TECNAMP2006T

ID: 17-178
Issue date: 2017-12-22
Source: EASA
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Flight Controls – Rudder Trim Actuator – Life Limit Implementation send comment

EASA PAD No.: 17-178


Notification of a Proposal to issue
an Airworthiness Directive
PAD No.: 17-178
Issued: 22 December 2017
Note: This Proposed Airworthiness Directive (PAD) is issued by EASA, acting in accordance with
Regulation (EC) 216/2008 on behalf of the European Union, its Member States and of the
European third countries that participate in the activities of EASA under Article 66 of that
Regulation.

In accordance with the EASA Continuing Airworthiness Procedures, the Executive Director is proposing the issuance of an EASA Airworthiness Directive
(AD), applicable to the aeronautical product(s) identified below.
All interested persons may send their comments, referencing the PAD Number above, to the e-mail address specified in the ‘Remarks’ section, prior to
the consultation date indicated.


Design Approval Holder’s Name: Type/Model designation(s):
Costruzioni Aeronautiche TECNAM Srl P2006T aeroplanes

Effective Date:
[TBD - standard: 14 days after AD issue date]
TCDS Number(s): EASA.A.185
Foreign AD: Not Applicable
Supersedure: None


ATA 27 – Flight Controls – Rudder Trim Actuator – Life Limit Implementation



Manufacturer(s):

Costruzioni Aeronautiche TECNAM Srl (Tecnam)

Applicability:

P2006T aeroplanes, all serial numbers (s/n), except those on which TECNAM modification (Mod)
2006/322 has been embodied in production.

Reason:

It was identified that the Part Number (P/N) of the rudder trim actuator mentioned in the P2006T
AMM Airworthiness Limitations Section (ALS) document was erroneously mentioned. As a result, it
cannot be excluded that the life limit applicable to this actuator is not being applied in service.

This condition, if not corrected, could lead to failure of the rudder control system, possibly resulting
in reduced control of the aeroplane.

To address this potential unsafe condition, TECNAM published Service Bulletin (SB)-285-CS Ed. 1
Rev. 0 (later revised) to inform operators about this typographical error. It is expected that, during


TE.CAP.00112-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 1 of 3
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EASA PAD No.: 17-178

the next revision of the P2006T AMM Airworthiness Limitations Section (ALS) document, it will list
the correct the P/N for that rudder trim actuator.

For the reason described above, this AD requires implementation of a life limit for rudder trim
actuator.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

Replacement of Life Limited Parts:
(1) Within the compliance times specified in Table 1 of this AD, as applicable, and, thereafter, at
intervals not exceeding the life limit as specified in TECNAM SB-285-CS Ed. 1 Rev. 1, replace
the rudder trim actuator P/N B6-7T in accordance with the instructions of TECNAM
SB-285-CS Ed. 1 Rev. 1.

Table 1 – Initial Replacement
Flight hours (FH)
accumulated by the Compliance Times (A or B, whichever occurs later)
aeroplane
A Before exceeding 1 000 FH
Less than 1 000 Within 25 FH of 30 days, whichever occurs first after the
B
effective date of this AD
Within 25 FH of 30 days, whichever occurs first after the
1 000 or more
effective date of this AD

Aircraft Maintenance Programme (AMP) Revision:
(2) Within 12 months after the effective date of this AD, revise the approved AMP, on the basis of
which the operator or the owner ensures the continuing airworthiness of each operated
aeroplane, by incorporating the life limit for the rudder trim actuator P/N B6-7T, as specified in
TECNAM SB-285-CS Ed. 1 Rev. 1.

Credit:
(3) For an AMP that, on the effective date of this AD, is already updated to incorporate the correct
life limit as specified in TECNAM SB-285-CS Ed. 1 Rev. 1, that action ensures (see Note 1 of this
AD) the continued accomplishment of those tasks and limitations.

Recording AD compliance:
(4) When the AMP of an aeroplane has been revised as required by paragraph (2) of this AD, that
action ensures (see Note 1 of this AD) continued accomplishment of the task as required by
paragraph (1) of this AD for that aeroplane. Consequently, after revising the AMP, as required
by paragraph (2) of this AD, it is not necessary that accomplishment of individual action is
recorded for demonstration of AD compliance on a continued basis.

Note 1: For affected P2006T aeroplanes registered in Europe, complying with the approved AMP, as
specified in paragraph (2) or (3) of this AD, as applicable, is required by Commission Regulation
(EU) 1321/2014, Part M.A.301, paragraph 3.

TE.CAP.00112-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA PAD No.: 17-178




Ref. Publications:

TECNAM SB-285-CS Ed. 1 Rev. 1, dated 07 November 2017.

The use of later approved revisions of the above-mentioned document is acceptable for compliance
with the requirements of this AD.

Remarks:
1. This Proposed AD will be closed for consultation on 19 January 2018.

2. Enquiries regarding this PAD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.

3. For any question concerning the technical content of the requirements in this PAD, please
contact: Costruzioni Aeronautiche TECNAM Airworthiness Office, Telephone: +39 0823 620134,
Fax: +39 0823 622899, E-mail: airworthiness@tecnam.com.




TE.CAP.00112-005 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 3 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union

This is a partial extract of the full document - please refer to the actual report for full information.
Sources as credited.