EASA AD No.: 2013-0069

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2013-0069 

Date: 18 March 2013 

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 EC 2042/2003 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 [EC 

2042/2003 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: 

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 Gearbox 

Compartment / Hydraulic Flexible Pipes – Inspection / Replacement

Manufacturer(s): Eurocopter (formerly EUROCOPTER France). 

Applicability: AS 332 C, AS 332 C1, AS 332 L, AS 332 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 sheath. The subsequent 

investigation revealed that the pressure loss was caused by a hydraulic fluid 

leakage from an hydraulic pressure pipe of the MGB compartment located 

between the forward main rotor servo-control and the hydraulic manifold. The 

failed flexible pipe, supplied by TECALEMIT, burst due to severe corrosion on 

the metal braid of the pipe underneath its fire-resistant 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 sheath and the metal braid. 

Following this incident, Eurocopter issued Service Bulletin (SB) 

No.AS332-05.00.92 and SB No.EC225-05-027, as applicable to helicopter 

model, recommending repetitive inspection of the fire-resistant sheath of all the 

hydraulic flexible pipes located in the MGB compartment, and launched the 

update of both Aircraft Maintenance Manual and Maintenance 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 evidenced the potential of a higher 

number of damaged hydraulic pipes than initially appreciated and the 

reanalysis of the issue concluded that severe sheath damages are more critical 
EASA AD No.: 2013-0069

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on TECALEMIT hydraulic flexible pipes than on other equivalent parts from 

different supplying sources. 

This condition, if not detected and corrected, could lead, in case of 

simultaneous LH and right hand (RH) hydraulic system 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 RH hydraulic system 

circuits located in the MGB compartment and, depending on findings, 

replacement of damaged pipes. 

Effective Date: 01 April 2013 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 110 flight hours (FH) or 3 months, whichever occurs first after the 

effective date of this AD, inspect to identify hydraulic flexible pipes installed 

on both LH and RH hydraulic circuits in the helicopter MGB compartment.

A review of helicopter delivery or maintenance records is acceptable to 

determine the installed hydraulic flexible pipe manufacturer, provided the 

flexible pipe manufacturer can be determined from that review. 

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

TECALEMIT flexible pipes are found to be installed on both, LH and RH, 

hydraulic circuits in the helicopter MGB compartment, within 110 FH or 

3 months, whichever occurs first after the effective 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 applicable 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 paragraph (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 in Table 1 of this AD, as 

applicable, replace each damaged hydraulic flexible pipe with a 

serviceable part in accordance with the instructions of paragraph 3.B.3 of 

Eurocopter SB No.AS332-05.00.92 or EC225 SB No.EC225-05.027, 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 sheath tear or cut or open 

cracking that shows the pipe metallic braid underneath, when pinching or 

twisting the sheath. 

Note 3: Less critical sheath damage is defined as any other sheath damage 
EASA AD No.: 2013-0069

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(e.g. notch, light tear or crack, friction mark, gaping) as specified in paragraph 3 

of Eurocopter SB No.AS332-05.00.92 or SB No.EC225-05.027, 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 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. This AD was posted on 27 February 2013 as PAD 13-039 for consultation 

until 13 March 2013. No comments were received during the consultation 

period. 

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

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

4. For any question concerning the technical content 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; facsimile +33 (4) 42 85 99 

66; E-mail: Directive.technical-support@eurocopter.com.