EASA AD No.: 2013-0009

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0009

Date: 11 January 2013

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 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 and A119 helicopters

TCDS Number: EASA.R.005

Foreign AD: Not applicable

Supersedure: None

ATA 64 Tail Rotor – Blade Retaining Bolts – Inspection / Replacement

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

Corporation (formerly Agusta Aerospace Corporation).

Applicability: A109C, A109K2, A109E and A119 helicopters, all serial numbers (s/n).

Reason: Cases of cracked tail rotor (TR) blade retaining bolts, part number (P/N)

109-8131-09-1 installed on an A109K2 and on an A109E helicopter, have been 

reported.

The investigation of these occurrences carried out by AgustaWestland revealed 

that the cracks were in the same area of the bolts and in correspondence with

some corrosion pits.

This condition, if not detected and corrected, could cause damage to, or loss of, 

a TR blade, possibly resulting in loss of control of the helicopter.

For the reasons described above, this AD requires a one-time visual and liquid 

penetrant inspection TR blade retaining bolts. Thereafter, this AD also requires

repetitive inspections of the TR blade retaining bolts and, if any crack, corrosion 

or damage is found, accomplishment of the applicable corrective actions.

Effective Date: 25 January 2013
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Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within the compliance time as specified in Table 1 of this AD, depending on 

the time in service of the TR blade retaining bolts on the effective date of 

this AD, accomplish a visual and liquid penetrant inspection of the retaining 

bolts P/N 109-8131-09-1 in accordance with the instructions of Part I of 

AgustaWestland Bollettino Tecnico (BT) 109-135, BT 109K-55, BT 109EP125 or BT 119-052, as applicable, depending on helicopter model.

Table 1 – First inspection

Flight Hours (FH) accumulated by 

the TR blade retaining bolts on the 

effective date of this AD

Compliance time

Less than 400 FH Before exceeding 500 FH 

accumulated by the retaining bolts

400 FH or more Within 100 FH or 2 months, 

whichever occurs first after the 

effective date of this AD

(2) After accomplishment of the inspection as required by paragraph (1) of this 

AD, within the compliance time specified in Table 2 of this AD, accomplish 

repetitive inspections of the TR blade retaining bolts P/N 109-8131-09-1 in 

accordance with the instructions of Part II of AgustaWestland BT 109-135, 

BT 109K-55, BT 109EP-125 or BT 119-052, as applicable, depending on 

helicopter model.

Table 2

Helicopter Model(s) Compliance time - Interval

A109C At each”300 FH helicopter inspection” or at 

intervals not to exceed 6 months, whichever 

occurs first

A109K2, A109E

and A119

At each “200 FH helicopter inspection” or at 

intervals not to exceed 6 months, whichever 

occurs first

(3) If, during any inspection as required by paragraph (1) or (2) of this AD, any 

crack, corrosion, damage or removal of cadmium plating in the central part 

of the bolt is identified, before next flight, replace the affected TR blade 

retaining bolt P/N 109-8131-09-1 with a serviceable part in accordance with 

the instructions of AgustaWestland BT 109-135, BT 109K-55, BT 109EP125 or BT 119-052, as applicable, depending on helicopter model.

(4) Replacement of TR blade retaining bolts as required by paragraph (3) of 

this AD does not constitute terminating action for the inspections as 

required by paragraphs (1) and (2) of this AD.

(5) From the effective date of this AD, do not install a TR retaining bolt P/N 

109-8131-09-1 that has accumulated more than 400 FH, on any helicopter 

unless it has passed the inspections as required by paragraph (1) of this 

AD.

Ref. Publications: AgustaWestland BT 109-135 dated 19 December 2012.

AgustaWestland BT 109K-55 dated 19 December 2012.

AgustaWestland BT 109EP-125 dated 19 December 2012.

AgustaWestland BT 119-052 dated 19 December 2012.

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

compliance with the requirements of this AD.
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Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative 

Methods of Compliance for this AD.

2. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until 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: 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.