AD 2022-14-51 Airworthiness Directives; Airbus Helicopters

Models named: EC225LP. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Helicopters Model EC225LP helicopters, certificated in any category, with main rotor hub (MRH) sleeve part number 332A31-3071-00 installed.

Comply with this AD within the compliance times specified, unless already done.

(1) Before further flight after the effective date of this AD, visually inspect the “Specific area” of each MRH sleeve as depicted in Figure 3 of Airbus Helicopters Emergency Alert Service Bulletin No. 62A017, Revision 0, dated June 30, 2022 (ASB 62A017), for flaking and paint touch-up. (2) As a result of the actions required by paragraph (g)(1) of this AD, if there is no flaking or paint touch-up, no further action is required. If there is any flaking or paint touch-up, before further flight, visually inspect the “Specific area” of the MRH sleeve as depicted in Figure 3 of ASB 62A017 for a crack. (3) As a result of the actions required by paragraph (g)(2) of this AD, if there is a crack, before further flight, remove the MRH sleeve from service and replace it with an airworthy part. If there is not a crack, within 15 hours time-in-service (TIS) or 3 months, whichever occurs first after accomplishing the actions required by paragraph (g)(1) of this AD, use high-frequency eddy current (HFEC) to inspect the “Specific area” of the MRH sleeve as depicted in Figure 3 of ASB 62A017 for a crack. This HFEC inspection must be accomplished by a Level II or III inspector certified in the eddy current fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard. (4) As a result of the actions required by paragraph (g)(3) of this AD, if there is a crack, before further flight, remove the MRH sleeve from service and replace it with an airworthy part. If there is not a crack, before further flight, chemically strip and fluorescent penetrant inspect (FPI) the “Specific area” of the MRH sleeve as depicted in Figure 3 of ASB 62A017 for corrosion. (i) If there is corrosion as a result of the actions required by the introductory text of paragraph (g)(4) of this AD, before further flight, accomplish the actions required by paragraph (g)(4)(i)(A) or (B) of this AD. (A) Remove the corrosion by hand using 120-grit abrasive cloth, followed by 400-grit abrasive cloth. After removing the corrosion, perform an FPI of each affected area to inspect for corrosion, and accomplish the actions required by paragraph (g)(4)(i)(A)( 1 ) or ( 2 ) of this AD. ( 1 ) If there is corrosion, before further flight, remove the MRH sleeve from service and replace it with an airworthy part or repair it in accordance with a method approved by the Manager, General Aviation & Rotorcraft Section, International Validation Branch, FAA; or European Union Aviation Safety Agency (EASA); or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. ( 2 ) If there is no corrosion, before further flight, completely dry the MRH sleeve and apply a protective coating, primer, and paint protection. Following application, within 15 hours TIS and thereafter at intervals not to exceed 15 hours TIS, use HFEC to inspect the “Specific area” of the MRH sleeve as depicted in Figure 3 of ASB 62A017 for a crack. This HFEC inspection must be accomplished by a Level II or III inspector certified in the eddy current fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard. If there is a crack, before further flight, remove the MRH sleeve from service and replace it with an airworthy part. Accomplishment of the HFEC inspections with no detected cracks after 75 hours TIS since applying the coating, primer, and paint protection constitutes a terminating action for the repetitive inspections required by this paragraph. (B) If the corrosion cannot be removed by hand as specified in paragraph (g)(4)(i)(A) of this AD, before further flight, remove the MRH sleeve from service and replace it with an airworthy part or repair it in accordance with a method approved by the Manager, General Aviation & Rotorcraft Section, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (ii) If there is no corrosion as a result of the actions required by the introductory text of paragraph (g)(4) of this AD, before further flight, apply primer and paint protection. (5) As an option to the actions required by paragraph (g)(4) of this AD, if there is not a crack, accomplish the actions required by paragraphs (g)(5)(i) and (ii) of this AD. (i) Before further flight, apply primer and paint protection. If there is any area with flaking paint, you may apply only varnish instead of primer and paint protection on each flaking paint area. (ii) Within 15 hours TIS after accomplishing the actions required by paragraph (g)(5)(i) of this AD and thereafter at intervals not to exceed 15 hours TIS, HFEC inspect the “Specific area” of the MRH sleeve as depicted in Figure 3 of ASB 62A017 for a crack. This HFEC inspection must be accomplished by a Level II or III inspector certified in the eddy current fault detection method in the Aeronautics Sector according to the EN4179 or NAS410 standard. If there is a crack, before further flight, remove the MRH sleeve from service and replace it with an airworthy part. (6) As of the effective date of this AD, do not install an MRH sleeve identified in paragraph (c) of this AD on any helicopter unless the actions required by paragraphs (g)(1) and (2) of this AD have been accomplished.

This AD was prompted by a report of a cracked MRH sleeve. The FAA is issuing this AD to detect corrosion or cracking in an MRH sleeve. The unsafe condition, if not addressed, could result in failure of an MRH sleeve, loss of a main rotor blade, and subsequent loss of the helicopter.

None.