EASA AD No.: 2012-0251

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0251 

Date: 27 November 2012 

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 21A.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: 

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 – Modification 

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

Applicability: C-212-CB, C-212-CC, C212-CE, C-212-CD, C-212-DD, C212-DF and 

C-212-EE aeroplanes, all manufacturer serial numbers, except those that have 

been modified in production to incorporate modification (mod) 10515. 

Reason: An occurrence was reported where the propeller 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 loss of an affected propeller 

pitch control, possibly resulting in uncommanded change to the engine power 

settings and consequent reduced control of the aeroplane. 

To address this potential unsafe condition, EADS-CASA developed a 

modification (mod 10515) that eliminates the possibility of PPC shaft 

disconnection and made this available through Service Bulletin 

SB-212-76-0009 to be applied in service. 

For the reasons described above, this AD requires modification of PPC lever 

attachment system. 

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

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Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

Within 24 months after the effective date of this AD, modify the aeroplane 

engine power control in accordance with the accomplishment instructions of 

EADS-CASA SB-212-76-0009 Revision 1. 

Ref. Publications: EADS CASA (Airbus Military) SB-212-76-0009 Revision 1, dated 3 August 

2012. 

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 24 October 2012 as PAD 12-133 for consultation 

until 21 November 2012. 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: 

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.