Leonardo ASB 169-148: Revision B

N° 169-148 DATE: May 29, 2019 REV. : B - February 4, 2020 Page 1 of 36 TITLE ATA 64 - TAIL ROTOR FLIGHT CONTROL IMPROVED PERIODICAL INSPECTION

REVISION LOG Revision B of this Service Bulletin cancels and supersedes all the previous Revisions.

Revision A is issued to:

• Update the “Compliance” section clarifying the note rel evant to accomplishment of Part VI;

• Update cross-reference in Part V step 4;

• 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 are a in Part V before installation of the spider plug

• Add details to cleaning procedure of spacer control rod su rface with aliphatic naphtha

• Add note for accessibility to inspection Area in Part I.

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

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

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°169-148 EMERGENCY ALERT DATE: May 29, 2019 Page 2 of 36 REVISION: B - February 4, 2020

• Update the reference to Annex A - UTC Microtecnica Ser vice Bulletin 67-0006 Issue

1.

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

• Change effectivity for Part I from “All AW 169 hel icopters” to “All AW 169 helicopters equipped with TRA P/N 6F6730V00331”;

• Remove Annex A and all the references to the subject document, as all the relevant information is now enclosed in applicable AMP Data Modules.

Revision bars in the margins identify changes.

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 REVISION: B - February 4, 2020 Page 3 of 36

1. PLANNING INFORMATION A. EFFECTIVITY Part I: All AW169 helicopters equipped with TRA P/N 6F6730V00331.

Part II: All AW169 helicopters.

Part III: All AW169 helicopters.

Part IV: All AW169 helicopters.

Part V: All AW169 helicopters.

Part VI: All AW169 helicopters.

B. COMPLIANCE Part I:

Within 10 FH from last application of Part I of SB 16 9-135 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 lastly.

Part II:

Within 50 FH from last application of Part II of SB 1 69-135 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 169-135 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 Part IV of SB 169- 135 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.

Part V:

Within 10 FH from last application of Part I of SB 16 9-135 or from the issue of this Service Bulletin, whichever occurs first. Then repeat the inspection every 10 FH.

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 Page 4 of 36 REVISION: B - February 4, 2020

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 16 9-135 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 169-135.

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 an 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.

In details Part I of this Service Bulletin provides the periodical detailed inspection of the slippage marking of the castellated nut installed on the back end of the TRA.

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 REVISION: B - February 4, 2020 Page 5 of 36 Part II partly retains the requirement of the Part I I of the SB 169-135 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 169-135 and it is now confirmed with a tighter compliance.

Part VI prescribes an additional roughness check of the d uplex 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);

Part III: approximately half (0.5);

Part IV: approximately one (1);

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 Page 6 of 36 REVISION: B - February 4, 2020 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 69-A-00-20-00-00A-120A-A Helicopter on ground f or a safe maintenance.

I, II, III,

IV, V, VI DM02 69-A-06-40-00-00A-010A-A Access door provision I, II DM03 69-A-64-31-01-00A-520A-A Pitch link - Remove pro cedure II DM04 69-A-64-21-05-00A-520A-A Lightning conductor jum per – Remove procedure II DM05 69-A-64-31-03-00A-520A-A Spider plug - Remove procedure II, III, IV, V, VI DM06 69-A-64-31-03-00A-720A-A Spider plug - Install procedure II, III, IV, V, VI DM07 69-A-64-31-02-00A-520A-A Scissors group – Remove procedure II DM08 69-A-64-31-07-00A-520A-A Boot - Remove procedur e II DM09 69-A-64-31-04-00A-520A-A Sliding control assy – R emove procedure II, VI DM10 69-A-64-31-04-00A-720A-A Sliding control assy – I nstall procedure II, VI DM11 69-A-64-31-05-00A-520A-B Duplex bearing - Remo ve procedure

II, IV, V, VI DM12 69-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°169-148 EMERGENCY ALERT DATE: May 29, 2019 REVISION: B - February 4, 2020 Page 7 of 36 MMH Maintenance Man Hours SB Service Bulletin FH Flight Hours TR Tail Rotor TRA Tail Rotor Actuator

3) ANNEX N.A.

J. PUBLICATIONS AFFECTED N.A.

K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 Page 8 of 36 REVISION: B - February 4, 2020

2. MATERIAL INFORMATION A. REQUIRED MATERIALS

1) PARTS Refer to AW169 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 AW169 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_aw169.mbx.aw@leonardocompany.com).

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 REVISION: B - February 4, 2020 Page 9 of 36 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 instructions 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°169-148 EMERGENCY ALERT DATE: May 29, 2019 Page 10 of 36 REVISION: B - February 4, 2020

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 69-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 470AT and 470BT can be avoided if visual access to the inspection area is available by other means. A suitable borescope can be used for this purpose.

2. In accordance with AMP DM 69-A-06-40-00-00A-010A-A remove the access panels 470AT and 470BT.

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_aw169.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_aw169.mbx.aw@leonardocompany.com).

5.4 If the helicopter is already compliant with the SB 169-140, perform HUMS data download from AMMC to DTD. Upload the HUMS data to Heliwise.

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.

S.B. N°169-148 EMERGENCY ALERT DATE: May 29, 2019 REVISION: B - February 4, 2020 Page 11 of 36

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

pse_aw169.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°169-148 EMERGENCY ALERT DATE: May 29, 2019 Page 12 of 36 REVISION: B - February 4, 2020

PART II

1. In accordance with AMP DM 69-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 If not damaged, the O-ring removed in the following step can be retained for later reinstallation.

2. In accordance with AMP DM 69-A-64-31-03-00A-520A-A, remove the spider plug.

3. In accordance with AMP DM 69-A-64-31-01-00A-520A-A, remove all the pitch links from the TR.

4. In accordance with applicable steps of AMP DM 69-A-64- 31-02-00A-520A-A, disconnect the upper half scissors from the spider.

5. In accordance with applicable steps of AMP DM 69-A-64- 31-07-00A-520A-A, disconnect and lower the boot from the spider.

6. In accordance with AMP DM 69-A-64-21-05-00A-520A-A, disconnect the TR lightning conductor jumper.

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

7.1 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).

7.2 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 View B and Detail C, apply a 25 ± 2.5 N upward force on the squared rod end by means of a dynamometer while performing the instructions reported in steps from 7.3 to 7.7. It is allowed to apply the force either pushin g or pulling the rod end with the dynamometer.

7.3 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).

7.4 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 rig htward the device until a