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Federal Register / Vol. 86, No. 96 / Thursday, May 20, 2021 / Rules and Regulations
necessary for safety in air commerce.
This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I
certify that this AD:
1 Is not a significant regulatory action under Executive Order 12866, 2 Will not affect intrastate aviation in Alaska, and 3 Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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:

20211014 Airbus Helicopters Deutschland GmbH: Amendment 39
21547; Docket No. FAA20210143;
Product Identifier 2019SW024AD.
a Effective Date This airworthiness directive AD is effective June 24, 2021.
b Affected ADs This AD affects AD 20162514, Amendment 3918740 81 FR 94944, December 27, 2016 AD 20162514.
c Applicability This AD applies to Airbus Helicopters Deutschland GmbH Model BO105A, BO
105C, BO105S, and BO105LS A3
helicopters, certificated in any category, equipped with a tension torsion strap TT-

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strap as identified in European Aviation Safety Agency now European Union Aviation Safety Agency EASA AD 2019
0024, dated February 4, 2019 EASA AD
20190024.
d Subject Joint Aircraft System Component JASC
Code 6200, Main Rotor System.
e Reason This AD was prompted by the FAAs determination that aging of the elastomeric material in a TT-strap could affect the structural characteristics of the TT-strap. The FAA is issuing this AD to address aging of the elastomeric material in a TT-strap, which could lead to premature failure of a TT-strap, resulting in loss of control of the helicopter.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Requirements 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 20190024.
h Exceptions to EASA AD 20190024
1 Where EASA AD 20190024 refers to its effective date, this AD requires using the effective date of this AD.
2 The Remarks section of EASA AD
20190024 does not apply to this AD.
3 Where EASA AD 20190024 and the service information referenced in EASA AD
20190024 specify contacting Airbus Helicopters Deutschland if the storage time for a TT-strap is equal to or greater than 5
years, this AD requires repair using a method approved by the Manager, International Validation Branch, FAA. For a repair method to be approved by the Manager, International Validation Branch, as required by this paragraph, the Managers approval letter must specifically refer to this AD.
4 Although the service information referenced in EASA AD 20190024 specifies to scrap certain parts, this AD requires removing those parts from service instead.
5 Where paragraph 1 of EASA AD 2019
0024 specifies to replace each Lord TT-Strap and Bendix TT-Strap in accordance with the instructions of the applicable ASB, the replacement must be done using FAAapproved procedures.
6 Where EASA AD 20190024 refers to the airworthiness limitations items of the airworthiness limitations section of the aircraft maintenance manual AMM for the definition of service life limit SLL, this AD
requires using the life limits specified in paragraphs h6i through iii of this AD, as applicable:
i For Bendix TT-Strap part number P/N
2604067 and P/N 11714110: Before 10 years or 40,000 flight cycles on the part, whichever occurs first.
ii For Bendix TT-Strap P/N 2602559 and P/N 2606576: Before 10 years, 2,400 hours time-in-service, or 40,000 flight cycles on the part, whichever occurs first.
iii For Lord TT-Strap P/N J173221 and P/N 11714111: Before 12 years or 40,000

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flight cycles on the part, whichever occurs first.
7 Where paragraph 3 of EASA AD 2019
0024 specifies that installation of a Lord TTStrap is allowed provided the first flight of that helicopter after that installation is accomplished before the storage life of that Lord TT-Strap exceeds 5 years, for this AD, the installation of a Lord TT-Strap is allowed provided the first flight of that helicopter after that installation is accomplished before 5 years since the TT-straps date of manufacture.
8 Where EASA AD 20190024 defines serviceable part as a Lord TT-Strap having a storage life not exceeding 5 years, for this AD, a serviceable part is Lord TT-straps P/
N J173221 and P/N 11714111 having less than 5 years since that TT-straps date of manufacture.
9 Where EASA AD 20190024 specifies that the cure date of a TT-Strap can be determined using the information provided in the applicable service information specified in EASA AD 20190024, or contacting Airbus Helicopters for applicable instructions, for this AD, the option of contacting Airbus Helicopters is not required.
i Repetitive Replacement After accomplishing the replacement specified in paragraph 1 of EASA AD 2019
0024, thereafter, replace the Lord TT-straps P/N J173221 and P/N 11714111, at intervals not to exceed: Before 12 years or 40,000 flight cycles on the part, whichever occurs first.
j Terminating Action for AD 20162514
For Model B0105LS A3 helicopters:
After accomplishing the replacement specified in paragraph 1 of EASA AD 2019
0024 all of the actions required by AD 2016
1514 are terminated for that helicopter only.
k Special Flight Permit Special flight permits, as described in 14
CFR 21.197 and 21.199, are not allowed.
l Alternative Methods of Compliance AMOCs 1 The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Validation Branch, send it to the attention of the person identified in paragraph m of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
2 Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/
certificate holding district office.
m Related Information For more information about this AD, contact Blaine Williams, Aviation Safety Engineer, Los Angeles ACO Branch, 3960
Paramount Boulevard, Lakewood, CA 90712
4137; telephone 5626275371; email blaine.williams@faa.gov.

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