BOLLETTINO TECNICO N° 139-311

The technical content of this document is approved 

under the authority of DOA nr. EASA.21J.005 DATE February 21, 2014

REV. B – June 4, 2014

Compliance with

this bulletin is: 

Page 1 of 37

SUBJECT 

SUBFLOOR FRAME STA2105 RETROMODIFICATION P/N 3G5306P47211, 

INSTALLATION OF.

REASON 

To reinforce the Tail Rotor (TR) pedals support frame, performing interim repetitive 

inspections until implementation of the retromodification. 

HELICOPTERS AFFECTED 

All AB139/AW139 helicopters from 31005 (except S/N 31007) to S/N 31517 (except 

S/N’s 31415, 31431, 31491, 31500, 31508, 31516) and from S/N 41001 to S/N 41356 

(except S/N 41355). 

NOTE 

Implementation of this revision is not required for 

helicopters that have already successfully complied 

with Part II of this Bollettino Tecnico. 

AgustaWestland S.p.A

Via Giovanni Agusta, 520

21017 Cascina Costa di Samarate (VA) Italy

Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595

MANDATORY

An appropriate entry should be made in the aircraft log book upon accomplishment.

If ownership of aircraft has changed, please, forward to new owner.
B.T. 139-311 Rev. B

Page 2 of 37

COMPLIANCE

Part I: within thirty (30) flight hours or two (2) months, whichever comes first, and then 

every three hundred (300) flight hours or six (6) months until accomplishment of 

part II.

Part II: immediately after the inspection, if cracks are detected while complying with part 

I, or within twelve hundred (1200) flight hours, if cracks are not identified.

DESCRIPTION

Cracks on the TR pedals support frames have been reported on some aircraft in service. 

Part II of this Bollettino Tecnico provides the instructions to implement appropriate 

structural reinforcements acting both as a preventive measure and as a repair in case of 

cracks. Moreover specific periodic inspections are introduced in Part I in order to monitor 

aircraft in service up to the introduction of the reinforcements. These retromodifications 

have been already introduced on new build aircraft.

Revision A introduces some changes to the installation fixing hardware related to the 

central reinforcement repair while in revision B some editorial changes have been made 

in the compliance instructions to make them clearer.

REQUIRED MANPOWER

It is estimated that, in order to accomplish this Bollettino Tecnico, the following

maintenance man-hours (MMH) are necessary:

Part I: two (2) MMH;

Part II:two hundred and forty (240) MMH.

Man-hours are based on hands-on time and may vary with personnel and facilities 

available.

WARRANTY

 Owners/Operators who comply with the instructions in this Bulletin, no later than the 

applicable date in the “Compliance section” will be eligible to receive replacements 

parts on a “free of charge basis”, with the exception of consumable materials. 
B.T. 139-311 Rev. B

Page 3 of 37

NOTE: Customers who fail to comply with the instructions in this bulletin before the 

compliance date are not eligible for the aforementioned special

 Please destroy locally the removed parts.

REQUIRED MATERIALS

The following materials, necessary to comply with part II of this Bollettino Tecnico, must 

be requested to AgustaWestland:

P/N DESCRIPTION Q.TY NOTE

3G5306P47211 SUBFLOOR FRAME STA2105 RETROMOD Ref

Composed of:

3G5306P47251 Shim 1

3G5331A45851 Profile RH 1

3G5331A45951 Profile LH 1

3G5331A46051 Reinforcement 2

3G5331A46152 Central Reinforcement 1 (1)

3G5331A46252 Central Profile 1

3G0203R10511 SUBFLOOR FRAME STA2105 REPAIR Ref (2)

Composed of:

3G5331A46451 Shim 2 (2)

3G5331A46551 Doubler 2 (2)

3G5331A46651 Doubler 1 (2)

MS21069L4 Nut, self-locking, plate 6

MS21071L4 Nut, self-locking, plate 2

NAS6604H9 Bolt 4

Moreover, the following consumable materials are necessary to comply with part II of this 

Bollettino Tecnico:

SPEC./AW Code Number DESCRIPTION Q.TY NOTE

MS20427M4-5 Rivet, solid AR Local supply
B.T. 139-311 Rev. B

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SPEC./AW Code Number DESCRIPTION Q.TY NOTE

MS20427M4-7 Rivet, solid AR Local supply

MS20470AD4-4 Rivet, solid AR Local supply

MS20470AD4-5 Rivet, solid AR Local supply

MS20470AD4-6 Rivet, solid AR Local supply (2)

MS20615-4M3 Rivet, solid AR Local supply

MS20615-4M5 Rivet, solid AR Local supply

MS20615-4M6 Rivet, solid AR Local supply

NAS1097AD4-4 Rivet, solid AR Local supply

NAS9301B-4-02 Rivet, blind AR Local supply

NAS9301B-4-03 Rivet, blind AR Local supply (3)

NAS9301B-4-04 Rivet, blind AR Local supply

NAS9301B-5-05 Rivet, blind AR Local supply

NAS9303B-4-03 Rivet, blind AR Local supply (2)

NAS9307M-4-02 Rivet, blind AR Local supply

NAS9307M-4-03 Rivet, blind AR Local supply (2)

NAS9307M-4-04 Rivet, blind AR Local supply

NAS9308M-4-03 Rivet, blind AR Local supply

MS20426AD3-6 Rivet AR Local supply

MS20426AD3-7 Rivet AR Local supply

MS20426AD4-4 Rivet AR Local supply

199-05-004 Ty. II Cl. B-2

MIL-S-8802

cod. 900001586

Sealant, Proseal 890B2

(C153)

AR

199-05-002 Ty. I Cl. 2

cod. 900000581

Adhesive, Epoxy, 

EA9309NA (C231)

AR (2)

TT-M-261 Solvent, Methyl-ethyl-ketone 

(MEK) (C005)

AR (2)

Notes

(1) May be supplied with productive P/N 3G5331A46152A.
B.T. 139-311 Rev. B

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(2) Required only if cracks are found performing inspection described in part I of this 

Bollettino Tecnico or if reinforcements/doublers had been previously applied 

according to ASRP or repair drawings.

(3) Rivet P/N NAS9301BNS-4-03 may be supplied as an alternative.

SPECIAL TOOLS

The following special tools are necessary to accomplish this Bollettino Tecnico:

Part I

P/N DESCRIPTION Q.TY NOTES

Local supply Flashlight 1

Part II

P/N DESCRIPTION Q.TY NOTES

3G0705G00232 or

an approved alternative

Jack, hydraulic

(HA-01-00)

4

WEIGHT AND BALANCE CHANGES

Compliance with part II of this Bollettino Tecnico has the following effect on weight and 

balance:

P/N WEIGHT ARM MOMENT

3G5306P47211

Subfloor frame 

STA2105 retro-mod

0.689 Kg 2120 mm 1460.7 Kgmm

3G0203R10511

Subfloor frame 

STA2105 repair

0.877 Kg 2117 mm 1856.6 Kgmm

(1)

Notes:

(1) Weight and balance data of the repair already cover also the retromod application.

REFERENCES

 AW139 Aircraft Material Data Information (AMDI)

 AW139 Aircraft Maintenance Publication (AMP)
B.T. 139-311 Rev. B

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 AW139 Aircraft Structural Repair Publication (ASRP)

 AW139 Illustrated Tools and Equipment Publication (ITEP)

PUBLICATIONS AFFECTED

 AW139 Illustrated Parts Data (IPD)

COMPLIANCE INSTRUCTIONS:

Part I

1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and all 

the electrical power sources and/or the external power supply. Refer to AMP, see 

DM n° 39-A-00-20-00-00A-120A-A.

2. With reference to figures 1 and 2, to get access to the area shown in figures 10 and 

11, remove/open access doors/panels that follow:

NOTE

With reference to figure 2, it is possible to remove 

access panels 131AL (6) and 132AR (5) without 

removing the LH sheet skin assy (7) and the RH 

sheet skin assy (3) or the FWD float assemblies 

(where installed), just removing screws (4).

 access panel 130AL;

 access panel 131AL;

 access panel 132AR.

Refer to AMP, see DM n° 39-A-06-41-00-00A-010A-A.

3. With reference to figures 1, do a visual inspection for cracks of the subfloor frames at 

STA 2105 (LH frame, middle frame and RH frame, shown in figures 1 and 10 thru 

13), from both sides (front and rear), using a flashlight.

3.1 If no cracks are found, go to step 4.
B.T. 139-311 Rev. B

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3.2 If cracks are found, contact Product Support Engineering

(aw139.mbx@agustawestland.com) to report about the inspection findings and 

perform Part II of this Bollettino Tecnico.

4. Return helicopter to flight configuration and record for compliance with part I of this 

Bollettino Tecnico on the helicopter logbook.

Part II

1. Prepare the helicopter for a safe ground maintenance. Disconnect the battery and all 

the electrical power sources and/or the external power supply. Refer to AMP, see 

DM n° 39-A-00-20-00-00A-120A-A.

2. Remove from the cockpit, to get access to the area shown in figures 10 and 11, the 

elements that follow:

 cockpit equipments, liners, floor panels as necessary.

 the pilot pedal set. Refer to AMP, see DM n° 39-A-67-21-01-00A-520A-A.

 the copilot pedal set. Refer to AMP, see DM n° 39-A-67-21-02-00A-520A-A.

3. With reference to figure 3, remove the LH and RH nose windows. Hold the hardware 

for further re-use.

CAUTION

Be careful when you remove the central panel at 

step 4. There are studs and clamps fixing cables to 

the panel. Make sure to disconnect studs and clamps 

before pulling down the central panel.

4. With reference to figure 1, remove the central panel from the helicopter.

5. With reference to figures 1 and 2, remove from the helicopter the elements that 

follow:

NOTE

It is possible to remove access panels 131AL (6) and 

132AR (5) without removing the LH sheet skin assy 

(7) and the RH sheet skin assy (3) or the FWD float 
B.T. 139-311 Rev. B

Page 8 of 37

assemblies (where installed), just removing screws 

(4).

 the access panel 131AL. Refer to AMP, see DM n° 39-A-06-41-00-00A-010A-A.

 the access panel 132AR. Refer to AMP, see DM n° 39-A-06-41-00-00A-010A-A.

 the control rod Y2. Refer to AMP, see DM n° 39-A-67-21-03-00A-520A-A.

 the control rod Y3. Refer to AMP, see DM n° 39-A-67-21-04-00A-520A-A.

 the bellcrank Y2-Y3. Refer to AMP, see DM n° 39-A-67-21-05-00A-520A-A.

 the control rod Y4. Refer to AMP, see DM n° 39-A-67-21-06-00A-520A-A.

NOTE

Nose landing gear removal at following step 6 is 

optional. It is possible to apply Subfloor Frame 

STA2105 Retro-Mod P/N 3G5306P47211 with the 

nose landing gear installed, provided that the 

helicopter is lifted on jacks and that operators adjust 

nose landing gear position while installing central 

reinforcement P/N 3G5331A46152 and central profile 

P/N 3G5331A46251 at steps 7.5 and 7.6. To lift the 

helicopter on jacks, refer to AMP, see data module 

n° 39-A-07-11-00-00A-000A-A.

With reference to figure 19, it is also allowed to 

remove AFT channel to get an easier access to the 

work area. In this case, use rivets P/N 

NAS1097AD4-4 to re-install AFT channel.

6. Remove the nose landing gear, if required, to get an easier access to the work area. 

Refer to AMP, see DM n° 39-A-32-21-01-00A-520A-A or DM n° 39-A-32-21-01-00A520B-A.

WARNING

THE MATERIALS THAT FOLLOW ARE 

DANGEROUS. BEFORE YOU PERFORM STEP 7 

MAKE SURE THAT YOU KNOW ALL THE SAFETY 

PRECAUTIONS AND FIRST AID INSTRUCTIONS 

FOR THESE MATERIALS:

 METHYL-ETHYL-KETONE (C005);

 PROSEAL 890B2 (C153);
B.T. 139-311 Rev. B

Page 9 of 37

 ADHESIVE (C231).

REFER TO AMDI, SEE DM N° 39-A-00-50-00-00A074A-D.

NOTE

As an alternative to rivets indicated in step 7 and in 

related figures, it is allowed to use high lock pins with 

related collars. Refer to ASRP (Section 51-40) for 

details about hi-locks installation preparation.

NOTE

Figures 4 thru 9 show how to apply 

reinforcement/doublers on areas where cracks have 

been found. Figures 20 and 21 show subfloor frame 

STA 2105 after retro-mod installation.

NOTE

Productive P/N may be supplied with pilot holes or 

without holes in order to allow a field countermark 

action before finale riveted installation.

7. With reference to figures 4 thru 21, apply Subfloor Frame STA2105 Retro-Mod P/N 

3G5306P47211 as follows:

NOTE

If reinforcements/doublers had been previously 

applied, according to ASRP or repair drawings, in the 

areas concerning this modification, remove them 

before proceeding with following step 7.1.

7.1. With reference to figure 12, remove existing rivets and self-locking nuts from 

RH frame in indicated positions.

7.2. With reference to figures 12 and 15, install reinforcements on RH frame as 

follows:

NOTE

Following steps 7.2.1 and 7.2.2 are applicable only if

cracks have been found on RH frame (STA2105).

7.2.1. Perform cut-out of the affected area according to figure 7 and to figure 

9 section D-D.
B.T. 139-311 Rev. B

Page 10 of 37

NOTE

It is allowed to use a peeling shim at following step 

7.2.2 if it is necessary to ensure the flat surface.

7.2.2. Put in position shim P/N 3G5331A46451 and doubler P/N 

3G5331A46551 on RH profile P/N 3G5331A45851 according to figure 

8 and to figure 9 section E-E.

7.2.3. Install RH profile P/N 3G5331A45851 using Proseal 890B2 (C153). Fix 

it to the frame (STA 2105) with rivets P/N MS20470AD4-4 and P/N 

NAS9301B-5-05 according to figure 12 and with rivets P/N NAS9301B5-04, P/N NAS9301B-5-05 and P/N NAS9301B-5-06 according to 

figure 16.

NOTE

Performing following step 7.2.4, make sure to put

reinforcement P/N 3G5331A46051 in position to drill

the lateral holes at the same distance from both 

sides. The dimensions indicated in figure 12 are for 

reference only.

7.2.4. Install reinforcement P/N 3G5331A46051 using rivets P/N 

MS20470AD4-5 according to figure 12 and rivets P/N NAS9301B-4-02

according to figure 15.

7.2.5. With reference to figure 12, install self-locking nuts P/N MS21069L4

according to existing holes on the structure, using rivets P/N

MS20426AD3-6.

7.3. With reference to figure 13, remove existing rivets and self-locking nuts from 

LH frame in indicated positions.

7.4. With reference to figures 14 and 15, install reinforcements on LH frame as 

follows:

NOTE

Following steps 7.4.1 and 7.4.2 are applicable only if

cracks have been found on LH frame (STA2105).
B.T. 139-311 Rev. B

Page 11 of 37

7.4.1. Perform cut-out of the affected area according to figure 7 and to figure 

9 section D-D.

NOTE

It is allowed to use a peeling shim at following step 

7.4.2 if it is necessary to ensure the flat surface.

7.4.2. Put in position shim P/N 3G5331A46451 and doubler P/N 

3G5331A46551 on LH profile P/N 3G5331A45951 according to figure 8

and to figure 9 section E-E.

7.4.3. Install LH profile P/N 3G5331A45951 using Proseal 890B2 (C153). Fix 

it to the frame (STA 2105) with rivets P/N MS20470AD4-4 and P/N 

NAS9301B-5-05 according to figure 14 and with rivets P/N NAS9301B5-04, P/N NAS9301B-5-05 and P/N NAS9301B-5-06 according to 

figure 16.

NOTE

Performing following step 7.4.4, make sure to put 

reinforcement P/N 3G5331A46051 in position to drill 

the lateral holes at the same distance from both 

sides. The dimensions indicated in figure 14 are for 

reference only.

7.4.4. Install reinforcement P/N 3G5331A46051 using rivets P/N 

MS20470AD4-5 according to figure 14 and rivets P/N NAS9301B-4-02 

according to figure 15.

7.4.5. With reference to figure 14, install self-locking nuts P/N MS21069L4

according to existing holes on the structure, using rivets P/N

MS20426AD3-6.

NOTE

If nose landing gear has not been removed at step 6, 

adjust its position as required, while performing

following steps 7.5 and 7.6.

7.5. With reference to figure 17, remove existing omega shape P/N 3P5331A47152 

and related rivets and self-locking nuts.
B.T. 139-311 Rev. B

Page 12 of 37

7.6. Install on middle frame P/N 3P5331A05531 central reinforcement P/N 

3G5331A46152 and central profile P/N 3G5331A46252, as follows:

7.6.1. With reference to figures 17 and 18, remove the cover, cut it and 

rework it as shown to move the self-locking nut in the new position.

Seal the existing self-locking nut hole using Proseal 890B2 (C153).

NOTE

Following steps 7.6.2 thru 7.6.4 are applicable only if

cracks have been found on middle frame (STA2105).

7.6.2. Make a stop drill at both ends of the crack.

7.6.3. Clean with Methyl-Ethyl-Ketone (C005).

7.6.4. Put in position doubler P/N 3G5331A46651 according to figure 6 and to 

figure 4 section F-F and countermark holes position for self-locking 

nuts and rivets installation, from the middle frame on the doubler. Drill 

6.50-6.65 mm diameter holes on the doubler.

7.6.5. Put in position reinforcement P/N 3G5331A46152 and central profile 

P/N 3G5331A46252 according to figures 18 and 19.

NOTE

Following steps 7.6.6 and 7.6.7 are applicable only if

cracks have been found on middle frame (STA2105).

7.6.6. Install doubler P/N 3G5331A46651 using adhesive (C231).

7.6.7. Fix the doubler to the middle frame (STA2105) with eight rivets P/N 

NAS9307M4-02 and to the floor with seven rivets P/N MS20470AD4-6.

Seal using Proseal 890B2 (C153) all over the doubler contour.

7.6.8. Fix central profile P/N 3G5331A46252 to the middle frame (STA2105) 

with rivets P/N NAS9307M-4-04 and P/N NAS9307M-4-02 according to 

figures 18 and 21.

NOTE

Performing following step 7.6.9 on helicopters where 

doubler P/N 3G5331A46651 has been installed at 

step 7.6.6, use six rivets P/N NAS9307M-4-03 
B.T. 139-311 Rev. B

Page 13 of 37

instead of P/N MS20427M4-5 to fix the reinforcement 

on the frame and the doubler, according to figure 6.

7.6.9. Fix reinforcement P/N 3G5331A46152 to the middle frame (STA2105) 

and to the central profile with five rivets P/N MS20615-4M6, four rivets 

P/N MS20615-4M5, eight rivets P/N MS20427M4-5, seven rivets P/N 

MS20427M4-7 and five rivets P/N NAS9307M-4-04, using existing 

holes according to figures 18, 19 and 21.

7.7. With reference to figure 18, install self-locking nuts on the central reinforcement 

as follows:

7.7.1. Drill 6.50-6.65 mm diameter holes on central reinforcement according 

to existing holes on the longeron.

NOTE

On helicopters where doubler P/N 3G5331A46651 

has been installed at step 7.6.6, use P/N 

MS20426AD3-7 instead of P/N MS20426AD3-6 to 

install self-locking nuts at following steps 7.7.2 and 

7.7.3.

7.7.2. Install two self-locking nuts P/N MS21069L4 using rivets P/N 

MS20426AD3-6.

7.7.3. Install two self-locking nuts P/N MS21071L4 using rivets P/N 

MS20426AD3-6.

7.8. With reference to figure 19 and 21, fix central profile P/N 3G5331A46251 on 

the AFT channel using rivets P/N NAS9308-M-4-3 and on the middle lower 

panel using rivets P/N MS20427M4-5.

7.9. Install reworked cover P/N 3G5306P47253 on the middle frame and install 

removed self-locking nuts P/N MS21069L08 using rivets P/N MS20426AD3-6 

according to figure 18.

7.10.On helicopters where doubler P/N 3G5331A46651 has been installed, install 

also self-locking nuts P/N MS21069L08K using two rivets P/N MS20426AD3-6, 

according to figure 6.
B.T. 139-311 Rev. B

Page 14 of 37

8. Install the nose landing gear, if you have removed it at step 6. Refer to AMP, see DM 

n° 39-A-32-21-01-00A-720A-A or DM n° 39-A-32-21-01-00A-720B-A.

9. Install on the helicopter the elements that follow:

 the bellcrank Y2-Y3. Refer to AMP, see DM n° 39-A-67-21-05-00A-720A-A.

 the control rod Y2. Refer to AMP, see DM n° 39-A-67-21-03-00A-720A-A.

 the control rod Y3. Refer to AMP, see DM n° 39-A-67-21-04-00A-720A-A.

 the control rod Y4. Refer to AMP, see DM n° 39-A-67-21-06-00A-720A-A.

10. Install in the cockpit the elements that follow:

NOTE

To install pilot/copilot pedal set on the frame portion 

where reinforcement have been added, use bolts 

P/N NAS6604H9 instead of the old ones (P/N 

NAS6604H7).

 the pilot pedal set. Refer to AMP, see DM n° 39-A-67-21-01-00A-720A-A.

 the copilot pedal set. Refer to AMP, see DM n° 39-A-67-21-02-00A-720A-A.

11. Install the central panel using hardware shown in figure 22.

12. Install other access panels, floor panels, liners and equipments removed at step 2 

and step 5.

13. With reference to figure 3, install the LH and RH nose windows as follows:

13.1.Install the LH nose window (1) using twenty-seven screws (2) P/N MS27039-1-

10 and four screws (4) P/N MS27039-1-9 (in the corners) with washers (3).

13.2.Install the RH nose window (5) using twenty-seven screws (6) P/N MS27039-1-

10 and four screws (8) P/N MS27039-1-9 (in the corners) with washers (7).

WARNING

THE PROSEAL 890B2 (C153) IS DANGEROUS. 

MAKE SURE THAT YOU KNOW ALL THE SAFETY 

PRECAUTIONS AND FIRST AID INSTRUCTIONS 

FOR THIS MATERIAL. REFER TO AMDI, SEE DM 

N° 39-A-00-50-00-00A-074A-D.
B.T. 139-311 Rev. B

Page 15 of 37

13.3.Seal the head of the screws and the contour of the nose windows with Proseal 

890B2 (C153).

14. In accordance with weight and balance changes, update the Chart A (see Rotorcraft 

Flight Manual, Part II, section 6).

15. Return helicopter to flight configuration and record for compliance with part II of this 

Bollettino Tecnico on the helicopter logbook.
B.T. 139-311 Rev. B

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Figure 1
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Figure 2
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Figure 3
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Figure 4
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Figure 5
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Figure 6
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Figure 7
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Figure 8
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Figure 9
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Figure 10
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Figure 11
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Figure 12
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Figure 13
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Figure 14
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Figure 15
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Figure 16
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Figure 17
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Figure 18
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Figure 19
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Figure 20
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Figure 21
B.T. 139-311 Rev. B

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Figure 22

Note: 

Remarks:

Informazioni: 

Information:

Al fine di gestire le varianti alla configurazione base, in relazione all’emissione del Bollettino Tecnico, preghiamo di voler compilare il presente modulo in tutte le sue parti e spedirlo all’indirizzo sopra indicato. Si ringrazia per la gentile collaborazione data. 

We request your cooperation in filling this form, in order to keep out statistical data relevant to aircraft configuration up-to-date. The form should be filled in all 

its parts and sent to the above address. We thank you beforehand for the information given.

MODULO APPLICAZIONE BOLLETTINO TECNICO

TECHNICAL BULLETIN COMPLIANCE FORM

Data: 

Date:

Numero: 

Number:

Revisione: 

Revision:

Prego spedire a questo indirizzo: 

Please send to the following address: 

AGUSTAWESTLAND S.p.A. 

CUSTOMER SUPPORT & SERVICES - ITALY

PRODUCT SUPPORT ENGINEERING DPT.

Via del Gregge, 100

21015 Lonate Pozzolo (VA) - ITALY 

Tel.: +39 0331 664905

Fax: +39 0331 664684

Telefono: 

Telephone:

Fax:

Data Applicazione B.T.: 

B.T. Compliance Date:

Denominazione Cliente ed Indirizzo: 

Customer Name and Address:

Modello Elicottero 

Helicopter Model S/N Matricola Tail Number

Ore Totali 

Total Hours

Ore D.U.R. 

T.S.O.