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.

Rules and Regulations Federal Register

50449 

Vol. 86, No. 172 

Thursday, September 9, 2021 

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: info@

bnaircraft.com; website: https://brittennorman.com/approvals-technicalpublications/. 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: penelope.trease@faa.gov. 

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. (BrittenNorman 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. 


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50450 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. 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 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 timein-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. 


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

AVS-AIR-730-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. 

(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: 

penelope.trease@faa.gov. 

(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: info@bnaircraft.com; website: 

https://britten-norman.com/approvalstechnical-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: fr.inspection@nara.gov, 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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0459; Project 

Identifier MCAI–2021–00129–T; Amendment 

39–21697; AD 2021–17–14] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Gulfstream Aerospace LP Model 

Gulfstream G280 airplanes. This AD was 

prompted by a report that during fullscale fatigue testing, a crack was found 

in the area of the attachment of the wing 

rib 0 to the front spar. This AD requires 

non-destructive testing on the forward 

(front) spar vertical stiffener and rib 0 

for any cracking, installation of a 

doubler to the forward (front) spar and 

rib 0 attachment, and repair if 

necessary, as specified in a Civil 

Aviation Authority of Israel (CAAI) AD, 

which is incorporated by reference. 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 material incorporated 

by reference (IBR) in this AD, contact 

the CAAI, P.O. Box 1101, Golan Street, 

Airport City, 70100, Israel; telephone 

972–3–9774665; fax 972–3–9774592; 

email aip@mot.gov.il. You may find this 

IBR material on the CAAI website at 

https://www.caa.gov.il. You may view 

this material at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available in 

the AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0459. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0459; 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 mandatory continuing 

airworthiness information (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: Tom 

Rodriguez, Aerospace Engineer, Large 

Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3226; email 

Tom.Rodriguez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The CAAI, which is the aviation 

authority for Israel, has issued CAAI AD 

I–57–2020–06–01, dated January 27, 

2021 (CAAI AD I–57–2020–06–01) (also 

referred to as the MCAI), to correct an 

unsafe condition for certain Gulfstream 

Aerospace LP Model Gulfstream G280 

airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Gulfstream Aerospace 

LP Model Gulfstream G280 airplanes. 

The NPRM published in the Federal 

Register on June 10, 2021 (86 FR 30819). 

The NPRM was prompted by a report 

that during full-scale fatigue testing, a 

crack was found in the area of the 

attachment of the wing rib 0 to the front 

spar. The NPRM proposed to require 

non-destructive testing on the forward 

(front) spar vertical stiffener and rib 0 

for any cracking, installation of a 

doubler to the forward (front) spar and 

rib 0 attachment, and repair if 

necessary, as specified in CAAI AD I– 

57–2020–06–01. 

The FAA is issuing this AD to address 

any cracking at the area of the wing rib 

0 to the front spar, which could affect 

the structural integrity of the wing. See 

the MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the cost to the public. 


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