EASA AD No.: 2015-0156

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0156

[Correction: 30 July 2015]

Date: 29 July 2015

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of 

the European third countries that participate in the activities of EASA under Article 66 of that 

Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

AIRBUS HELICOPTERS

Type/Model designation(s):

AS 332 and EC 225 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2014-0263R1 dated 19 January 2015.

ATA 52

Doors – Cabin Sliding Plug Doors / Emergency Jettisoning System

– Inspection

Manufacturer(s): Airbus Helicopters (formerly Eurocopter, Eurocopter France, Aerospatiale)

Applicability: AS 332 C, AS 332 C1, AS 332 L, AS 332 L1 and AS 332 L2 helicopters, all 

manufacturer serial numbers with a manufacturing date before 14 July 2014

and equipped with cabin sliding plug doors modified in accordance with Airbus 

Helicopters modification (mod) AL25612 or mod 0725870.

EC 225 LP helicopters, all manufacturer serial numbers with a manufacturing 

date before 14 July 2014 and equipped with cabin sliding plug doors.

Reason: During a scheduled inspection of the jettisoning mechanism of the cabin lateral 

sliding plug doors, failure of an emergency jettisoning test of a door was 

reported. Subsequent investigation of the affected door revealed significant 

corrosion damage affecting the door jettisoning system. The detected 

corrosion was due to the accumulation of un-drained water, as excessive 

Plastic-Rubber compound was found obstructing the water drain of the door 

jettisoning mechanism.

This condition, if not detected and corrected, could lead to jamming of the door 

jettisoning mechanism, possibly preventing jettisoning of the affected door in 

an emergency situation and jeopardizing the safe evacuation of occupants.

To address this potential unsafe condition, Airbus Helicopters issued Alert 

Service Bulletin (ASB) AS332-53.01.86 and ASB EC225-53A048 to provide 

inspection instructions.

Consequently, EASA issued AD 2014-0263 (later revised) to require a one-
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time inspection of both left hand (LH) and right hand (RH) cabin lateral sliding 

plug doors to verify that no corrosion is present in the affected area of the door 

emergency jettisoning system and, depending on findings, corrective action(s).

After that AD was issued, it was determined that the unsafe condition 

addressed by that AD actually affects AS 332 C, AS 332 C1, AS 332 L, and

AS 332 L1 helicopters, if modified in accordance with Airbus Helicopters mod 

0725870, instead of those modified in accordance with Airbus Helicopters mod 

0723047, as was erroneously specified in Airbus Helicopters ASB 

AS332-53.01.86. That ASB was moreover incorrect in addressing all AS 332 

L2 helicopters as only those equipped with mod AL25612 or mod 0725870 

could have been affected by the corrosion issue.

Prompted by this determination, Airbus Helicopters revised ASB AS332-

53.01.86 to make the inspection instructions and corrective action(s) 

applicable to the affected AS 332 helicopters.

For the reasons described above, this AD retains the requirements of EASA 

AD 2014-0263R1, which is superseded, and redefines the Applicability.

This AD was republished to correct a typographical error with the publication 

month.

Effective Date: 12 August 2015

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time and in accordance with the instructions of the 

applicable ASB, as defined in Appendix 1 of this AD, as applicable to 

helicopter model, and, depending on helicopter configuration and calendar 

time accumulated by the helicopter since new, inspect the affected area of 

the door emergency jettisoning system of both LH and RH cabin lateral 

sliding plug doors to detect any corrosion.

AS 332 L2 helicopters inspected and, depending on findings corrected,

before the effective date of this AD as required by EASA AD 2014-0263

(or EASA AD 2014-0263R1), are compliant with requirements of 

paragraph (1) of this AD.

(2) If, during the inspection as required by paragraph (1) of this AD, any 

corrosion is detected, before next flight, measure the depth of the 

corrosion and accomplish a jettisoning test of the affected door, in 

accordance with the instructions of the applicable ASB, as defined in 

Appendix 1 of this AD, as applicable to helicopter model and 

configuration.

(3) If, during the measurement as required by paragraph (2) of this AD, a 

depth of corrosion less than 0,5 mm is detected, before next flight, 

depending on the result of the jettisoning test as required by paragraph (2) 

of this AD, accomplish the applicable corrective action as specified in 

Table 1 of this AD in accordance with the instructions of the applicable 

ASB, as defined in Appendix 1 of this AD, as applicable to helicopter 

model and configuration.

Table 1 – Corrective Action

Jettisoning Test Corrective Action

Failed Replace the door jettisoning system with a 

serviceable part

Passed Rework the door jettisoning system

(4) If, during the measurement as required by paragraph (2) of this AD a 

depth of corrosion equal to or more than 0,5 mm is detected, before next 

flight, depending on the result of the jettisoning test as required by 
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paragraph (2) of this AD, accomplish the applicable corrective action as 

specified in Table 1 of this AD in accordance with the accomplishment 

instruction(s) of the applicable ASB, as defined in Appendix 1 of this AD, 

as applicable to helicopter model and configuration.

(5) Within 2 months after door jettisoning system rework, as required by 

paragraph (4) of this AD, and thereafter at intervals not to exceed 2 

months, accomplish a jettisoning test of the affected door in accordance 

with the instructions of the applicable ASB, as defined in Appendix 1 of 

this AD, as applicable to helicopter model and configuration.

(6) If, during any jettisoning test as required by paragraph (5) of this AD, the 

test fails, before next flight, replace the door jettisoning system with a 

serviceable system in accordance with the instructions of the applicable 

ASB, as defined in Appendix 1 of this AD, as applicable to helicopter 

model and configuration.

(7) Unless accomplished as required by paragraph (6) of this AD, within 6 

months after door jettisoning system rework as required by paragraph (4) 

of this AD, replace the door jettisoning system with a serviceable system

in accordance with the instructions of the applicable ASB, as defined in 

Appendix 1 of this AD, as applicable to helicopter model and 

configuration.

(8) Replacement of the door jettisoning system on a helicopter, as required 

by paragraph (6) or (7) of this AD, constitutes terminating action for the 

repetitive jettisoning tests as required by paragraph (5) of this AD for that 

helicopter.

Ref. Publications: Airbus Helicopters ASB AS332-53.01.86, dated 18 August 2014 or Revision 1 

dated 29 June 2015.

Airbus Helicopters ASB EC225-53A048, dated 18 August 2014.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact:

Airbus Helicopters (EBSESB) – Aéroport de Marseille Provence 13725 

Marignane Cedex, France;

Telephone +33 (4) 42 85 97 97; Fax +33 (4) 42 85 99 66;

E-mail: Directive.technical-support@airbus.com.
EASA AD No.: 2015-0156

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Appendix 1 – Compliance Times and applicable ASB

AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters, post-mod AL25612

Calendar time accumulated on

12 December 2014 [the effective date of 

EASA AD 2014-0263 at original issue] by 

the helicopter since new

Compliance time ASB

Equal to or more than 12 months Within 3 months after 12 December 

2014 [the effective date of EASA AD 

2014-0263 at original issue]

ASB AS332-53.01.86

or later approved 

revisions Less than 12 months Before exceeding 15 months since the 

date of manufacture

AS 332 C, AS 332 C1, AS 332 L, and AS 332 L1 helicopters, post-mod 0725870

Calendar time accumulated on the 

effective date of this AD by the 

helicopter since new

Compliance time ASB

Equal to or more than 12 months Within 30 days after the effective date 

of this AD ASB AS332-53.01.86

Revision 1 or later 

Less than 12 months Before exceeding 15 months approved revisions since the 

date of manufacture

AS 332 L2 helicopters, post-mod AL25612 or post-mod 0725870, except helicopters inspected and 

corrected before the effective date of this AD as required by EASA AD 2014-0263 (or EASA AD 2014-

0263R1).

Calendar time accumulated on the 

effective date of this AD by the 

helicopter since new

Compliance time ASB

Equal to or more than 12 months Within 30 days after the effective date 

of this AD ASB AS332-53.01.86

Revision 1 or later 

Less than 12 months Before exceeding 15 months since approved revisions the 

date of manufacture

EC 225 LP helicopters

Calendar time accumulated on

12 December 2014 [the effective date of 

EASA AD 2014-0263 at original issue] by 

the helicopter since new

Compliance time ASB

Equal to or more than 12 months Within 3 months after 12 December 

2014 [the effective date of EASA AD

2014-0263 at original issue]

ASB EC225-53A048, 

or later approved 

revisions Less than 12 months Before exceeding 15 months since the 

date of manufacture