EASA AD No.: 2010-0117-E

EASA Form 111 Page 1/3 

## EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2010-0117-E

Date: 16 June 2010
Note: This Emergency Airworthiness Directive (AD) i s issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, 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 EC 1702/2003, Part 21A.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 accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption]. 

### Type Approval Holder’s Name:
EUROCOPTER Type/Model designation(s): AS 332 helicopters

TCDS Number: EASA.R.002
Foreign AD: Not applicable

Revision: None



### ATA 67 Rotors Flight Controls – Main Rotor Servocontrols End Fitting Ball

Joints - Inspection / Replacement

Manufacturer(s): Eurocopter (formerly Eurocopter France)
Applicability: AS 332 C, AS 332 C1, AS 332 L, AS 332 L1 and AS 332 L2 helicopters, all serial

numbers, if equipped with main rotor servocontrols Manufacturer Part Number (MP/N) SC7203-1 or SC7221-1 with the Serial Numbers (S/N) listed in the following table 1 below and not marked with a letter "R" after the S/N:
MP/N: SC7203-1 MP/N: SC7221-1

S/N 633 to 643 inclusive S/N 1693 to 1723 inclusive S/N 645 to 659 inclusive S/N 1726 to 1727 inclusive S/N 664 to 665 inclusive Table 1
Note: Servocontrols with the letter “R” after the S/N hav e already been made compliant.
Reason: EUROCOPTER has been informed of non-complia nt swaging of the end fitting

ball joints on main rotor servocontrols. Two servoc ontrol production batches have been identified by the equipment manufacturer (GOOD RICH). Investigations have revealed that the swaging load applied to the ball joints in these two batches was 1.3 metric tons, instead of t he specified 13 metric tons, which could lead the ball joints to slip in service

.EASA AD No.: 2010-0117-E

EASA Form 111 Page 2/3 The slipping of the ball joint of the servocontrol lower end fitting does not significantly affect the service life of this end f itting while the slipping of the ball joint of the servocontrol upper end fitting can lea d to a significant reduction in the service life of this end fitting. This last conditi on, if not corrected, could likely lead to damage of the upper end fitting ball joints of t he main rotor servocontrols and possibly resulting in failure of upper end fittings

. For the reasons stated above, this AD requires an i nspection of the upper end fitting ball joints of the main rotor servocontrols and the necessary corrective action (replacement), depending on findings.

Effective Date: 18 June 2010.
Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 15 Flight Hours (FH) after the effective date of this AD, for each servocontrol concerned, measure the shifting value between the outer ring of the ball joint and the face of the upper end fittin g in accordance with the instructions of paragraph 2.B.2. of Eurocopter AS 3 32 Alert Service Bulletin (ASB) No. 67.00.40. Accomplish the same inspection on the second face of the servocontrol upper end fitting. (2) If the shifting value measured, as required by paragraph (1) of this AD, is more (higher) than or equal to 1 mm (0.04 in.) and the servocontrol has accumulated 825 FH or more since new (Time Since Ne w (TSN)), before next flight, replace the servocontrol with a servic eable one. (3) If the shifting value measured, as required by paragraph (1) of this AD, is more (higher) than or equal to 1 mm (0.04 in.) and the servocontrol has accumulated less that 825 FH since new, before the servocontrol accumulates 825 FH but without exceeding two years after the effective date of this AD, replace the servocontrol with a service able one. (4) If the shifting value measured, as required by paragraph (1) of this AD, is less (lower) than 1 mm (0.04 in.), accomplish the f ollowing actions: (4.1) At intervals not to exceed 300 FH, repeat the inspection required by paragraph (1) of this AD. (4.2) If the shifting value measured, as required b y paragraph (4.1) of this AD, is more (higher) than or equal to 1 mm (0. 04 in.), within 525 FH, replace the servocontrol with a serviceable one. (4.3) Within two years after the effective date of this AD, replace all servocontrols with serviceable ones or accomplish i nstructions of GOODRICH Service Bulletin No. SC7203-67-31-02 (serv ocontrols MP/N SC7203-1) or No. SC7221-67-39-02 (servocontrol s MP/N SC7221-1), as applicable, on each servocontrol to r estore conformity.

Ref. Publications: Eurocopter AS 332 Alert Service Bulletin No. 67.00. 40 dated 15 June 2010.

GOODRICH Service Bulletin No. SC7203-67-31-02 dated 11May 2010.
GOODRICH Service Bulletin No. SC7221-67-39-02 dated 11May 2010. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.EASA AD No.: 2010-0117-E

EASA Form 111 Page 3/3 Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. The safety assessment has requested not to imple ment the full consultation process and an immediate publication and notificati on. 3. Enquiries regarding this AD should be referred t o the Airworthiness Directives, Safety Management & Research Section, C ertification 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) 12 85 97 97, facsimile +33 (4) 42 85 99 66 E-mail: Directive.technical-support@eurocopter.com

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