EASA AD No.: 2011-0019 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0019 

Date: 03 February 2011 

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 : 

Agusta S.p.A. 

Type/Model designation(s) : 

AB139 and AW139 helicopters 

TCDS Number : EASA.R.006 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2009-0234-ER1 dated 29 October 2009. 

ATA 53 Fuselage – Tail Boom – Inspection / Modification 

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

Applicability: All AB139 and AW139 helicopters, all serial numbers (S/N), if equipped with 

one of the following tail assembly part numbers (P/N): 

 3G5350A00132; 

 3G5350A00133; 

 3G5350A00134; 

 3G5350A00135, 

except those having already embodied tail boom reinforcement structural 

retro-modification (mod.) P/N 3G5309P01812 either in production or through 

the accomplishment of Agusta Bollettino Tecnico BT 139-200. 

Reason: Some operators of AB/AW139 helicopters have reported debonding of 

fuselage tail boom panels. This condition, if not detected and corrected, could 

lead to the structural collapse of the tail boom installation, resulting in loss of 

control of the helicopter. 

EASA AD 2008-0157 required repetitive inspections of the tail boom 

assembly and, in case of debonding detection, the accomplishment of 

corrective actions. 

EASA AD 2009-0198-E, superseding EASA AD 2008-0157, required as a 

precautionary measure to perform repetitive inspections of the tail boom 

panels at closer intervals and, in case of findings, the accomplishment of the 

relevant corrective actions. 

EASA AD 2009-0234-E, which superseded AD 2009-0198-E, required the 
EASA AD No.: 2011-0019 

EASA Form 110 Page 2/3 

accomplishment of additional inspections. 

Such additional inspection programme consisted of daily General Visual 

Inspections (GVI) and repetitive detailed inspections of the tail boom panels, 

to detect bulgings and/or deformations on the right hand (RH) side of the tail 

boom outer panel skin. Furthermore, for helicopters equipped with some tail 

assembly P/N, repetitive tap inspections were required at intervals not to 

exceed 25 Flight Hours (FH) on two specific areas of the tail boom RH side. 

EASA AD 2009-0234-E also required the accomplishment of the relevant 

corrective actions, as necessary. 

EASA AD 2009-0234-ER1 was issued to add some S/N to those for which 

the inspection in accordance with paragraph (2) of the Required action and 

Compliance Time section was required. Reference to Agusta Alert Bollettino 

Tecnico (BT) 139-195 Rev. A was also added. Furthermore, it was mentioned 

the need to use a Platform to carry out the inspection in accordance with 

paragraph (1) of the AD. 

This AD, which supersedes EASA AD 2009-0234-ER1 partially retaining its 

requirements, is issued to limit the applicability only to those helicopters 

equipped with tail assemblies which have not embodied mod. P/N 

3G5309P01812, either in production or through the accomplishment of 

Agusta Bollettino Tecnico (BT) 139-200. In addition, whenever an area of 

disbond is found exceeding the limits described in Agusta BT 139-195 

Rev. B, this AD requires, before next flight, the embodiment of mod. P/N 

3G5309P01812 and to contact Agusta for further instructions. 

Effective Date: 17 February 2011 

Required action(s) 

and Compliance 

Time(s): 

Required as indicated, unless already accomplished: 

(1) Within 10 flying hours after the effective date of this AD and thereafter at 

intervals not to exceed 10 flying hours or 24 hours, whichever occurs 

first or, if the helicopter is not flown, before restarting operations, 

perform GVI made from within touching distance and using a light 

source, of the tail panels on the tail boom RH side to detect outer skin 

bulgings and/or deformations, in accordance with the instructions of 

Agusta BT 139-195 Rev. B. To carry out the inspection use Platform 

(GG-07-00) P/N 2004-5007-B or approved equivalent. 

(1.1) If sign of bulgings or deformation are found, before further flight do 

a tap inspection of the tail assembly to better identify the affected 

area. 

(1.2) If, during the inspection required by paragraph (1.1) of this AD, an 

area of single disbond is found, which exceeds the maximum 

permitted size given in paragraph 3.3 of Agusta BT 139-195 Rev. 

B, before further flight mark the area(s) of disbond for identification, 

install mod. P/N 3G5309P01812, contact Agusta for instructions 

and follow their corrective actions.

 (2) Within 50 FH from the last inspection carried out in compliance with 

EASA AD 2009-0234-ER1, and thereafter at intervals not to exceed 50 

FH, perform a detailed inspection of all the tail panels in accordance 

with the instructions of Agusta BT 139-195 Rev. B. 

(2.1) If, during any inspection required by paragraph (2) of this AD, an 

area of single disbond is found, which exceeds the maximum 

permitted size given in paragraph 2.1 of Agusta BT 139-195 Rev. 

B, before further flight mark the area(s) of disbond for identification, 

install mod. P/N 3G5309P01812, contact Agusta for instructions 

and follow their corrective actions.

(3) For AB139/AW139 helicopters, if equipped with tail assembly P/N 

 3G5350A00132, 3G5350A00133 or 3G5350A00134 (up to S/N A7/109 

 for short nose configuration and up to S/N A7/063 for long nose 

 configuration) not having embodied Agusta BT 139-159 Rev. B: 

Within 25 FH from the last inspection carried out in compliance with 
EASA AD No.: 2011-0019 

EASA Form 110 Page 3/3 

EASA AD 2009-0234-ER1 or 7 days after the effective date of this AD, 

whichever occurs later, and thereafter at intervals not to exceed 25 FH, 

do tap inspections of the areas identified as Area 3 (except for the 

longeron area) and Area 5 in accordance with the instructions of Agusta 

BT 139-195 Rev. B. 

(3.1) If, during any inspection required by paragraph (3) of this AD, one 

or more of the conditions described in paragraphs 4.2, 4.3 and 4.4 

of Agusta BT 139-195 Rev. B are exceeded, before further flight 

mark the area(s) of disbond for identification, install mod. P/N 

3G5309P01812, contact Agusta for instructions and follow their 

corrective actions.

(4) The embodiment of mod. P/N 3G5309P01812 in accordance with 

paragraphs (1.2), (2.1) or (3.1) of this AD terminates the repetitive 

inspection requirements of this AD. 

(5) A Ferry Flight may be authorized to allow helicopters to be delivered to 

proper maintenance basis in order to install mod. P/N 3G5309P01812 or 

to replace the tailboom. 

(6) After the effective date of this AD do not install any tail assembly P/N 

3G5350A00132, 3G5350A00133, 3G5350A00134 or 3G5350A00135 on 

any helicopter, unless in compliance with the requirements of this AD. 

Ref. Publications: Agusta Alert Bollettino Tecnico 139-195 Rev. B dated 2 February 2010; 

Agusta Bollettino Tecnico 139-200 Original Issue dated 2 February 2010; 

Agusta Bollettino Tecnico 139-159 Rev. B dated 6 September 2010. 

The use of later approved revisions of these documents 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 required actions and the risk allowance have granted the issuance of 

a Final AD with Request for Comments, postponing the public 

consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

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. 

E-mail: aw139.mbx@agustawestland.com .