AD 2019-19-13 Airworthiness Directives; Airbus Helicopters

This AD becomes effective November 5, 2019.

Actions accomplished before the effective date of this AD by following the procedures specified in Airbus Helicopters Emergency Alert Service Bulletin No. 04A016, Revision 1, dated June 28, 2019, are considered acceptable for compliance with the corresponding requirements specified in paragraphs (e)(1) through (e)(2)(i) of this AD.

A one-time special flight permit to a maintenance facility may be permitted.

(1) Within 10 hours time-in-service (TIS), determine the total hours TIS of the RH and LH free wheel shafts since new or last RH free wheel shaft replacement during overhaul. For the purpose of this AD, if the total hours TIS of the RH and LH free wheel shafts are different, use the greater number of total hours TIS as the RH free wheel shaft total hours TIS. (i) If the total hours TIS of the RH free wheel shaft is 1,000 or more hours TIS, before further flight, replace the MGB or replace the RH free wheel shaft under the supervision of an Airbus Helicopter Specialist that is qualified for this replacement. (ii) If the total hours TIS of the RH free wheel shaft is less than 1,000 hours TIS, before exceeding 1,000 hours TIS, replace the MGB or replace the RH free wheel shaft under the supervision of an Airbus Helicopter Specialist that is qualified for this replacement. (2) Within 10 hours TIS: (i) Install one or two self-adhesive placards on the instrument panel in full view of the pilot and co-pilot with 6-millimeter red letters on a white background that state the information contained in Figure 1 to paragraph (e)(2)(i) of this AD. Refer to Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 04A016, Revision 1, dated June 28, 2019, for an example of this placard. ER21OC19.006 (ii) After installing the placard(s) required by paragraph (e)(2)(i) of this AD, before further flight, revise the limitations section of the Rotorcraft Flight Manual (RFM) for your helicopter by adding the information in Figure 2 to paragraph (e)(2)(ii) of this AD, by inserting a copy of this AD, or by making pen-and-ink changes. This action may be done by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD by following 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439 ER21OC19.007 (3) After the effective date of this AD, do not install an MGB P/N 332A325001.XX, P/N 332A325002.XX, or P/N 332A325003.XX, with a main reduction gear module (main module), with modification (MOD) 07-53016 (16-roller free wheel of free wheel shaft P/N 332A322191.20) installed, P/N 332A325011.XX, P/N 332A325012.XX, or P/N 332A325013.XX, with “XX” denoting any dash number unless the requirements of paragraph (e)(2) of this AD have been accomplished. (4) As an optional terminating action for the requirements of this AD, install MGB P/N 332A325001.XX, P/N 332A325002.XX, or P/N 332A325003.XX, with a main module (12-roller free wheel), without MOD 07-53016 installed, P/N 332A325011.XX, P/N 332A325012.XX, or P/N 332A325013.XX, with “XX” denoting any dash number.

This AD defines the unsafe condition as wear of the ramps of the right-hand side (RH) free wheel shaft. During an in-flight shutdown of the left-hand side (LH) engine, this condition could result in reduced ability to transfer one engine inoperative (OEI) power from the RH engine to the main rotor, and subsequent reduced control of the helicopter.