Leonardo ASB 189-237: Revision A

N° 189-237 DATE: May 29, 2019 REV. : A - September 5, 2019 Page 1 of 48 TITLE ATA 64 - TAIL ROTOR FLIGHT CONTROL IMPROVED PERIODICAL INSPECTION

REVISION LOG Revision A of this Service Bulletin cancels and supersedes the previous Revision /.

Revision A is issued in order to introduce the following changes:

• Update the “Compliance” section clarifying the note relevant to accomplishment of Part VI.

• Provide instruction to remove the castellated nut in pl ace of loosen it while performing the replacement of the TR duplex bearing.

• Add closure action in case of findings after accomplishment with Part VI step 3.

• Add cleaning instruction of the TR duplex bearing area in Part V before installation of the spider plug.

• Add details to cleaning procedure of spacer control rod surface with aliphatic naphtha.

• Add use of a borescope as alternative mean to perform i nspection of Part I, in such case the removal of the access panels 495A and 496A is not required.

• In case of no-findings after the inspections, it is not required anymore to send feedback to LHD.

• Add HUMS data download in case TRA HUMS accelerometer h as been already installed to helicopter.

• Update the reference to Annex A - UTC Microtecnica Service Bulletin 67-0006 Issue 1.

Leonardo S.p.A.

Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) Italy Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595 An appropriate entry should be made in the aircraft log book upon accomplishment.

If ownership of aircraft has changed, please, forward to new owner.

EMERGENCY ALERT

SERVICE BULLETIN

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 2 of 48 REVISION: A - September 5, 2019 Revision bars in the margins identify changes.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 3 of 48

1. PLANNING INFORMATION A. EFFECTIVITY Part I: All AW189 helicopters.

Part II: All AW189 helicopters.

Part III: All AW189 helicopters.

Part IV: All AW189 helicopters.

Part V: All AW189 helicopters.

Part VI: All AW189 helicopters.

B. COMPLIANCE Part I:

Within 10 FH from last application of Part I of SB 18 9-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH.

NOTE Every time it is required to perform Part II, accomplishment of Part I, Part IV and Part V on the same maintenance downtime, must be performed as a prerequisite.

If Part III is required in the same maintenance downtime, it shall be performed last.

Part II:

Within 50 FH from last application of Part II of SB 1 89-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 50 FH.

Part III:

Within 20 FH from last application of Part III of SB 189-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the installation every 20 FH.

Part IV:

Within 10 FH from last application of Part IV of SB 1 89-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH.

NOTE Perform as a prerequisite Part I and Part IV.

If Part III is required in the same maintenance downtime, it shall be performed lastly.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 4 of 48 REVISION: A - September 5, 2019 Part V:

Within 10 FH from last application of Part I of SB 18 9-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH.

NOTE

• After the first accomplishment of Part VI repeat Part VI phased with Part II, not exceeding 200FH from the first application of the Part VI.

Then repeat every 200FH.

• Perform in sequence Part I, Part IV, Part V as a prerequisite.

• If Part II is required in the same maintenance downtime, it shall be performed after Part V and before Part VI.

• If Part III is required in the same maintenance downtime, it shall be performed after Part VI.

Part VI:

Within 10 FH from last application of Part I of SB 18 9-224 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 200 FH.

C. CONCURRENT REQUIREMENTS This SB supersedes and replaces the SB 189-224.

D. REASON This Service Bulletin is issued in order to require the periodical inspection of the slippage marking of the back-end castellated nut of th e TR servo-actuator and the periodical detailed inspection of the TR duplex bearing.

E. DESCRIPTION Following additional tests and the completion of the i nitial phase of the in service monitoring carried out on the AW169 and AW189 fleet, it has been confirmed that the introduction of a temperature monitoring represents a n effective independent measure to confirm the health of the TR bearing. In addition a refinement of the current inspection schedule is required with this SB along with the introduction of an additional instruction for duplex bearing roughness check.

This Service Bulletin provides the instructions for the above together with the transition to the new inspection regime.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 5 of 48 In details Part I of this Service Bulletin provides th e periodical detailed inspection of the slippage marking of the castellated nut installed on the back end of the TRA.

Part II partly retains the requirement of the Part I I of the SB 189-224 defining the required detailed inspection requirement of TR duplex bearing.

Part III provides the instructions to install a dedicated thermal strip in the area of the TR duplex bearing.

Part IV provides the instructions to recursively check the thermal strip.

Part V requires the verification of metallic particle presence in the grease that could be found on the visible part of the duplex bearing. Thi s check was already present in the Part II of the SB 189-224 and it is now confirmed with a tighter compliance.

Part VI prescribe an additional roughness check of the duplex bearing to be performed after removal of the spider assembly.

Incorrect installation of the TR servo-actuator back-end nut or seizure of the TR duplex bearing may lead to loss of Tail Rotor control which, depending on the flight condition, could lead to loss of control of the aircraft.

Feedback on the compliance to this Service Bulletin is required.

Revision A of this Service Bulletin allows the simplif ication of Part I inspection and reduce the amount of feedback required after “no-findings” inspections.

F. APPROVAL The technical content of this Service Bulletin is approve d under the authority of DOA nr. EASA.21.J.005. For helicopters registered under oth er Aviation Authorities, before applying the Service Bulletin, applicable Aviation Auth ority approval must be checked within Leonardo Helicopters customer portal.

E.A.S.A. states mandatory compliance with inspections, mod ifications or technical directives and related time of compliance by means of rel evant Airworthiness Directives.

If an aircraft listed in the effectivity embodies a m odification or repair not LHD certified and affecting the content of this Service Bulletin, it is responsibility of the Owner/Operator to obtain a formal approval by Aviation Authority having jurisdiction on the aircraft, for any adaptation necessary before incor poration of the present Service Bulletin.

G. MANPOWER To comply with this Service Bulletin the following MMH are deemed necessary:

Part I: approximately one (0.5);

Part II: approximately three (3);

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 6 of 48 REVISION: A - September 5, 2019 Part III: approximately half (0.5);

Part IV: approximately one (1).

Part V: approximately one (0.5);

Part VI: approximately three (3);

MMH are based on hands-on time and can change with per sonnel and facilities available.

H. WEIGHT AND BALANCE N.A.

I. REFERENCES

1) PUBLICATIONS

DATA MODULE DESCRIPTION PART DM01 89-A-00-20-00-00A-120A-A Helicopter on ground f or a safe maintenance.

I, II; III,

IV, V, VI DM02 89-A-06-41-00-00A-010A-A Access door provision I, II DM03 89-A-64-31-01-00A-520A-A Pitch link - Remove pro cedure II DM04 89-A-64-31-01-00A-720A-A Pitch link - Install pr ocedure II, IV, V, VI DM05 89-A-64-31-03-00A-520A-A Spider plug - Remove procedure II, III, IV,V DM06 89-A-64-31-03-00A-720A-A Spider plug - Install procedure II, III, IV, V DM07 89-A-64-31-02-00A-520A-A Scissors group – Remove procedure II DM08 89-A-64-31-04-00A-520A-A Spider and slider assemb ly - Remove procedure II, VI DM09 89-A-64-31-04-00A-720A-A Spider and slider assemb ly - Install procedure II, VI DM10 89-A-64-31-05-00A-520A-B Duplex bearing - Remo ve procedure

II, IV, V, VI DM11 89-A-64-31-05-00A-720A-B Duplex bearing - Insta ll procedure II, IV, V, VI

2) ACRONYMS SB Service Bulletin DM Data Module DOA Design Organization Approval EASA European Aviation Safety Agency LHD Leonardo Spa Helicopters

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 7 of 48 MMH Maintenance Man Hours SB Service Bulletin FH Flight Hours TR Tail Rotor TRA Tail Rotor Actuator

3) ANNEX Annex A UTC AEROSPACE SYSTEMS SB 67-0006 Issue 1.

J. PUBLICATIONS AFFECTED N.A.

K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 8 of 48 REVISION: A - September 5, 2019

2. MATERIAL INFORMATION A. REQUIRED MATERIALS

1) PARTS Refer to AW189 IPD for the spares materials required t o comply with the AMP DMs referenced in the accomplishment instructions.

2) CONSUMABLES The following consumable materials, or equivalent, are necessary to accomplish this Service Bulletin:

# Spec./LHD code number DESCRIPTION Q.TY NOTE PART 1 Thermax 8 Level strip indicator code No.26805 Thermal strip AR (1)(2)(3) III,IV 2 TT-N-95-B / Code No. 531055030 Aliphatic Naphtha (C059) AR (1) III,IV

Refer to AW189 AMDI for the consumables required to com ply with the AMP DMs referenced in the accomplishment instructions.

3) LOGISTIC MATRIX N.A.

NOTE

(1) Item to be furnished as local supply.

(2) Thermal strip Thermax 5 Level clock style indicat or code No.26004 may be used as a valid alternative.

(3) The use of further alternative strip is allowed pr ovided that it complies with the following requirements:

• Irreversible temperature indication.

• Self-Adhesive.

• Temperature Range shall be included within 100°C – 1 60°C provided that it shows a discrete level at 121±2°C.

• Overall measurement accuracy: ±2°C.

• The maximum allowed length to prevent overlap is 80 mm.

In case any clarification is needed, contact the Product S upport Engineering (pse_aw189.mbx.aw@leonardocompany.com).

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 9 of 48 B. SPECIAL TOOLS Refer to ITEP for the special tools required to comply with the AMP DMs referenced in the accomplishment instructions.

C. INDUSTRY SUPPORT INFORMATION Owners/Operators who comply with the instructions of this Service Bulletin no later than the applicable date in the “Compliance” section wi ll be eligible to receive REQUIRED MATERIALS on free of charge basis, except for Consumable Materials and Special Tools.

NOTE: Customers who fail to comply with the instruction s in this Service Bulletin before the compliance date are not eligible for the aforementioned special policy.

Please Issue relevant MMIR form to your Warranty Administration Dpt.

NOTE: WRM will include RETURN MATERIAL AUTHORIZATION (RMA) number; the unit disembarked from the aircraft has to be returned to LHD within thirty (30) calendar days after the shipment of the replacement part. In case of missing return within thirty

(30) calendar days, Customer will be invoiced for the price of the replacement part.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 10 of 48 REVISION: A - September 5, 2019

3. ACCOMPLISHMENT INSTRUCTIONS

GENERAL NOTES

a) Place an identification tag on all components that are re-usable, including the attaching hardware that has been removed to gain access to the modification area and adequately protect them until their later re-use.

PART I

1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply.

NOTE Removal of access panels 496A and 495A can be avoided if visual access to the inspection area is available by other means. A suitable boroscope can be inserted in the grid of access panel 496A as shown on Figure 3.

2. In accordance with AMP DM 89-A-06-41-00-00A-010A-A, remove the access panels 496A and 495A.

3. Take a picture of the back-end area of the TRA clear ly showing the slippage mark, and keep a record in a local archive to be made available if required.

4. With reference to Figure 3, check the slippage mark o n the castellated nut for absence of evidence of rotation between the parts. Record the result on Table I (refer to Figure

7).

5. If any evidence of rotation is found, contact the Pr oduct Support Engineering (pse_aw189.mbx.aw@leonardocompany.com), wait for further instructions before to perform the following checks:

5.1 Perform Part II of this SB;

5.2 Perform Part V of this SB;

5.3 Send the picture taken at step 3 to Product Suppo rt Engineering (pse_aw189.mbx.aw@leonardocompany.com).

5.4 If the helicopter is already compliant with the SB 189-227, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 REVISION: A - September 5, 2019 Page 11 of 48

6. If no evidence of rotation is found in step 4, ret urn the helicopter to a ready to flight condition and record for compliance with Part I of this Service Bulletin on the helicopter logbook.

7. Send the attached compliance form and the compiled T able I to the following mail box:

pse_aw189.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”.

S.B. N°189-237 EMERGENCY ALERT DATE: May 29, 2019 Page 12 of 48 REVISION: A - September 5, 2019

PART II

1. In accordance with AMP DM 89-A-00-20-00-00A-120A-A, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, a ll electrical power sources and/or the external power supply.

2. In accordance with AMP DM 89-A-64-31-03-00A-520A-A, remove the spider plug.

3. In accordance with AMP DM 89-A-64-31-01-00A-520A-A, remove all the pitch links from the TR.

4. In accordance with applicable steps of AMP DM 89-A-64- 31-02-00A-520A-A, disconnect the upper half scissors from the spider.

5. Remove and discard the strap that attach the boot to the spider and slider assembly.

Disconnect and lower the boot from the spider.

6. Perform the inspection of the TR duplex bearing in accordance with the following procedure:

6.1 Inspect the visible part of the TR duplex bearing (including the seals) for absence of wear, damages and security of attachment. Record the results on Table II (refer to Figure 8).

6.2 Check for absence of axial play when trying to move t he spider along the control rod axis. Record the result on Table II (refer to Figure 8).

NOTE With reference to Figure 1 and Figure 2 Details B and C, apply a 35 ± 2.5 N upward force on the squared ro d end by means of a dynamometer while performing the instructions reported in steps from 6.3 to 6.7. It is allowed to apply the force either pushing or pulling the rod end with the dynamometer.

6.3 Perform at least three (3) complete and continuous revolutions of the spider both in clockwise and in counterclockwise directions and verify that the spider has a free and easy rotation. Record the result on Table II (refer to Figure 8).

6.4 Put one arm of the spider along the vertical posit ion; locate a dynamometer gauge on the spider arm hole (pitch link upper bolt l ocation). Hold the gauge perpendicular to the spider arm surface. Gently push ri ghtward the device until a slight rotation of the spider occurs (see Figure 2 for fu rther details and dynamometer positioning). Record the force measured on Table II (refer to Figure 8).

6.5 Repeat step 6.4 for the opposite spider rotation o n the same arm, pushing leftward the dynamometer gauge from the vertical posi tion of the spider arm.