Airworthiness Directive · Amendment 39-21571 · Main rotor system
Airbus Helicopters Deutschland GmbH Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters, certificated in any category, with an “affected `angle 0' parts” or “affected `angle 1' parts” installed, as identified in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2018-0061, dated March 20, 2018 (EASA AD 2018-0061).
The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A- 3, MBB-BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. This AD was prompted by an analysis of the main rotor (M/ R) blade loop area. This AD requires repetitive inspections of certain M/R blade thimble areas and corrective actions if necessary, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2018-0061.
(1) Where EASA AD 2018-0061 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2018-0061 refers to flight hours, this AD requires using hours time-in-service (TIS).
(3) Where Table 1, Table 2, and Note 2 of EASA AD 2018-0061 specify inspection thresholds, intervals, and a non-cumulative compliance time tolerance of 10% for certain required compliance times, this AD requires accomplishing those requirements, as follows:
(i) For helicopters with an “affected `angle 0' parts,” the compliance time is before accumulating 660 total hours TIS on the affected part or within 100 hours TIS after the effective date of this AD, whichever occurs later, and without accumulating 1,600 total hours TIS on the affected part. Thereafter, the compliance time is at intervals not to exceed 330 hours TIS.
(ii) For helicopters with an “affected `angle 1' parts,” the compliance time is before accumulating 110 total hours TIS on the affected part or within 50 hours TIS after the effective date of this AD, whichever occurs later, and without accumulating 950 total hours TIS on the affected part. Thereafter, the compliance time is at intervals not to exceed 110 hours TIS.
(iii) For helicopters specified in paragraph (c) of this AD, Note 1 of EASA AD 2018-0061 specifies accumulated FH as, “Unless otherwise specified, the FH specified in Table 2 of this AD are those accumulated since the previous M/R blade thimble inspection.” This AD requires intervals thereafter to be accumulated since accomplishment of paragraph (g) of this AD.
(4) While paragraph (5) and Note 3 of EASA AD 2018-0061 specify revising the Aircraft Maintenance Program (AMP), this AD does not require this action.
(5) Where the service information referenced in EASA AD 2018-0061 specifies accomplishment of certain corrective action by “ECD” or an authorized service or repair station, this AD requires the corrective actions to be performed by a qualified mechanic.
(6) Where the service information referenced in EASA AD 2018-0061 specifies contacting “ECD” or an authorized service or repair station, this AD requires performing the corrective action in accordance with FAA-approved procedures.
(7) The “Remarks” section of EASA AD 2018-0061 does not apply to this AD.
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.
