EASA AD No :2012-0064

EASA Form 110 Page 1/6

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0064

Date: 20 April 2012

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 EC 1702/2003, Part 21A.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].

Type Approval Holder’s Name :

ATR-GIE Avions de Transport Régional

Type/Model designation(s) :

ATR 42-500 and ATR 72-212A aeroplanes

TCDS Number: EASA.A.084

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA Emergency AD 2010-0063-E dated 01 April 2010.

ATA 27 Flight Controls – Rudder Tab, Rudder Pedal and Elevator Control 

Rods – Inspection / Replacement

Manufacturer(s): ATR-GIE Avions de Transport Régional (formerly AEROSPATIALE –

AERITALIA, AEROSPATIALE – ALENIA, AEROSPATIALE ATR- ALENIA, 

EADS ATR – ALENIA)

Applicability: ATR 42-500 aeroplanes, from Manufacturer Serial Number (MSN) 671 to 815 

inclusive, except MSN 811.

ATR 72-212A aeroplanes, from MSN 769 to MSN 914 inclusive, except MSN 

826, 905, 908 and 911.

Note: Not all aeroplanes to which this AD applies are affected by all the required 

actions; see paragraph (1) of the Required Actions section of this AD which 

refers to ATR Service Bulletins for detailed applicability and exceptions.

Reason: Prompted by the findings that led to publication of EASA AD 2010-0063-E, 

additional quality investigation showed that the non-conformity of certain

control rods, which was due to incorrect polishing during the rod manufacturing 

process, could also affect other flight control rods.

These other potentially non-conforming control rods are installed on elevator 

controls, rudder pedal assemblies and rudder tab controls of certain ATR 

aeroplanes.

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

affected control rod which, under certain circumstances, could result in 

reduced control of the aeroplane.

As a result of further investigations, other batches have been incriminated, in 

addition to the ones identified by EASA AD 2010-0063-E, and new safety 
EASA AD No :2012-0064

EASA Form 110 Page 2/6

analyses also indicate the need for replacement of the rods (within an adapted 

compliance time), which had passed the check required by EASA AD 2010-

0063-E. Consequently, EASA AD 2010-0063-E is superseded by this new AD.

For the reasons described above, this AD requires a one-time inspection of the 

affected control systems rods and, depending on findings, replacement of the 

affected rods.

Effective Date: 04 May 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless already accomplished

(1) Within 6 months after the effective date of this AD, accomplish the following 

actions concurrently:

(1.1) Only for aeroplanes (MSN) listed in ATR Service Bulletin (SB) ATR42-

27-0105 or ATR72-27-1066, as applicable to aeroplane model, inspect 

all four elevator control rods Part Number (P/N) S27381930-004 and 

P/N S27381831-006 for batch number identification in accordance 

with the instructions of ATR SB ATR42-27-0105 or ATR72-27-1066, 

as applicable to aeroplane model.

(1.2) Only for aeroplanes (MSN) listed in ATR SB ATR42-27-0104 or 

ATR72-27-1065, as applicable to aeroplane model, inspect all four 

rudder pedal rods P/N S2728116400000 for batch number 

identification in accordance with the instructions of ATR SB ATR42-

27-0104 or SB ATR72-27-1065, as applicable to aeroplane model.

(2) If, during the inspection as required by paragraph (1.1) of this AD, any

elevator control rod is found belonging to a batch number identified in SB 

ATR42-27-0105 or SB ATR72-27-1066, or if the batch number is 

unreadable, within the compliance time as specified in Table 1 of this AD, as 

applicable, replace the affected rod in accordance with the instructions of 

SB ATR42-27-0105 or ATR72-27-1066, as applicable to aeroplane model, 

and identify each removed rod as unserviceable component.

Table 1 – Elevator Control Rod Replacement

Number of 

affected rod(s)

Compliance Time for rod 

replacement

One Within 10 days after the inspection as 

required by paragraph (1.1) of this AD

Two or more Before next flight after the inspection 

as required by paragraph (1.1) of this 

AD, replace all affected rods, except 

one rod, the replacement of which can 

be deferred for 10 days.

(3) If, during the inspection as required by paragraph (1.2) of this AD, a rudder 

pedal rod is found belonging to a batch number identified in SB ATR42-27-

0104 or SB ATR72-27-1065, as applicable, or if the batch number is 

unreadable, before next flight, check the rod diameter by using a special 

tool, in accordance with the instructions of SB ATR42-27-0104 or SB 

ATR72-27-1065, and depending on the result, within the compliance time 

specified in Table 2 of this AD, replace the affected rod in accordance with 

the instructions of SB ATR42-27-0104 or SB ATR72-27-1065, as applicable 

to aeroplane model, and identify each removed rod as unserviceable 

component.
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EASA Form 110 Page 3/6

Table 2 – Rudder Pedal Rod Replacement

Result of the check Compliance time for rod replacement

Rod passes through the 

tool

Before next flight after the check as 

required by paragraph (3) of this AD

Rod does not pass 

through the tool

Within 5 000 FH after the check as 

required by paragraph (3) of this AD

(4) For rudder pedal rods that have been inspected as required by EASA AD 

2010-0063-E, having been identified belonging to the batch 2109699 or 

2118930, or for which the batch number could not be identified, and having 

passed the check criteria (rod does not pass through the tool), the 

inspection by paragraph (1.2) of this AD is not required and these identified 

rudder pedal rods must be removed from the aeroplane within 5 000 FH

after the effective date of this AD.

(5) In addition to the actions required by paragraphs (1), (2), (3) and/or (4) of 

this AD, as applicable, for aeroplanes (MSN) listed in the applicability 

paragraph of this AD, except MSN 671, 673 and 769 to 784 inclusive, within 

24 months after the effective date of this AD, inspect the rudder tab control 

rod P/N S27281929-002 for batch number identification, in accordance with 

the instructions of the applicable ATR Aircraft Maintenance Manual / Job 

Instruction Card (AMM/JIC) 27-20-00 DVI 10000. Refer to Appendix 1 of this 

AD for rod location.

(6) If, during the inspection as required by paragraph (5) of this AD, the rudder 

tab control rod is found belonging to batch number 2107267 or 2120855, or 

if the batch number is unreadable, before next flight, replace the rod with a

serviceable one in accordance with the instructions provided in AMM/JIC 

27-21-42 RAI 10000, and identify the removed rod as unserviceable 

component.

(7) Within 20 days after the rod inspection and check as required by paragraph

(1), (2), (3), (4) or (5) of this AD, as applicable, send the relevant SB 

accomplishment report or the reporting form provided in Appendix 2 of this 

AD (including no-findings) to ATR.

(8) Within 30 days after the removal of an unserviceable rod, as required by 

paragraph (2) (3), (4) or (6) of this AD, as applicable, or within 30 days after 

the effective date of this AD, whichever occurs later, send a declaration that 

the unserviceable rod has been quarantined or scrapped, to ATR.

Ref. Publications: ATR Service Bulletins:

ATR42-27-0104 original issue or revision 1

ATR42-27-0105 original issue or revision 1

ATR72-27-1065 original issue, revision 1 or revision 2

ATR72-27-1066 original issue or revision 1

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

ATR 42/72 AMM/JIC 27-20-00 DVI 10000 and AMM/JIC 27-21-42 RAI 10000.

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

Methods of Compliance for this AD.

2. The required actions and the risk allowance have granted the issuance of a 

Final AD with Request for Comments, postponing the public consultation 
EASA AD No :2012-0064

EASA Form 110 Page 4/6

process after publication.

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:

ATR – GIE Avions de Transport régional

Continued Airworthiness Service

Tel.: + 33 (0) 5 62 21 62 21 - Fax:+ 33 (0) 5 62 21 67 8

E-mail: continued.airworthiness@atr.fr.
EASA AD No :2012-0064

EASA Form 110 Page 5/6

Appendix 1 - Rudder tab control rod location

P/N S27281929-002
EASA AD No :2012-0064

EASA Form 110 Page 6/6

Appendix 2 - Inspection Reporting Form

Send this report to: techdesk@atr.fr and continued.airworthiness@atr.fr

Aeroplane Identification

Aeroplane MSN :

Aeroplane Registration:

Inspection date:

Inspection results of rudder tab control rod P/N S27281929-002

Batch Number :

Serial Number :

Performed action : 

Reminder: if batch number is 2107267 or 2120855 or if batch number is unreadable, the rod 

must be replaced before next flight.

Maintenance organization identification

Maintenance organization name :

Date : 

Name & Signature :