# ASB No. EC155-05A027

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### Civil version: B, B1



# ALERT SERVICE BULLETIN

SUBJECT: TIME LIMITS - MAINTENANCE CHECKS - External life rafts installed in the footsteps

Check of the deployment system of th e external life rafts located in the footsteps

ATA 25



### Revision No. Date of issue

Revision 0 2014-06-12

Revision 1 2014-09-01



### Summary:

Check for corrosion and measurement of the operational clea rance in the junction units of the external life raft installation in the footstep.



### Reason for last Revision:

Revision 1 of this ALERT SERVIC E BULLETIN consists in adding: - modifications to the junction unit illustrations. - details concerning compliance with AMM Task 25-69-01-721.



### Compliance:

Airbus Helicopters renders compliance with this ALERT SERVICE BULLETIN mandatory, except for paragraph 3.D. For the attention of

# ASB No. EC155-05A027

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### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters/installed equipment

Helicopters equipped with external life rafts in the footsteps, with junction units with Part Number (MP/N) 200188 (P/N 704A341302.30).

1.A.2. Non-installed equipment

On junction units with Part Number (MP/N) 200188 (P/N 704A341302.30).



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

On an AS365 helicopter, during the maintenance operat ion scheduled at 600 flying hours or 24 months on the external life rafts located in the footstep, the life raft deployment test carried out by the operator by pulling the LH internal deployment handle did not function correctly.

Investigations revealed the presence of corrosion in side the LH junction unit MP/N 200197. The deployment

handle was blocked due to this corrosion.

Some EC155 version B and B1 helicopters are equipped with similar junction units with Part Number (MP/N) 200188.

Consequently, pending a definitive solution and in order to prevent any risk of blockage in the external life raft deployment control system, Airbus Helicopters makes compliance with the instructions of this ALERT SERVICE BULLETIN mandatory, except for paragraph 3.D.

Revision 1 does not affect compliance with Revision 0 of this ALERT SERVICE BULLETIN.

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### 1.D. DESCRIPTION

Compliance with this ALERT SERVICE BULLETIN Revision 0 consisted in:

- Checking that the drainage hole blank, located on th e RH and LH junction units of the external life raft

installation, is correctly positioned. - Measuring the operational clearance between the junction unit pulleys and cover. - Checking that there is no corrosion inside the junction units. - If necessary, removing the corrosion from the cover surface and/or pulleys of the junction unit(s).

This ALERT SERVICE BULLETIN Revision 1 consists in:

- Adding modifications to the illustrations of the juncti on unit, in order to comply with its dimensions and

geometry. - Specifying the acceptable tensile loads during co mpliance with AMM Task 25-69-01-721, by adding

paragraph 4.B. and modifying the fl ow chart in paragraph 1.E.2. - Modifying part of the wording in paragraph 1.E.2. - Limiting compliance with this ALERT SERVICE BULLETI N required in the flow chart to paragraphs 3.A. and

3.B.



### 1.E. COMPLIANCE

1.E.1. Compliance at the works

Helicopters/installed equipment:

Not applicable.

Non-installed equipment:

Before delivery, comply with paragraph 3.B.6. on t he junction units specified in paragraph 1.A.2.

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The work on the helicopter is to be performed by the operator.

Helicopters/installed equipment:

- Comply with this ALERT SERVICE BULLETIN within the time limits defined in the flowchart below:

NO Time limits for compliance

with this ALERT SERVICE

BULLETIN

Comply with AMM Task 25-69-01-721 before the next mission for which life rafts are needed following receipt of this ALERT SERVICE BULLETIN Revision 1, iss ued on the date indicated at the bottom of the page.

YES

Comply with paragraphs 3.A. and 3.B. o f

this ALERT SERVICE BULLETIN within 110 flying hours following compliance

with AMM Task 25-69-01-721

.

Comply with paragraphs 3.A. and 3.B.

of this ALERT SERVICE BULLETIN no later than within 15 days following compliance with AMM Task

25-69-01-721. Comply with paragraphs 3. A . and

3.B. of this ALERT SERVICE

BULLETIN before the next

mission for which life rafts are

needed.

Fill in and return the list of the checked juncti on units (list given in the Appendix) within 1 month following compliance with paragraph s 3.A. and 3.B. of this ALERT SERVICE

BULLETIN Revision 1. - If corrosion is found, send the list of c hecked junction units along with photos of

the corroded unit (before rework of the unit).

. Contact the Airbus Helicopters Technical Support Department: Fax: + 33 (0)4.42.85.99.66.

E-mail: Support.Technical-Optionnal@airbus.com

END NO

YES Are the tensile loads compliant

with AMM Task 25-69-01-721 and paragraph 4.B. of this ASB?

Did the snap wire break? A pply a maximum load of 29 DaN (65.195 lbf) to one of the two handles during compliance with AMM

Task 25-69-01-721.

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Revision 1 2014-09-01 This document is available on the internet: www.airbushelicopters.com/techpub - For helicopters, regardless of whether or not t hey carry out missions for which life rafts are needed:

. In order to ensure that the operational clearance is checked and measured within a controlled calendar

time limit

, Airbus Helicopters makes compliance with paragraph 3. of this ALERT SERVICE BULLETIN mandatory, no later than within 3 months following re ceipt of this ALERT SERVICE BULLETIN, issued on the date indicated at the bottom of the page.

Non-installed equipment:

At the latest before installation on the helicopter, comply with paragraph 3.B.6. on the junction units specified in paragraph 1.A.2.



### 1.F. APPROVAL

Approval of modifications:

Not applicable.

Approval of this document:

The technical information contained in this AL ERT SERVICE BULLETIN Revision 0 was approved
on June 11, 2014 under the authority of EASA Design Organization A pproval No. 21J.056 for helicopters of civil versions subject to an Airworthiness Certificate.

The technical information contained in this AL ERT SERVICE BULLETIN Revision 1 was approved on September 01, 2014 under the authority of EASA Design Organization A pproval No. 21J.056 for helicopters of civil versions subject to an Airworthiness Certificate.



### 1.G. MANPOWER

For compliance with this ALERT SERVICE BULLETIN, Airbus Helicopters recommends the following personnel qualifications:

Qualification: 1 Mechanical Engineering Technician

The time for the operations is given for information purposes, for a standard configuration.

Time for the operations: 6 hours for 1 Mechanical Engineering Technician



### 1.H. WEIGHT AND BALANCE

Not applicable.

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### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.



### 1.K. REFERENCES

The documents required for compliance with this ALERT SERVICE BULLETIN are as follows:

MTC: 20.02.01.418: General - Protection of elec trical wiring during maintenance operations

MTC: 20.04.03.401: Corrosion inhi biting and removal procedures - General method for reconditioning

corroded metal surfaces MTC: 20.04.04.403: Surface treatment before painting - Touch-up of protective treatment with Alodine 1200 MTC: 20.04.05.434: Paint and primer application proc edure - Application of metal primer scheme P50

AMM: 25-69-01-063: External life raft insta llation - Removal/installation of life rafts

AMM: 25-69-01-061: Life raft - Removal/inst allation of the life raft deployment controls

AMM: 25-69-01-721: Life raft - Functional te st of the life raft deployment control system



### 1.L. DOCUMENTS AFFECTED

Airbus Helicopters will modify the Aircraft Maintenance Manual (AMM) with respect to this ALERT SERVICE

BULLETIN.

The affected document will be updated as part of a future revision.



### 1.M. INTERCHANGEABILITY OR MIXABILITY OF PARTS

Not applicable.

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### 2. MATERIAL INFORMATION

2.A. MATERIAL: PRICE - AVAILABILITY - PROCUREMENT

Price

For any information concerning the kits and/or comp onents, contact the Airbus Helicopters Network Sales and Customer Relations Department.

Availability

The kits and/or components will be delivered on customer's order.

Procurement conditions

Order the required quantity ( unless otherwise specified)

from

Airbus Helicopters Etablissement de Marignane Direction Ventes et Relations Client (ECR)

13725 MARIGNANE CEDEX

France



### NOTE 1

On the purchase order, pl ease specify the mode of transport, the destination and the serial numbers of the helicopters to be modified.



### NOTE 2

For ALERT SERVICE BULLETINS, order by:

Telex: HELICOP 410 969F Fax: +33 (0)4.42.85.99.96



### 2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



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

Components to be ordered for one helicopter or one assembly:

Designation Qty New P/N Item Former

P/N → Instruction

Junction unit 1 or 2 200188 1 / To be returned as per paragraph 2.D.

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Refer to the Work Cards and Tasks specified in this ALERT SERVICE BULLETIN and the list below:

Designation Qty Product P/N CM Item

Protective product

DINOL AV 30 A/R - CM 508 yy

The products can be ordered separately from the INTERTURBINE AVIATION LOGISTICS company.

Website: http://www.interturbine.com Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444

Specific tooling:

Designation Qty Tool P/N or equivalent Item

Internal micrometer,

diameter 60 to 80mm 1 Off the shelf zz



### 2.D. MATERIAL TO BE RETURNED

Return the non-compliant junction unit(s) to the following address:

Airbus Helicopters Département EBSEEE Bâtiment R6 Marseilleveyre

13725 MARIGNANE CEDEX - FRANCE

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### 3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

Read and comply with the protection rules for electrical wiring during maintenance operations as per MTC

Work Card 20.02.01.418.



### 3.B. OPERATIONAL PROCEDURE

The operational clearance measurements and the check fo r corrosion are only described for the LH junction unit. Carry out the operational clearance measurements and the check for corrosion in the RH junction unit by complying with the sa me operational procedure.

3.B.1. Preliminary steps



### HANDLE THE CONTAINER WITH CARE, TO

PREVENT ACTIVATING THE CYLINDER

PERCUSSION AND TO PREVENT INJURY TO

PERSONNEL.

BEFORE ANY WORK, RIG THE FLIGHT

CONTROLS IN ORDER TO PREVENT INJURY TO

PERSONNEL AND MAKE SURE THAT THE

LOCKING PIP PIN FITTED WITH ITS PENNANT IS

PRESENT ON THE CYLINDER PERCUSSION SYSTEM, IN ORDER TO PREVENT ACCIDENTAL

PERCUSSION.

- Remove and/or open all cowlings, panels, doors and equipment as required for access to the various work

zones. - Disconnect the cylinder percussion system connection kit as per AMM Task 25-69-01-063. 

### WARNIN G

WARNING

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3.B.2.a. Check of the junction unit cover (Figures 1 and 2)

- Remove the screws (b) from the junction unit (f) (Figure 1). - Remove the cover (a). - Disconnect the deployment cables (c ) and percussion cable (d) from the pul leys (e) located in the junction

unit (f) (Figure 1) as per AMM Task 25-69-01-061. - Remove the junction unit (f) as per AMM Task 25-69-01-061. - Make sure that the drainage hole located on the upper face of the junction unit cover (a) is blanked with a

cap (g) (Figure 2). - Make sure that the drainage hole located on the lowe r face of the junction unit cover (a) is not blanked

(Figure 2).



### NOTE

The blanking of the drainage holes depends on the position of the junction unit on the helicopter (refer to Figure 2).

- Comply with paragraph 3.B.2.b.

3.B.2.b. Check of the condition of the junction unit co ver and measurement of the operational clearance (Figures 3 and 4)

- Make sure that there is no corrosion inside the cover (a) (Area A, Figure 3).

. If there is no corrosion:

- Measure and record the diameter (D1) of the cover using an inter nal micrometer (zz) (Figure 4). - Comply with paragraph 3.B.2.c.

. If there is corrosion: - Carry out and record measurements of the diameter of the cover using an internal micrometer (zz)

(Figure 4):

. Carry out an initial measurement (D1) on a non-corroded surface of the cover. - If the measurement (D1) cannot be carried out (d ue to corrosion over the entire circumference

of the cover), comply with paragraph 3.B.3.

. Carry out a measurement (D2) on each corroded surface point of the cover.

- Comply with paragraph 3.B.2.c.

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- Make sure that there is no corrosion on the junction unit pulleys (Area B, Figure 3).

. If there is no corrosion: - Measure and record the diameter (d1) (not shown) of the pulleys using a caliper gage. - Interpret the results as per paragraph 3.B.2.d.

. If there is corrosion: - Carry out and record measurements of the diameter of the pulleys using a caliper gage:

. Carry out an initial measurement (d1) (not shown) on a non-corroded surface

of the pulleys.

- If the measurement (d1) cannot be carried out (due to corrosion over the entire circumference

of the pulleys), comply with paragraph 3.B.3.

. Carry out a measurement (d2) (not shown) on each corroded surface point of the pulleys.

- Interpret the results as per paragraph 3.B.2.d.

3.B.2.d. Interpretation of the results

- Calculate the initial clearance (J) between the inter nal/external pulley and the cover of the junction unit:

. Initial clearance J =

. If (J) is greater than (Jmax) (see Fi gure 4), comply with paragraph 3.B.3.

. If (J) is smaller than or equal to (Jmax) (see Figure 4):

- If there are no corrosion marks on the junction unit cover and pulleys, comply with paragraph 3.B.4.

- If there is a corrosion mark on the junction unit cover:

. Calculate the depth of the rework (P1) to be carried out on the junction unit cover, for each

corrosion point:

- Depth of the rework P1 = D2 - D1

. If P1 is lower than 0, mechanically remove the corrosion from the surface as per MTC Work

Card 20.04.03.401 until P1 is higher than or equal to 0 on each reworked surface point. . If P1 is higher than or equal to 0, record the P1 value for each reworked surface point. D1 - d1

2

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Revision 1 2014-09-01 This document is available on the internet: www.airbushelicopters.com/techpub - If there is a corrosion mark on the junction unit pulley(s):

. Calculate the depth of the rework (P2) to be carried out on the junction unit pulley(s), for each

corrosion point:

- Depth of the rework P2 = d1 - d2

. If P2 is less than 0, mechanically remove the corrosion from the surface as per MTC Work

Card 20.04.03.401 until P2 is higher than or equal to 0 on each reworked surface point. . If P2 is greater than or equal to 0, record the P2 value for each reworked surface point.

- Calculate the total clearance between the internal /external pulleys and the cover of the junction unit

for each reworked surface point:

. Total clearance = J + P1 +P2.

. If at least one of the two calculated total clearance values is greater than (Jmax) (see Figure 4), comply

with paragraph 3.B.3.

. If all calculated total clearance values are less than or equal to (Jmax) (see Figure 4), comply with

paragraph 3.B.4. on the junction unit (f).

3.B.3. Replacement of the junction unit

- Return the junction unit (f) as per paragraph 2.D. - Order a new junction unit (1) as per paragraph 2.A. - Comply with paragraph 3.B.4. on the new junction unit (1).

3.B.4. Protection and installation of the junction unit (Figures 1 and 3)

- If the junction unit has been reworked as per 3.B.2.: . Apply Alodine 1200 to each reworked surface point as per MTC Work Card 20.04.04.403. - Apply metal primer scheme P50 to Areas A and B of the junction unit (Figure 3) as per MTC Work

Card 20.04.05.434. - Apply Dinol AV 30 to Areas A and B of the junction unit (Figure 3) using a brush.



### CAUTION

POSITION THE JUNCTION UNIT WITH THE

DOUBLE CONNECTION POINTING TOWARD

THE FRONT OF THE HELICOPTER.

- Install the junction unit as per AMM Task 25-69-01-061. - Connect the deployment cables (c) and percussion cable (d ) to the pulleys (e) located in the junction unit as

per AMM Task 25-69-01-061. - Carry out a functional test of the life raft control system as per AMM Task 25-69-01-721

. - Install the cover (a) using the screws (b) of the junction unit,
then, - tighten to torque as per Figure 1. - Comply with paragraph 3.B.5.

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### CAUTION

REMOVE THE PIP PIN FROM THE PERCUSSION

SYSTEM CYLINDER AND THE RIGGING PINS

FROM THE FLIGHT CONTROLS.

- Connect the cylinder percussion system conn ection kit as per AMM Task 25-69-01-063. - Install and/or close all cowlings, panels, doors and equipment removed and/or opened during the

preliminary steps (paragraph 3.B.1.).

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

3.B.6.a. Measurement of the operational clearance betw een the junction unit cover and pulleys (Figures 1 and 4)

- Remove the screws (b) from the junction unit (f) (Figure 1). - Remove the cover (a).

- Measure and record the diameter (D1) of the cover using an inter nal micrometer (zz) (Figure 4). - Measure and record the diameter (d1) (not shown) of the pulleys using a caliper gage. - Calculate the initial clearance (J) between the inter nal/external pulley and the cover of the junction unit:

. Initial clearance J =

- If (J) is greater than (Jmax) (see Figure 4):

. Transmit the Serial Number (S/N) of the ch ecked junction unit to Airbus Helicopters:

Contact the Airbus Helicopters Technical Support Department:

Fax: +33 (0)4.42.85.99.66.

E-mail: Support.Technical-Optionnal@eurocopter.com

. Return the junction unit (f) as per paragraph 2.D.

- If (J) is less than or equal to (Jmax) (see Figure 4), comply with paragraph 3.B.6.b.

3.B.6.b. Protection of the junction unit (Figure 3)

- Apply Alodine 1200 to each reworked surface point as per MTC Work Card 20.04.04.403. - Apply metal primer scheme P50 to Areas A and B of the junction unit (Figure 3)

as per MTC Work Card 20.04.05.434. - Apply Dinol AV 30 (yy) to Areas A and B of the junction unit (Figure 3) using a brush. - Install the cover (a) using the screws (b) of the junction unit,
then, - tighten to torque as per Figure 1. - The junction unit can be installed. D1 - d1

2

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### 3.C. IDENTIFICATION

Identification of this document:

Record first compliance with this ALERT SERVICE BULLETIN, with the revision number, in the helicopter

documents.



### 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Operating instructions:

Not applicable.

Maintenance instructions:

- Pending a definitive solution, comply with parag raphs 3.A. and 3.B. every 600 flying hours or 1 year following first compliance with the instruct ions given in this ALERT SERVICE BULLETIN.

Then,

- fill in and return the list of checked junction units (list given in the Appendix) within 1 month following latest

compliance with this ALERT SERVICE BULLETIN.

- If corrosion is found, send the list of checked juncti on units along with photos of the corroded unit (before

rework of the unit).

. Contact the Airbus Helicopters Technical Support Department:

Fax: +33 (0)4.42.85.99.66.

E-mail: Support.Technical-Optionnal@airbus.com

The Aircraft Maintenance Manual (AMM) will incorporate these instructions as part of a future revision. Refer to the AMM once these instructions are integrated.

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e

a f

1

Figure 1: Removal/installation of the junction unit c

d

5

44.25

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h

g j a

a Junction unit cover located on the LH side of the helicopter, with blank (g) on the upper drainage hole (h).

Junction unit cover located on the RH side of the helicopter, with blank (g) on the upper drainage hole (j).

Figure 2: Drainage holes on the junction unit cover

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d = 60 mm (2.36 in) +0

-0.25 +0

- .0098

A rea B Check of the junction unit cover

Check of the junction unit pulleys

Figure 3: Check for corrosion

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, 75 mm ( .029 in )

Jmax = 0

, 75 mm ( .029 in )

Figure 4: Measurement of the clearance on the junction unit Second measurement D2 Initial measurement D1 Corroded surface (cylindrical surface)

Non-corroded surface (cylindrical surface)

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### 4. APPENDIX

4.A. LIST OF CHECKED JUNCTION UNITS

Helicopter Serial

Number (S/N) Number of flying hours logged by

the helicopter Check of junction unit

number Presence of

corrosion in the

junction unit* Flight for

which life

rafts are

needed*

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

YES / NO YES / NO

* Cross out as appropriate



### 4.B. ACCEPTABLE TENSILE LOADS

During compliance with AMM Task 25-69-01-721 on a junction unit MP/N 200188, a tensile load of between 15 DaN (33.721 lbf) and 20 DaN (44.961 lbf) is acceptable.