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

EUROCOPTER 

DIRECTION TECHNIQUE SUPPORT

13725 MARIGNANE CEDEX FRANCE

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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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 protective 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 check and the tapping test, scheduled at 85 flying hours, 

on the leading edge stainless steel protective strip, without 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 BULLETIN 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 rotor 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 edge 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 and/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 difficulty 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 maintenance documentation are unchanged. 

EUROCOPTER rendered compliance with this ALERT SERVICE BULLETIN mandatory.

Revision 2: 

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

blade part numbers 332A11.0050.02 and 332A11.0055.02 following MOD 0740714. 

NOTE 

The purpose of MOD 0740714 is to replace the current 

stainless steel tip cap leading 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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1.E. COMPLIANCE 

1.E.1. Compliance at the works 

1.E.1.a. On helicopters: Comply 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 June 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 date 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 intervals 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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1.F. APPROVAL 

Approval is limited to civil version helicopters subject to an Airworthiness Certificate. 

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

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

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

on July 27, 2007 under the authority of EASA Design Organization Approval No. 21J.056. 

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

on April 22, 2013 under the authority of EASA Design Organization Approval No. 21J.056 for 

helicopters of civil versions subject to an Airworthiness Certificate. 

For the French Government helicopters, as the content 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 ALERT SERVICE BULLETIN Revision 2 was approved 

on April 22, 2013 by the EUROCOPTER Airworthiness 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 blade 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 rotor blade leading edge stainless steel protective strip 

- Carry out a visual check and a tapping test on the 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 accordance 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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b) If there is open de-bonding: 

- Make sure that the detected de-bonding is within 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 instructions 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 paragraph 2.B.3., then, every 15 flying hours, carry out a 

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

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

- Remove the main rotor blade in accordance 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 polyurethane 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 configuration 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 permissible criteria defined in MMA Task 62-10-00-211. 

. If the crack is within the permissible criteria: 

- Return the helicopter to flight configuration 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 accordance 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 Sub-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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Figure 1 

Area D 
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332A11.0055.00 

332A11.0055.02 

332A11.0050.00 

332A11.0050.02 

Figure 2 

Area A

Area A
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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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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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3. MATERIAL INFORMATION

3.A. MATERIAL: COST – AVAILABILITY 

For any information contact the Customer 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.