EASA AD No : 2011-0100 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0100 

Date: 26 May 2011 

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 EAD is issued in accordance with EC 1702/2003, Part 21A.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]. 

Type Approval Holder’s Name : 

Diamond Aircraft Industries GmbH

Type/Model designation(s) : 

DA 42 aeroplanes 

TCDS Number : EASA.A.005 and EASA.A.513 

Foreign AD : Not applicable 

Supersedure: None 

ATA 57 Wings – Upper Centre Wing Skin-to-Spar Adhesive Joint – 

Inspection / Repair 

Manufacturers: Diamond Aircraft Industries GmbH (Austria), and Diamond Aircraft Industries 

Inc. (Canada) 

Applicability: DA 42 and DA 42 NG (modified by DAI from DA 42 through DAI Optional SB 

42-068) aeroplanes, serial numbers (s/n) 42.006 through 42.007, 42.010, 

42.012 through 42.014, 42.016 through 42.033, 42.035 through 42.043, 

42.045, 42.046, 42.048 through 42.051, 42.053, 42.055 through 42.059, 

42.061 through 42.081, 42.083 through 42.093, 42.096 through 42.097, 

42.099 through 42.120, 42.122 through 42.125, 42.127 through 42.148, 

42.150 through 42.156, 42.158 through 42.170, 42.172 through 42.176, 

42.178, 42.179, 42.181 through 42.190, 42.192 through 42.200, 42.202 

through 42.224, 42.AC001 through 42.AC028 and 42.AC030 through 

42.AC052; and 

DA 42 M (both Normal and Restricted category, modified from DA 42 through 

DAI Optional SB 42-056) and DA 42 M-NG aeroplanes (both Normal and 

Restricted category, modified by DAI from DA 42 M through DAI Optional SB 

42-081): s/n 42.008, 42.157 and 42.191.

Reason: During conversion of a DA 42 to a DA 42 NG, voids were detected in the 

adhesive joint between the centre wing spars and the upper centre wing skins, 

between the fuselage wall and the engine nacelle. The available information 

indicates that wings with voids continue to meet the certification design limits, 

provided the voids are within established criteria. 

However, to detect any wings that may have voids exceeding these criteria, 

Diamond has issued Mandatory Service Bulletin (MSB) 42-092 and MSB 

42NG-022 (single document) that describes instructions for inspection of the 
EASA AD No : 2011-0100 

EASA Form 110 Page 2/2 

aeroplanes that had these wings installed during manufacture. Aeroplanes 

that have voids within the inspection criteria may continue to operate without 

restriction, pending the outcome of ongoing investigations. Aeroplanes that 

have voids exceeding the inspection criteria must be repaired. 

For the reasons described above, this EASA AD requires the inspection of the 

affected aeroplanes to measure the voids in the adhesive joint between the 

centre wing spars and the upper centre wing skins, the reporting of all findings 

to Diamond Aircraft Industries and the repair of any voids exceeding the 

criteria as specified in the MSB.

Effective Date: 09 June 2011 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the next 100 flight hours or 3 months, whichever occurs first after 

the effective date of this AD, inspect the adhesive joint between the 

centre wing spars and the upper centre wing skin in accordance with the 

instructions of Diamond Aircraft Industries GmbH MSB 42-092/42NG022 (the MSB) and the associated Working Instruction (WI) WI-MSB 42-

092/42NG-022 (the WI). 

(2) Within 30 days after the inspection as required by paragraph (1) of this 

AD, report the results to Diamond Aircraft Industries in accordance with 

the instructions of the MSB and the WI. 

(3) If, during the inspection as required by paragraph (1) of this AD, voids 

are detected that exceed the criteria as specified in the WI, before next 

flight, repair the aeroplane in accordance with the instructions of Section 

III.2 of the WI, or contact Diamond Aircraft Industries for approved repair 

instructions and accomplish the repair accordingly. 

(4) For the purpose of compliance with paragraph (3) of this AD, a single 

positioning flight is allowed to a location where the repair can be 

accomplished, in accordance with the provisions as specified in Section 

III.1 of the WI. 

Ref. Publications: Diamond Aircraft Industries GmbH MSB 42-092 / MSB 42NG-022 (single 

document) and the associated WI-MSB 42-092 / 42NG-022 (single document), 

both dated 20 May 2011. 

The use of later approved revisions of these documents 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. The required actions and the risk allowance have granted the issuance 

of a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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: 

Diamond Aircraft Industries GmbH, Austria. 

Telephone +43 2622 26700; 

Facsimile +43 2622 26700 1369 

E-mail office@diamond-air.at or airworthiness@diamond-air.at