EASA AD No.: 2009-0194 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2009-0194 

Date: 01 September 2009 

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 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 : 

328 Support Services GmbH 

Type/Model designation(s) : 

328 aeroplanes 

TCDS Number : EASA A.096 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA Emergency AD 2008-0087-E dated 08 May 2008. 

ATA 57 Wings – Lower Inner Panel – Inspection / Repair / Modification 

Manufacturer(s): Dornier Luftfahrt GmbH; Fairchild-Dornier GmbH; AvCraft Aerospace GmbH 

Applicability: Model 328-100 aeroplanes, all serial numbers; and 

Model 328-300 aeroplanes, all serial numbers. 

Reason: 

During a routine inspection, cracks have been found on an aeroplane at the lower 

wing panel rear trailing edge inboard of flap lever arm 1 (rib 5). A subsequent 

inspection of the other aeroplanes in that operator’s fleet revealed several more 

aeroplanes with cracks at the same location. This condition, if not corrected, could 

lead to structural failure of the affected wing panel, possibly resulting in the wing 

separating from the airplane with consequent loss of control. 

To correct this unsafe condition, EASA issued Emergency AD 2008-0087-E to 

require detailed visual inspections (DVI) of both the left (LH) and right (RH) wing 

panel rear trailing edge around rib 3 and rib 5 and a subsequent Eddy Current 

inspection (NDI) of the same area to detect cracks, follow-up repair actions when 

cracks are found, and the reporting of all findings. The TC holder has now 

developed a modification, consisting of the cold expansion of the former lower 

wing panel CAMLOC holes together with the installation of new attachment 

material that will prevent the onset of cracks in the affected wing panel. 

For the reasons described above, this AD retains the inspection and repair 

requirements of AD 2008-0087-E, which is superseded, adds repetitive 

inspections and a requirement to modify both the LH and RH wing panel rear 

trailing edges from rib 3 to rib 9. Modification does not constitute terminating 

action for the new repetitive inspection requirements of this AD. 

Effective Date: 15 September 2009 
EASA AD No.: 2009-0194 

EASA Form 110 Page 2/3 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the next 10 flight cycles (FC) or 10 flight hours (FH) or 7 days, 

whichever occurs first after 08 May 2008 [the effective date of AD 2008-0087-

E], accomplish a DVI of the affected area in accordance with the 

accomplishment instructions of 328 Support Services GmbH Alert Service 

Bulletin ASB-328-57-037 or ASB-328J-57-015, both Revision 1, as applicable 

to the aeroplane model. If no crack is detected, repeat the DVI at intervals not 

to exceed 50 FH. When cracks are detected, before further flight, accomplish 

an NDI in accordance with paragraph (2) of this AD. 

Note 1: One non-revenue ferry flight (up to 3 FC) is permitted to allow the 

aeroplane to reach a maintenance facility where the required inspection and 

repair can be accomplished, provided the crack indication does not exceed 12.5 

mm in total length. When crack indication exceeds 12.5 mm, a special ferry permit 

may be requested from State of Registry of the aeroplane. 

(2) Within the next 400 FH or 3 months, whichever occurs first after 08 May 2008 

[the effective date of AD 2008-0087-E], accomplish an NDI of the affected 

area in accordance with the accomplishment instructions of 328 Support 

Services GmbH Alert Service Bulletin ASB-328-57-037 or ASB-328J-57-015, 

both Revision 1, as applicable to the aeroplane model. 

Note 2: Previous accomplishment of the DVI and NDI before 08 May 2008 [the 

effective date of AD 2008-0087-E] in accordance with 328 Support Services 

GmbH ASB-328J-57-015 or ASB-328-57-037, both dated 05 May 2008, as 

applicable to aeroplane model, is acceptable for compliance with the 

requirements of paragraphs (1) and (2) of this AD. 

(3) Within 800 FC after the NDI as required by paragraph (2) of this AD, or within 

2 months after the effective date of this AD, whichever occurs later, and 

thereafter at intervals not to exceed 800 FC, accomplish an NDI in 

accordance with the accomplishment instructions of 328 Support Services 

GmbH Alert Service Bulletin ASB-328-57-037 or ASB-328J-57-015, both 

Revision 1, as applicable to the aeroplane model. 

Maintenance Review Board (MRB) Task 57-11-13-02 (for 328-100 

aeroplanes) and Task 57-11-13-03 (for 328-300 aeroplanes) pertain to these 

requirements. These MRB tasks were published as Temporary Revisions 

(TR) MRB-134 and MRB-056 respectively, dated 11 September 2008. 

Accomplishment of any NDI, prior to the effective date of this AD, in 

accordance with the applicable MRB TR is acceptable to comply with 

paragraph (3) of this AD. 

(4) Within the next 24 months after the effective date of this AD, accomplish an 

NDI and, provided no cracks are found, modify the affected area in 

accordance with the accomplishment instructions of 328 Support Services 

GmbH Service Bulletin SB-328-57-481 or SB-328J-57-230, as applicable to 

aeroplane model. 

(5) If a crack is detected during any inspection required by this AD, before further 

flight, contact the TC holder, address as indicated in the ‘Remarks’ section of 

this AD, for approved repair instructions and accomplish the repair 

accordingly. 

(6) Within 30 days after each inspection as required by this AD, send a report 

(even if no cracks are detected) to the TC holder, address as indicated in the 

‘Remarks’ section of this AD. The results of any inspection done before the 

effective date of this AD must be reported within 3 days after the effective 

date of this AD. The report must include the inspection results, a description 

of any cracks found, the serial number, and the number of FC and FH the 

aeroplane has accumulated. 

(7) Modification of an aeroplane as required by paragraph (4) of this AD does not 

constitute terminating action for the repetitive inspections required by 

paragraph (3) of this AD. 
EASA AD No.: 2009-0194 

EASA Form 110 Page 3/3 

Ref. Publications: 

328 Support Services GmbH ASB-328-57-037 for 328-100 aeroplanes and 

ASB-328J-57-015 for 328-300 aeroplanes, original issue, both dated 05 May 2008 

or Revision 1, both dated 08 May 2008. 

328 Support Services GmbH Service Bulletin SB-328-57-481 for 328-100 

aeroplanes and SB-328J-57-230 for 328-300 aeroplanes, original issue, both 

dated 07 May 2009. 

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. This AD was posted on 22 July 2009 as PAD 09-094 for consultation until 

19 August 2009. The Comment Response Document can be found at 

http://ad.easa.europa.eu. 

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: 

328 Support Services GmbH 

Global Support Center, P.O. Box 1252 

D-82231 Wessling, Federal Republic of Germany; 

Telephone: +49 8153 88111 6666 ; Fax 49 8153 88111 6565; 

E-mail: gsc.op@328support.de