EASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0170R2

Date: 20 June 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an Community, its Member States and of the European third countries that participate in th e activities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accor dance with the requirements of that AD, unless othe rwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/200 8, Article 14(4) exemption].



### Design Approval Holder’s Name:

AIRBUS HELICOPTERS Type/Model designation(s):

SA 365, AS 365, SA 366 and EC 155 helicopters

TCDS Number: EASA.R.105

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2012-0170R1, date d 18 October 2013.



### ATA 05

ATA 65 Time Limits and Maintenance Checks – Tail Rotor Gea rbox (TGB)

Oil Level and Magnetic Chip Detector – Inspection

Tail Rotor – Pitch Control Rod Bearing – Inspection / Replacement

Manufacturer(s): Airbus Helicopters (formerly Euroc opter, Eurocopter France, Aerospatiale).

Applicability: SA 365 N1, AS 365 N2, AS 365 N3, SA 366 G1, EC 155 B and EC 155 B1 helicopters, all serial numbers, except those modif ied in accordance with Eurocopter (EC) modification (mod) 07 65B63.

Reason: In early 2006, a report was received concer ning the loss of the tail rotor pitch control on a helicopter during a landing phase. Inv estigation showed that this loss of pitch control was due to significant damage to the bearing of the control rod in the tail gearbox (TGB). The loss of tail rot or pitch control can lead to the loss of yaw control of the helicopter.

In February 2006, EASA issued Emergency AD 2006-005 1-E to address this unsafe condition, which was subsequently superseded by Emergency AD 2006-0258R1-E dated 29 August 2006. That AD require d the affected operators to maintain the TGB oil level at the maxi mum and to check the axial play in the tail rotor pitch control rod bearing, e ach time metallic particles were detected at the TGB magnetic plug.

Since the issuance of AD 2006-0258 R1-E, another AS 365 N3 helicopter experienced loss of yaw control due to deterioratio n of the control rod bearing, with a damage mode similar to the previous case. Fo llowing the investigation on this event, Eurocopter (EC) determined that a re petitive check for absence of axial play in the pitch control rod bearing is n ecessary to ensure safety of flight and a new procedure has been developed and p ublished in revised AlertEASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Service Bulletins (ASB) AS 365 No. 05.00.54, SA 366 No. 05.37 and EC 155 No. 05A015, respectively. In addition, for 365 N he licopters only, the interval for checking the TGB oil level has been revised fro m “after the last flight of the day” (ALF check) to 10 Flight Hours (FH).

For the reasons described above, Emergency AD 2008- 0147-E, which superseded Emergency AD 2006-0258 R1-E, required th e implementation of the additional and revised inspection and correctiv e actions as described in the

above-mentioned service bulletins.

Following two new cases of loss of yaw control effi ciency during the landing phase, both of which did not result in loss of cont rol of the aircraft, EC modified the procedure for checking play in the control rod bearing.

The maintenance history of these TGBs showed that, in spite of compliance
with the instructions contained in ASB AS 365 No. 0 5.00.54 at Revision 1 or Revision 2; SA 366 No. 05.37 at Revision 1 or Revis ion 2; EC 155 No. 05A015 at Revision 1 or Revision 2, no play had been detec ted before the incident.

EASA AD 2009-0247 which retained the requirements o f EASA AD 2008-0147- E, was superseded, and additionally required accomp lishment of the new procedure to control wear of the rod double bearing , in accordance with the instructions of paragraph 2.B.3 of the applicable A SB at Revision 3.

Since the issuance of EASA AD 2009-0247, a further case of major damage to the control rod double bearing has been discovered after the detection of particles by an operator of a helicopter fitted wit h a TGB electrical chip detector. The analysis of this incident led EC to i ntroduce flight cycle (FC) intervals in addition to the flight hour monitoring intervals for helicopters fitted with the basic magnetic plug, i.e. without electric al indicating through the Revision 4 of ASB AS 365 No. 05.00.54, ASB SA 366 N o. 05.37 and ASB EC

155 No. 05A015.

Furthermore, during cleaning of the damaged TGB con trol shaft/rod assemblies, magnetic particles, which were not from the double bearing, were found by some operators. This led to the replacemen t of double bearings although they were in good condition. Therefore, Re vision 4 of ASB AS 365 No. 05.00.54, ASB SA 366 No. 05.37 and ASB EC 155 N o. 05A015 integrates also a metallurgical analysis of the particles coll ected during cleaning in order to inspect whether they originate from the double b earing, so as to be able to maintain the bearing in service according to the an alysis result.

In parallel to the issuance of Revision 4 of ASB AS 365 No. 05.00.54, ASB SA 366 No. 05.37 and ASB EC 155 No. 05A015, EC develop ed a method to allow inspection of the axial play in the rod bearings. T his inspection is the subject of the new ASB AS365 05.00.61, ASB SA 366 No. 05.41 an d ASB EC155 No. 05A022. These ASB, which also retain the instructio ns of Revision 4 of ASB AS 365 No. 05.00.54, ASB SA 366 No. 05.37 and ASB E C 155 No. 05A015, additionally instruct to embody Modification (MOD) 0765B58 which consists in the replacement of both guide bushes by 2 TORLON gu ide bushes. This modification improves the tolerance between the con trol shaft and the TGB
wheel in order to limit the friction loads on the c ontrol bearing.

Subsequently, EASA issued AD 2011-0105 which supers eded, and partially retained the requirements of EASA AD 2009-0247, and additionally required:

- the introduction of an interval of 50 FC (in addi tion to the existing interval of 25 FH, whichever occurs first) for the repetitive i nspections of the magnetic plug for helicopters fitted with magnetic plug with out electrical indicating,

- the analysis of the particles collected (in the r insing product used to clean the control shaft/rod assembly) to check for the presen ce of M50 particles before the replacement of the double bearing,

- the embodiment of MOD 0765B58, and

- the accomplishment of the simplified procedure to control the play of the rodEASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 3/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. double bearing after embodiment of MOD 0765B58.

Since the issuance of EASA AD 2011-0105, some opera tors commented that the repetitive inspection of the rod double bearing play, by using the simplified procedure, was not clearly required by EASA AD 2011 -0105 for helicopters
that have embodied in-service the MOD 0765B58 befor e the effective date of
EASA AD 2011-0105.

EASA concurred with the comments and issued AD 2011 -0117, superseding EASA AD 2011-0105, retaining its requirements, clar ifying that the repetitive inspection of the rod double bearing play by using the simplified procedure is required by the AD for helicopters that have embodi ed in-service the MOD
0765B58 before the effective date of EASA AD 2011-0 105 and makes paragraph (1) of the AD also applicable to EC 155 B helicopters.

Since AD 2011-0117 was issued, EC discovered that t he instructions to measure the play in the bearing of the TGB control shaft/rod assembly were incorrect for helicopters equipped with an 11-blade fenestron, because the Flight Manual of those helicopters prohibits operat ion of the yaw control with rotor stopped. Consequently, EC has revised the ASB instructions, including those for helicopters with the 10-blade fenestron. This modification of the procedure does not affect any measurements previous ly carried out, or the results obtained. In addition, it has been discover ed that EC 155 ASB 05A015 and paragraph (9) of EASA AD 2011-0117 (and all the previous superseded ADs) were requiring, for TGBs equipped with electri cal chip detector, a onetime inspection at the next scheduled check of the magnetic plug instead of requiring repetitive inspections at each scheduled check. This has been
corrected in EC 155 ASB 05A015 at Revision 5.

Subsequently, EASA issued AD 2011-0145 which supers eded AD 2011-0117, retaining most of its requirements, required repeti tive inspections of the magnetic plug for TGBs equipped with electrical chi p detector and required the play measurement of the TGB control rod/shaft assem bly double bearing to be accomplished in accordance with the type of fenestr on installed, making reference to the revised ASBs, ASB AS365 05.00.61, ASB SA 366 No. 05.41
and ASB EC155 No. 05A022.

Since the issuance of EASA AD 2011-0145, new occurr ences have been reported. Following the investigation of these even ts, It has been determined that the procedure for play measurement of the TGB control shaft/rod assembly bearings should be improved and the interv al between play measurements reduced from 110 to 55 FH. Consequentl y, EC has revised the
ASB instructions.

Prompted by these findings, EASA issued AD 2012-017 0, which superseded AD 2011-0145, retaining its requirements, reducing the time between each inspection from 110 FH to 55 FH and requiring play measurements in accordance with the instructions of paragraphs 3.B. 4 of the applicable SB at Revision 2 or subsequent.

After that AD was issued, Eurocopter issued ASB AS3 65 No. 05.00.61 and ASB EC155 No. 05A022, both at Revision 3, to recogn ise that helicopters which have TGB part number (P/N) 365A33-6005-09 ins talled (mod 07 65B63) were not affected by degradation of TGB control rod bearing.

To reflect that development, EASA issued AD 2012-01 70R1 to exclude helicopters modified in accordance with EC mod 07 6 5B63.

Since that AD was issued, an additional analysis co nfirmed the possibility to extend the inspection interval of the control shaft /rod assembly bearing for helicopters equipped with post MOD 0765B57 bearing.

For the reasons described above this, AD is revised to introduce the extended inspection interval.

Effective Date: Revision 2: 20 June 2014EASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 4/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Revision 1: 18 October 2013

Original issue: 14 September 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:

For the purpose of this AD, Eurocopter service publ ications (SP) are defined as specified in Table 1 of this AD:

Table 1 – Alert Service Bulletins (ASB) and Service Bulletins (SB)

SP No. revision level as indicated in each paragrap h of this AD

#1 AS365 ASB No. 05.00.54

#2 SA366 ASB No. 05.37

#3 EC155 ASB No. 05A015

#4 AS365 ASB No. 05.00.61

#5 SA366 ASB No. 05.41

#6 EC155 ASB No. 05A022

#7 AS365 SB No. 65.00.17

#8 SA366 SB No. 65.04

#9 EC155 SB No. 65-006

(1) For SA 365 N1, AS 365 N2 and AS 365 N3 helicopters : Within 10 FH after 05 August 2008 (effective date of EASA AD 200 8-0147-E), and thereafter at intervals not to exceed 10 FH, inspec t the oil level in accordance with the instructions of paragraph 2.B.1 of SP#1 Revision 1, 2, 3 or 4, or in accordance with the instructions of paragraph 3 .B.1 of SP#4 and, depending on findings, accomplish the app licable corrective actions as defined in SP#1 or SP#4, as applicable.

For SA 366 G1 helicopters: After 05 August 2008 (the effective date of EASA AD 2008-0147-E), during each ALF check and dur ing each flightrelated check (15 FH or 7 days, whichever occurs fi rst), inspect the oil level in accordance with the instructions of paragr aph 2.B.1 of SP#2 Revision 1, 2, 3 or 4, or in accordance with the instructions of paragraph 3.B.1 of SP#5 and, depending on findings, accomplis h the applicable corrective actions as defined in SP#2 or SP#5, as a pplicable.

For EC 155 B and EC 155 B1 helicopters: After 05 August 2008 (the effective date of EASA AD 2008-0147-E), during each ALF check and during each flight-related check (15 FH or 7 days, whichever occurs first), inspect the oil level in accordance with th e instructions of paragraph 2.B.1 of SP#3 Revision 1, 2, 3, 4 or 5, or in accordance with the instructions of paragraph 3.B.1 of SP#6 and, de pending on findings, accomplish the applicable corrective actions as def ined in SP#3 or SP#6, as applicable.

(2) For helicopters which, on 14 June 2011 (the eff ective date of EASA AD 2011-0105), do not embody in-production MOD 0765B58 or MOD 0765B56 (which includes MOD 0765B58) or which embod y MOD 0765B58 through the in-service accomplishment of SP #7, SP#8 or SP#9 as applicable to the helicopter version and having accumulated less than 60 FH after the last inspection for play in the dou ble bearing of the TGB control rod/shaft assembly, as required by paragrap h (2) of EASA AD 2008-0147-E, as applicable, and for all other helic opters which have not complied with paragraph (2) of EASA AD 2008-0147-E:

Within 50 FH after 27 November 2009 (the effective date of EASA AD 2009-0247), and thereafter at intervals not to exce ed 110 FH, inspect forEASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 5/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. play in the double bearing of the TGB control rod/s haft assembly, in accordance with the instructions of paragraph 2.B.3 of SP#1 Revision 3 or 4, SP#2 Revision 3 or 4, or SP#3 Revision 3, 4 o r 5, as applicable to the helicopter version.

(3) For helicopters which, on 14 June 2011 (the eff ective date of EASA AD 2011-0105), do not embody in-production MOD 0765B58 or MOD 0765B56 (which includes MOD 0765B58) or which embod y MOD 0765B58 through the in-service accomplishment of SP #7, SP#8 or SP#9, as applicable to the helicopter version, and having accumulated more than 60 FH after the last inspection for play in the double bearing of the TGB control rod/shaft assembly, as previousl y required by paragraph (2) of EASA AD 2008-0147-E:

Within 110 FH after accomplishment of the last che ck as previously required by paragraph (3) of EASA AD 2009-0247, and thereafter at intervals not to exceed 110 FH, inspect for play in the double bearing of the TGB control rod/shaft assembly in accordance wi th the instructions of paragraph 2.B.3 of SP#1 Revision 3 or 4, SP#2 Re vision 3 or 4, or SP#3 Revision 3, 4 or 5, as applicable to the helic opter version.

(4) If, during any inspection required by paragraph (2) or (3) of this AD, play is detected in the double bearing of the TGB contro l rod/shaft assembly, before next flight, replace the double bearing and, within 10 days after the inspection, report the inspection results to EC , in accordance with the instructions of paragraph 2.B.3 of SP#1 Revision 3 or 2.B.3.b of SP#1 Revision 4, or 2.B.3 of SP#2 Revision 3 or 2.B.3.b of SP#2 Revision 4,
or 2.B.3 of SP#3 Revision 3 or 2.B.3.b of SP#3 Revi sion 4 or 5, as applicable to the helicopter version.

(5) If, during any inspection required by paragraph (2) or (3) of this AD, NO play is detected in the double bearing of the TGB c ontrol rod/shaft assembly, before next flight, clean the control sha ft/rod assembly, collect the rinsing product and inspect for the presence of particles and/or of magnetic abrasion in the rinsing product, in accord ance with the instructions of paragraph 2.B.3 of SP#1 Revision 3 or 2.B.3.a of SP#1 Revision 4, or of paragraph 2.B.3 of SP#2 Revision 3 or 2.B.3.a of SP#2 Revision 4, or paragraph 2.B.3 of SP#3 Revision 3 o r 2.B.3.a of SP#3

Revision 4 or 5.

(6) If, during the inspection required by paragraph (5) of this AD, particles and/or magnetic abrasion dust are found in the rins ing product, accomplish the actions of one of the following para graphs:

(6.1) Before next flight, replace the double bearin g and, within 10 days after the inspection, report the inspection results to EC in accordance with the instructions of paragraph 2.B.3 of SP#1 Revision 3 or paragraph 2.B.3.a of SP#1 Revision 4, or paragraph 2.B.3 of SP#2 Revision 3, or paragraph 2.B.3.a of S P#2 Revision 4, or paragraph 2.B.3 of SP#3 Revision 3, or paragraph 2.B.3.a of SP#3 Revision 4 or 5, as applicable to the helicopt er version,

or

, (6.2) Before next flight, analyze the collected par ticles and/or the collected magnetic abrasion dust, in accordance wit h the instructions of paragraph 2.B.3.a of SP#1 Revision 4, SP#2 Revision 4, or SP#3 Revision 4 or 5, as applicable to the helicopter

version.

(7) If, during the analysis of the collected partic les as required by paragraph (6.2) of this AD, one or more M50 particles are det ected, and unless the double bearing has been replaced as required by par agraph (6.1) of this AD, before next flight, replace the double bearing and within 10 days after the inspection, report the inspection results to EC in accordance with the instructions of paragraph 2.B.3.a. of SP#1 Revision 4, SP#2EASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 6/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Revision 4, or SP#3 Revision 4 or 5, as applicable to the helicopter

version.

(8) For TGBs which are not equipped with an electrical chip detector , at the next scheduled check of the magnetic plug after 05 August 2008 (effective date of EASA AD 2008-0147-E) and thereaf ter at intervals not to exceed 25 FH or 50 FC whichever occurs first, in spect that there are no particles at the magnetic plug, in accordance wi th the instructions of paragraph 2.B.2 SP#1 Revision 1, 2, 3 or 4, SP#2 Re vision 1, 2, 3 or 4 or SP#3 Revision 1, 2, 3, 4 or 5 OR with the instru ctions of paragraph 3.B.2 of SP#4, SP#5 or SP#6, as applicable to the h elicopter version and corresponding ASB version.

(9) For TGBs equipped with electrical chip detector , at the next scheduled check of the magnetic plug, or after illu mination of the TGB “CHIP” warning light, whichever occurs first after 05 August 2008 (effective date of EASA AD 2008-0147-E), and therea fter upon each event of illumination of the TGB “CHIP” warning lig ht and, after 14 September 2012 [the effective date of the original issue of this AD], during each scheduled check of the magnetic plug, i nspect that there are no chips at the magnetic plug, in accordance with t he instructions of paragraph 2.B.2 of SP#1 Revision 1, 2, 3 or 4, SP#2 Revision 1, 2, 3 or 4 or SP#3 Revision 1, 2, 3, 4 or 5, or in accordanc e with the instructions of paragraph 3.B.2 of SP#4, SP#5 or SP#6 as applica ble to the helicopter version.

(10) If, during any check as required by paragraph (8) or (9) of this AD, as applicable, particles are detected, before next fli ght, depending on findings, accomplish the applicable corrective acti ons in accordance with the instructions of paragraph 2.B.2.b of SP#1 Revis ion 1, 2, 3 or 4, SP#2 Revision 1, 2, 3 or 4, or SP#3 Revision 1, 2, 3, 4 or 5, or in accordance with the instructions of paragraph 3.B.2 of SP#4, S P#5 or SP#6, as applicable to the helicopter version.

(11) Within 3 calendar months or within 300 FH, whi chever occurs first after 14 June 2011 (the effective date of EASA AD 2011-01 05), unless MOD 0765B56 (which includes MOD 0765B58) is already emb odied, modify the helicopter (embody MOD 0765B58) in accordance w ith the instructions of SP#7, SP#8 or SP#9, as applicable t o the helicopter

version.

(12) Accomplish the actions of one of the following paragraphs as applicable:

(12.1) Concurrently with embodiment of MOD 0765B58 as required by paragraph (11) of this AD, clean the control shaft/ rod assembly, collect the rinsing product and analyze the particl es and/or of magnetic abrasion collected in the rinsing product, in accordance with the instructions of paragraph 3.B.3.b of SP#4, SP#5 or SP#6 as applicable to the helicopter version,

or

(12.2) For helicopters that have MOD 0765B58 embodi ed before 14 June 2011 (the effective date of EASA AD 2011-0105) in accordance with SP#7, SP#8 or SP#9 as applicable to the helicopter version, within 3 calendar months or 300 FH after 14 June 2011 (the effective date of EASA AD 2011-0105) , whichever occurs first, clean the control shaft/rod assembly, collect the rinsing product and analyse the particles and/or th e magnetic abrasion dust collected in the rinsing product, in accordance with the instructions of paragraph 3.B.3.b of SP#4, SP#5 or SP#6 as applicable to the helicopter version.

(13) If, during the particle analysis as required b y paragraph (12.1) or (12.2) of this AD, as applicable, one or more M50 particle s are detected in the particles and/or in the collected magnetic abrasion dust, accomplish theEASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 7/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. following actions:

(13.1) Before next flight, replace the double beari ng in accordance with the instructions of paragraph 3.B.3.b of SP#4, SP#5 or SP#6 as applicable to the helicopter version,

and

(13.2) Before next flight after replacement of the double bearing , measure the reference play of the (new) double bear ing of the TGB control rod/shaft assembly, in accordance with the instructions of paragraph 3.B.4.a of SP#4, SP#5 or SP#6, as applicable to the helicopter version and depending on the type of fenestron installed, and, thereafter at intervals n ot to exceed the value as indicated in Table 2 of this AD, as applic able to helicopter configuration, measure the play (evolution) in the double bearing of the TGB control rod/shaft assembly and, dependin g on findings, accomplish the applicable corrective actions, in ac cordance with the instructions of paragraphs 3.B.4.b and 3.B.4.c of SP#4, SP#5 or SP#6, as applicable to the helicopter version an d depending on the type of fenestron installed,

and

(13.3) Within 10 days after the particle analysis a s required by paragraph (12.1) or (12.2) of this AD, as applicable, report the analysis results to EC, in accordance with the instructions of paragraph 3.B.3.b of SP#4, SP#5 or SP#6, as applicable to the helicopter

version.

Table 2 – Measurement of Play in Double Bearings

of TGB Control Rod/Shaft Assembly

Helicopter configuration Compliance Time (Interval – not to exceed)

Post MOD 0765B57 110 FH

All other configurations 55 FH

(14) If, during the particle analysis as required b y paragraphs (12.1) or (12.2) of this AD, as applicable, no M50 particle is detec ted in the particles or in the collected magnetic abrasion dust, before next f light, measure the reference play of the double bearing of the TGB con trol rod/shaft assembly in accordance with the instructions of par agraph 3.B.4.a of SP#4, SP#5 or SP#6, as applicable to the helicopter version and depending on the type of fenestron installed, and, thereafter at intervals
not to exceed the value as indicated in Table 2 of this AD, as applicable to helicopter configuration, measure the play (evol ution) in the double bearing of the TGB control rod/shaft assembly and, depending on findings, accomplish the applicable corrective acti ons, in accordance with the instructions of paragraphs 3.B.4.b and 3.B .4.c of SP#4, SP#5 or SP#6, as applicable to the helicopter version and d epending on the type
of fenestron installed.

(15) For helicopters on which MOD 0765B58 or MOD 07 65B56 (which includes MOD 0765B58) has been embodied in-producti on (since new or complete overhaul) before 08 July 2011 [the effecti ve date of AD 2011- 0117], within 110 FH after the last inspection for play in the double bearing of the TGB control rod/shaft assembly, as p reviously required by paragraph (2) of EASA AD 2008-0147-E or paragraph ( 2) or (3) of EASA AD 2009-0247, as applicable, measure the reference play of the double bearing of the TGB control rod/shaft assembly, in a ccordance with the instructions of paragraph 3.B.4.a of SP#4, SP#5 or SP#6, as applicable to the helicopter version and depending on the type of fenestronEASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 8/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. installed, and, thereafter, at intervals not to exc eed the value as indicated in Table 2 of this AD, as applicable to h elicopter configuration, measure the play (evolution) in the double bearing of the TGB control rod/shaft assembly and accomplish the associated co rrective actions, in accordance with the instructions of paragraphs 3.B. 4.b and 3.B.4.c of SP#4, SP#5 or SP#6, as applicable to the helicopter version and depending on the type of fenestron installed.

(16) If, during any interpretation of the results i n accordance with the instructions of paragraph 3.B.4.c of SP#4, SP#5 or SP#6, as applicable to the helicopter version and depending on the type of fenestron installed, as required by paragraphs (14) and (15) of this AD, as applicable, deviation found is below 0.5 mm, before next flight, accomplish the additional check for play in the dou ble bearing of the TGB control rod/shaft assembly and, depending on fi ndings, accomplish the applicable corrective actions in accordance wit h the instructions of paragraph 3.B.6 of SP#4, SP#5 or SP#6, as applicabl e to the helicopter version and depending on the type of fenestron inst alled.

(17) Accomplishment of required actions of paragrap hs (11), (12), (13.1) and (13.3) of this AD, as applicable, terminates the re petitive inspection requirements of paragraphs (2) and (3) of this AD.

(18) Embodiment of MOD 0765B58 or MOD 0765B56, as r equired by paragraph (11) of this AD, and replacement of the d ouble bearing of the TGB control rod/shaft assembly as required by parag raph (12) of this AD, do not constitute terminating action for the re petitive measurements of the play of the TGB control rod/shaft assembly, as required by paragraphs (13.2), (14) and (15) of this AD.

(19) For the play measurements (reference and evolu tion) of the double bearing of the TGB control rod/shaft assembly, as r equired by paragraphs (13.2), (14) and (15) of this AD, after 14 September 2012 [the effective date of the original issue of this A D], these must be accomplished in accordance with the instructions of paragraphs 3.B.4.a, 3.B.4.b and 3.B.4.c of SP#4, SP#5 or SP#6 at Revisi on 2 (or later revision), as applicable to the helicopter version and depending on the type of fenestron installed.

Ref. Publications: Eurocopter AS365 ASB No. 05.00.5 4 Revision 4 dated 16 May 2011.Eurocopter AS365 ASB No. 05.00.61 Revision 2 d ated 05 July 2012, or Revision 3 dated 25 June 2013, or Airbus Helicopter s AS365 ASB No. 05.00.61 Revision 4 dated 08 April 2014. Eurocopter AS365 SB No. 65.00.17 Revision 1 dated 2 1 March 2011.

Eurocopter SA366 ASB No. 05.37 Revision 4 dated 16 May 2011. Eurocopter SA366 ASB No. 05.41 Revision 2 dated 05 July 2012. Eurocopter SA366 SB No. 65.04 Revision 1 dated 21 M arch 2011.

Eurocopter EC155 ASB No. 05A015 Revision 5 dated 25 July 2011. Eurocopter EC155 ASB No. 05A022 Revision 2 dated 04 July 2012, or Revision 3 dated 25 June 2013, or Airbus Helicopter s EC155 ASB No. 05A022 dated 08 April 2014. Eurocopter EC155 SB No. 65-006 Revision 1 dated 21 March 2011.

The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have decided to issue of a Final AD with Request for Com ments, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety InformationEASA AD No.: 2012-0170R2

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 9/9 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical conten t of the requirements in this AD, please contact: Airbus Helicopters – Aéroport de Marseille Provence 13725 Marignane Cedex, France; telephone +33 (4) 42 85 97 97; facsi mile +33 (4) 42 85 99
66; E-mail: Directive.technical-support@eurocopter.com



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