ASB No. EC225-30A032

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 Civil version(s): LP 

ALERT SERVICE BULLETIN 

SUBJECT: ICE AND RAIN PROTECTION - Electric Multi-Purpose Air Intakes 

 Relocation of one of the two power supply circuit breakers of the electric 

multi-purpose air intakes onto an essential bus bar which cannot be cut off 

 Corresponds to modification 332P083736.01/.02 

Revision No. Date of issue 

Revision 0 2013-07-31 

Summary: 

The relocation of the power supply circuit breaker of the electric multi-purpose air intake of engine 2 onto an 

essential bus bar which cannot be cut off enables the inflation of the multi-purpose air intake seal in the event of 

battery powered emergency flight. 

Compliance: 

EUROCOPTER makes compliance with this ALERT SERVICE BULLETIN mandatory. 

For the attention of 

S/N: 2600, 2623, 2645, 2656, 2659, 2663, 2666, 2670, 2673, 2685, 2691, 2692, 2693, 2702, 2715, 2716, 

2721, 2725, 2739, 2744, 2747, 2753, 2756, 2759, 2767, 2779, 2794 
 

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1. PLANNING INFORMATION 

1.A. EFFECTIVITY 

1.A.1. Helicopters/installed equipment 

Helicopters listed on page 1 and in the table below, equipped with Electric Multi-Purpose Air Intakes (MPAI) 

and which do not embody modification 332P083736.01 or 332P083736.02. 

Modification Helicopter serial numbers 

332P083736.01 2600, 2623, 2645, 2656, 2659, 2663, 2666, 2670, 2673, 2693 

332P083736.02 2685, 2691, 2692, 2702, 2715, 2716, 2721, 2725, 2739, 2744, 2747, 2753, 

2756, 2759, 2767, 2779, 2794 

NOTE 

Refer to the aircraft individual inspection record to identify 

the actual configuration of the helicopter. 

1.A.2. Non-installed equipment 

Not applicable. 

1.B. ASSOCIATED REQUIREMENTS 

Not applicable. 

1.C. REASON 

In case of battery operated emergency flight (loss of both alternators or both Transformer-Rectifiers (TRU)), 

the two P2 electro-valves used to inflate the MPAI seal are no longer energized. 

Consequently, on each engine air intake, deflation of the MPAI seals can occur, or they may be impossible to 

inflate when needed. 

If this happens, helicopters equipped with MPAIs and de-icing equipment could be exposed to the risk of 

dual engine flame-out if ice ingestion occurs during flight in icing conditions. 

In order to prevent this situation from occurring, EUROCOPTER has defined modifications 332P083736.01 

and 332P083736.02 which ensure that MPAI seal inflation of at least one air intake is always maintained, 

regardless of it being battery powered emergency flight or another type of electrical power generation failure. 

1.D. DESCRIPTION 

Compliance with this ALERT SERVICE BULLETIN consists in relocating circuit breaker "MPURP A INT" or 

"EA I 2" of engine 2 from its position to a position on an essential bus bar which cannot be cut off. 
 

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1.E. COMPLIANCE 

1.E.1. Compliance at the works 

Not applicable. 

1.E.2. Compliance in service 

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

Helicopters/installed equipment: 

Comply with paragraph 3. of this ALERT SERVICE BULLETIN before reaching 110 flying hours following 

receipt of this ALERT SERVICE BULLETIN, issued on the date indicated at the bottom of the page. 

 Non-installed equipment: 

Not applicable. 

1.F. APPROVAL 

 Approval of modifications: 

The information or instructions relate to modification 332P083736.01 or 332P083736.02 which was approved 

on July 19, 2013 by the EASA for helicopters of civil versions subject to an Airworthiness Certificate. 

 Approval of this document: 

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

on July 29, 2013 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of 

civil versions subject to an Airworthiness Certificate. 

1.G. MANPOWER 

EUROCOPTER recommends that compliance with this ALERT SERVICE BULLETIN be ensured by 

personnel with the following qualification: 

Qualification: 1 Avionics Technician. 

1 Pilot. 

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

Time for the operations: 8 hours for one Avionics Technician. 

 1 hour for the ground run-up. 

The estimated helicopter downtime is 1 day. 
 

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1.H. WEIGHT AND BALANCE 

Not applicable. 

1.I. EFFECT ON ELECTRICAL LOADS 

It is the responsibility of the customer to update the helicopter’s electrical breakdown, with technical 

assistance from EUROCOPTER. 

A copy of the electrical breakdown duly updated following modification on the helicopter must be sent to the 

EUROCOPTER Technical Support Department: 

Fax: + 33 (0)4.42.85.99.66 

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

1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD 

Not applicable. 

1.K. REFERENCES 

The following documents are required for compliance with this ALERT SERVICE BULLETIN. 

- MMA: 24-00-00-611 - General: General instructions 

- MMA: 25-12-01-051 - Third crewmember seat - Removal-Installation 

- MMA: 30-00-00-611 - General: General instructions 

- MTC: 20.02.01.411 - General: Cable binding methods 

- MTC: 20.02.01.415 - General: Installation of electrical cable bundles and optical fibres 

- MTC: 20.02.01.418 - General: Protection of electrical wiring during maintenance operations 

1.L. DOCUMENTS AFFECTED 

The modification will be integrated into the following manuals: 

- MMA: Aircraft Maintenance Manual 

- IPC: Illustrated Parts Catalog 

- MCS: Wiring Diagrams Manual 

- PMV: Flight Manual (Section 3.8) 

The documents affected will be updated during 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 

EUROCOPTER's Super Puma Program Department will advise customers of availability times for kits or 

components. 

EUROCOPTER 

Etablissement de Marignane 

Direction Ventes et Relations Client (ECR) 

13725 MARIGNANE CEDEX 

FRANCE 

NOTE 1 

On the purchase order, please specify the mode of 

transport, the destination and the serial numbers of the 

aircraft 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 

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

Sales & Customer Relations Department. 

2.C. MATERIAL REQUIRED FOR EACH HELICOPTER/COMPONENT 

 Material to be ordered separately: 

Designation Qty New P/N Item Former 

P/N → Instruction 

 

Extension lead A/R ECS0739C20-20 1 

Cable A/R EN2267-010A004S 2 

NOMEX sheath A/R EN6049-003-02-5 3 

Cable tie A/R E0043-1A0P 4 

Cable clamp 1 EN3545-007SCD 5 

Label A/R 332A62-9910-22 6 

Label A/R 332A-62-9010-20 7 

Label A/R 332P624503FK 8 

 
 

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Special tools: 

Designation Qty Tool P/N or equivalent Item 

 

Insertion and extraction tool 1 M81969/39–01 zz 

Multimeter 1 Off the shelf yy 

 

 Products to be ordered separately: 

 As per Work Cards and Tasks mentioned in this ALERT SERVICE BULLETIN. 

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

Website: http://www.interturbine.com

 Phone: +49.41.91.809.300 

AOG: +49.41.91.809.444 

2.D. MATERIAL TO BE RETURNED 

Not applicable. 
 

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3. ACCOMPLISHMENT INSTRUCTIONS 

3.A. GENERAL 

Read and comply with the general electrical instructions as per MMA Task 24-00-00-611. 

Read and comply with the general instructions as per MMA Task 30-00-00-611. 

Read and comply with the cable binding methods as per MTC Work Card 20.02.01.411. 

Read and comply with the general instructions concerning the installation of electrical cable bundles as per 

MTC Work Card 20.02.01.415. 

Read and comply with the instructions concerning the protection of electrical wiring during maintenance 

operations as per MTC Work Card 20.02.01.418. 

3.B. OPERATIONAL PROCEDURE 

3.B.1. Preliminary steps 

- Install the access equipment. 

- If necessary, remove the 3rd crewmember seat as per MMA Task 25-12-01-051. 

- Open all cowlings, panels, doors and remove all equipment required to gain access to the different work 

areas. 

3.B.2. Relocation of the engine 2 MPAI power supply circuit breaker (Figures 1 to 3) 

3.B.2.a. Modification 332P083736.01: relocation of circuit breaker "2PP-D12" to "2PP-F20" 

(Figures 1 and 2) 

- Release the captive screws (c) from the front panel assembly (d), (Figure 1). 

- Remove the front panel assembly (d). 

- Remove the seal (e) from the front panel assembly (d). 

- Remove the centering plate (f). 

- Remove circuit breaker (g) installed in location D12. 

- Install circuit breaker (g) on location F20 of circuit breaker panel 2PP as per Detail B, (Figure 2). 

- Disconnect connectors BD and BF. 

- Remove the blank (k) installed on location "20" of connector BF. 

- Using the extraction tool (zz) unplug contact 25 from connector BD. 

- Using the insertion tool (zz) plug the contact into location 20 of connector BF. 

- Install the blank (k) on location "25" of connector BD. 
 

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- Check that the plugged-in contact is correctly retained: 

. Hold the back of the connector, 

CAUTION 

THE PULLING MOVEMENT MUST BE PERFORMED 

SMOOTHLY, PARALLEL TO THE CONNECTOR 

AXIS WITHOUT DETERIORATING THE 

ELECTRICAL WIRE (E.G.: BY FOLDING, TWISTING 

OR WINDING IT). 

. Carry out an electrical continuity test between contact 20 of connector BF and contact G of connector A of 

control panel 4HA, (Figure 2). 

- Install the cable clamp (5) (not shown) on connector "BF". 

- Connect connectors BD and BF. 

- Using the cable ties (4) (not shown), route and attach wire 3021-82 to prevent any interference. 

- Remove label (j) located at F20 as per Detail B, (Figure 2). 

- Remove label (h) located at D12. 

- Install label (j) or (7) at D12. 

- Install label (h) or (6) at F20. 

- Install the centering plate (f), (Figure 1). 

- Install the seal (e) of the front panel assembly (d). 

- Install the front panel assembly (d) using the captive screws (c). 

3.B.2.b. Modification 332P083736.02: relocation of circuit breaker "2PP-D9" to "2PP-F20" (Figures 1 and 3) 

- Release the captive screws (c) from the front panel assembly (d), (Figure 1). 

- Remove the front panel assembly (d). 

- Remove the seal (e) from the front panel assembly (d). 

- Remove the centering plate (f). 

- Remove circuit breaker (g) installed in location D9. 

- Install circuit breaker (g) on location F20 of circuit breaker panel 2PP as per Detail C, (Figure 3). 

- Disconnect connectors BD and BF. 

- Remove the blank (k) installed at location 20 on connector BF. 

- Using the extraction tool (zz) unplug contact 28 from connector BD. 

- Using the insertion tool (zz) plug the contact into location 20 of connector BF. 

- Install the blank (k) at location 28 on connector BD. 

- Check that the plugged-in contact is correctly retained: 

. Hold the back of the connector, 

CAUTION 

THE PULLING MOVEMENT MUST BE PERFORMED 

SMOOTHLY, PARALLEL TO THE CONNECTOR 

AXIS WITHOUT DETERIORATING THE 

ELECTRICAL WIRE (E.G.: BY FOLDING, TWISTING 

OR WINDING IT). 

. Carry out an electrical continuity test between contact 20 of connector BF and contact G of connector A of 

control panel 4HA, (Figure 3). 
 

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- Install the cable clamp (5) (not shown) on connector BF. 

- Connect connectors BD and BF. 

- Using the cable ties (4), route and attach wire 3021-942 to prevent any interference. 

- Remove label (j) located at F20 as per Detail C, (Figure 3). 

- Remove label (m) located at D9. 

- Install label (j) or (7) at D9. 

- Install label (m) or (8) at F20. 

- Install the centering plate (f) (Figure 1). 

- Install the seal (e) from the front panel assembly (d). 

- Install the front panel assembly (d) using the captive screws (c). 

3.B.3. Final steps 

- Install all the removed equipment and close all cowlings, panels and doors opened during the preliminary 

steps. 

- If necessary, install the 3rd crewmember seat as per MMA Task 25-12-01-051. 

- Remove the access equipment. 
 

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3.B.4. Ground run-up/Flight test 

Functional check of the Multi-Purpose Air Intakes (MPAI) 

Preliminary operations: 

 - Remove or open the equipment giving access to test panel “56VU” 

- Start both engines at nominal rating in accordance with the Flight Manual Procedure (PMV). 

- Test the MPAIs in accordance with the Flight Manual Procedure and visually check the correct inflation of 

the seals. 

Functional check of MPAIs on PRE MOD 07-26556 helicopters: 

- Set the MPAIs into “ANTI-ICING” configuration. 

- On panel “56VU”, press “PP2” 

- Check that indicator lights “BAT+”, “ESS BUS”, “BUS-TIE” and “TRU2” come on. 

- Place the voltage measurement selector on “ESS.BUS” and check that there is no voltage: 

 . Visually check that the MPAI seal of engine No. 1 remains inflated and that the MPAI seal of engine 

 No. 2 deflates. 

- Switch the “BUS TIE” control to “OPEN” then to “NORM” 

- Reset “TRU2”: 

. Visually check that the MPAI seal of engine No. 1 remains inflated and that the MPAI seal of engine 

No. 2 inflates. 

- On panel “56VU”, press “PP3”. 

- Check that the “SEC BUS”, BUS TIE” and “TRU 1” indicator lights come on, 

- Switch the “SHEDDING” invertor to “SHED” or for equipped helicopters activate the emergency hydroelectric power supply as per procedure SUP12 paragraph 4.1 in the Flight Manual. 

. Visually check that the MPAI seal of engine No. 1 deflates and that the MPAI seal of engine No. 2 

remains inflated. 

NOTE 1 

For helicopters equipped with an emergency hydro-electric 

power supply, shedding is only effective when the “FLOW” 

indicator light is out. 

- Switch the "SHEDDING" invertor to "NORM" then switch the "BUS TIE" selector to "OPEN" then to 

"NORM” or, for equipped helicopters, deactivate the hydro-electric power supply as per procedure SUP12 

paragraph 4.1 of the Flight Manual. 

- Reset “TRU1”: 

 . Visually check that the MPAI seal of engine No. 1 inflates and that the MPAI seal of engine No. 2 

remains inflated. 

- Shut down both engines according to the Flight Manual Procedure. 

- Install or close the equipment giving access to test panel “56VU” 

 
 

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Functional check of MPAIs on POST MOD 07-26556 helicopters: 

- Set the MPAIs into “ANTI-ICING” configuration. 

- On the panel "56VU", press "PP2". 

- Check that the “BAT+”, “ESS BUS”, “BUS TIE” and “TRU2” indicator lights come on. 

- Place the voltage measurement selector on “ESS.BUS” and check that there is no voltage. 

 . Visually check that the MPAI seal of engine No.1 remains inflated and that the MPAI seal of engine 

 No. 2 deflates. 

. Check that the "BULL" indicator light for the MPAI of engine No. 2 comes on. 

- Switch the "BUS TIE" selector to “OPEN” then to “NORM”. 

- Reset "TRU2": 

. Visually check that the MPAI seal of engine No.1 remains inflated and that the MPAI seal of engine 

No. 2 inflates. 

. Check that the “BULL” indicator light for the MPAI of engine No. 2 goes out. 

- On test panel "56VU", press "PP3". 

- Check that the “SEC BUS”, “BUS.TIE”, and “TRU1” indicator lights come on. 

- Switch the "SHEDDING" invertor to "SHED" or, for equipped helicopters, activate the emergency hydroelectric power supply as per procedure SUP12 paragraph 4.1 of the Flight Manual. 

. Visually check that the MPAI seal of engine No. 1 deflates and that the MPAI seal for engine No. 2 

remains inflated. 

. Check that the "BULL" indicator light for the MPAI of engine No. 1 comes on. 

NOTE 2 

For helicopters equipped with an emergency hydro-electric 

power supply, shedding is only effective when the “FLOW” 

indicator light is out.

- Switch the "SHEDDING" invertor to "NORM" then switch the "BUS TIE" selector to "OPEN" then to 

"NORM” or, for equipped helicopters, deactivate the hydro-electric power supply as per procedure 

SUP12 paragraph 4.1 of the Flight Manual. 

- Reset "TRU1": 

. Visually check that the MPAI seal of engine No.1 inflates and that the MPAI seal of engine No. 2 

remains inflated. 

. Check that the “BULL” indicator light for the MPAI of engine No. 2 goes out. 

- Shut down both engines according to the Flight Manual Procedure. 

- Install or close the equipment giving access to test panel “56VU” 
 

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3.C. IDENTIFICATION 

 Identification of this document: 

Record compliance with this document, with the revision number, in the helicopter documents. 

 Identification of modifications on the documentation: 

Record embodiment of modification 332P083736.01 or 332P083736.02 in the helicopter documents. 

3.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

 Operating instructions: 

- Pending its update, incorporate the pages from the appendix into the Flight Manual. 

- The Flight Manual (PMV) will incorporate these instructions as part of a future revision. After integration of 

these instructions in the Flight Manual (PMV), refer to it. 

 Maintenance instructions: 

Not applicable. 
 

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Figure 1: Circuit breaker panel 2PP 

a 

c 

f 

e 

g 

b 

d 

See Figure 2 and 3 

-
 

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Figure 2: Circuit breaker panel 2PP Front face (Modification 332P083736.01) 

g

j

h

6 

h

j

7 

See Figure 1 

PRE MOD 

POST MOD 

k 

k 

a 
 

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Figure 3: Circuit breaker panel 2PP Front face (Modification 332P083736.02) 

PRE MOD 

POST MOD 

g

j

m

8 

m

j

7 

See Figure 1 

k 

k 

a 
 

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4. APPENDIX 

Sheets to be inserted in the Flight Manual: 
 

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