EASA 

EASA AD No.: 2014-0155 

AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0155 

Date: 02 July 2014 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) No 21612008 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: Type/Model designation(s): 

CEAPR 

TCDS Numbers: 

Foreign AD: 

Supersedure: 

ATA73 

Manufacturer(s): 

Applicability: 

Reason: 

ATL, DR 200, DR 220, DR 221, DR 250, DR 253, 

DR 300, DR 460, HR 100, R 1180 and R 3000 

aeroplanes 

EASAA367, EASAA368, EASAA372, EASAA374, EASA.A.510, EASAA551 

and EASA.A.552 

Not applicable 

This AD supersedes DGAC France AD 1999-053 R1 dated 10 March 1999 and 

AD 1999-470 dated 01 December 1999. 

Engine - Engine Air Intake Box and Air Ducting -Inspection I 

Replacement 

Centre est Aeronautique, Avions Pierre Robin, Robin Aviation, Constructions 

Aeronautiques de Bourgogne, APEX Industries, Finch Aircraft, Robin Aircraft. 

ATL, DR 200, DR 220, DR 221, DR 250, DR 253, DR 300, HR100, R1180 and 

R 3000 aeroplanes, all models, all serial numbers (s/n) and 

DR 400 aeroplanes, all models, all s/n except those modified in accordance 

with EASA STC EASA.A.S.01380 or STC No. 10014219 (TAE 125 diesel 

engine installation) . 

An accident occurred on a DR 400 aeroplane during take-off phase. Technical 

investigations showed paint adherence defects inside the engine air intake box, 

Part Number 56.15. 01 .000. It was determined that the engine carburettor had 

been blocked by small pieces of paint from the engine air intake box, so that 

the engine could not deliver its maximum power and the performance of the 

aeroplane, notably during take-off, had been significantly degraded. 

This condition, if no1 detected and corrected, could lead to an engine failure, 

possibly resulting in loss of control of the aeroplane. 

To initially address this issue, DGAC France published AD 1999-053 (later 

revised) to require inspection of the engine air intake box. After that AD was 

issued, cohesion defects were found inside the laminated air ducting from 

engine filter to engine air intake box. Prompted by these findings, DGAC 

France issued AD 1999-470 to require inspection of the engine laminated air 

ducting. 

TE.CAP.OOll0-003 ©European Aviation Safety Agency. All rights reserved. 1/ 2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/lntranet. 
EASAAD No.: 2014-0155 

Since DGAC France AD 1999-053 R1 and AD 1999-470 were issued, several 

engine failures and malfunctions have occurred due to the same root causes. 

Consequently, CEAPR issued SB N" 161 Revision 3 to provide more detailed 

inspection and replacement instructions. 

For the reasons described above, this AD retains the requirements of DGAC 

France AD 1999-053 R1 and AD 1999-470, which are superseded, and 

requires repetitive inspections and, depending on findings, replacement of the 

engine air intake box and engine air dueling in accordance with the revised 

instructions. 

Effective Date: 16 July 2014 

Required Action(s) Required as indicated, unless accomplished previously: 

and Compliance (1) Within 110 flight hours (FH) after the effective date of this AD, and, Time(s): thereafter. at intervals not to exceed 110 FH, accomplish a visual and 

tactile inspection of the engine air intake box (including the deflection flap) 

and the engine air ducting (including the area located downstream of the 

filter) in accordance with the instructions of CEAPR SB W161 Revision 3. 

(2) If, during any inspection as required by paragraph (1) of this AD, any 

damage such as bubbling, blistering, peeled off areas or paint detachment 

is found, before next flight, replace each damaged part with a serviceable 

part in accordance with the instructions of CEAPR SB N°161 Revision 3. 

(3) Replacement of damaged parts on an aeroplane, as required by paragraph 

(2) of this AD. does not constitute terminating action for the repetitive 

inspections as required by paragraph ( 1) of this AD for that aeroplane. 

(4) From the effective date of this AD, do not install on any aeroplane a 

painted engine air intake box or a repaired engine air dueling. 

Ref. Publications: CEAPR SB N"161 Revision 3 dated 06 September 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 21 May 2014 as PAD 14-084 for consultation until 

18 June 2014. 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: 

CEAPR. Bureau de Navigabilite. 1 Route de Troyes21121 DAROIS, FRANCE 

Telephone: +33 380 35 25 22, Fax : +33 380 35 25 25 

E-mail : info@ceapr.com. 

TE.CAP.OOll0-003 © European Aviation Safety Agency. All righ ts reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-lnternei;/Intranet.