EASA AD No.: 2015-0128

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0128

Date: 03 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:

TURBOMECA

Type/Model designation(s):

TURMO IV C engines

TCDS Number: EASA.E.074

Foreign AD: Not applicable

Supersedure: This AD supersedes DGAC France AD F-2005-037 dated 02 March 2005, EASA 

approval 2005-1910.

ATA 72 Engine – Centrifugal Compressor – Replacement / Inspection

Manufacturer(s): Turbomeca, S.A.

Applicability: TURMO IV C engines, all serial numbers.

These engines are known to be installed on, but not limited to, Airbus 

Helicopters (formerly Eurocopter, Aerospatiale) SA 330 J (PUMA) helicopters.

Reason: Several occurrences were reported of engine power loss or in-flight shut-down 

as a result of detachment of one or more blade pieces from a TURMO IV 

centrifugal compressor inducer. Investigations revealed that the failures were 

due to fatigue cracks on these blades, caused either by a corrosion 

phenomenon, or by an impact associated to vibratory stress in a range from 

80% to 83% gas generator speed, or by a superposition of the inducer vibratory 

resonances. 

This condition, if not detected and corrected, could lead to an uncommanded 

engine in-flight shut-down, possibly resulting in an emergency landing with 

consequent damage to the helicopter and injury to occupants.

To address this potential unsafe condition, Turbomeca developed several 

standards of centrifugal compressor inducers. In-service experience shows 

different behaviour in terms of initiation of corrosion and/or cracks between 

these standards. This led to the issuance of Service Bulletins providing 

instructions for repetitive inspections (ultrasonic, Eddy Current or boroscopic) of 

the centrifugal compressors, with different periodicities depending on the 

standard of centrifugal compressors.

Prompted by these findings, DGAC France issued AD 97-122 (later revised and 

re-numbered as 1997-122) to require those repetitive inspections of the 
EASA AD No.: 2015-0128

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centrifugal compressor, in order to detect incipient cracks on the blades and/or 

presence of corrosion. DGAC France AD 1997-122 R3 was subsequently 

superseded by DGAC France AD F-2005-037 (EASA approval 2005-1910), 

retaining the requirements, but specifying amended inspections intervals.

Since AD F-2005-037 was issued, a specific vibration criterion was introduced 

during manufacture on certain centrifugal compressors, incorporating 

modification (mod) TU 224 (centrifugal compressor assembly Part Number 

(P/N) 0 249 25 790 0, or P/N 0 249 25 811 0) to prevent vibratory resonances 

superposition. In-service experience shows that no crack associated to this 

resonance phenomenon has been reported on post-mod TU 224 engines. 

More recently, a case of centrifugal compressor inducer blade loss occurred on 

a post-mod TU 224 engine. This blade loss was determined to be due to cracks 

caused by impacts combined with significant erosion of the part. 

For the reasons described above, this AD does not retain the requirements of 

DGAC France AD F-2005-037, which is superseded, and requires modification 

of engines in post-mod TU 197 or TU 215 configuration to post-mod TU 224 

configuration, repetitive ultra-sonic or Eddy Current inspections of centrifugal 

compressor inducers, repetitive boroscope inspections of centrifugal 

compressor inducers and, depending on findings, replacement of the 

centrifugal compressor.

Effective Date: 17 July 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) For engines in post-mod TU 197 or post-mod TU 215 configuration: within 

30 days after the effective date of this AD, replace each pre-mod TU 224 

centrifugal compressor with a post-mod TU 224 centrifugal compressor in 

accordance with the instructions of Turbomeca Mandatory SB (MSB) 

A249 72 0100 Version H.

(2) Within the threshold specified in Turbomeca MSB A249 72 0100 Version 

H, as applicable depending on the engine configuration, and, thereafter, at 

intervals not to exceed the values specified in Table 1 of this AD, (except 

as specified in Note 1 of this AD), accomplish an ultra-sonic or Eddy 

Current inspection of the centrifugal compressor inducer in accordance 

with the instructions of Turbomeca MSB A249 72 0100 Version H.

Table 1 – Intervals for Repetitive Inspection

Engine Configuration Interval

Engines without the following modifications: TU 191, 

TU 197, TU 215 or TU 224

400 flight hours 

(FH)

Post-mod TU 191 engines

1 000 FH

Post-mod TU 224 engines, fitted with a centrifugal 

compressor assembly Part Number (P/N) 

0 249 25 802 0

Post-mod TU 224 engines fitted with a centrifugal 

compressor assembly P/N 0 249 25 790 0 or 

P/N 0 249 25 811 0 and an inducer serial number 

(S/N) listed in Appendix 1 of this AD

Post-mod TU 224 engines fitted with a centrifugal 

compressor assembly P/N 0 249 25 790 0 or P/N 

0 249 25 811 0, and an inducer S/N not listed in 

Appendix 1 of this AD

3 000 FH
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(3) Within the threshold specified in Turbomeca MSB A249 72 0100 Version 

H, as applicable depending on the engine configuration, and, thereafter, at 

intervals not to exceed 100 FH or 12 months, whichever occurs first, 

accomplish a boroscope inspection of the centrifugal compressor inducer 

in accordance with the instructions of Turbomeca MSB 

A249 72 0100 Version H.

Note 1: A non-cumulative tolerance of 10 FH may be applied only to the 

repetitive inspection interval expressed in FH, as specified in paragraphs (2) 

and (3) of this AD.

(4) Accomplishment on an engine of an ultra-sonic or Eddy Current inspection 

of the inducer, as required by paragraph (2) of this AD, is acceptable in lieu 

of a boroscope inspection as required by paragraph (3) of this AD for that 

engine.

(5) If, during any inspection as required by paragraph (2) or (3) of this AD, as 

applicable, any crack, corrosion or other damage is detected on the 

inducer, before next flight, replace the affected centrifugal compressor with 

a serviceable part.

(6) Modification of an engine, accomplished before the effective date of this 

AD in accordance with the instructions of Turbomeca MSB A249 72 0100 

Version G or an earlier version, is acceptable to comply with the 

modification requirement of paragraph (1) of this AD for that engine.

(7) Inspections and corrective actions, accomplished on an engine before the 

effective date of this AD in accordance with the instructions of Turbomeca 

MSB A249 72 0100 Version G or an earlier version, are acceptable to 

comply with the initial inspection requirements of this AD for that engine.

(8) Replacement of a centrifugal compressor on an engine, as required by 

paragraph (5) of this AD, does not constitute terminating action for the 

repetitive inspections as required by paragraphs (2) and (3) of this AD for 

that engine.

(9) From the effective date of this AD, installation of a centrifugal compressor 

on an engine is allowed, provided the part has been modified to 

incorporate Turbomeca mod TU 224.

Ref. Publications: Turbomeca MSB A249 72 0100 Version H dated 27 May 2015.

The use of later approved revisions of this document 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. This AD was posted on 29 May 2015 as PAD 15-071 for consultation until 

26 June 2015. No comments were received during the consultation period.

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 PAD, please contact: Operator Support & Sales TURMO -

TURBOMECA 40220 TARNOS – France

Telephone: +33 (0)5 59 74 40 00, Fax: +33 (0)5 59 74 45 15,

or contact your nearest TURBOMECA field representative on 

http://www.turbomeca-support.com.
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Appendix 1 – Affected Inducers P/N 2 249 25 138 0 listed by S/N

3594AD 3646AD 3757AD 3877AD 3931AD 3996AD

3595AD 3647AD 3758AD 3878AD 3932AD 3997AD

3596AD 3648AD 3759AD 3879AD 3933AD 3999AD

3597AD 3649AD 3760AD 3880AD 3935AD 4001AD

3599AD 3653AD 3761AD 3881AD 3936AD 4004AD

3600AD 3670AD 3762AD 3882AD 3937AD 4005AD

3601AD 3671AD 3763AD 3883AD 3939AD 4006AD

3603AD 3672AD 3764AD 3884AD 3940AD 4007AD

3604AD 3674AD 3765AD 3885AD 3941AD 4008AD

3606AD 3675AD 3766AD 3886AD 3942AD 4009AD

3607AD 3676AD 3767AD 3887AD 3943AD 4010AD

3609AD 3678AD 3768AD 3888AD 3944AD 4011AD

3610AD 3679AD 3769AD 3890AD 3945AD 4012AD

3611AD 3680AD 3770AD 3891AD 3946AD 4013AD

3612AD 3681AD 3771AD 3893AD 3947AD 4016AD

3613AD 3682AD 3772AD 3894AD 3948AD 4017AD

3614AD 3683AD 3773AD 3895AD 3949AD 4018AD

3615AD 3685AD 3835AD 3896AD 3950AD 4023AD

3616AD 3686AD 3840AD 3897AD 3951AD 4061AD

3617AD 3687AD 3843AD 3899AD 3952AD 4062AD

3618AD 3688AD 3844AD 3900AD 3955AD 4063AD

3619AD 3689AD 3849AD 3901AD 3956AD 4064AD

3620AD 3690AD 3850AD 3902AD 3958AD 4065AD

3621AD 3691AD 3851AD 3903AD 3960AD 4066AD

3622AD 3692AD 3853AD 3904AD 3961AD 4067AD

3623AD 3714AD 3854AD 3905AD 3964AD 4068AD

3624AD 3715AD 3855AD 3906AD 3965AD 4069AD

3625AD 3716AD 3856AD 3907AD 3966AD 4070AD

3626AD 3717AD 3857AD 3908AD 3967AD 4071AD

3627AD 3718AD 3859AD 3910AD 3969AD 4072AD

3628AD 3719AD 3860AD 3911AD 3970AD 4075AD

3629AD 3720AD 3861AD 3912AD 3972AD 4076AD

3630AD 3721AD 3862AD 3913AD 3973AD 4077AD

3631AD 3722AD 3863AD 3914AD 3975AD 4078AD

3633AD 3723AD 3864AD 3916AD 3976AD 4080AD

3634AD 3724AD 3865AD 3917AD 3978AD 4083AD

3635AD 3725AD 3866AD 3918AD 3982AD 4084AD

3636AD 3726AD 3867AD 3919AD 3984AD 4088AD

3637AD 3728AD 3868AD 3920AD 3985AD 4089AD

3638AD 3729AD 3870AD 3921AD 3986AD 4092AD

3639AD 3730AD 3871AD 3922AD 3987AD 4100AD

3640AD 3732AD 3872AD 3924AD 3989AD

3641AD 3733AD 3873AD 3925AD 3990AD

3642AD 3754AD 3874AD 3926AD 3991AD

3643AD 3755AD 3875AD 3928AD 3992AD

3645AD 3756AD 3876AD 3929AD 3995AD