EASA AD No.: 2012-0251

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0251

Date: 27 November 2012

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 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 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: EADS-CASA Type/Model designation(s): C-212 aeroplanes

TCDS Number: Spain No. 01-82

Foreign AD: Not applicable

Supersedure: None



### ATA 76 Engine Controls – Engine Power Control – Mod ification

Manufacturer(s): EADS-CASA, formerly Construcciones Aeronáuticas S.A.(CASA)

Applicability: C-212-CB, C-212-CC, C212-CE, C-212-C D, C-212-DD, C212-DF and C-212-EE aeroplanes, all manufacturer serial number s, except those that have been modified in production to incorporate modifica tion (mod) 10515.

Reason: An occurrence was reported where the propel ler pitch control (PPC) lever disconnected from the engine (a TPE331-10R-511C) on a C-212-CC aeroplane. The result of the subsequent investigation revealed that the PPC lever disconnection occurred due to a missing bolt, which fixes the clamp that joins the PPC lever to the PPC rod. This condition, if not corrected, could lead to a l oss of an affected propeller pitch control, possibly resulting in uncommanded ch ange to the engine power settings and consequent reduced control of the aero plane. To address this potential unsafe condition, EADS-CA SA developed a modification (mod 10515) that eliminates the possib ility of PPC shaft disconnection and made this available through Servi ce Bulletin SB-212-76-0009 to be applied in service. For the reasons described above, this AD requires m odification of PPC lever attachment system.

Effective Date: 11 December 2012EASA AD No.: 2012-0251

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
Within 24 months after the effective date of this A D, modify the aeroplane engine power control in accordance with the accompl ishment instructions of EADS-CASA SB-212-76-0009 Revision 1.

Ref. Publications: EADS CASA (Airbus Military) SB-2 12-76-0009 Revision 1, dated 3 August 2012. The use of later approved revisions of this documen t 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 24 October 2012 as PAD 12- 133 for consultation until 21 November 2012. No comments were received d uring 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: EADS CASA (Airbus Military) Services / Engineering Support e-mail: MTA.TechnicalService@military.airbus.com. Fax: +34 91 585 3127 For US operators, contact alternatively: e-mail: TechnicalSupport@airbusmilitaryna.com

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