EASA AD No.: 2013-0131

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0131

Date: 25 June 2013

Note: This Airworthiness Directive (AD) is issued b y 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 th e activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.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): CN-235-300 aeroplanes

TCDS Number: EASA.A.186

Foreign AD: Not applicable

Supersedure: None



### ATA 53 Fuselage – Centre Fuselage Lower Skin Panel – Inspection

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

Applicability: CN-235-300 aeroplanes, manufacturer serial numbers (MSN) from C-143 through C-208 (inclusive).

Reason: During delivery of a spare centre fuselage lower skin panel to a CN-235 aeroplane operator, a reduced thickness of the spar e panel was identified. The affected panel is used as the lower part of the fus elage between Frame (FR) FR13 and FR21, and from Stringer (STR) 24 left hand (LH) side to STR24 right hand (RH) side. Several CN-235 aeroplanes cou ld have been delivered with a reduced thickness panel.
This condition, if not detected and corrected, coul d result in reduced fatigue and damage tolerant characteristics of the lower pa nel joint to the adjacent side panels and lead to failure of the part. To address this potentially unsafe condition, EADS- CASA issued All Operator Letter (AOL) 235-024 to provide instructions to det ermine correct centre fuselage lower panel configuration by accomplishing a detailed visual inspection (DVI) of affected fuselage area.
For the reason described above, this AD requires a one-time inspection of the affected panel thickness at STR24 LH and STR24 RH. In case a nonconforming panel is found to be installed, this AD requires repetitive Non Destructive Testing (NDT) inspections and, dependin g on findings, the accomplishment of applicable corrective action(s).EASA AD No.: 2013-0131

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 09 July 2013

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) For aeroplanes with MSN C-143 to C-195, C-201 and C -202: Within the threshold as defined in Table 1 of this AD, as applicable to the aeroplane version, or within 10 flight cycles (FC) accumulated during no more than 30 days after the effective date of this AD, whichever occurs later, accomplish a DVI to determine the presence o f panel thickness reduction of the lower panel joint with the side pa nels at STR24 LH and STR24 RH in accordance with instructions of EADS-CA SA AOL 235-024 at Revision 1. Table 1 – Compliance time

Aeroplane version(s) Compliance time (FC accumulated since aeroplane first flight)
CG01, CL04, ED01, GC01, MM01 and SM01 1 900 FC

Any other version 3 800 FC

(2) For aeroplanes with MSN C-196 to C-200, C-203 to C- 208 or aeroplanes with a reduced panel thickness identifie d during inspection as required by paragraph (1) of this AD : Initially within the threshold as defined in Table 1 of this AD, as applicable to the aeroplane version, or within 50 FC, whicheve r occurs later after the effective date of this AD, and thereafter at interv als not to exceed the value as defined in Table 2 of this AD, as applicab le to the aeroplane version, accomplish a NDT inspection in accordance with the instructions of EADS-CASA AOL 235-024 at Revision 1.

Table 2 – Repetitive Inspections
Aeroplane version(s) Inspection Interval (not to exceed)
CG01, CL04, ED01, GC01, MM01 and SM01 1 000 FC

Any other version 2 000 FC

(3) If, during any inspection as required by paragr aph (2) of this AD, any discrepancy is detected, before next flight, contac t EADS-CASA (Airbus Military) for approved repair instructions and acco mplish those instructions accordingly. (4) Inspections, accomplished before the effective date of this AD, in accordance with the instructions of EADS-CASA AOL 2 35-024 at original issue, are acceptable to comply with the requiremen ts of paragraphs (1) and (2) of this AD. After the effective date of thi s AD, the instructions of EADS-CASA AOL 235-024 at Revision 1 (or later appro ved revisions) have to be used.

Ref. Publications: EADS-CASA AOL 235-024 Revision 1 , dated 01 March 2013. 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 May 2013 as PAD 13-066 for consultation until 19 June 2013. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the Safety InformationEASA AD No.: 2013-0131

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/3 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 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.