2019-19-13: Main Rotor Gearbox

The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2019-19-13 Airbus Helicopters: Amendment 39-19749; Docket No. FAA- 2019-0738; Product Identifier 2019-SW-017-AD. (a) Applicability This AD applies to Airbus Helicopters Model EC225LP helicopters, certificated in any category, with a main rotor gearbox (MGB) part number (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. (b) Unsafe Condition 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. (c) Effective Date This AD becomes effective November 5, 2019. (d) Compliance 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. [[Page 56111]] (e) Required Actions (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. [GRAPHIC] [TIFF OMITTED] TR21OC19.006 (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 [GRAPHIC] [TIFF OMITTED] TR21OC19.007 (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-rollerfree 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. (f) Credit for Previous Actions 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. (g) Special Flight Permits A one-time special flight permit to a maintenance facility may be permitted. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to Rao Edupuganti, Aviation Safety Engineer, Regulations and Policy Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (i) Additional Information (1) Airbus Helicopters Emergency Alert Service Bulletin No. 04A016, Revision 1, dated June 28, 2019, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in [[Page 56112]] this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) No. 2019-0152-E, dated June 28, 2019. You may view the EASA AD on the internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2019-0738. (j) Subject Joint Aircraft Service Component (JASC) Code: 6320, Main Rotor Gearbox.