EASA AD No.: 2015-0023-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2015-0023-E

Date: 18 February 2015

Note: This Emergency 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 EU 1321/2014 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

[EU 1321/2014 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:

FFA AIRCRAFT BRAVO AG (in liquidation)

Type/Model designation(s):

AS 202 “Bravo” aeroplanes

TCDS Number: EASA.A.591

Foreign AD: Not applicable

Supersedure: None

ATA 53 Fuselage – Upper Forward Fuselage Stringers – Inspection / Repair

Manufacturer(s): FFA Flugzeugwerke Altenrhein AG

Applicability: AS 202 aeroplanes, all models, all serial numbers.

Reason: Heavy corrosion was reportedly discovered on an AS 202 aeroplane, between 

the forward (FWD) windshield frame angle and the upper FWD stringer, left

hand (LH) and right hand (RH). The corrosion was found underneath the 

removed windshield frame. Corrosion was not detected during a general visual 

inspection from below.

This condition, if not detected and corrected, could lead to failure of the FWD

upper stringer, which reduces the structural integrity of the affected area.

To address this potential unsafe condition, Gomolzig Flugzeug- und 

Maschinenbau GmbH (GFM), acting on behalf of the TC holder, have issued

Service Bulletin (SB) No. 2015-1 to provide inspection instructions.

For the reasons described above, this AD requires repetitive inspections of the 

upper FWD stringer (LH and RH) structure for signs of corrosion and, 

depending on findings, the accomplishment of applicable corrective action(s).

This AD is considered to be an interim action and further AD action may follow.

Effective Date: 20 February 2015
EASA AD No.: 2015-0023-E

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Before next flight after the effective date of this AD, except as specified in 

paragraph (2) of this AD, and, thereafter, at intervals not to exceed 12 

months, accomplish a detailed visual inspection of the FWD upper stringer 

(LH and RH) top side structure in accordance with the instructions of 

paragraph (§) 1.d. of GFM SB No. 2015-1.

(2) A ferry flight is allowed for the purpose of moving the aeroplane to a 

location where the inspection, as required by paragraph (1) of this AD, can 

be accomplished. During this ferry flight, before the initial inspection and, 

depending on findings, corrective actions are accomplished, no acrobatic 

flights are allowed and normal category manoeuvring load factors must not 

exceed +3,8g / -1,9g.

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

of corrosion, or damaged corrosion protection, is found, before next flight, 

remove the corrosion at the affected area in accordance with the 

instructions of § 1.f. and 1.g of GFM SB No. 2015-1.

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

detected corrosion exceeds the allowable limits as specified in GFM SB 

No. 2015-1, before next flight, contact GFM for approved repair instructions 

and accomplish those instructions accordingly.

(5) Within 30 days after the initial inspection as required by paragraph (1) of 

this AD, report the results (including no findings) to GFM, using the 

evidence report attached to GFM SB 2015-1.

(6) Repair of an aeroplane as required by paragraph (3) or (4) of this AD, as 

applicable, does not constitute terminating action for the repetitive 

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

Ref. Publications: Gomolzig Flugzeug- und Maschinenbau GmbH SB 2015-1, original issue dated 

05 February 2015.

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. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

3. Enquiries regarding this AD should be referred to the Safety Information 

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:

Gomolzig Flugzeug- und Maschinenbau GmbH,

Eisenwerkstraße 9, 58332 Schwelm, Germany,

Telephone: +49 (0)2336 490 330, Fax: +49 (0)2336 490 339

E-Mail : info@gomolzig.de.