERVICE BULLETIN ARE INTENDED FOR

MAINTENANCE PERSONNEL.



### 1.A. EFFECTIVITY

1.A.1. Helicopters/installed equipment

Helicopters:

- pre-modifications 0753C98 and 0745C96,

or

- pre-modification 365A084485.00.

1.A.2. Non-installed equipment

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

The purpose of this Alert Service Bulletin Revision 0 wa s to improve draining of the helicopter tank boxes by:

- canceling some drain plugs in order to drain tank compartments,

- installing self-sealing drain valves for aircraft equipped with buoyancy FP.

The purpose of this Alert Service Bulletin Revision 1 is to:

- in order to reduce the grounding time, propose for aircraft equipped with emergency buoyancy FP and

panels under bottom structure (u) (see photo page 11), a new operational procedure to create new drain

points without disassem bling center tanks,

- take into account customers feedback.



### NOTE

Aircraft not equipped with panels under bottom structure (u)

must mandatorily disassemble center tanks to create new

drain points.

Revision 1 of this Alert Service Bulletin does not question compliance with Revision 0.

Revision 1 of this Alert Service Bulletin will be subject to EASA Airworthiness Directive.

# ASB No. EC155-53A031

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### 1.D. DESCRIPTION

For aircraft equipped with emergency buoyancy FP :

- remove drain plug located on:

. front tanks at X2800 / Y570 and Y-570,

. intermediate tank at X4920 / Y360,

. rear tank (if equipped) at X5927 / Y-73,

- create two new drain points (on the center tanks) at X3207 / Y408 and Y-408,

- install a self-sealing drain valve on:

. front tanks at X2800 / Y570 and Y-570,

. center tanks at X3207 / Y408 and Y-408,

. intermediate tank at X4920 / Y360,

. . rear tank at X5927 / Y-73.

For aircraft not equipped with emergency buoyancy FP :

- remove drain plug located on:

. front tanks at X2800 / Y570 et Y-570,

. center tanks at X3193 / Y576 et Y-576,

. intermediate tank at X4920 / Y360,

. rear tank (if equipped) at X5927 / Y-73.



### 1.E. COMPLIANCE

1.E.1. Compliance at the works

1.E.1.a. Helicopters/installed equipment

According to facilities install ed or not on the aircraft (emergen cy buoyancy FP and/or the 6 th tank), comply

with the different paragraphs of Paragra ph 3.B. of this Alert Service Bulletin.



### NOTE

Modifications 0753C98 and 0745C96 (if aircraft equipped

with buoyancy FP) are incorporat ed in the definition of new

helicopters delivered from Januar y 01, 2012. This date is

given for information only, refer to the Individual Inspection

Log Book (RIC-AMS), the Equipment Log Cards (FM) or the

aircraft Log Book to identify the actual modification status of

the aircraft.

1.E.1.b. Non-installed equipment

Not applicable.

1.E.2. Compliance in service

1.E.2.a. Helicopters/installed equipment

EUROCOPTER makes mandatory compliance with this Alert Service Bulletin.

The works must be performed on helicopter by the Operator.

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Apply § 3. except § 3.B.2.b., within 24 months as from receipt of this Alert Service Bulletin, published at

the date mentioned in page footer.

1.E.2.a.2. Helicopters not equi pped with emergency buoyancy FP

Apply § 3. except § 3.B.2.a., during the next schedul ed inspection without exceeding 110 flight hours as

from receipt of this Alert Service Bulletin, published at the date mentioned in page footer.

1.E.2.b. Non-installed equipment

Not applicable.



### 1.F. APPROVAL

Approval of modifications :

The information or instructions relating to modifi cation 0753C98 was approved on February 09, 2011 under

the authority of EASA Design Organizati on Approval No. 21J.056 for civil version helicopters subject to an

Airworthiness Certificate.

The information or instructions relating to modifi cation 0745C96 was approved on February 09, 2011 under

the authority of EASA Design Organizati on Approval No. 21J.056 for civil version helicopters subject to an

Airworthiness Certificate.

The information or instructions relating to modifi cation 365A084485.00 was approved on February 09, 2011

under the authority of EASA Design Organization Approval No. 21J.056 for civil version helicopters subject to

an Airworthiness Certificate.

Approval of this document :

The technical information contained in this Alert Service Bulletin Revision 0 was approved on April 29, 2011

under the authority of EASA Design Organization Approval No. 21J.056 for civil version helicopters subject to

an Airworthiness Certificate.

The technical information contained in this Alert Service Bulletin Revision 1 was approved on

September 20, 2011 under t he authority of EASA Design Organiza tion Approval No. 21J.056 for civil

version helicopters subject to an Airworthiness Certificate.

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### 1.G. MANPOWER

1.G.1. Manpower (MOD 0753C98 and 0745C96)

1.G.1.a. Manpower with re moval of center tanks

For compliance with this Alert Service Bulletin, EUROCOPTER recommends the following personnel

qualifications:

Qualification: 2 Airframe Technicians.

Time for the operations is indicated for reference, for a standard configuration.

Time for the operations:

- 80 hours approximately for the Airframe Technicians (polymerization time for sealing mixture excluded).

Estimated helicopter grounding time: 10 days approximately.

1.G.1.b. Manpower without removal of center tanks

For compliance with this Alert Service Bulletin, EUROCOPTER recommends the following personnel

qualifications:

Qualification: 2 Airframe Technicians.

Time for the operations is indicated for reference, for a standard configuration.

Time for the operations:

- 8 hours approximately for the Airfra me Technicians (polymerization time for sealing mixture excluded).

Estimated helicopter grounding time:

- 1 day 1⁄2 approximately (polymerization time for sealing mixture excluded).

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For compliance with this Alert Service Bulletin, EUROCOPTER recommends the following personnel

qualifications:

Qualification: 1 Airframe Technician.

Time for the operations is indicated for reference, for a standard configuration.

Time for the operations:

- 1 hour approximately for the Airframe Technician.

Estimated helicopter grounding time: 1 hour 1⁄2 approximately.



### 1.H. WEIGHT AND BALANCE

1.H.1. Weight and balance (MOD 0753C98)

Weight: Weight negligible.

Moment : Moment negligible.

1.H.2. Weight and balance (MOD 0745C96)

Weight : + 0.228 kg.

Moment:

- Longitudinal moment: + 1.29 m.kg.

- Lateral moment: + 0.01 m.kg.

1.H.3. Weight and balance (MOD 365A084485.00)

Weight : Weight negligible.

Moment : Moment negligible.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.

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### 1.K. REFERENCES

The following documents are required for compliance with this Alert Service Bulletin:

AMM : 05-22-00-213 : 15–Hour Inspection,

AMM : 24-00-00-911 : General Safety Instructions – Electrical Power,

AMM : 28-11-03-061 : Removal / Installation – Center Left Fuel Tank,

AMM : 28-11-04-061 : Removal / Installation – Center Right Fuel Tank,

MTC: 20.02.05.401 : ASSEMBLY – Assembly with rivets.

MTC: 20.02.06.101 : LOCKING AND BL OCKING OF ASSEMBLIES – General.

MTC: 20.02.06.402 : LOCKING AND BLOCKING OF ASSEMBLIES – Locking with lockwire.

MTC: 20.03.02.406 : GENERAL RIVET REPLACEM ENT PRINCIPLES – "CHERRY-MAX" rivets

A.S.N.A 0077 and 0078.

MTC: 20.06.01.101 : BONDING WITH ADHESIVES – General rules for bo nding with adhesives.

MTC: 20.06.01.102 : BONDING WITH ADHESIVES – Bonding method.

MTC: 20.06.01.411 : COMPOS ITE STRUCTURE REPAIR – BONDING WITH ADHESIVES –

HYSOL EA 9396.

MTC: 20.06.04.101 : USE OF MIXTURES – General information on mixtures.

MTC: 20.06.04.303 : USE OF MIXTURES – Casting No. 11 mixture.

MTC: 20.07.02.201 : SAFETY INSTRUCTIONS – Helicopter parked in a hangar.

MTC: 20.07.03.406 : TECHNICAL INSTRUCTIONS – Inst ructions applicable when working on an aircraft

electrical circuit or when energizing aircraft power generating systems on ground.

MTC: 20.07.03.408 : TECHNICAL INSTRUCTIONS – Genera l principles applicable for visual cleanliness

and appearance checks on an aircraft after an inspection or a repair.



### 1.L. DOCUMENTS AFFECTED

Document to be updated :

The modification will be incorporated in the following manuals: IPC and AMM.

Document already updated :

Not applicable.



### 1.M. INTERCHANGEABILITY AND MIXABILITY BETWEEN THE PARTS

Interchangeability :

Not applicable.

Mixability :

Not applicable.

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### 2. MATERIAL INFORMATION

2.A. MATERIAL: PRICE - AVAILABILITY - PROCUREMENT

Kits and/or components will be delivered in spec ial pricing conditions until December 31, 2012.

EUROCOPTER

Etablissement de Marignane

Direction VENTES et Relations Client (ECR)

13725 MARIGNANE CEDEX

FRANCE



### NOTE

On the purchase order, please specify the mode of

transport, the destination and the serial numbers of the

aircraft to be modified.



### NOTE

For ALERT SERVICE BULLETINS, order by:

Telex: HELICOP 410 969F

Fax: +33 (0)4.42.85.99.96.



### 2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

For any information concerning the modification kits and/or components or assistance, contact the

EUROCOPTER network's Customer Support Sales Department.



### 2.C. MATERIAL REQUIRED FOR EACH HELICOPTER/COMPONENT

Kits or components to be ordered for one helicopter or one assembly only if equipped with emergency

buoyancy FP :

Components required for aircraft modification.

Order components listed below according to modifications to be incorporated.

Designation Qty New

P/N It. Old

P/N Instruction

1 Drain plug support 2 365A21-4019-20 1

2 Rivet 5 ASNA0078A401

(CHERRY-MAX) 2

3 Self-sealing drain valve 6 ENCCDM12 3

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Designation Qty New

P/N CM It. Old

P/N Instruction

Lockwire 4 m EN3628-0,8 CM776 4

Products to be ordered separately :

As per Work Cards mentioned in this Alert Service Bulletin and list below:

Designation Qty Product P/N CM It.

Adhesive compound, 1 L container

(HYSOL EA 9396) 0.1 kg ECS0010.10 CM616 5

Sealing mixture

(Casting No. 11 mixture) 0.2 kg DHS268-112.20 6

Material supplied by the operator :

Not applicable.

Material required for non-installed components :

Not applicable.

Specific tooling :

As per Work Cards mentioned in this Alert Service Bulletin.



### 2.D. MATERIAL TO BE RETURNED

Not applicable.

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### 3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

- Comply with electrical power supply instructions as per AMM Task 24-00-00-911.

- Refer to safety instructions as per MTC Work Card 20.07.02.201 to park a helicopter in a hangar.

- Use adhesives as per MTC Work Cards 20.06.01.101 and 20.06.01.102.

- Carry out assemblies by riveting as per MTC Work Card 20.02.05.401.

- Carry out assemblies by locking as per MTC Work Card 20.02.06.101.

- During the use of mixtures, be informed of the general information on mixtures as per MTC Work Card

20.06.04.101.



### 3.B. OPERATIONAL PROCEDURE

3.B.1. Preliminary steps

- Disconnect all electrical supply sources as per MTC Work Card 20.07.03.406.

- Install suitable access means.

- Remove and/or open all panels, padding and equipment as required for easy access to different work

zones.

3.B.2. Procedures

3.B.2.a. Helicopter equipped with emergency buoyancy FP

3.B.2.a.1. Removal of drain plugs (MOD 0753C98)

As per Figure 1

- Remove the 4 drain plugs (b):

. 1 plug on the front RH tank at X2800 / Y570,

. 1 plug on the front LH tank at X2800 / Y-570,

. 1 plug on the intermediate tank at X4920 / Y360,

. 1 plug on the rear tank at X5927 / Y-73,

and store them back in the warehouse.

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Two operational procedures for the insta llation of new drain points are proposed:

- for aircraft not fitted with panel (u) and symmetrical panel (see Photo below):

. installation of new drain points with removal of center tanks (§ 3.B.2.a.2.a.),

- for aircraft fitted with panel (u) and symmetrical panel (see Photo below):

. installation of new drain po ints without removal of cent er tanks (§ 3.B.2.a.2.b.),



### NOTE

Panel (u) is located on the RH side of the aircraft (at X3276 /

Y496), a second panel is symmetrically located on the LH

side (at X3276 / Y-496). These two panels allow drain plugs

to be installed without removing center tanks.

For aircraft equipped with panel (u) and symmetrical panel , the selection of either of these operational

procedures is left to the operator's initiative. Fo r aircraft not equipped with panel (u) and symmetrical

panel, removal of center tanks is mandatory.

Photo : panel under bottom structure

u

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Remove the RH and LH center tanks as per AMM Tasks 28-11-04-061 and 28-11-03-061.

As per Figure 3



### NOTE

The procedure below describes the operations to be

performed on the RH si de of the aircraft. Operations on the

LH side are symmetrical.

- Drill 1 through hole (G ) (both skins of NIDA) to diameter 18 mm.

- Counterdrill hole (G) to diameter 22 mm th rough the first skin of NIDA (outer side).

- Drill 2 holes (H) to diameter 1.5 mm through the seco nd skin of NIDA (inner side). Both holes will be

used as filling and vent holes for sealing mixture (6).

- Drill NIDA to diameter 26 mm.

- Install drain plug support (1):

. by means of 2 rivets (2) as per MTC Work Card 20.03.002.406,

. by interlaying adhesive compound (5) as per MTC Work Card 20.06.01.411.

- Inject sealing mixture No. 11 (6) through holes (H) and let polymerize as per MTC Work Card

20.06.04.303.

- Perform the same operations (see above-me ntioned §) on the LH side of the aircraft.

Install the RH and LH center tanks as pe r AMM Tasks 28-11-04-061 and 28-11-03-061.

3.B.2.a.2.b. Installation of new drain points without removal of center tanks



### NOTE

The procedure below describes the operations to be

performed on the RH si de of the aircraft. Operations on the

LH side are symmetrical.

As per Figure 5

- Remove blanking plate (u) and retain its attachments (plate on which a drain plug is positioned)

(Photos A1 and B1).

According to the aircraft equipment, this plate can hold an antenna; in this case, disconnect the

antenna connector.



### NOTE

Removal of panel (u) makes it possible to check cleanliness

of the front tank compartment, during and after the

modification.

- Carry out marking/positioning of the new drai n plug by taking the dimension (Photo C1):

. at + 68 ± 2 mm from the theoretical profile of frame at 9°,

. at Y408.

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### CAUTION

DURING THE PROCEDURE AND PARTICULARLY

DURING DRILLING OPERATIONS (INTERNAL AND

EXTERNAL COATINGS), TREPANNING AND BORING,

MAKE SURE THAT:

- YOU DO NOT DAMAGE THE DIFFERENT EQUIPMENT

LOCATED IN THE TANK COMPARTMENT

(PARTICULARLY THE TANK),

- THERE IS NO FOREIGN BODY IN THE TANK

COMPARTMENT (CHIPS, FILINGS, TOOLS,...),

- THE FUEL TANK COMPARTMENT IS CLEAN.

As per Figure 6



### - Inside the tank box, position adhesive tape (aa) on the inner coating of the first drilling (Detail U1 and

Photo V1). This is to prevent chip projection inside the tank box.

- Drill hole G through (external and internal) coatings to diameter 4.2 mm, by respecting perpendicularity

of the drilling with respect to (externa l and internal) coatings (Photo E1).

- Trepan the external coating to diameter 20 mm (Photo F1).

As per Figure 7

- Drill honeycomb to diameter 37 mm, then clean by suction (Photo G1 and detail D1).



### - Trepan the inner coating to diameter 17 mm making sure to machine the coating only without passing

through adhesive tape (aa) previously positioned. The adhesive tape enables filings to be collected

during drilling and trepanning, and prevents any filing projection inside the tank box; these filings

mainly remain trapped in adhesive tape (aa) (Photos H1 and J1, and Detail D1)).

- Remove adhesive tape (aa) and clean the trepanned area (Photo J1).

As per Figure 8

- Position drain plug support (1) and point the 2 rivet holes (2) (Photo K1).

- Drill the 2 rivet holes to diameter 3.2 mm on the ex ternal coating and make sure that the honeycomb is

sufficiently drilled on the 2 holes (Photo K1 and Detail Q1).

- Make sure that the area is completely cleaned.

- Bond drain plug support (1) using adhesive comp ound (5) as per MTC Work Card 20.06.01.411,

positioning it with "Spincers" (ab) (Photo L1, and Details Q1 and R1).

As per Figure 9

- Slowly inject sealing mixture No. 11 (6) through t he first rivet hole until it goes out through the periphery

of hole diameter 17 mm of the inner coating as per MTC Work Card 20.06.04.303 (Photo M1 and

Detail T1). Rivet firstly drain plug support (1) through the first filling hole by means of a rivet (2) as per

MTC Work Card 20.03.02.406 (Photo P1, and Details S1 and T1):

The operation must be carried out by 2 persons (Photos N1 and M1, Detail T1):

. the first person inject s the sealing mixture,

. the second person checks with mirror (ac) (i nside the fuel compartment) until the mixture

appears at the periphery of drain plug support (1).

- Clean the excess sealing mixture.

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Revision 1 2011-09-21 This document is available on the Internet: www.eurocopter.com/techpub - Then, inject sealing mixture No. 11 (6) through t he second rivet hole. Apply the same procedure as

before in order to improve the filling (Photo M1).

- Secondly, rivet drain plug support (1) through the second filling hole with rivet (2) as per MTC Work

Card 20.03.002.406 (Photo P1, and Details S1 and T1).

- Clean the excess sealing mixture.

- Clean the internal and external area and let polymerize.

As per Figure 5



### - Re-install blanking plate (u) by means of attach ments previously retained (Photo A1). If the antenna

is installed on the plate, reconnect the antenna connector.

Perform the same operations (mentioned in § above) on the LH side of the aircraft.

3.B.2.a.3. Installation of self-sealing drain valves (MOD 0745C96)

As per Figure 4

- Install 6 valves (3):

. 1 valve on the front RH tank at X2800 / Y570,

. 1 valve on the front LH tank at X2800 / Y-570,

. 1 valve on the RH center tank at X3207 / Y408,

. 1 valve on the LH center tank at X3207 / Y-408,

. 1 valve on the intermediate tank at X4920 / Y360,

. 1 valve on the rear tank at X5927 / Y-73,

. direct holes (T) of all valves (3 ) towards the rear of the aircraft,

. torque to between 1.3 and 1.7 m.daN (115.1 – 150.5 lbf.in),

. lock all the valves by means of lockwire (4) as per MTC Work Card 20.02.06.402.

3.B.2.b. Helicopter not equipped with emergency buoyancy FP

Removal of drain plugs (MOD 365A084485.00) as per Figure 2

- Remove the 6 drain plugs (b):

. 1 plug on the front RH tank at X2800 / Y-570,

. 1 plug on the front LH tank at X2800 / Y-570,

. 1 plug on the RH center tank at X3193 / Y576,

. 1 plug on the LH center tank at X3193 / Y-576,

. 1 plug on the intermediate tank at X4920 / Y360,

. 1 plug on the rear tank at X5927 / Y-73,

and store them back in the warehouse.

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Not applicable.

3.B.4. Final steps

- Remove access means installed in § 3.B.1.

- Perform a visual cleanliness and appearance check as per MTC Work Card 20.07.03.408.

- Reconnect all electrical supply sources disconnec ted in § 3.B.1 as per MTC Work Card 20.07.03.406.

- Re-install and/or close all the padding, panels and equipment removed and/or opened when restoring the

aircraft to flight conditions (§ 3.B.1.).

3.B.5. Ground run-up / flight test

Not applicable.

3.B.6. Operational procedure on non-installed equipment

Stock retrofitting :

Not applicable.

Stock replacement, stock sc rapping and stock building-up :

Stock building-up of spare parts, in particular self -sealing drain valves P/N ENCCDM12, related to the

compliance of this Alert Service Bulleti n is left to the operator's initiative.



### 3.C. IDENTIFICATION

Identification of this document :

Record compliance with this Alert Serv ice Bulletin in the aircraft documents.

Identification of modifications in the documents :

As per incorporated modifications, record compliance with modifications 0753C98 and 0745C96, or

modification 365A084485.00 in the aircraft documents.

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### 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Operating instructions :

Not applicable.

Maintenance instructions:

Refer to AMM Task 05-22-00-213 and:

§ 6 FUSELAGE STRUCTURE LH SIDE

Tank compartment and sealed compartments under the

cabin

- Existing drain plugs Open and close.

- Self-sealing valves (if installed) Ch eck each valve for correct operation by

actuating the float with the push-button.

§ 12 FUSELAGE STRUCTURE RH SIDE

Tank compartment and sealed compartments under the

cabin

- Existing drain plugs Open and close.

- Self-sealing valves (if installed) Ch eck each valve for correct operation by

actuating the float with the push-button.

The Aircraft Maintenance Manual (AMM) will incorporate this instruction at the time of a further revision. After

incorporation of this instruction in the Ai rcraft Maintenance Manual (AMM), refer to it.ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 17/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 1ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 18/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 19/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 2ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 20/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 21/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 3ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 22/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 23/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 4ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 24/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 25/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 5ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 26/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 27/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 6ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 28/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 29/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 7ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 30/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 31/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 8ASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 32/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYASBNo. EC155-53A031Revision 0 2011-05-03Approved under EASA DOA No. 21J.056.Page 33/33Revision 1 2011-09-21This document is available on the Internet:www.eurocopter.com/techpubFigure 9