EASA AD No.: 20 15

- 0040

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 15 - 0040

Date: 06 March 2015

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 E U 748/2012 , Part 21

. A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requ irements of that AD , unless otherwise specified by the Agency [ EU 1321/2014 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): CN

- 235 aeroplanes

TCDS Number: EASA.A.186

F oreign AD: Not applicable
Supersedure: None



### ATA 57 Wings

– Aileron Fittings

– Inspection

Manufacturer(s): EADS

- CASA; formerly Construcciones Aeronáuticas S.A.(CASA)
Applicability: CN

- 235 , CN

- 235

- 100, CN

- 235

- 200 and CN

- 235

- 300 aeroplanes, all serial numbers.
Reason: A CN

- 235 o perator recently reported finding , during scheduled maintenance tasks , cracks on the lugs of the control rod fittings (inboard and outboard) of the ailerons [ R ight H and ( RH ) and L eft H and ( LH ) side ] of two aeroplanes

. At the time of the finding , the two a ffected aeroplanes had accumulated between 16 000 and 17 000 f light h ours (FH), around 6 000 f light c ycles and had been in service for 20 years

. Following the investigation results , it was determined that these cracks were due to stress corrosion. T his condition , if not detected and corrected , could lead to aileron fittings failure , possibly resulting in reduced control of the aeroplane

. To address this unsafe condition and verify the integrity of the fittings , EADS

CASA (Airbus Military) issued Alert Operators Transmission (AOT) CN235

- 57

- 0001 to provide instructions for a one - time Non

- Destructive (NDT) i nspection of the affected fitting s for cracks and corrosion

. For the reasons described above, this AD requires a one

- time NDT inspection of the affected aileron fittings and, if discrepancies are detected, accomplishment of applicable corrective action(s).
Effective Date: 20 March 2015EASA AD No.: 20 15

- 0040

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 2 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within the compliance time as defined in Table 1 of this AD, as applicable, accomplish an NDT inspection of the affected aileron fitting s in accordance with the instructions of EADS

- CASA (Airbus Military) AOT

- CN235

- 57

- 0001

. Table 1

– NDT Inspection Compliance Time (whichever occurs later, A or B )
A B efore exceeding 8 000 FH or 10 years , whichever occurs first since aeroplane first flight

. B Within 3 months after the effective date of this AD (2) If during the inspection as required in paragraph (1) of this AD , any crack or corrosion is detected, before next flight, contact EADS

- CASA for approved repair instructions and , within the compliance time indicated in those instructions , accomplish the repair accordingly.
Ref. Public ations: EADS

- CASA ( Airbus Military ) AO T

- CN235

- 57

- 0001 o riginal issue dated 26 February 2014 or Revision 1 dated 14 March 2014

. The use of later approved revisions of th is 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 04 February 2015 as PAD 15

- 009 for consultation until 04 March 2015

. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification 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

.