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# EMERGENCY



# ALERT SERVICE BULLETIN

SUBJECT : FUSELAGE

Chec k of the tail boom / Fenestron junction frame

AIRCRAFT

CONCERNED NUMBER Version(s)

Civil Military

EC130 53A019 B4



### Revision No. Date of issue

Revision 0 2011

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- 14

Revision 1 2014

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- 15



### Summary :

Check for cracks i n the tail boom/Fen e stron junction frame.



### Reason for last revision :

The purpose of Revision 1 of this ALERT SERVICE BULLETIN is:

- To extend the inspection to the entire c ircumference of the frame

.

- To cancel the instructions in this ALERT SERVICE BULLETIN for helicopters which have embodied

MOD 074609 through SB 53

- 024

.



### Compliance :

Compliance with this ALERT SERVICE BULLETIN is mandatory. For the attention of

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### 1. PLANNING INFORMATION

1.A

. EFFECTIVITY

1.A.1. Helicopters/installed equipment

- Helicopters equipped with a tail boom assembly fitted with countersunk head rivets at the tail

boom / Fenestron junction on the Fenestron side, which do not embody:

. modification 073880 (Reinfor cement of the tail boom / Fenestron junction),

or

. 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 or 350 53 523 11 or 350 53 504 12 or RDAS

- AE11

- 0205 o r

RDAS

- AE11

- 0380

,

or

. modification 074609 (Reinforcement of the tail boom / Fenestron junction through retrofit) (see NOTE 5)

.

- The helicopter equipped with tail boom assembly number TB 7377 is not concerned by the instructions of

this ALERT SERVICE BULLETIN.



### NOTE 1

Refer to t

he aircraft individual inspection log book (MOD record) to identify the

actual configuration of the helicopter.



### NOTE 2

The tail boom assemblies which are not identified by one of the above

- mentioned

RDAS numbers and contain a tail boom / Fenestron juncti on frame riveted with

brazier head rivets on the Fenestron side, have embodied m odification 073880

.



### NOTE 3

The RDASs are identified by the mark ing of the ir number close to the tail boom

identification label, visible from the inside of the rear cargo comp artment.



### NOTE 4

The tail boom assemblies which have been subject to compliance with Service

Bulletin No. 53

- 017 are concerned by the instructions of this ALERT SERVICE

BULLETIN, except for tail boom assembly number TB 7377.



### NOTE 5

The tail boom assemb lies which embody MOD 074609 ( through Service Bulletin

No. 53

- 024

) are not concerned by the instructions of this ALERT SERVICE

BULLETIN.

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- installed equipment

- Tail boom assemblies fitted with countersunk head rivets at the ta il boom / Fenestron junction on the

Fenestron side and which do not embody:

. modification 073880 (Reinforcement of the tail boom / Fenestron junction) (See NOTE 2),

or

. 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 or 350 53 523 11 o r 350 53 504 12 or RDAS

- AE11

- 0205 o r RDAS

AE11

- 0380

. (See NOTE 3)

,

or . modification 074609 (Reinforcement of the tail boom / Fenestron junction) (See NOTE 5).

- T he t ail boom assembly with part number TB 737 7 is not concerned by the instructions of this ALERT

SERVICE BULLETIN.



### 1.B. ASSOCIATED REQUIREMENTS

Not applicable.

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### 1.C. REASON

Revision 0 : Following the issue of Information Notice No. 2167

- I

- 53, EUROCOPTER has received new reports o f cracks

i n the tail boom/Fenestron junction frame.

The cracks start ed in the plane of the rivet head countersinks on the RH side of the Fenestron (Detail E,

Figure 3) and spread to the web of the frame (Details C and D, Figure 2).

The examination of th e parts showed that the cracks were longer than in the previous cases , questioning

easy detection of the cracks from the outside as well as the inspection interval to substantiate the strength of

the frame.

Consequently, EUROCOPTER rendered compliance wi th this ALERT SERVICE BULLETIN mandatory,

whose purpose was t o enable a detailed visual check from the outside and inside of the frame and to

schedule its replacement if a crack is found

.

Revision 1 :

Airbus Helicopters has defined modification 074609, w hose purpose is to li mit the risk of cracks appearing on

the tail boom / Fenestron junction frame.

The purpose of Revision 1 of this ALERT SERVICE BULLETIN is to:

- inform operators that the embodiment of MOD 074609 (Service Bulletin 53

- 024) cancels the inst ructions

defined in this ALERT SERVICE BULLETIN.

- modify compliance with paragraph 1.E.2. by requesting the embodiment of MOD 074609 through Service

Bulletin 53

- 024 before 31/12/2017.

- To extend the inspection to the entire circumference of the frame on heli copters defined in paragraph 1.A.

Revision 1 of this ALERT SERVICE BULLETIN affects compliance with Revision 0.



### 1.D. DESCRIPTION

Compliance with this ALERT SERVICE BULLETIN consists in checking for cracks in the tail boom/Fenestron

junction frame

.



### 1 .E. COMPLIANCE

NOTE 6

In the following paragraphs, use the contact information below to contact the

Technical Support Department of the Customer Service:

Tel.: +33 (0)4.42.85.97.16.

Fax: + 33 (0)4.42.85.99.66.

E

- mail: airframe.technical

- support@eurocopter.com



### NOTE 7

Airbus Helicopters reminds you that a visual check for cracks is scheduled at the

flight

- related check (VLV) as per AMM Task 05

- 40

- 00,6

- 1 and makes it possible to

detect a c rack, if any

.

1.E.1. Compliance at the works

Not applicable.

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Helicopters/ installed equipment: The work on the helicopter is to be performed by the operator.

a) Within 10 flying hours following receipt of Revision 0 of this ALERT SERVICE BULLETIN , issued

on 14/06/2011 : . Comply with paragraph s 3.B.1. and 3.B.2. pending compliance with paragraph s 3.B.3. and 3.B.4.

Interpretation of results following compliance with paragraph s 3.B.1. and 3.B.2. :

1) Presence of a cra ck entirely crossing the web (c) of frame (a) (See detail D, Figure 2) :

. All flights are prohibited.

. For the conditions for returning the helicopter to service, contact the Customer Service Technical

Support Department (See NOTE 6 )

.

2) Presence of a c rack crossing part of the web (c) of frame (a) :

. All flights are prohibited except for the ferry flight not exceeding 10 flying hours.

. For the conditions for returning the helicopter to service, c ontact the Customer Servi ce Technical

Support Departmen t (See NOTE 6 )

.

3 ) Presence of a crack o n the outside of frame (a) and no crack in the web (c) of frame (a) :

. Comply successively with paragraph s 3.B.3. ( u nless already carried out ) and 3.B.4

.

4 ) If no crack is found :

. Flights can be continued

.

. Pending compliance with paragraph s 3.B.3. and 3.B.4 ., c omply with paragraph s 3.B. 1

. and 3.B.2. at

periodic intervals not exceeding 40 flying hours.

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Rev ision 1 of this ALERT SERVICE BULLETIN , issued on the date indicated at the bottom of the page :

. Co mply with paragraph s 3.B.3. and 3.B.4

. successively.

Interpretation of results following compliance with paragraph s 3.B.3 . and 3.B.4. :

1) Presence of a c rack reaching the radius of frame (a) (Figure 3) : . All flights are prohibited beyond 85 flying hours following the inspection (compliance with paragraph

3.B.4. or the flight

- related check (VLV)) prior to the one during which a crack

, reaching the radius

of frame (a), was detected , except for the ferry flight not exceeding 10 flying hours

. . Comply with paragraph 3.B.1. at periodic intervals not exceeding 40 flying hours.

. For the conditions for returning the helicopter to service, contact the Customer Service Technical

Support Department (See NOTE 6 )

.

2) Presence of a crack not reach ing the radius of frame (a) (Figure 3) : . All flights are prohibited after 12 months from initial detection of a crack on the outside of the

frame

, except for the ferry fli ght not exceeding 10 flying hours

.

. Comply successively with paragraph s 3.B.1. and 3.B.4. at periodic intervals not exceeding 40 flying

hours.

. Inform the Customer Service Technical Support De partment ( See NOTE 6 )

.

3) If n o crack is found :

. Flights can be continued.

. Pending compliance with Serv ice Bulletin 53

- 024, comply with paragraph 3.B.4. at periodic intervals

not exceeding 100 flying hours.

. Comply with Service Bulletin 53

- 024 (MOD 074609) before 31/12/2017.

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the outside of the

frame (§ 3.B.3)

Check stripped area

on the outside of

frame (§ 3.B.4) Yes

Crack on the

outside (T1)

Crack

entirely

crossing

the web Yes No Crack?

110 flyi ng hours //

6 months since T0

Check s tripped area

on the outside of the

frame (§ 3.B.4) Or

No Check for cracks on the inside and outside

(§ 3.B.1 . and 3.B.2.) Within 10 flying hours from

receipt of this AL ERT SERVICE

BULLETIN Revision 0 (T0)

Ch eck for cracks on the inside and

the outside (§ 3.B. 1. and 3.B.4) Check the inside of

the frame (§ 3.B.1) Crack on the

inside

Strip the are a on

the outside of the

frame (§ 3.B.3)

FLIGHT PROHIBITED except for

ferry flight ≤ 10 flying hours.

Contac t Airbus Helicopters 40 flying

hours 100

flying

hours

40 flying

hours 40 flying

hours

12 months

since T1? Does the c r ack on

the outside reach the

radius of the frame?

Crack on the inside or

85 flying hours since

T2? No Yes

No

Yes

Yes No Contact Airbus Helicopters Crack on the

outside ?

k on the outside ? Cr ack crossing

part of the web

FLIGHT

PROHIBITED

except for

ferry flight

≤ 10 flying

hours.

Contact

Airbus

Helicopters FLIGHT

P ROHIBITED.

Contact Airbus

Helicopters

Yes= T1

No Key :

T0: date of receipt of this

EASB Rev 0.

T0: date of receipt of this

EASB Rev 1.

T1: date of in itial detection

of a crack on the

outside.

T2: date of the inspection

prior to the one during

which a crack, reaching

the radius of the frame,

was detected.

Comply with SB

53

- 024 before

31/12/2017

Airworthiness

Directive

lifted

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- installed equipment :

Before installation on a helicopter

, comply with paragraph 3.



### 1.F. APPROVAL

Approval of modifications :

Not applicable.

Approval of this document :

T he technical information contained in this ALERT SERVICE BULLET IN Revision 0 was approved

on June 10, 2011 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of

civil versions subject to an Airworthiness Certificate.

Th e technical information contained in this ALERT SERVICE BULLETIN Revision 1 was approved

on April 08, 2014 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters of

civil versions subject to an Airworthiness Certifica te.



### 1.G. MANPOWER

Airbus Helicopters recommends that compliance with this ALERT SERVICE BULLETIN be ensured by

personnel with the following qualification:

Qualification: 1 Mechanical Engineering Technician or Aircraft Structure Technician (paragr aph 3.B.)

and/or,

1 suitably trained pilot, qualified in accordance with local regulation s (paragraphs 3.B.1.

, 3 .B. 2

. and 3.B.4. ).

The time for the operations is given for information purposes, for a standard configuration.

Time for the operations: Approximately 10 minutes for compliance with paragraph 3.B.1.

Approximately 10 minutes for compliance with paragraph 3.B.2.

Approximately 4 hour s for compliance with paragraph 3.B. 3 . excluding drying time.

Approximately 30 minutes for compliance wit h paragraph 3.B.4

.



### 1.H. WEIGHT AND BALANCE

Not applicable.



### 1.I. EFFECT ON ELECTRICAL LOADS

Not applicable.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.

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### 1.K. REFERENCES

The following documents are necessary for compliance wit h this ALERT SERVICE BULLETIN.

Standard Practices Manual (MTC):

MTC: 20.02.07.403: Applying VERNELEC 43022 varnish.

MTC: 20.04.01.102: Description and use of standard cleaning products for individual parts and on aircraft.

MTC: 20.04.02.401: Stripping o rganic surface coatings.

MTC: 20.04.05.101: General information concerning painting means and paint touch

- ups.

MTC: 20.04.05.402: EPOXY primer P05

- P20 scheme.

Aircraft Maintenance Manual (AMM):

AMM: 55

- 11

- 00,4

- 1: Removal/Installation

- Horizontal stabi lizer



### 1.L. DOCUMENTS AFFECTED

M odification 074609 of this ALERT SERVICE BULLETIN will be integrated into the following manual:

- MSM.

These documents will be issued subsequently.



### 1.M. INTERCHANGEABILITY OR MIXABILITY OF PARTS

Not applicable.

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### 2. MATERIAL INFORMATION

2.A. MATERIAL: PRICE

- AVAILABILITY

- PROCUREMENT

Not applicable.



### 2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

Not applicable.



### 2.C. MATERIAL REQUIRED FOR EACH HELICOPTER/COMPONENT

Products to be ordered separately :

Refer to the Work Cards and Tasks specified in this ALERT SERVICE BULLETIN and the list below:

Designation Qty Product P/N CM Item

No.

Primer P05 A/R DHS186

- 111.20 CM 48 7 1

Primer P20 A/R DHS186

- 111.40 CM 48 8 2

VERNELEC v arnish A/R ECS2228.1 0 CM 514 3

The products can be ordered separately from the INTERTURBIN E AVIATION LOGISTICS company.

Website: http://www.interturbine.com

Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444



### 2 .D. MATERIAL TO BE RETURNED

Not applicable.

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### 3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

Read and comply with the general instructions concerning painting means and paint touch

- ups as per MTC

Work Card 20.04.05.101.



### 3.B. OPERATIONAL PROCEDURE

3 .B.1. Inspection of the R H side of the tail boom/Fenestron junction frame from the i nside (Figure s 1 and 2 )

- C heck that there is no crack in the web (c) of frame (a) on the RH side (Detail s C and D, Figure 2) u sing a

light source positioned in front of the opening of the drive shaft tube and by looking through the yaw control

opening in the Fene stron (Detail B, Figure 1).



### FOR THIS INSPECTION, THE SURFACE OF THE

FRAME MUST BE CLEAN

.

- If necessary, clean the web (c) of junction frame (a):

. Remove the horizontal stabilizer as per AMM Task 55

- 11

- 00,4

- 1.

. Clean junction frame (a) as per MTC Work Card 20.04.01.102.

. Install the horizontal stabilizer as per AMM Task 55

- 11

- 00,4

- 1.

- Interpret the results in accordance with paragraph 1.E.2. a).

3.B.2. Inspection o f the RH side of the tail boom/Fenestron junction frame from the out side before stripping

(Figures 1 and 2)

- Check that there is no crack on the external surface of junction frame ( a) (Detail A, Figure 1).

- Interpret the results in accordance with paragraph 1.E.2. a).

3.B.3

. Stripping the entire circumference of the tail boom/Fenestron junction frame (Figure 3 )

- Remove the cowling (b)

.

- Strip the two rows of rivets over the circumference of the junctio n frame on the Fenestron side up to the tail

boom coating , as per Detail E and as per MTC Work Card 20.04.02.401:

. over the visible width of 45 mm (1.771 in.) from the cowling (b).

- Apply a coat of primer (1) or (2) to the stripped area as per MTC Work Card 20.04.05.402.

- Apply varnish (3) to the stripped area as per MTC Work Card 20.02.07.403.

- Install the cowling (b)

3.B.4

. Inspection of the entire circumference of the tail boom/Fenestron junction frame from the outside after

stripping (Figure 3 )

- Remove the cowling (b)

.

- Check that there are no cracks in the area stripped in accordance with paragraph 3.B.3

.

- Interpret the results as per paragraph 1.E.2. b).

- Install the cowling (b)

. 

### CAUTION

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### 3.C. IDENTIFICATION

Identification of this document :

Record initial compliance with this ALERT SERVICE BULLETIN in the helicopter documents

.



### 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Not applicable.

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# C a

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### c 

# D

c

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### a Area to be stripped

over the entire

circumference of the

frame 45 mm (1.771 in.)

DETAIL of the A rea to be stripped



### a radius of frame (a)



### b