EASA AD No.: 2012-0195-E

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EASA EMERGENCY AIRWORTHINESS DIRECTIVE

AD No.: 2012-0195-E

[Correction: 25 September 2012]

Date: 24 September 2012

Note: This Emergency 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 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 :

AgustaWestland S.p.A.

Type/Model designation(s) :

A109 helicopters

TCDS Number: EASA.R.005

Foreign AD: Not applicable

Supersedure: None

ATA 64 Tail Rotor – Tail Rotor Duplex Bearing Ring Nut – Inspection

Manufacturer(s): AgustaWestland S.p.A (formerly Agusta S.p.A.).

Applicability: A109E helicopters, serial numbers (S/N) from 11002 to 11807, except 11796;

A109LUH, all S/N;

A109S, all S/N;

AW109SP, S/N from 22202 to 22278, except 22239, 22264, 22266, 22272, 

22273, 22275 and 22277;

A109C helicopters, all S/N;

and A109K2 helicopters, all S/N.

Reason: Cases of loosening of the tail rotor duplex bearing locking nut Part Number 

(P/N) 109-0130-97 have been reported on A109 helicopters. The investigation 

identified the absence or the damage of one or both of the locking wires 

securing the tail rotor duplex bearing locking nut P/N 109-0130-97.

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

rotor function, resulting in loss of control of the helicopter.

To address this unsafe condition, AgustaWestland issued six Bollettino 

Tecnico (BT), BT 109-134, BT 109SP-051, BT 109S-48, BT 109L-051, BT 

109EP-121 and BT 109K-54 for all affected models.

For the reasons described above, this AD requires an inspection of the lock 

wire(s) securing the tail rotor duplex bearing locking nut, for condition and 

identification of any discrepancy. It also requires repetitive inspections of the 

affected part(s) for identification of any discrepancy. Finally, this AD requires
EASA AD No.: 2012-0195-E

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accomplishment of some maintenance tasks on the housing and slider group 

of the tail rotor rotating controls.

This AD has been republished to correct a typographical mistake with the 

applicable TCDS number (EASA.R.005 is correct instead of EASA.A.005).

Effective Date: 27 September 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 5 Flight Hours (FH) after the effective date of this AD, accomplish a 

visual inspection of the lock wire(s) MS20995C32 securing the tail rotor 

duplex bearing locking nut P/N 109-0130-97-101 or P/N 

109-0130-97-103 to the housing, in accordance with Part I of 

AgustaWestland BT 109-134, BT 109SP-051, BT 109S-48, BT 109L-051, 

BT 109EP-121 or BT 109K-54, as applicable depending on helicopter 

model.

(2) If during the inspection required by paragraph (1) of this AD, a 

discrepancy is identified, before next flight, depending on the 

configuration and condition, accomplish the applicable corrective action 

as specified in Table 1 of this AD.

Table 1

Configuration and condition Corrective action

1 or 2 lock wires are installed and 1 or 

both are damaged

Accomplish Part III of the BT on 

the housing and slider group of 

the tail rotor rotating controls

1 lock wire is installed and it is not 

damaged

Install a second lock wire 

MS20995C32.

(3) Within 25 FH after accomplishment of the inspection required by 

paragraph (1) of this AD, and thereafter at intervals not to exceed 25 FH 

from the last inspection, accomplish a visual inspection of the 2 lock wires 

securing the tail rotor duplex bearing locking nut P/N 109-0130-97-101 or 

P/N 109-0130-97-103 to the housing, in accordance with Part II of 

AgustaWestland BT 109-134, BT 109SP-051, BT 109S-48, BT 109L-051, 

BT 109EP-121 or BT 109K-54, as applicable depending on helicopter 

model.

(4) If during any inspection required by paragraph (3) of this AD, a 

discrepancy is identified, before next flight, accomplish Part III of 

AgustaWestland BT 109-134, BT 109SP-051, BT 109S-48, BT 109L-051, 

BT 109EP-121 or BT 109K-54, as applicable depending on helicopter 

model, on the housing and slider group of the tail rotor rotating controls.

(5) Within 100 FH or 7 months, whichever occurs first after the effective date 

of this AD, unless already accomplished following identification of a 

discrepancy in compliance with the requirements of paragraph (2) or (4) of 

this AD, accomplish Part III of AgustaWestland BT 109-134, BT 

109SP-051, BT 109S-48, BT 109L-051, BT 109EP-121 or BT 109K-54, as 

applicable depending on helicopter model, on the housing and slider 

group of the tail rotor rotating controls.

Note: For A109LUH helicopters, the “Tail Rotor Duplex Bearing Nut” 

correct torque value is to be found in the applicable BT and not in the 

applicable Maintenance Manual (MM).

(6) Accomplishment of Part III of of AgustaWestland BT 109-134, BT 109SP051, BT 109S-48, BT 109L-051, BT 109EP-121 or BT 109K-54, as 

applicable depending on helicopter model, on the housing and slider 

group of the tail rotor rotating controls constitutes terminating action for 

the repetitive inspections required by paragraph (3) of this AD.
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Ref. Publications: AgustaWestland BT 109-134 dated 21 September 2012.

AgustaWestland BT 109SP-051 dated 21 September 2012.

AgustaWestland BT 109S-48 dated 21 September 2012.

AgustaWestland BT 109L-051 dated 21 September 2012.

AgustaWestland BT 109EP-121 dated 21 September 2012.

AgustaWestland BT 109K-54 dated 21 September 2012.

AgustaWestland A109E MM “A109E-MM” second issue, Revision 2 dated 29 

June 2012.

AgustaWestland A109LUH MM “09-A/AM-00-X” Issue 1.0, Change 15 dated 

15 December 2011.

AgustaWestland A109S & AW109SP MM “0B-A-AMP-00-X” dated 08 June 

2012.

AgustaWestland A109C MM “A109C-MM” Basic Issue, Rev. 15 dated 14 July 

2010 and Temporary Revisions 64-1 and 64-2 dated 25 May 2012.

AgustaWestland A109K2 MM “A109K2-MM” Basic Issue, Rev. 15 dated 15

September 2010 and Temporary Revisions 64-1 and 64-2 dated 25 May 2012.

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. The results of the safety assessment have indicated the need for 

immediate publication and notification, without the full public consultation 

process.

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: Agusta S.p.A. Customer Support

Via del Gregge, 100 - 21015 Lonate Pozzolo (VA) – Italy

Telephone + 39 0331 664600 ; Fax: + 39 0331 664684

E-mail: custserv@agustawestland.com.