EASA AD No.: 2013-0069

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0069

Date: 18 March 2013

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, A rticle 14(4) exemption].



### Design Approval Holder’s Name:

EUROCOPTER Type/Model designation(s): AS 332 and EC 225 helicopters

TCDS Number: EASA.R.002

Foreign AD: Not applicable

Supersedure: None



### ATA 29, 67 Hydraulic Power / Rotors Flight Control – Main Gear box Compartment / Hydraulic Flexible Pipes – Inspection / Replacement

Manufacturer(s): Eurocopter (formerly EUROCOPTER Fr ance).

Applicability: AS 332 C, AS 332 C1, AS 332 L, AS 33 2 L1, AS 332 L2 and EC 225 LP helicopters, all serial numbers.

Reason: In-flight loss of left hand (LH) hydraulic pressure was reported on a helicopter equipped in the Main Gearbox (MGB) compartment with hydraulic flexible pipes fitted with surrounding fire-resistant protection s heath. The subsequent investigation revealed that the pressure loss was c aused by a hydraulic fluid leakage from an hydraulic pressure pipe of the MGB compartment located between the forward main rotor servo-control and th e hydraulic manifold. The failed flexible pipe, supplied by TECALEMIT, burst due to severe corrosion on the metal braid of the pipe underneath its fire-res istant protection sheath. This corrosion was a result of a large tear damage found on the pipe fire-resistant sheath, enabling humidity to enter between the shea th and the metal braid.
Following this incident, Eurocopter issued Service Bulletin (SB) No.AS332-05.00.92 and SB No.EC225-05-027, as applic able to helicopter model, recommending repetitive inspection of the f ire-resistant sheath of all the hydraulic flexible pipes located in the MGB compart ment, and launched the update of both Aircraft Maintenance Manual and Main tenance Program accordingly.
In the meanwhile, new cases of in-flight hydraulic pressure loss were reported, for which the same root cause, significant tears on the protection sheath of other MGB hydraulic flexible pipes manufactured by TECALEMIT, was identified. This repetition of similar incidents ev idenced the potential of a higher number of damaged hydraulic pipes than initially ap preciated and the reanalysis of the issue concluded that severe sheat h damages are more criticalEASA AD No.: 2013-0069

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. on TECALEMIT hydraulic flexible pipes than on other equivalent parts from different supplying sources.
This condition, if not detected and corrected, coul d lead, in case of simultaneous LH and right hand (RH) hydraulic syste m leakage, to loss of hydraulic systems and consequent loss of helicopter control.
For the reasons described above, this AD requires a one-time inspection of the TECALEMIT flexible pipes installed on both LH and R H hydraulic system circuits located in the MGB compartment and, depend ing on findings, replacement of damaged pipes.

Effective Date: 01 April 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
(1) Within 110 flight hours (FH) or 3 months, which ever occurs first after the effective date of this AD, inspect to identify hydr aulic flexible pipes installed on both LH and RH hydraulic circuits in the helicop ter MGB compartment. A review of helicopter delivery or maintenance reco rds is acceptable to determine the installed hydraulic flexible pipe man ufacturer, provided the flexible pipe manufacturer can be determined from t hat review.
(2) If, during the identification as required by pa ragraph (1) of this AD, TECALEMIT flexible pipes are found to be installed on both, LH and RH, hydraulic circuits in the helicopter MGB compartmen t, within 110 FH or 3 months, whichever occurs first after the effectiv e date of this AD, inspect all TECALEMIT hydraulic flexible pipes installed in the MGB compartment in accordance with the instructions of paragraph 3 of Eurocopter SB No.AS332-05.00.92 or SB No.EC225-05.027, as applica ble to helicopter model.
Note 1: The name of the flexible pipe manufacturer may not be indicated on the pipe. However, the Part Number (P/N) of a TECALEMIT hydraulic flexible pipe starts with “66”.
(3) If, during the inspection as required by paragr aph (2) of this AD, at least one TECALEMIT pipe is found damaged on both LH and RH hydraulic circuits, within the compliance time as specified i n Table 1 of this AD, as applicable, replace each damaged hydraulic flexible pipe with a serviceable part in accordance with the instruction s of paragraph 3.B.3 of Eurocopter SB No.AS332-05.00.92 or EC225 SB No.EC22 5-05.027, as applicable to helicopter model.

Table 1

Hydraulic Flexible Pipe Condition / Location Compliance Time

Severe sheath damage (see note 2) detected on the RH hydraulic system Before next flight after the inspection as required by paragraph (2) of this AD

Less critical sheath damage (see note 3) detected on the RH hydraulic system Within 300 FH or 6 months, whichever occurs first after the effective date of this AD

Any damage detected on the LH hydraulic system Within 600 FH or 12 months, whichever occurs first after the effective date of this AD

Note 2: Severe sheath damage is defined as any shea th tear or cut or open cracking that shows the pipe metallic braid underne ath, when pinching or twisting the sheath.
Note 3: Less critical sheath damage is defined as a ny other sheath damageEASA AD No.: 2013-0069

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. (e.g. notch, light tear or crack, friction mark, ga ping) as specified in paragraph 3 of Eurocopter SB No.AS332-05.00.92 or SB No.EC225-0 5.027, as applicable to helicopter model.

Ref. Publications: Eurocopter SB No.AS332-05.00.92, revision 0 dated 24 September 2012,
Eurocopter SB No.EC225-05.027, revision 0 dated 24 September 2012.
The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 27 February 2013 as PAD 13 -039 for consultation until 13 March 2013. No comments were received duri ng the consultation period.
3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: EUROCOPTER (STDI) – Aéroport de Marseille Provence, 13725 Marignane Cedex, France; telephone +33 (4) 42 85 97 97; facsi mile +33 (4) 42 85 99 66; E-mail: Directive.technical-support@eurocopter.com

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