EASA AD No.: 2011-0116 

EASA Form 110 Page 1/4 

 EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2011-0116 

Date: 06 July 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 : 

EUROCOPTER 

Type/Model designation(s) : 

EC130 B4 helicopters 

TCDS Number : EASA R.008 

Foreign AD: Not applicable. 

Supersedure : None 

ATA 53 Fuselage – Tail Boom / Fenestron Junction Frame – Inspection 

Manufacturer(s): Eurocopter (formerly Eurocopter France, Aerospatiale) 

Applicability: EC 130 B4 helicopters, all serial numbers, except: 

- those that have been modified in production by EC modification 073880 

(Reinforcement of the tail boom / Fenestron junction), and 

- all those which have been repaired in accordance with Repair Design 

Approval Sheet (RDAS) No. 350 53 522 07 or 350 53 521 10 or 350 53 524 

10 or 350 53 525 10 or 350 53 526 10 or 350 53 511 11 or 350 53 512 11. 

NOTE: Tail boom assembly serial number TB 7377 is not affected by this AD.

Reason: Several reports have been received of finding cracks in the tail boom / 

Fenestron junction frame. Prompted by these reports, Eurocopter published 

Information Notice No. 2167-I-53. Since publication of this document, new 

cases of cracks in the tail boom / Fenestron junction frame have been 

reported. 

The examination of the parts showed the cracks were longer than in the 

previous cases. The cracks start to develop in the plane of the rivet head 

countersink on the Right Hand (RH) side of the Fenestron and spread to the 

web of the frame. 

This condition, if not detected and corrected, could lead to structural failure, 

possibly resulting in Fenestron detachment and consequent loss of control of 

the helicopter. 

For the reasons described above, this AD requires repetitive inspections of 

the affected area and, depending on findings, accomplishment of corrective 

actions. 

Effective Date: 20 July 2011 
EASA AD No.: 2011-0116 

EASA Form 110 Page 2/4 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within 10 flight hours (FH) after the effective date of this AD and 

thereafter at intervals not exceeding 40 FH, inspect the RH side of the tail 

boom / Fenestron junction frame (the frame) for cracks, in accordance 

with the instructions of paragraph 3.B.1 and paragraph 3.B.2 of 

Eurocopter EC130B4 Emergency Alert Service Bulletin (ASB) No. 

53A019. 

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

is detected, depending on the extent of the crack(s), accomplish the 

action as specified in Table 1 of this AD, as applicable. 

Table 1 – Crack detected 

Extent of crack(s) Action 

(a) entirely crossing the frame 

web 

Before next flight, contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 

(b) crossing part of the frame 

web 

Up to 10 FH are allowed to ferry the 

helicopter to a location where the 

corrective action can be 

accomplished; then contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 

(c) outside of frame only - no 

crack in the frame web 

Before next flight, strip the frame in 

accordance with the instructions of 

paragraph 3.B.3 and inspect the 

frame in accordance with the 

instructions of paragraph 3.B.4 of 

EC130B4 ASB No. 53A019. 

(3) If, during any inspection as required by paragraph (1) of this AD, no crack 

is found, within 110 FH or 6 months, whichever occurs first after the 

effective date of this AD, strip the frame in accordance with the 

instructions of paragraph 3.B.3 and inspect the frame in accordance with 

the instructions of paragraph 3.B.4, and thereafter at intervals not 

exceeding 100 FH inspect the frame in accordance with the instructions 

of paragraph 3.B.4 of EC130B4 ASB No. 53A019. After the initial 

inspection as required by paragraph (3) of this AD, the repetitive 

inspections of paragraph (1) of this AD are no longer required. 

(4) If, during any inspection as required by paragraph (2) – Table 1 or by 

paragraph (3) of this AD, or during any other maintenance action, a crack 

is detected that reaches the radius of the frame, inspect the frame in 

accordance with the instructions of paragraph 3.B.1 of EC130B4 ASB 

No. 53A019. Thereafter repeat the same inspection at intervals not 

exceeding 40 FH. 

(5) Depending on findings during any inspection as required by paragraph 

(4) of this AD, accomplish the corrective action as specified in Table 2 of 

this AD, as applicable. 
EASA AD No.: 2011-0116 

EASA Form 110 Page 3/4 

Table 2 – Crack detected 

Extent of crack(s) Action 

(a) entirely crossing the frame 

web 

Before next flight, contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 

(b) crossing part of the frame 

web 

Up to 10 FH are allowed to ferry the 

helicopter to a location where the 

corrective action can be 

accomplished; then contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 

(c) outside of frame only - no 

crack in the frame web 

Up to 85 FH are allowed after the 

previous maintenance action when 

the frame was inspected (i.e. the one 

preceding the maintenance action 

during which a crack reaching the 

radius of the frame was detected). 

Then, up to 10 FH are allowed to 

ferry the helicopter to a location 

where the corrective action can be 

accomplished; then contact EC for 

approved instructions and 

accomplish those instructions 

accordingly. 

If the crack that reaches the radius of 

the frame was detected during the 

initial inspection as required by 

paragraph (1) of this AD, accomplish 

the actions required by line (b) of this 

Table 2 

(6) If, during any inspection as required by paragraph (2) – Table 1 or by 

paragraph (3) of this AD, or during any other maintenance action, a crack 

is detected that does not reach the radius of the frame, inspect the frame 

in accordance with the instructions of paragraph 3.B.1 and 3.B.4 of 

EC130B4 ASB No. 53A019. Thereafter repeat the same inspection at 

intervals not exceeding 40 FH. 

(7) Depending on findings during any inspection as required by paragraph 

(6) of this AD, accomplish the corrective action as specified in Table 3 of 

this AD, as applicable. 

Table 3 – Crack detected 

Extent of crack(s) Action 

(a) entirely crossing the frame 

web 

Before next flight, contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 

(b) crossing part of the frame 

web 

Up to 10 FH are allowed to ferry the 

helicopter to a location where the 

corrective action can be 

accomplished; then contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 
EASA AD No.: 2011-0116 

EASA Form 110 Page 4/4 

(c) outside of frame only - no 

crack in the frame web 

Flights are allowed within 12 months 

after detecting the crack that does 

not reach the radius of the frame.

Then, up to 10 FH are allowed to 

ferry the helicopter to a location 

where the corrective action can be 

accomplished; then contact EC for 

approved instructions and 

accomplish those instructions 

accordingly 

(8) From the effective date of this AD, do not install a tail boom assembly on 

a helicopter unless it incorporates modification 073880.

Ref. Publications: Eurocopter EC130B4 Emergency ASB 53A019 dated 14 June 2011. 

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 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: 

Eurocopter Technical Support Department of the Customer Service: 

Telephone +33 (0)4.42.85.97.16, Fax + 33 (0)4.42.85.99.66, 

E-mail: airframe.technical-support@eurocopter.com