## EASA EASA AD No .: 2014 -0155 

## AIRWORTHIN ESS DIR ECTIV E A D No.: 2014-01 55


### Date : 02 July 2014 Note: Thi s Airworthiness Directive (AD) is issued by EASA, acting in accorda nce 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 Regul ati on . Th is 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 airworth i ness of an ai rcraft shall be e nsu red by accompl i shing any applicable ADs
. Conseque ntly , no person may operate an a i rcraft to wh ich an AD applies
. except in accordance with the requ irements of that AD, u nle ss otherwise speci fied by t he Agency [EC 2042/2003 Annex I , Part M.A.303) or agreed with t he Authority of the State of Registry [EC 216/2008 , Article 1 4(4) exemption]
. 

### Des ign 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 4 6 0 , 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. 

### E ngine - Engine Air Intake Box and Air Ducting -Inspecti o n 

### I Replacement Centre est Aeronaut ique , Avions Pierre Robin , Robin Aviation , Constructions Aeronautiques de Bourgogne, APEX In dustries , Finch Aircraft, Robin Aircraft
. ATL, DR 200, DR 220, DR 221, DR 2 50, 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 i nstallation ) . 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 perfo rmance of the aeroplane, notab ly during take-off, had been significantly degraded
. This condit ion, if no1 detected and correc ted, could lead to an engine failu re, possibly resulting in loss of control of the aeroplane
. To i nitia lly 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 , cohes ion defects were found inside the lam inated air ducting from eng in e filter to eng ine air i ntake box. Prompted by these findings, DGAC France issued AD 1999-470 to require in spection of the engine lamin ated air 

### ducting.
TE.CAP.OO ll0 - 003 ©Euro pe an Aviation Safety Age ncy . All rig hts rese rved. 1/ 2 Pro prietary document. Copies are not co ntrolled. Confirm revi s io n status throug h the E ASA - Internet/lnt ranet.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 deta iled 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 t he revi sed instructions . Effective Date: 16 July 2014 Req u ired 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 duc ti ng (including the area located downstream of the filter) in accordance with the instructions of CEAPR SB W161 Revision 3 . (2) If, during any i nspection 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 , rep lace 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 th is 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 th is AD , do not i nstall on any aeroplane a painted engine air intake box or a repa i red engine air duel i ng . 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 w ith the requirements of this AD . Remarks : 1 . If requested and appropriately substantiated , EASA can approve Alternative Methods of Compliance for th is AD. 2. This AD was posted on 21 May 2014 as PAD 14-084 for co nsultation u ntil 18 June 20 14 . 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 techn i cal content of the requirements i n 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 -ma il : info@ceapr.com .

TE.CAP
. O Oll 0 - 003 © Europea n Av ia t ion Safety Agency . All rig h ts reserved . 2 /2 Proprietary document. Copies a re not controlle d. Confi r m revisi on status th rough the EASA- lnternei;/Intranet.