Airworthiness Directive · Amendment 39-21873 · Fuselage structure
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS332L2 and Model EC225LP helicopters, certificated in any category, as specified in paragraphs (c)(1) and (2) of this AD.
(1) Model AS332L2 helicopters equipped with extended aluminum splices on frame 5295 installed in accordance with Airbus Helicopters (AH) Modification (MOD) 0726517, Eurocopter (EC) AS332 Service Bulletin (SB) 53.01.52, or AH repair design 332-53-507-06, 332-53-21-07, or 332-53-82-06; except helicopters embodying AH MOD 0728463, AH SB AS 332-53.01.97, or repair design 332-53-409-12, 332-53-1284-13, 332-53-1079-16, or 332-53-1358-16.
Note 1 to paragraph (c)(1): As referenced in paragraphs (c)(1) and (2) of this AD, helicopters with AH MOD 0728463 installed have replaced the aluminum splices with steel splices.
(2) Model EC225LP helicopters equipped with extended aluminum splices on frame 5295 installed in accordance with AH MOD 0726517, or EC EC225 SB 53-003 (pre AH MOD 0726493 and post AH MOD 0726517), except helicopters embodying AH MOD 0728463, or SB EC225-53-061.
Note 2 to paragraph (c)(2): Helicopters with AH MOD 0726493 have installed steel splice kit part number 332A08-2649-3072.
The FAA is superseding Airworthiness Directive (AD) 2018-11- 01, which applied to certain Airbus Helicopters Model AS332L2 and EC225LP helicopters. AD 2018-11-01 required installing a cut-out for the left-hand (LH) and right-hand (RH) rail support junction profiles and repetitively inspecting splices, frame 5295, and related equipment for a crack. Since the FAA issued AD 2018-11-01, the manufacturer has developed a modification for in-service helicopters for replacing aluminum splices with steel splices on frame 5295. This AD retains the requirements of AD 2018-11-01 and requires a modification for replacing aluminum splices with steel splices on frame 5295 if cracking is found. This AD also provides terminating action for the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
This paragraph retains the requirements of paragraph (e) of AD 2018-11-01, with new service information and corrective actions (modification).
(1) Before a splice reaches 1,700 hours time-in-service (TIS), within 50 hours TIS, or before the helicopter reaches 11,950 hours TIS, whichever occurs latest, do the following.
(i) Install the rail support cut-out and identify the left-hand (LH) and right-hand (RH) junction profile, in accordance with the Accomplishment Instructions, paragraph 3.B.2., of Airbus Helicopters Alert Service Bulletin (ASB) No. EC225-05A038, Revision 1, dated February 9, 2021 (Airbus Helicopters ASB No. EC225-05A038, Revision 1); or Airbus Helicopters ASB No. AS332-05.00.97, Revision 1, dated February 9, 2021 (Airbus Helicopters ASB No. AS332-05.00.97, Revision 1); whichever is applicable to your helicopter.
(ii) Inspect each splice for a crack in the area depicted as Area Y in Figure 3 of Airbus Helicopters ASB No. EC225-05A038, Revision 1; or Airbus Helicopters ASB No. AS332-05.00.97, Revision 1; whichever is applicable to your helicopter. If a crack exists, do the applicable action required by paragraph (g)(1)(ii)(A) or (B) of this AD.
(A) For any cracking found before the effective date of this AD: Repair or replace the splice before further flight.
(B) For any cracking found on or after the effective date of this AD: Before further flight, modify the helicopter in accordance with paragraph 3.B.2. of the Accomplishment Instructions of Airbus Helicopters Service Bulletin (SB) No. AS332-53.01.97, Revision 0, dated February 9, 2021 (Airbus Helicopters SB No. AS332-53.01.97, Revision 0); or Service Bulletin No. EC225-53-061, Revision 0, dated February 9, 2021 (Airbus Helicopters SB No. EC225-53-061, Revision 0); as applicable to your helicopter; except as specified in paragraph (h) of this AD.
(2) Thereafter at intervals not to exceed 110 hours TIS, inspect each splice for a crack in the area depicted as Area Y in Figure 3 of Airbus Helicopters ASB No. EC225-05A038, Revision 1; or Airbus Helicopters ASB No. AS332-05.00.97, Revision 1; whichever is applicable to your helicopter. If a crack exists, do the applicable actions required by paragraph (g)(2)(i) or (ii) of this AD. Accomplishing the modification specified in paragraph (g)(1)(ii)(B) and (g)(2)(ii) of this AD terminates the inspections required by this paragraph.
(i) For any cracking found before the effective date of this AD: Repair or replace the splice before further flight.
(ii) For any cracking found on or after the effective date of this AD: Before further flight, modify the helicopter in accordance with paragraph 3.B.2. of the Accomplishment Instructions of Airbus Helicopters SB No. AS332-53.01.97, Revision 0; or Airbus Helicopters SB No. EC 225-53-061, Revision 0; as applicable to your helicopter; except as specified in paragraph (h) of this AD.
(1) Where Airbus Helicopters ASB No. EC225-05A038, Revision 1; Airbus Helicopters ASB No. AS332-05.00.97, Revision 1; Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus Helicopters SB No. EC 225-53-061, Revision 0; specify to perform dye-penetrant inspections “if in doubt” or “if any doubt,” this AD requires performing a dye-penetrant inspection during inspections done on or after the effective date of this AD.
(2) Where Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus Helicopters SB No. EC 225-53-061, Revision 0; specify discarding parts, this AD requires removing those parts from service.
(3) Where Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus Helicopters SB No. EC 225-53-061, Revision 0, specify contacting Airbus Helicopter for corrective action or further procedures, this AD requires repair done in accordance with a method approved by the Manager, General Aviation & Rotorcraft Section, International Validation Branch, FAA; or EASA; or Airbus Helicopters' EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(4) Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus Helicopters SB No. EC 225-53-061, Revision 0, specify a visual check and dye penetrant inspection for cracks on the inside and outside of frame 5295. For this AD, if any cracking is found during any visual check or dye penetrant inspection on the inside and outside of frame 5295, before further flight, repair 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.
Although Airbus Helicopters SB No. AS332-53.01.97, Revision 0; and Airbus Helicopters SB No. EC 225-53-061, Revision 0; specify to submit certain information to the manufacturer, this AD does not include that requirement.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
