### T.F.S. No. 00000745

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2013.04.22 This document is available on the internet: www.eurocopter.com/techpub EUROCOPTER

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE C EDEX F RANCE



# EMERGENCY 

# ALERT SERVICE BULLETIN

SUPER PUMA NUMBER VERSIONS



# EC225 05A010 Civil: LP



# EC725 05A010 Military: AP



### SUBJECT: TIME LIMITS – MAINTENANCE CHECKS

Check of the bonding of the stainless steel protective strip on the leading

edge of main rotor blades



### ATA: 62

REVISION No. DATE OF APPROVAL DATE OF ISSUE

Revision 0 On: June 28, 2007 2007.06.28

Revision 1

Revision 2 On: July 27, 2007

On: April 22, 2013 2007.07.30

2013.04.22

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2013.04.22 

### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters / Installed equipment

Helicopters equipped with main rotor blades P/N:

- 332A11.0050.00

- 332A11.0050.02

- 332A11.0055.00

- 332A11.0055.02

1.A.2. Non-installed equipment

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.



### 1.C. REASON

To check the bonding of the stainless steel protecti ve strips on the leading edge of the main rotor

blades at regular intervals.

The purpose of Revision 1 of this ALERT SERVICE BULLETIN was:

- To enable operators to perform the visual chec k and the tapping test, scheduled at 85 flying hours,

on the leading edge stainless steel protective strip, wi thout removal of the main rotor blades from the

helicopter.

Revision 1 had no effect on compliance with Revision 0 of this ALERT SERVICE BULLETIN.

The purpose of Revision 2 of this ALERT SERVICE BU LLETIN is to extend the effectivity to main rotor

blade part numbers 332A11 .0050.02 and 332A11.0055.02.

Revision 2 does not affect compliance with Revision 1 of this ALERT SERVICE BULLETIN.

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### 1.D. DESCRIPTION

Revision 0:

The initial investigations conducted on the main ro tor blade showing significant de-bonding of the

stainless steel protective strip (see TELEX INFORMATION No. 00000392 issued on June 15, 2007)

revealed rapidly progressing de-bonding which may be due to water that may have entered from the

crack that was detected in the leading e dge stainless steel protective strip.

If this de-bonding remains undetected, it can, in time , cause the loss of the main rotor blade stainless

steel protective strip, and vibrations induced by the weight unbalance may compel the pilot to land

immediately.

Pending complementary examinations, EUROCOPTER reduced the interval:

- For the visual check for de-bonding and/or cracks which may allow water to enter,

then,

- For the tapping test of de-bonded an d/or cracked areas identified beforehand, in order to monitor the

progress of the de-bonding.

Revision 1:

Initially, EUROCOPTER stipulated that the main rotor blades were to be removed

to perform the visual check and the tapping test on the leading edge stainless steel protective strip,

scheduled at 85 flying hours,

EUROCOPTER is aware of the operational difficult y that may be caused by this task and therefore

conducted the necessary tests and checks to modify the operational procedure.

Consequently, EUROCOPTER now authorizes the performance of the required checks without

removal of the main rotor blades.

The criteria currently defined in the ma intenance documentation are unchanged.

EUROCOPTER rendered compliance with this ALERT SERVICE BULLETIN mandatory.

Revision 2:

The purpose of Revision 2 of this ALERT SERVICE BU LLETIN is to extend the effectivity to main rotor

blade part numbers 332A11.0050.02 an d 332A11.0055.02 following MOD 0740714.



### NOTE

The purpose of MOD 0740714 is to replace the current

stainless steel tip cap leadi ng edge protection on the blade

with a Nickel-Cobalt tip cap leading edge protection. This

modification creates new blade P/Nos.

Revision 2 does not affect compliance with Revision 1 of this ALERT SERVICE BULLETIN.

EUROCOPTER renders compliance with this ALERT SERVICE BULLETIN mandatory.

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2013.04.22 

### 1.E. COMPLIANCE

1.E.1. Compliance at the works

1.E.1.a. On helicopters: Comp ly with paragraph 1.E.2.a.

1.E.1.b. On non-installed equipment: Not applicable.

1.E.2. Compliance in operation: By the operator:

1.E.2.a. On helicopters / installed equipment:

On main rotor blades with P/Nos. 332A11.0050.00 and 332A11.0055.00:

- Comply with paragraph 2.B. within 15 flying hours following receipt of Revision 0 of this ALERT

SERVICE BULLETIN, issued on J une 28, 2007, and then interpret the results according to the

paragraph below.

On main rotor blades with P/Nos. 332A11.0050.02 and 332A11.0055.02:

- Comply with paragraph 2.B. within 15 flying hours following receipt of Revision 2 of this ALERT

SERVICE BULLETIN, issued on the dat e indicated at the foot of the page, and then interpret the

results according to the paragraph below.

Interpretation of results:

1) If there is no crack, no cut, no open and no blind de-bonding:

. comply with paragraph 2.B. at intervals not exceeding 85 flying hours.

2) If there is open de-bonding within the permissible criteria inside area D (see Figure 1):

. comply with paragraph 2.B. at in tervals not exceeding 85 flying hours.

3) If there is a crack and/or a cut and/or open de- bonding within the permissible criteria

outside area D (see Figure 1):

. comply with paragraph 2.B.2.b) and/or 2.B.2.c) and/or 2.B.2.d) at intervals not exceeding

15 flying hours.

1.E.2.b. On non-installed equipment:

On main rotor blades listed in paragraph 1.A.1., having logged flying hours:

- Comply with paragraph 2.B. before installation on a helicopter.

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2013.04.22 

### 1.F. APPROVAL

Approval is limited to civil version helicopte rs subject to an Airworthiness Certificate.

The technical information contained in Revision 0 of this ALERT SERVICE BU LLETIN was approved

on June 28, 2007 under the authority of EASA Design Organi zation Approval No. 21J.056.

The technical information contained in Revision 1 of this ALERT SERVICE BU LLETIN was approved

on July 27, 2007 under the aut hority of EASA Design Organiza tion Approval No. 21J.056.

The technical information contained in this AL ERT SERVICE BULLETIN Revision 2 was approved

on April 22, 2013 under the aut hority of EASA Design Organizati on Approval No. 21J.056 for

helicopters of civil versions subject to an Airworthiness Certificate.

For the French Government helicopters, as the cont ent of this ALERT SERVICE BULLETIN is strictly

identical to ALERT SERVICE BULLETIN EC225 No . 05A010 of the civil version, the technical

information contained in this ALERT SERVICE BULLETIN Revision 2 was approved

on April 22, 2013 under the prerogatives of the recognition of design capability FRA21J-002-DGA.

The technical information contained in this AL ERT SERVICE BULLETIN Revision 2 was approved

on April 22, 2013 by the EUROCOPTER Airworthi ness Department for export military versions.



### 1.G. MANPOWER

Qualification: Mechanic.

Time for one main rotor blade: Approximately 1 hour to comply with paragraph 2.B.



### 1.H. WEIGHT AND BALANCE

Not applicable.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT STATE

Not applicable.

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### 1.K. REFERENCES

Aircraft Maintenance Manual (MMA), Tasks: 62-10-00-061 – 62-10-00-211.



### 1.L. OTHER DOCUMENTS CONCERNED

Not applicable.



### 1.M. TOOLING CONCERNED

Not applicable.



### 1.N. INTERCHANGEABILITY AND MIXABILITY OF PARTS

Not applicable.

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### 2. ACCOMPLISHMENT INSTRUCTIONS

2.A. GENERAL

The operational procedure given in paragraph 2.B. is described for one main rotor blade and must be

applied to the 5 main rotor blades.



### 2.B. OPERATIONAL PROCEDURE

2.B.1. Preliminary steps

- Open the sliding cowling and the engine cowlings.

- Move the main rotor blade to be checked to the right three-quarter forward position with respect to

the aircraft centerline (see Figure 4).

- Apply the rotor brake.

- Position a maintenance platform along the blade leading edge side.

- When performing the tapping test on the blade leading edge stainless steel protective strip:

. on the blade pressure face side, support the main rotor blade tip without lifting it,

. on the suction face side, lift the main rotor bl ade over approximately 75 centimeters at the blade

tip.



### NOTE

To support and lift the blade, make two wooden supports

locally (one for the blade pressure face, and one for the blade

suction face, see Figure 3). Put these supports at the blade

tip, at the end of the main blade section (see Figure 3).

2.B.2. Visual check and tapping test of the main ro tor blade leading edge stainless steel protective strip

- Carry out a visual check and a tapping test on t he leading edge stainless steel protective strip.

. If there is no crack, no cut and no de-bonding:

- Leave as is.

- Return the helicopter to flight configuration in compliance with paragraph 2.B.3. and comply with

the instructions of paragraph 1.E.2.a.1.

a) If there is blind de-bonding:

- Make sure that the de-bonded surface area is within the permissible criteria defined in MMA

Task 62-10-00-211.

- If the de-bonded surface area is within the permissible criteria:

. Return the helicopter to flight configuration in compliance with paragraph 2.B.3. and comply

with the instructions of paragraph 1.E.2.a.1.

- If the de-bonded surface area is beyond the permissible criteria:

. Remove the main rotor blade in accordan ce with Sub-Task 62-10-00-031-001 of MMA

Task 62-10-00-061.

. Remove the blade from service before resuming flights.

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2013.04.22 b) If there is open de-bonding:

- Make sure that the detected de-bonding is wi thin the permissible criteria defined in MMA

Task 62-10-00-211.

. If the de-bonded surface area is within the permissible criteria:

- And this surface area is located inside area D at the end of the blade main section, on the blade

tip cap side (see area D Figure 1), return the helicopter to flight configuration in compliance with

paragraph 2.B.3. and comply with the in structions of paragraph 1.E.2.a.2.

- And this surface area is located outside area D (see area D Figure 1), return the helicopter to

flight configuration in compliance with paragrap h 2.B.3., then, every 15 flying hours, carry out a

tapping test limited to the detected de-bonded surf ace area, in order to monitor its behavior.

. If the de-bonded surface area is beyond the permissible criteria:

- Remove the main rotor blade in accordan ce with Sub-Task 62-10-00-031-001 of MMA

Task 62-10-00-061.

- Remove the blade from service before resuming flights.

c) If there is a cut in the blade root polyure thane protective strip (see Figure 2, Area A):

- Carry out a tapping test of the area.

. If there is no de-bonding:

- Return the helicopter to flight configurati on in compliance with paragraph 2.B.3., then,

. every 15 flying hours, on the blade installed on the helicopter, carry out a tapping test on

the blade leading edge stainless steel strip in the blade root area, in the stainless steel

leading edge / neoprene junction area, in order to make sure that there is no de-bonding.

. If there is de-bonding, comply with paragraph 2.B.2.b.

d) If there is a crack in the blade leading edge:

- Make sure that the crack is within the perm issible criteria defined in MMA Task 62-10-00-211.

. If the crack is within the permissible criteria:

- Return the helicopter to flight configurati on in compliance with paragraph 2.B.3., then,

. every 15 flying hours, perform a tapping test in the immediate vicinity of the crack to make

sure that there is no de-bonding.

. If there is de-bonding, comply with paragraph 2.B.2.b).

. If the crack is beyond the permissible criteria:

- Remove the main rotor blade in accordan ce with Sub-Task 62-10-00-031-001 of MMA

Task 62-10-00-061.

- Remove the blade from service before resuming flights.

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### NOTE

Send the results of the check of the main rotor blades,

indicating their serial number and that of the

helicopter, to:

Etablissement de LA COURNEUVE

For the attention of Mr. Olivier TILLIER

2 à 20 Av Marcel Cachin

93123 LA COURNEUVE Cedex

France

(Fax: +33(0)1.49.39.41.70)

2.B.3. Final steps

- Where necessary, install the blade as per S ub-Task 62-10-00-431-001 of MMA Task 62-10-00-061.

- Remove the maintenance platform from the main rotor blade.

- Close the engine cowlings and the sliding cowling.



### 2.C. IDENTIFICATION

Record initial compliance with this ALERT SERVICE BULLETIN in the Log Card (FM) of the main rotor

blade.



### 2.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.

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2013.04.22 Figure 1 Area D

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2013.04.22 

# 332A11.0055.00

332A11.0055.02

332A11.0050.00

332A11.0050.02

Figure 2 Area A

Area A

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2013.04.22 300 mm

Figure 3 Height of the Support

- Blade pressure face: H

- Blade suction face: H + 0.75 meters

Note: H = Height depending on the local access

equipment

Blade pressure face Support seating zone 

# H

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2013.04.22 Figure 4 Check on the blade pressure face

Check on the blade suction face Support the blade but do

not lift it

Lift the blade by

0.75 meters Maintenance platform

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2013.04.22 

### 3. MATERIAL INFORMATION

3.A. MATERIAL: COST – AVAILABILITY

For any information contact the Cu stomer Service Sales Department.



### 3.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



### 3.C. MATERIAL REQUIRED FOR EACH HELICOPTER / ENGINE / COMPONENT

Not applicable.



### 3.D. PROCUREMENT CONDITIONS

Order the required quantity ( unless otherwise specified)

from

EUROCOPTER

Etablissement de La Courneuve

Direction VENTES Service Client (S.V.) Fax: +33(0)1 49 34 41 70

93123 LA COURNEUVE

FRANCE



### NOTE 1

For ALERT SERVICE BULLETINS, order by:

Telex: HELICOP 410 969F

Fax: +33 (0)4 42 85 99 96



### NOTE 2

On the purchase order, please specify

the mode of transport, the destination

and the serial numbers of the helicopters

to be modified.



### 4. APPENDIX

Not applicable.