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Federal Register / Vol. 86, No. 53 / Monday, March 22, 2021 / Proposed Rules List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety.
The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

Airbus Helicopters: Docket No. FAA2017
1036; Product Identifier 2018SW015
AD.
a Applicability This airworthiness directive AD applies to Airbus Helicopters Model AS365N2, AS
365 N3, SA365N, and SA365N1
helicopters, certificated in any category.
b Unsafe Condition This AD defines the unsafe condition as failure of a main gearbox MGB planet gear assembly. This condition could result in failure of the MGB and subsequent loss of helicopter control.
c Affected ADs None.
d Comments Due Date The FAA must receive comments by May 6, 2021.

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e 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.
f Required Actions 1 For helicopters with at least one Type X planet gear assembly with a serial number S/N listed in Appendix 4.A. of Airbus Helicopters Alert Service Bulletin No.
AS36505.00.78, Revision 3, dated March 2, 2018 ASB AS36505.00.78 installed on the main gearbox MGB, before further flight, replace the MGB or as an alternative to replacing an affected MGB, replace the epicyclic reduction gear module Post Modification MOD 0763C52 in the affected MGB in accordance with paragraph 3.B.2 of the Accomplishment Instructions of Airbus Helicopters Service Bulletin No. AS365
63.00.21, Revision 3, dated July 26, 2018 SB
AS36563.00.21, except you are not required to contact Airbus Helicopters.
2 For helicopters without any Type X
planet gear assembly installed but with at least one Type Y planet gear assembly with an S/N listed in Appendix 4.B. of ASB AS

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36505.0078 installed on the MGB, within 300 hours time-in-service TIS, or before any gear accumulates 1,300 hours TIS since new, whichever occurs first, replace the MGB or as an alternative to replacing the MGB, replace the epicyclic reduction gear module MOD
0763C52 in the affected MGB in accordance with paragraphs 3.B.2. of the Accomplishment Instructions of SB AS365
63.00.21, except you are not required to contact Airbus Helicopters.
3 As of the effective date of this AD, do not install an MGB with a Type X or Type Y gear assembly with an S/N listed in Appendix 4.A. or 4.B. of ASB AS365
05.0078 installed on the MGB, on any helicopter.
4 For all helicopters, within 10 hours TIS
and thereafter before the first flight of the day or at intervals not to exceed 10 hours TIS, whichever occurs first, inspect the lower MGB magnetic plugs for particles.
i If there are particles that consist of any scale, flake, or splinter, or particles other than cotter pin fragments, pieces of lock wire, swarf, abrasion, or miscellaneous nonmetallic waste and the planet gear assembly has logged less than 50 hours TIS since new, inspect the MGB plugs for particles before further flight and inspect the oil filter for particles within 5 hours TIS. Thereafter, for 25 hours TIS, continue to inspect the MGB
plugs for particles before each flight, inspect the oil filter for particles at intervals not to exceed 5 hours TIS, and perform the actions required by paragraphs f4iiA through B of this AD.
ii If there are particles that consist of any scale, flake, or splinter, or particles other than cotter pin fragments, pieces of lock wire, swarf, abrasion, or miscellaneous nonmetallic waste and the planet gear assembly has logged more than 50 hours TIS since new, inspect the cumulative surface area of the particles collected from both the magnetic plug and the oil filter, since last MGB overhaul or since new if no overhaul has been performed.
A If the total surface area of the particles is less than 3 mm2, examine the particles with largest surface area S, longest particle length L and thickest particles e.
1 If largest surface area S of a particle is less than 1 mm2, the L is less than 1.5 mm, and the e is less than 0.2 mm, inspect the MGB plugs for particles before further flight and inspect the oil filter for particles within 5 hours TIS. Thereafter, for 25 hours TIS, continue to inspect the MGB plugs for particles before each flight, inspect the oil filter for particles at intervals not to exceed 5 hours TIS, and perform the actions required by paragraphs f4iiA through B of this AD.
2 If largest particle size S is greater than 1 mm2, the L is greater than 1.5 mm, or the e is greater than 0.2 mm, perform a metallurgical analysis for any 16NCD13
particles using a method in accordance with FAA-approved procedures.
3 If there are any 16NCD13 particles, replace the MGB with an airworthy MGB.
4 If there are no 16NCD13 particles, inspect the MGB plugs for particles before further flight and inspect the oil filter for particles within 5 hours TIS. Thereafter, for
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25 hours TIS, continue to inspect the MGB
plugs for particles before each flight, inspect the oil filter for particles at intervals not to exceed 5 hours TIS, and perform the actions required by paragraphs f4iiA through B of this AD.
B If the total surface area of collected particles is greater than or equal to 3 mm2, before further flight, perform a metallurgical analysis for any 6NCD13 particles using a method in accordance with FAA-approved procedures.
1 If there are any 16NCD13 particles, before further flight, replace the MGB with an airworthy MGB.
2 If there are no 16NCD13 particles, inspect the MGB plugs for particles before further flight and inspect the oil filter for particles within 5 hours TIS. Thereafter, for 25 hours TIS, continue to inspect the MGB
plugs for particles before each flight, inspect the oil filter for particles at intervals not to exceed 5 hours TIS, and perform the actions required by paragraphs f4iiA through B of this AD.
g Special Flight Permits Special flight permits may be permitted provided that there are no passengers on board.
h Alternative Methods of Compliance AMOCs 1 The Manager, International Validation Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Rao Edupuganti, Dynamic Systems Section, Technical Innovation Policy Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone 8172225110; email 9-ASW-FTWAMOC-Requests@faa.gov.
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 The subject of this AD is addressed in European Aviation Safety Agency now European Union Aviation Safety Agency EASA AD No. 20170116R2, dated March 2, 2018. You may view the EASA AD on the internet at https www.regulations.gov in Docket No. FAA20171036.
j Subject Joint Aircraft Service Component JASC
Code: 6300, Main Rotor Drive System.
Issued on February 19, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202105355 Filed 31921; 8:45 am BILLING CODE 491013P

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