[Federal Register Volume 86, Number 120 (Friday, June 25, 2021)]
[Proposed Rules]
[Pages 33576-33579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-13463]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0502; Project Identifier 2018-CE-043-AD]
RIN 2120-AA64


Airworthiness Directives; B-N Group Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain 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 
proposed AD results from 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 
proposed AD would require repetitively inspecting the rudder final 
drive rod assembly and replacing the rudder final drive assembly, if 
necessary. The FAA is proposing this AD to address the unsafe condition 
on these products.

DATES: The FAA must receive comments on this proposed AD by August 9, 
2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

[[Page 33577]]

    For service information identified in this NPRM, 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: [email protected]; 
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.

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 NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

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: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2021-0502; Project Identifier 
2018-CE-043-AD'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Penelope Trease, Aviation Safety Engineer, General Aviation & 
Rotorcraft Section, International Validation Branch, FAA, 26805 E 68th 
Avenue, Denver, CO 80249. Any commentary that the FAA receives which is 
not specifically designated as CBI will be placed in the public docket 
for this rulemaking.

Background

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0153, dated July 19, 2018 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for 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.

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.

FAA's Determination

    This product has been approved by the aviation authority of another 
country and is approved for operation in the United States. Pursuant to 
our 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 is issuing this NPRM 
after determining the unsafe condition described previously is likely 
to exist or develop on other products of the same type design.

Proposed AD Requirements in This NPRM

    This AD requires accomplishing the actions specified in the service 
information already described.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 76 airplanes of U.S. registry. The FAA also estimates that 
inspecting the rudder final drive assembly would take about 1 work-hour 
at the average labor rate of $85 per work-hour.
    Based on these figures, the FAA estimates the cost of this proposed 
AD on U.S. operators to be $6,460, or $85 per product, each inspection 
cycle.
    In addition, the FAA estimates that any necessary follow-on actions 
to replace the rudder final drive assembly would take about 5 work-
hours and require parts costing $1,200, for a cost of $1,625 per 
product. 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

[[Page 33578]]

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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would 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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

B-N Group Ltd.: Docket No. FAA-2021-0502; Project Identifier 2018-
CE-043-AD.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by August 9, 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.
    (4) 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.
    (5) 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.
    (6) 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.

(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: 
[email protected].
    (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: [email protected].
    (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.
    (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: 
[email protected]; website: https://britten-norman.com/approvals-technical-publications/. You may review this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 901 Locust, Kansas City, MO

[[Page 33579]]

64106. For information on the availability of this material at the 
FAA, call (816) 329-4148.

    Issued on June 11, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-13463 Filed 6-24-21; 8:45 am]
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