Leonardo ASB 109EP-168: No revision named

N° 109EP-168 DA TE: June 28, 2019 REV. : / - March 15, 2017 Pa ge 1 of 19 TITLE ATA 32 – INSPECTION OF LH/RH ENHANCED MAIN LANDING GEAR STRUT ASSY P /N 109-0503-45

REVISION LOG New Issue.

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

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

Leonardo S.p.A.

Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) Italy Tel.: +39 0331 229111 - Fax: +39 0331 229605/222595 ALERT

SERVICE BULLETIN

S.B. N°109EP-168 ALERT DATE: June 28, 2019 Page 2 of 19 REVISION: /

1. PLANNING INFORMATION A. EFFECTIVITY NOTE Refer to Figure 1 for LH/RH Wheel Axle P/N and S/N identification.

All the Leonardo S.p.A. A109E helicopters equipped w ith LH/RH Enhanced Main Landing Gear Strut. Assy P/N 109-0503-45-101/-102 which install the LH/RH Wheel Axle with P/N listed in Table 1 and S/N listed in Table 2.

LH/RH Enhanced MLG Strut. Assy P/N LH/RH Wheel Axle P/N 109-0503-45-101 M019-01H003-101 109-0503-45-102 M019-01H003-102 Table 1

LH Wheel Axle P/N M019-01H003-101 RH Wheel Axle P/N M019-01H003-102 from S/N 1 to S/N 146 from S/N 1 to S/N 147 from S/N 152 to S/N 172 from S/N 153 to S/N 173 Table 2 NOTE If a LH/RH Wheel Axle with P/N listed in Table 1 and S/N listed in Table 2 is installed on a MLG strut. assy in stock, attach a copy of this Service Bulletin to its box for future compliance before the MLG strut. assy installation on the helicopter.

B. COMPLIANCE Within and not later than 50 flight hours or 200 landings or 6 months, whichever occurs first, after the issue of this Service Bulletin and subsequently every 12 months.

C. CONCURRENT REQUIREMENTS N.A.

D. REASON This Service Bulletin is issued in order to introduce a periodical inspection of the LH/RH Enhanced Main Landing Gear Strut. Assy P/N 109-0503-45-101/-102.

S.B. N°109EP-168 ALERT DATE: June 28, 2019 REVISION: / Page 3 of 19 E. DESCRIPTION On two A109E helicopter in service, a failure of the RH Main Landing Gear Wheel Assy was reported. Further investigation revealed that the cause of the failure was caused by stress corrosion cracking, enhanced by local presence of hydrogen embrittlement, on the threaded end of the RH Enhanced Main Landing Gear Strut.

Assy P/N 109-0503-45-102, where lack of cadmium plating was observed.

This Service Bulletin is issued with the purpose to provide the necessary instruction to perform a periodical liquid penetrant inspection to verify the presence of cracks on the threaded end of the LH and RH Enhanced Main Landing Gear Strut. Assy P/N 109-0503-45-101/-102 and to apply a corrosion protective compound at wheel re-installation. An alternative inspection method with magnetic particles is provided, too.

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

EASA states mandatory compliance with inspections, modifications or technical directives and related time of compliance by means of relevant Airworthiness Directives.

If an aircraft listed in the effectivity embodies a modification 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 incorporation of the present Service Bulletin.

G. MANPOWER To comply with this Service Bulletin 2 (two) MMH are deemed necessary.

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

H. WEIGHT AND BALANCE N.A.

S.B. N°109EP-168 ALERT DATE: June 28, 2019 Page 4 of 19 REVISION: / I. REFERENCES

1) PUBLICATIONS

SECTION/PARAGRAPH DESCRIPTION PART DM01 00-20-1 Helicopter safety - DM02 07-10-2 Jacking and lowering of helicopter - DM03 32-41-14 Main wheels - Removal/installation - DM04 32-11-10 Left/right main landing gear struts - Removal/installation - DM05 CMM 32-11-19 4 th issue Main Landing Gear - Component Maintenance Manual (only for authorized service station) -

2) ACRONYMS AR As Required CMM Component Maintenance Manual DM Data Module DOA Design Organization Approval EASA European Aviation Safety Agency IPC Illustrated Part Catalog LH Left LHD Leonardo Helicopters MLG Main Landing Gear MM Maintenance Manual MMH Maintenance Man Hours N.A. Not Applicable RH Right P/N Part Number SB Service Bulletin S/N Serial Number

3) ANNEX Annex A A109E MLG Liquid Penetrant Inspection.

Annex B A109E MLG Magnetic Particle Inspection J. PUBLICATIONS AFFECTED A109E-MPM Maintenance Planning Manual

S.B. N°109EP-168 ALERT DATE: June 28, 2019 REVISION: / Page 5 of 19 K. SOFTWARE ACCOMPLISHMENT SUMMARY N.A.

S.B. N°109EP-168 ALERT DATE: June 28, 2019 Page 6 of 19 REVISION: /

2. MATERIAL INFORMATION A. REQUIRED MATERIALS

1) PARTS # P/N ALTERNATIVE P/N DESCRIPTION Q.TY LVL NOTE LOG P/N 1 MS24665-374 MS24665-372 Cotter pin 2 . - Refer also to IPC for the spares materials required to comply with the MM Paragraphs 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 2 MIL-PRF-16173, Cl I & II, Grade 1 (LHD cod. 999999999000000191) Tectyl 891D (C509) AR (1) - 3 MIL-PRF-16173, Cl I, Grade 4 (LHD cod. 999999999000000190) Tectyl 846 (C532) AR (1) - 4 SAE-AMS-2644 TY I, Method C, Level 3 Dye Penetrant AR (1)(2) - 5 SAE-AMS-2644, Form D Developer AR (1)(2) - 6 SAE-AMS-2644 Cl II Solvent (C290) AR (1)(2) - 7 ASTM F945 Ardrox 6333 (C292) AR (1) - 8 Commercial Alkaline Steel Cleaner AR (1) - Refer also to AMDI for the consumable materials required to comply with the MM Paragraphs referenced in the accomplishment instructions.

3) LOGISTIC MATRIX N.A.

NOTE

(1) Local supply.

(2) This material shall be certified in accordance with AMS2644, obtained from a supplier listed in QPL-AMS2644 and supplied in aerosol cans packaging.

B. SPECIAL TOOLS Refer also to PTUM for the special tools required to comply with the MM Paragraphs 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 will be eligible to receive

S.B. N°109EP-168 ALERT DATE: June 28, 2019 REVISION: / Page 7 of 19 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. Accompanied by INSPECTION REPORT and PICTURE of the affected area.

NOTE: The INSPECTION REPORT and PICTURE are mandatory; in case the MMIR is not accompanied by these documents, it will be rejected.

NOTE: WRM will include RETURN MATERIAL AUTHORIZATION (RMA) number; the unit removed from the aircraft has to be returned to LHD as per instructions defined into LHD Information Letter GEN-15-047.

S.B. N°109EP-168 ALERT DATE: June 28, 2019 Page 8 of 19 REVISION: /

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.

b) Exposed thread surface and nut must be protected using a layer of tectyl according to MIL-C-16173 grade I.

1. In accordance with the instructions given in MM P aragraph 00-20-1, prepare the helicopter on ground for a safe maintenance. Disconnect the battery, all electrical power sources and/or the external power supply.

2. In accordance with the instructions given in MM Paragraph 07-10-2, lift the helicopter on jacks.

3. In accordance with the instructions given in MM Paragraph 32-41-14 remove the LH and RH MLG wheel assy.

NOTE Magnetic Inspection in Annex B is a valid alternative to the liquid penetrant inspection. The two methods are equivalent.

4. In accordance with the instruction given in the A nnex A, perform the liquid penetrant inspection on the threaded end of the LH and RH enhanced MLG strut. assy P/N 109-0503-45-101/-102. Cracks are not allowed.

5. In case of no findings, proceed to step 7.

NOTE In case of finding contact Product Support Engineering (aw109.mbx.aw@leonardocompany.com).

6. In case of findings, perform the replacement of t he damaged leg as described in the following procedure:

NOTE The following steps are applicable both on LH and RH MLG strut. assy.

6.1 In accordance with the instructions given in MM Paragraph 32-11-10, remove

S.B. N°109EP-168 ALERT DATE: June 28, 2019 REVISION: / Page 9 of 19 and return to LHD the LH/RH enhanced MLG strut. assy P/N 109-0503-45-101/-102.

6.2 In accordance with the instructions given in MM Paragraph 32-11-10, install the new LH/RH enhanced MLG strut. assy P/N 109-0503-45-101/-102.

7. In accordance with the instructions given in MM Paragraph 32-41-14 reinstall the LH and RH MLG wheel assy.

8. Apply corrosion preventive compound MIL-PRF-16173 Grade 1 (Tectyl 891D) or Grade 4 (Tectyl 846) on the exposed surface of the threaded end and on inner surface of the end lightening hole of the LH/RH enhanced MLG strut. assy P/N 109-0503-45-101/-102.

9. Record for compliance with this Service Bulletin on the component log card.

10. Return the helicopter to a ready to flight condition and record for compliance with this Service Bulletin on the helicopter logbook.

11. Send the attached compliance form to the following mail box:

aw109.mbx.aw@leonardocompany.com As an alternative, gain access to My Communications section on Leonardo WebPortal and compile the “Service Bulletin Application Communication”.

Non cancellare mai questo segnalibro Non cancellare mai interruzione sezione 

S.B. N°109EP-168 ALERT DATE: June 28, 2019 Page 10 of 19 REVISION: /

(FOR REFERENCE ONLY)

ANNEX A S.B. N°109EP-168 ALERT DATE: June 28, 2019 REVISION: / Page 11 of 19

ANNEX A A109E MAIN LANDING GEAR

LIQUID PENETRANT INSPECTION

ANNEX A S.B. N°109EP-168 ALERT DATE: June 28, 2019 Page 12 of 19 REVISION: / 1 PURPOSE AND APPLICABILITY This procedure details the requirements for the Liquid Penetrant Inspection (PT) on the following P/Ns:

MAG P/N DESCRIPTION M019-01H003-101 Wheel Axle LH M019-01H003-102 Wheel Axle RH Purpose of this inspection is the detection of any possible crack starting from the root of the bottom of the thread of the hub; the inspection of this procedure shall be performed on all the thread of the hub after the removal of the wheel.

2 REFERENCES The following documents in their last revision are considered part of this procedure:

ASTM E1417 Standard Practice for Liquid Penetrant Testing;

ASTM E3022 Standard Practice for Measurement of Emission Characteristics and Requirements for LED UV-A Lamps Used in Fluorescent Penetrant and Magnetic Particle Testing;

EN4179/NAS410 Qualification and approval of personnel for non-destructive testing;

QPL AMS2644 Qualified Product List of Inspection Materials, Penetrant;

SAE AMS2644 Inspection Materials, Penetrant.

3 EQUIPMENT AND MATERIALS The following materials, equipment and tools are requested.

3.1 MATERIALS

a. Dye Penetrant SAE-AMS-2644 TY I, Method C, Level 3;

b. Developer SAE-AMS-2644 Form D;

c. Solvent SAE-AMS-2644 Class 2.

All the above materials shall be certified in accordance with AMS2644, obtained from a supplier listed in QPL-AMS2644 and supplied in aerosol cans packaging.

3.2 EQUIPMENT/TOOLS

a. A booth suitable for darkening the area of inspection up to an illuminance of 20 lux maximum;

b. a Luxmeter for checking the illuminance (20 lux maximum on the part during the inspection and the 1,000 lux minimum for the assessment of indications);