EASA AD No.: 2015-0116

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0116

Date: 24 June 2015

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 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:

FIBERGLAS-TECHNIK RUDOLF LINDNER 

GmbH & Co. KG

Type/Model designation(s):

GROB sailplanes

TCDS Number: EASA.A.250

Foreign AD: Not applicable

Supersedure: None

ATA 27 Flight Controls – Speed Brake Control System – Inspection / 

Replacement

Manufacturer(s): GROB Werke GmbH & Co KG, Burkhart Grob Flugzeugbau

Applicability: TWIN ASTIR, TWIN ASTIR TRAINER, GROB G 103 TWIN II and 

GROB G 103 A TWIN II ACRO sailplanes, all manufacturer serial numbers.

Reason: A report was received concerning a broken bell-crank, installed in the air brake 

control circuit approximately 1.4 m outside the wing root rib of a GROB G 103 

Twin II sailplane. Preliminary investigation results revealed additional cases of 

cracks on the same part, installed in the air brake control systems of the early 

Twin II type design.

The same bell-cranks are also installed at the same location in the control 

systems of other models belonging to the same type design (see list of affected 

models under Applicability).

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

brake system, possibly resulting in reduced control of the sailplane.

To address this potential unsafe condition, Fiberglas-Technik issued 

Technische Mitteilung (TM)/Service Bulletin (SB) TM-G08/SB-G08 (one 

document) and Anweisung (A)/Instructions (I) A/I-G08 (one document) to 

provide instructions for a check of the air brake locking forces, the inspection of 

the bell-crank and, if cracks are found, replacement of the bell-crank.

Additionally, TM-G07/SB-G07 (one document) and A/I-G07 (one document) 

provide instructions for the installation of inspection openings in the wing of 

GROB G 103 TWIN II and G 103 A TWIN II ACRO sailplanes to facilitate the 
EASA AD No.: 2015-0116

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

inspection of the bell-crank. (For the TWIN ASTIR and TWIN ASTIR TRAINER

sailplanes, such an opening is required by LBA AD 92-190/2 (GROB SB 315-

45/2.) This installation is optional for sailplanes not exceeding the original 

intended life limit. 

For the reason described above, this AD requires a check of the air brake 

locking forces, an inspection for cracks in the air brake control unit and, if 

cracks are found, replacement of the affected flight control system parts. This 

AD is a temporary measure and further AD action may follow.

Effective Date: 08 July 2015

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 30 days after the effective date of this AD and, thereafter, during 

each annual inspection, check the locking forces of the air brake control 

unit and, if any discrepancy is found, before next flight, correct the locking 

forces in accordance with the instructions of Fiberglas-Technik 

TM-G08/SB-G08 and A/I-G08.

(2) Within 2 months after the effective date of this AD, inspect the bell crank 

installed in the air brake control circuit and, if any cracks are found, before 

next flight, replace the bell crank with a serviceable part in accordance with 

the instructions of Fiberglas-Technik TM-G08/SB-G08 and A/I-G08.

(3) Within 30 days after replacing a bell crank as required by paragraph (2) of 

this AD, report the inspection results of the removed bell crank to 

Fiberglas-Technik.

Ref. Publications: Fiberglas-Technik TM-G08/SB-G08 and A/I-G08 original issue dated 

24 April 2015.

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD.

Fiberglas-Technik TM-G07/SB-G07 and A/I-G07 original issue dated 

24 April 2015.

GROB SB 315-45/2 dated 21 December 1995.

Remarks: 1. If requested and appropriately substantiated, EASA can approve

Alternative Methods of Compliance for this AD.

2. This AD was posted on 20 May 2015 as PAD 15-064 for consultation until 

17 June 2015. The Comment Response Document can be found at 

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

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:

Fiberglas-Technik Rudolf Lindner GmbH & Co.KG,

Steige 3, D-88487 Walpertshofen, Germany

E-mail: info@LTB-Lindner.com.