EASA AD No.: 2014-0212

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0212

Date: 19 September 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption]. 

### Design Approval Holder’s Name: GROB AIRCRAFT AG Type/Model designation(s): G 115 and G 120 aeroplanes

TCDS Numbers: EASA.A.364 and EASA.A.075

Foreign AD: Not applicable

Supersedure: None



### ATA 80 Starting – Starter Solenoid – Inspection

Manufacturer(s): GROB Aircraft AG (formerly Grob Ae rospace GmbH, Grob Werke GmbH & Co. KG).
Applicability: GROB G 115E and G 115EG aeroplanes, all serial numbers (S/N) up to and including S/N 82323/E, and GROB G 120A and G 120A-I aeroplanes, all S/N up to and including S/N 85063.
Reason: An operator of a G 115E aeroplane experienc ed a total loss of electrical power in flight. The root cause was found to be a defecti ve starter solenoid causing an internal short circuit, which resulted in breakdown of the system voltage. This condition, if not detected and corrected, coul d result in reduced control of the aeroplane. To address this potential unsafe condition, GROB Ai rcraft AG issued Service Bulletin (SB) MSB1078-196 for G 115 aeroplanes and SB MSB1121-144 for G 120 aeroplanes to provide instructions for inspec tion and corrective action. For the reason described above, this AD requires a one-time inspection of the starter solenoid and, depending on findings, replac ement of the starter. A technical solution is currently under development and further AD action may follow.

Effective Date: 03 October 2014EASA AD No.: 2014-0212

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 30 days after the effective date of this AD, inspect the starter solenoid in accordance with the instructions of GRO B SB MSB1078-196 or MSB1121-144, as applicable to aeroplane type. In ad dition, for G 115E aeroplanes, install a placard « IFR operation in VM C only » on the instrument panel in full view of the pilot in accor dance with the instructions of GROB SB MSB1078-196. (2) If, during the inspection as required by paragr aph (1) of this AD, any damage to the starter is found, before next flight, replace the affected starter with a serviceable part in accordance with the instructions of GROB SB MSB1078-196 or MSB1121 144, as applicable to aer oplane type.

Ref. Publications: GROB Aircraft AG SB MSB1078-196 original issue dated 14 July 2014 (for G 115E and G 115EG). GROB Aircraft AG SB MSB1121-144 original issue date d 14 July 2014 (for G 120A and G 120A-I). The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 29 July 2014 as PAD 14-123 for consultation until 26 August 2014. No comments were received during th e consultation period. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: GROB Aircraft AG, Product Support E-mail: productsupport@grob-aircraft.com

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