AD 2020-15-13 Airworthiness Directives; Airbus Helicopters Deutschland GmbH Helicopters

This AD replaces AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017).

Comply with either paragraphs (f)(1) and (2) of this AD, or paragraph (f)(3) of this AD, as applicable to your helicopter. (1) For helicopters with a hydraulic module plate assembly with a single locking attachment hardware installed, within 100 hours time-in-service (TIS): (i) Visually inspect the split pins, castellated nuts, plugs, nuts, and hexagon bolts of each attachment point for a crack and for proper installation by following the Accomplishment Instructions, paragraphs 3.B.1.3.a. through 3.B.1.3.d., of Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003 (ASB MBB-BK117 C-2-29A-003 Rev 3) or Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001 (ASB MBB-BK117 D-2-29A-001 Rev 3), both Revision 3 and dated December 19, 2017, as applicable to your model helicopter. Replace any part that has a crack before further flight. If the split pins, castellated nuts, or hexagon bolts are not as depicted in Figures 1 and 2 of ASB MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, before further flight, properly install them. (ii) Apply a torque of 9 to 10 Nm to the left-hand (LH) and right-hand (RH) nuts of each forward attachment point. If a torque of 9 to 10 Nm cannot be applied, replace the affected nut before further flight. (2) For helicopters with a hydraulic module plate assembly with a single locking attachment hardware installed, within 300 hours TIS: (i) Replace each forward single locking attachment hardware with double locking attachment hardware by following the Accomplishment Instructions, paragraphs 3.B.3.3. through 3.B.3.6. on page 11 of ASB MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to your model helicopter, except you are not required to discard old parts. (ii) Replace each aft single locking attachment hardware with double locking attachment hardware and reposition the LH and RH aft grounding straps by following the Accomplishment Instructions, paragraphs 3.B.3.1. through 3.B.3.7. on page 13 of ASB MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to your model helicopter, except you are not required to discard old parts. (3) If you have replaced the attachment hardware with double locking attachment hardware before the effective date of this AD in accordance with ASB MBB-BK117 C-2-29A-003 Rev 2 or ASB MBB-BK117 D-2-29A-001 Rev 2, as applicable to your model helicopter: Within 300 hours TIS, inspect the clamping effect of the LH and RH aft screw joints (bolts) of the hydraulic module plate by following the Accomplishment Instructions, paragraph 3.B.5., of ASB MBB-BK117 C-2-29A-003 Rev 3 or ASB MBB-BK117 D-2-29A-001 Rev 3, as applicable to your model helicopter, except you are not required to discard old parts. Note 1 to paragraph (f)(3) of this AD: Airbus Helicopters refers to bolts as “screw joints.”

Actions accomplished before the effective date of this AD in accordance with the procedures specified in the following are considered acceptable for compliance with the corresponding actions in paragraph (f)(1) of this AD: (1) AD 2017-02-07, Amendment 39-18786 (82 FR 10267, February 10, 2017). (2) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003, Revision 1, dated October 14, 2016. (3) Airbus Helicopters ASB No. ASB MBB-BK117 C-2-29A-003, Revision 2, dated February 1, 2017. (4) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, Revision 1, dated October 14, 2016. (5) Airbus Helicopters ASB No. ASB MBB-BK117 D-2-29A-001, Revision 2, dated February 1, 2017.

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

This AD defines the unsafe condition as failure of a hydraulic module plate assembly attachment point (attachment point). This condition could result in loss of the hydraulic module plate and subsequent loss of control of the helicopter.