EASA AD No.: 2013-0131 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2013-0131 

Date: 25 June 2013 

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 21.A.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): 

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 spare panel was identified. The 

affected panel is used as the lower part of the fuselage 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 could have been delivered 

with a reduced thickness panel. 

This condition, if not detected and corrected, could result in reduced fatigue 

and damage tolerant characteristics of the lower panel 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 determine 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, depending on findings, the 

accomplishment of applicable corrective action(s). 
EASA AD No.: 2013-0131 

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Effective Date: 09 July 2013 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(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 of panel thickness 

reduction of the lower panel joint with the side panels at STR24 LH and 

STR24 RH in accordance with instructions of EADS-CASA 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 identified 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, whichever occurs later after the 

effective date of this AD, and thereafter at intervals not to exceed the 

value as defined in Table 2 of this AD, as applicable 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 paragraph (2) of this AD, any 

discrepancy is detected, before next flight, contact EADS-CASA (Airbus 

Military) for approved repair instructions and accomplish those instructions 

accordingly. 

(4) Inspections, accomplished before the effective date of this AD, in 

accordance with the instructions of EADS-CASA AOL 235-024 at original 

issue, are acceptable to comply with the requirements of paragraphs (1) 

and (2) of this AD. After the effective date of this AD, the instructions of 

EADS-CASA AOL 235-024 at Revision 1 (or later approved 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 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 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 Information 
EASA AD No.: 2013-0131 

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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.