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Federal Register / Vol. 86, No. 172 / Thursday, September 9, 2021 / Rules and Regulations
Related Service Information Under 1
CFR Part 51
The FAA reviewed Britten-Norman Aircraft Limited Service Bulletin Number SB 363, Issue 3, dated May 23, 2018, and Service Bulletin Number SB
364, Issue 3, dated May 23, 2018. For the applicable airplane models identified on each document, this service information contains procedures for repetitively inspecting the rudder final drive rod assembly and replacing the rudder final drive assembly, if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in ADDRESSES.

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Costs of Compliance The FAA estimates that this AD
affects 76 airplanes of U.S. registry. The FAA also estimates that inspecting the rudder final drive assembly will take about 1 work-hour. The average labor rate is $85 per work-hour.
Based on these figures, the FAA
estimates the cost of this AD on U.S.
operators to be $6,460, or $85 per airplane, each inspection cycle.
In addition, the FAA estimates that any necessary follow-on actions to replace the rudder final drive assembly will take about 5 work-hours and require parts costing $1,200, for a cost of $1,625 per airplane. The FAA has no way of determining the number of airplanes that may need these actions.
Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more detail the scope of the Agencys authority.
The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA
with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds 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
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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:

20211801 BN Group Ltd.: Amendment 3921702; Docket No. FAA20210502;
Project Identifier 2018CE043AD.
a Effective Date This airworthiness directive AD is effective October 14, 2021.
b Affected ADs None.
c Applicability This AD applies to BN Group Ltd. Models BN2, BN2A, BN2A2, BN2A3, BN2A
6, BN2A8, BN2A9, BN2A20, BN2A
21, BN2A26, BN2A27, BN2B20, BN
2B21, BN2B26, BN2B27, BN2T, and BN2T4R airplanes, all serial numbers, certificated in any category, with a rudder final drive rod part number P/N NB45
0991 installed.
d Subject Joint Aircraft System Component JASC
Code 2720, Rudder Control System.
e Unsafe Condition This AD was prompted by mandatory continuing airworthiness information MCAI
originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI

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describes the unsafe condition as failure of the rudder final drive rod because of cracks in the region of the taper pins. The FAA is issuing this AD to detect and correct defects on the rudder final drive rod assembly to prevent failure of the assembly. The unsafe condition, if not addressed, could result in loss of rudder control and reduced airplane control.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Inspection and Corrective Action 1 Inspect the rudder final drive rod assembly for loose taper pins, loose end connections, bending, and cracks within the applicable compliance times for your airplane specified in paragraph g1i or ii of this AD.
i For Models BN2, BN2A, BN2A2, BN2A3, BN2A6, BN2A8, BN2A9, BN2A20, BN2A21, BN2A26, BN2A
27, BN2B20, BN2B21, BN2B26, and BN2B27 airplanes, within 100 hours timein-service TIS after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours TIS.
ii For Models BN2T and BN2T4R
airplanes, within 200 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours TIS.
2 If a loose taper pin, a loose end connection, any bending, or a crack is found during any inspection required by paragraph g1 of this AD, before further flight, replace the rudder final drive rod assembly by following section 7, Removal and Installation Instructions for Unserviceable Units, of Britten-Norman Service Bulletin Number SB
363, Issue 3, dated May 23, 2018 SB 363, Issue 3 or Britten-Norman Service Bulletin Number SB 364, Issue 3, dated May 23, 2018
SB 364, Issue 3, as applicable to your model airplane.
3 If no loose taper pins, no loose end connections, no bending, and no cracks are found during the initial inspection required by paragraph g1 of this AD, review the airplane maintenance records to determine whether any taper pins have been replaced or reworked on the rudder final drive rod assembly. If a taper pin has ever been replaced or reworked, without exceeding the initial compliance time in paragraph g1i or ii of this AD, replace the rudder final drive rod assembly by following section 7, Removal and Installation Instructions for Unserviceable Units, of SB 363, Issue 3 or SB
364, Issue 3, as applicable to your model airplane.
4 As of the effective date of this AD, do not install a rudder final drive rod assembly P/N NB450991 on any airplane unless:
i The rudder final drive rod assembly is unused zero hours TIS; or ii The taper pins in the rudder final drive rod assembly have never been replaced.
5 As of the effective date of this AD, do not replace any taper pin on a rudder final drive rod assembly P/N NB450991
installed on any airplane.

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