[Federal Register Volume 86, Number 172 (Thursday, September 9, 2021)]
[Rules and Regulations]
[Pages 50449-50451]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-19302]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 86, No. 172 / Thursday, September 9, 2021 / 
Rules and Regulations

[[Page 50449]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0502; Project Identifier 2018-CE-043-AD; Amendment 
39-21702; AD 2021-18-01]
RIN 2120-AA64


Airworthiness Directives; B-N Group Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for B-N 
Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-
2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B-21, BN-
2B-26, BN-2B-27, BN-2T, and BN-2T-4R airplanes. 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 identifies the unsafe 
condition as failure of the rudder final drive rod because of cracks in 
the region of the taper pins. This AD requires repetitively inspecting 
the rudder final drive rod assembly and replacing the rudder final 
drive assembly, if necessary. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective October 14, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 14, 
2021.

ADDRESSES: For service information identified in this final rule, 
contact Britten-Norman Aircraft Limited, Commodore House, Mountbatten 
Business Centre, Millbrook Road East, Southampton SO15 1HY, United 
Kingdom; phone: + 44 20 3371 4000; fax: + 44 20 3371 4001; email: 
<a href="/cdn-cgi/l/email-protection#076e696168476569666e7564756661732964686a"><span class="__cf_email__" data-cfemail="f59c9b939ab5979b949c879687949381db969a98">[email protected]</span></a>; website: https://britten-norman.com/approvals-technical-publications/. You may view this service information at the 
FAA, Airworthiness Products Section, Operational Safety Branch, 901 
Locust, Kansas City, MO 64106. For information on the availability of 
this material at the FAA, call (816) 329-4148. It is also available at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-0502.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0502; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this final rule, the 
MCAI, any comments received, and other information. The address for 
Docket Operations is U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Penelope Trease, Aviation Safety 
Engineer, General Aviation & Rotorcraft Section, International 
Validation Branch, FAA, 26805 E 68th Avenue, Denver, CO 80249; phone: 
(303) 342-1094; email: <a href="/cdn-cgi/l/email-protection#26564348434a495643085254434755436640474708414950"><span class="__cf_email__" data-cfemail="bacadfd4dfd6d5cadf94cec8dfdbc9dffadcdbdb94ddd5cc">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to B-N Group Ltd. Models 
BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-
2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-
2T, and BN-2T-4R airplanes. The NPRM published in the Federal Register 
on June 25, 2021 (86 FR 33576). The NPRM was prompted by MCAI 
originated by the European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union. EASA has 
issued EASA AD 2018-0153, dated July 19, 2018 (referred to after this 
as ``the MCAI''), to address an unsafe condition on certain B-N Group 
Ltd. (Britten-Norman Aircraft Ltd., or ``BNA'') Models BN-2, BN-2A, BN-
2B, BN-2T, BN-2T-2, BN-2T-2R, and BN-2T-4R airplanes. The MCAI states:

    Occurrences have been reported of failures of the rudder final 
drive rod, [part number] P/N NB-45-0991. Cracks were found in the 
region of the taper pins. There is evidence that replacing the taper 
pins could be a significant factor contributing to the failure of 
this rod.
    This condition, if not detected and corrected, could lead to 
failure of the affected part, possibly resulting in reduced control 
of the aeroplane.
    To address this potential unsafe condition, BNA issued the 
applicable SB [service bulletin], providing inspection instructions. 
Prompted by operator comments, BNA revised the applicable SB (issue 
3) to introduce repetitive inspections.
    For the reason described above, this [EASA] AD requires 
repetitive inspections of the affected part and, depending on 
findings, replacement. This AD also prohibits replacement of taper 
pins on an affected part. BNA will amend the applicable Maintenance 
Manuals accordingly.

    You may examine the MCAI in the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0502.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs. Paragraphs (g)(3) and (4) of the NPRM have been combined 
into one paragraph, (g)(3) of the final rule, to make it clear that the 
action of paragraph (g)(4) of the NPRM is a follow-on action of 
paragraph (g)(3).

Conclusion

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
the FAA's bilateral agreement with this State of Design Authority, it 
has notified the FAA of the unsafe condition described in the MCAI and 
service information referenced above. The FAA reviewed the relevant 
data and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. This AD is adopted as proposed in the 
NPRM.

[[Page 50450]]

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.

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 FAA's 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 Agency's 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 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 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:

2021-18-01 B-N Group Ltd.: Amendment 39-21702; Docket No. FAA-2021-
0502; Project Identifier 2018-CE-043-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective October 14, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, 
BN-2A-3, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, 
BN-2A-27, BN-2B-20, BN-2B-21, BN-2B-26, BN-2B-27, BN-2T, and BN-2T-
4R airplanes, all serial numbers, certificated in any category, with 
a rudder final drive rod part number (P/N) NB-45-0991 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 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 
(g)(1)(i) or (ii) of this AD.
    (i) For Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN-2A-8, 
BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B-21, 
BN-2B-26, and BN-2B-27 airplanes, within 100 hours time-in-service 
(TIS) after the effective date of this AD and thereafter at 
intervals not to exceed 1,000 hours TIS.
    (ii) For Models BN-2T and BN-2T-4R 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 
(g)(1) 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 (g)(1) 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 (g)(1)(i) 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 NB-45-0991 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 NB-45-0991 
installed on any airplane.

[[Page 50451]]

(h) 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 certification office, send it to the 
attention of the person identified in Related Information or email: 
<a href="/cdn-cgi/l/email-protection#0f36224e595c224e465d22383c3f224e42404c4f696e6e21686079"><span class="__cf_email__" data-cfemail="b48d99f5e2e799f5fde69983878499f5f9fbf7f4d2d5d59ad3dbc2">[email protected]</span></a>.
    (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.

(i) Related Information

    (1) For more information about this AD, contact Penelope Trease, 
Aviation Safety Engineer, General Aviation & Rotorcraft Section, 
International Validation Branch, FAA, 26805 E 68th Avenue, Denver, 
CO 80249; phone: (303) 342-1094; email: <a href="/cdn-cgi/l/email-protection#f383969d969f9c8396dd878196928096b3959292dd949c85"><span class="__cf_email__" data-cfemail="5121343f343d3e21347f252334302234113730307f363e27">[email protected]</span></a>.
    (2) Refer to European Aviation Safety Agency (EASA) AD 2018-
0153, dated July 19, 2018, for more information. You may examine the 
EASA AD in the AD docket at https://www.regulations.gov by searching 
for and locating it in Docket No. FAA-2021-0502.

 (j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information listed in this 
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Britten-Norman Service Bulletin Number SB 363, Issue 3, 
dated May 23, 2018.
    (ii) Britten-Norman Service Bulletin Number SB 364, Issue 3, 
dated May 23, 2018.
    (3) For service information identified in this AD, contact 
Britten-Norman Aircraft Limited, Commodore House, Mountbatten 
Business Centre, Millbrook Road East, Southampton SO15 1HY, United 
Kingdom; phone: + 44 20 3371 4000; fax: + 44 20 3371 4001; email: 
<a href="/cdn-cgi/l/email-protection#cda4a3aba28dafa3aca4bfaebfacabb9e3aea2a0"><span class="__cf_email__" data-cfemail="4a23242c250a28242b233829382b2c3e64292527">[email protected]</span></a>; website: https://britten-norman.com/approvals-technical-publications/.
    (4) You may view this service information at FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas 
City, MO 64106. For information on the availability of this material 
at the FAA, call (816) 329-4148.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: <a href="/cdn-cgi/l/email-protection#086e7a2661667b786d6b7c6167664866697a69266f677e"><span class="__cf_email__" data-cfemail="88eefaa6e1e6fbf8edebfce1e7e6c8e6e9fae9a6efe7fe">[email protected]</span></a>, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on August 17, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-19302 Filed 9-8-21; 8:45 am]
BILLING CODE 4910-13-P


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