## BOLLETTINO TECNICO N° 

# 139 -3 11

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 RETROMOD IFICATION 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.

## 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 prov ides 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 th e introduction of the reinforcements. These retromodifications have been already introduced on new build aircraft. R evision A introduces some changes to the installation fixing hardware re lated 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 I t 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 ( 2 40 ) 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 T he 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 RETRO MOD 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

Page 4 of 37 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 890 B2 (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

Page 5 of 37 (2) R equired 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 T he following special tools are necessary to accomplish this Bolle ttino Tecnico :
Part I P/N DESCRIPTION Q.TY NOTES Local supply Flashlight 1
Part II P/N DESCRIPTION Q.TY NOTES 3G0705G00232 or a n approved a lternative Jack, hydraulic ( HA

- 01

- 00) 4

WEIGHT AND BALANCE CHANGES C ompliance 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 r e pair 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

Page 6 of 37  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 figure s 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 t o 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 figure s 1, d o a visual inspection for cracks of the subfloor frames at STA 2105 (LH fr ame, 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

Page 7 of 37 3.2 If cracks are found, contact Product Support Engineering ( aw13 9

. mbx@agustawestland.com ) to report about the inspection findings and perform Part II of this Bollettino Tecnico

. 4. Return helicopter to flight configuratio n 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

.  t he pilot pedal set. Refer to AM P, 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 , r emove 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 fig ure s 1 and 2, r emove from the helicopter the elements that follow:
NOTE

I t 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 rein forcement P/N 3G5331A46152 and central profile P/N 3G5331A46251 at step s 7 .5 and 7

. 6

. To lift the helicopter on jacks, r efer 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

- 2 1

- 01

- 00A

520B

- 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 - 00A 074A - D

. NOTE As an alternative to rivets indicated in step 7 and in related figures, it is allowed to use high lock pins wit h 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. Figure s 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 2 1 , 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 1 2 , remove existing rivets and self

- locking nuts from RH frame in indicated positions

. 7.2. With reference to figure s 1 2 and 1 5 , install reinforcements on RH frame as follows:
NOTE

Following steps 7 .2.1 and 7 .2.2 are applicable only if cracks have b een 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. P ut in position shim P/N 3G5331A4645 1 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 1 2 and with rivets P/N NAS9301B

5

- 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 i n position to drill the lateral holes at the same distance from both sides. The dimension s indicated in figure 1 2 are for reference only. 7.2.4. Install reinforcement P/N 3G5331A46051 using rivets P/N MS20470AD4

- 5 according to figure 1 2 and rivets P/N NAS9301B

- 4

- 02 according to figure 1 5

. 7.2.5. With reference to figure 12 , i nstall 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 1 3 , remove existing rivets and self

- locking nuts from LH frame in indicated positions.
7.4. With reference to figures 1 4 and 1 5 , install reinforcements on L H frame as follows:
NOTE

Following steps 7 .4.1 and 7 .4.2 are applicable only if cracks have b een 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 L H 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 1 4 and with rivets P/N NAS9301B

5

- 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 dimension s indicated in figure 14 are for reference only. 7.4.4. Install reinforcement P/N 3G5331A460 51 using rivets P/N MS20470AD4

- 5 according to figure 1 4 and rivets P/N NAS9301B

- 4

- 02 according to figure 1 5

. 7.4.5. With reference to figure 14, i nstall 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 perform ing following step s 7 .5 and 7 .6. 7.5. With reference to figure 1 7 , 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. I nstall on middle frame P/N 3P5331A05531 central reinforcement P/N 3G5331A46152 and central profile P/N 3G5331A4625 2 , as follows:
7.6.1. With reference to figure s 1 7 and 18 , r emove the cover , cut it and rework it as shown to move the s elf

- locking nut in the new position

. Seal the existing self

- locking nut hole using Proseal 890 B2 (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 s top drill at both ends of the crack.
7.6.3. Clean with Methyl

- E thyl

- K etone (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 1 8 and 1 9

. NOTE Following step s 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 NAS930 7M 4

- 0 2 and to the floor with seven rivets P/N MS20470AD4

- 6. S eal using Proseal 890 B2 (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 o n 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 1 8 , install self

- locking nuts on the central reinforcement as follows:
7.7.1. D rill 6.50

- 6.65 mm diameter holes on central reinforcement according to existing holes on the longeron.
NOTE O n helicopters where doubler P/N 3G5331A46 651 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 sel f

- locking nuts P/N MS21071L4 using rivets P/N MS20426AD3

- 6.
7.8. With reference to figure 1 9 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 1 8

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

- locki ng 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

- 7 20A

- A or DM n° 39

- A

- 32

- 21

- 01

- 00A

- 7 20B

- 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 NAS6604H 7)

.  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. I nstall the central panel using hardware shown in figure 2 2

. 12. Install other access panels, floor pane ls, 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 cor ners) 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 win dows 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 Tecnic o on the helicopter logbook

.

## B.T. 139 - 311 Rev. B

Page 16 of 37 Figure 1

## B.T. 139 - 311 Rev. B

Page 17 of 37 Figure 2

## B.T. 139 - 311 Rev. B

Page 18 of 37 Figure 3

## B.T. 139 - 311 Rev. B

Page 19 of 37 Figure 4

## B.T. 139 - 311 Rev. B

Page 20 of 37 Figure 5

## B.T. 139 - 311 Rev. B

Page 21 of 37 Figure 6

## B.T. 139 - 311 Rev. B

Page 22 of 37 Figure 7

## B.T. 139 - 311 Rev. B

Page 23 of 37 Figure 8

## B.T. 139 - 311 Rev. B

Page 24 of 37 Figure 9

## B.T. 139 - 311 Rev. B

Page 25 of 37 Figure 10

## B.T. 139 - 311 Rev. B

Page 26 of 37 Figure 11

## B.T. 139 - 311 Rev. B

Page 27 of 37 Figure 1 2

## B.T. 139 - 311 Rev. B

Page 28 of 37 Figure 1 3

## B.T. 139 - 311 Rev. B

Page 29 of 37 Figure 1 4

## B.T. 139 - 311 Rev. B

Page 30 of 37 Figure 1 5

## B.T. 139 - 311 Rev. B

Page 31 of 37 Figure 16

## B.T. 139 - 311 Rev. B

Page 32 of 37 Figure 1 7

## B.T. 139 - 311 Rev. B

Page 33 of 37 Figure 1 8

## B.T. 139 - 311 Rev. B

Page 34 of 37 Figure 19

## B.T. 139 - 311 Rev. B

Page 35 of 37 Figure 20

## B.T. 139 - 311 Rev. B

Page 36 of 37 Figure 21

## B.T. 139 - 311 Rev. B

Page 37 of 37 Figure 22Note: Remarks:

Informazioni: Information: Al fine di gestire le varianti alla configur azione base, in relazione all’emissione de l Bollettino Tecnico, preghiamo di voler compilare il presente modulo in tutte le sue parti e sped irlo all’indirizzo sopra indicato. Si ring razia 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: 

### AGUSTA **WESTLAND S.p.A.**  CUSTOMER SUPPORT & SERVICES - ITALY PRODUCT SUPPORT ENGINEERING DPT. Via del Gregge, 100 2101 5 Lonate Pozzolo (VA) - I T ALY T el

. : +39 0331 664905 Fa x : +39 0331 66468 4 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.