EASA AD No.: 2014-0067

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0067

Date: 18 March 2014

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 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].

Design Approval Holder’s Name:

FIBERGLAS-TECHNIK RUDOLF LINDNER 

GmbH & Co. KG

Type/Model designation(s):

GROB G 102 and G 103 sailplanes and 

powered sailplanes 

TCDS Number: EASA.A.250

Foreign AD: Not applicable

Supersedure: None

ATA 27 Flight Controls – Rudder Control Unit Cable Pulleys –

Inspection / Replacement

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

Burkhardt Grob Luft- und Raumfahrt GmbH & Co. KG)

Applicability: GROB G 102 Standard Astir III (with letter „S“), G 102 Club Astir III (with letter 

„C“), and G 102 Club Astir IIIb, (with letter „Cb“) sailplanes, serial numbers (s/n) 

5501 to 5652 inclusive.

GROB G 103 TWIN II and G 103 A TWIN II ACRO (with letter „K“) sailplanes, 

s/n 3730 to 34078 inclusive.

GROB G 103 C TWIN III ACRO sailplanes, s/n 34101 to 34203 inclusive.

GROB G 103 C TWIN III sailplanes, s/n 36001 to 36014 inclusive.

GROB G 103 C TWIN III SL powered sailplanes, s/n 35002 to 35051 inclusive.

Reason: Control cable pulleys made from plastic (white or brown material) in the rudder 

control unit were reported to develop cracks due to aging. In one case, jamming 

of the rudder control unit was reported.

This condition, if not detected and corrected, could cause cable pulleys to 

break, potentially jamming the rudder control unit and resulting in loss of control 

of the sailplane.

To address this potential unsafe condition, Fiberglas-Technik issued 

Technische Mitteilung/Service Bulletin TM-G05/SB-G05 and Anweisung/

Instructions A/I-G05 (one document) to provide instructions for the replacement

of plastic cable pulleys with pulleys made from aluminium.
EASA AD No.: 2014-0067

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2

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

For the reason described above, this AD requires identification and 

replacement of plastic cable pulleys in the rudder control unit.

Plastic cable pulleys may also be installed in the cable circuits of pedal 

adjustment and/or tow hook actuation, their replacement is not required by this 

AD. 

Effective Date: 01 April 2014

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time defined in Table 1 of this AD, inspect the 

rudder control unit and, if plastic cable pulleys are installed, replace the 

plastic cable pulleys with aluminium cable pulleys in accordance with the 

instructions of Fiberglas-Technik TM-G05/SB-G05 and A/I-G05.

Table 1: Compliance time for replacement

Rudder control unit 

configuration

Compliance time (after the 

effective date of this AD)

Open cable cage Within 1 month

Closed cable cage Within 3 months

Note: All G 103 C (TWIN III, TWIN III ACRO) sailplanes and G 103 C (TWIN III 

SL) powered sailplanes have closed cable cages.

(2) From the effective date of this AD, do not install any plastic control cable 

pulley in the rudder control unit of a sailplane or powered sailplane.

Ref. Publication: Fiberglas-Technik TM-G05/SB-G05 and A/I-G05 original issue, dated 17 

January 2014.

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. This AD was posted on 30 January 2014 as PAD 14-027 for consultation 

until 27 February 2014. 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, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact:

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