EASA AD No :2012

- 0064

EASA Form 11 0 Page 1 / 6 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 12 - 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 Eur opean 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 Agen cy [EC 2042/2003 Annex I, Pa rt 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

F oreign AD: Not applicable
Supersedure: This AD supersedes EASA Emergency AD 2010

- 0063

- E dated 01 April 2010.



### ATA 27 Flight Controls

– Rudder T ab , Rudder Pedal and Elevator C ontrol

R od s – Inspection / Replacement

Manufacturer(s): ATR

- GI E Avions de Transport Régional (formerly AEROSPATIALE

– AERITALIA, AEROSPATIALE

– ALENIA, AEROSPATIALE ATR

- ALENIA, EADS ATR

– ALENIA) Applicability: ATR 42

- 500 aeroplanes, from Manu facturer 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 th is 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 inc orrect 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 aerop lanes

. 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 incr iminated , in addition to the ones identified by EASA AD 2010

- 0063

- E , and new safetyEASA AD No :2012

- 0064

EASA Form 11 0 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, E ASA 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 rod s

. Effective Date: 0 4 May 2012 Requir ed 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 f or aeroplanes (MSN) listed in ATR Service Bulletin ( SB) ATR42

- 27

- 0105 or ATR72

- 27

- 1066, as applicable to aeroplane model, i nspect 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 o r ATR72

- 27

- 1066, as applicable to aeroplane model

. (1.2) Only f or aeroplanes (MSN) listed in ATR SB ATR42

- 27

- 0104 or ATR72

- 27

- 1065, as applicable to aeroplane model, i nspect all four rudder pedal rods P/N S2728116400000 for batch number identification in a ccordance 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 e ach removed rod as unserviceable component.

Table 1

– Elevator Control Rod Replacement Number of a ffected rod ( s ) Compliance Time for rod

replacement One Within 10 days after the inspection as required by p aragraph (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 re quired 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 spe cial 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

- 010 4 or SB ATR72

- 27

- 1065, as applicable to aeroplane model , and identify each removed rod as unserviceable component.EASA AD No :2012

- 0064

EASA Form 11 0 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 fli ght 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 r udder p edal r od s 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 require d and these identified rudder pedal rod s must be removed from the aeroplane w ithin 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 , w ithin 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 t he 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 co ntrol 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 instruction s 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 Appendi x 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 lat er, send a declaration that the unserviceable rod ha s 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, revis ion 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

. Remar ks : 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 consulta tionEASA AD No :2012

- 0064

EASA Form 11 0 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 c ontent 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.a irworthiness@atr.fr

.EASA AD No :2012

- 0064

EASA Form 11 0 Page 5 / 6 

### Appendix 1

- Rudder tab control rod location

P/N S27281929

- 002EASA AD No :2012

- 0064

EASA Form 11 0 Page 6 / 6 

### Appendix 2

- Inspection R eporting F orm

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 replace d before next flight. 

### Maintenance organization identification
Maintenance organization name :

Date : Name & Signature :