30408 Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 

this AD or within 400 hours time-in-service 

(TIS) after the last inspection required by AD 

89–24–06 R1, whichever occurs later, and 

thereafter at intervals not to exceed 400 hours 

TIS; or 

(ii) For Model DHC–6–400 airplanes, 

before further flight after the effective date of 

this AD and thereafter at intervals not to 

exceed 400 hours TIS. 

Note 1 to paragraph (g)(1): The elevator 

quadrant may be identified as part number 

(P/N) C6CFM1138–27 (Pre Mod 6/1394), P/N 

C6CFM1450–27 (Post Mod 6/1394 or 

production cut-in (PCI) serial number (S/N) 

331, Pre Mod 6/1678), or P/N C6CFM1450– 

29 (Post Mod 6/1678 or PCI S/N 602), and is 

referred to as assembly P/N C6CF1137–1, –3, 

–5, or –7. 

(2) If any indication of distortion is found 

on the elevator quadrant during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, replace the 

elevator quadrant with a serviceable part and 

inspect the elevator quadrant support bracket 

assembly for cracks by following paragraphs 

III.B.1. through III.B.4.(b) of the 

Accomplishment Instructions in DHC–6 SB 

6–511, Revision A. This AD requires that you 

do a fluorescent penetrant inspection as the 

type of required dye penetrant inspection. If 

a crack is found in the elevator quadrant 

support bracket, before further flight, replace 

with a serviceable part by following 

paragraphs III.B.5 through III.B.12 of the 

Accomplishment Instructions in DHC–6 SB 

6–511, Revision A. 

(3) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes: 

Within 400 hours TIS after the effective date 

of this AD, unless already done within the 

preceding 12 months before the effective date 

of this AD, inspect the elevator quadrant 

support bracket assembly for cracks by 

following paragraphs III.B.1. through 

III.B.4.(b) of the Accomplishment 

Instructions in DHC–6 SB 6–511, Revision A. 

This AD requires that you do a fluorescent 

penetrant inspection as the type of required 

dye penetrant inspection. If a crack is found 

in the elevator quadrant support bracket, 

before further flight, replace with a 

serviceable part by following paragraphs 

III.B.5 through III.B.12 of the 

Accomplishment Instructions in DHC–6 SB 

6–511, Revision A. 

(h) Credit for Previous Actions 

(1) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes: This 

paragraph provides credit for the inspection 

required by paragraph (g)(1) of this AD if you 

performed the inspection before the effective 

date of this AD using paragraph (a)(1) of AD 

89–24–06 R1. 

(2) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes: This 

paragraph provides credit for the fluorescent 

penetrant inspection and subsequent 

replacement of the elevator quadrant support 

bracket due to a crack found from the 

fluorescent penetrant inspection required by 

paragraph (g)(2) of this AD if performed 

before the effective date of this AD using 

paragraphs (a)(3) and (4) of AD 89–24–06 R1. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, New York ACO 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 paragraph (j)(1) of 

this AD. 

(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Darren Gassetto, Aviation Safety 

Engineer, New York ACO Branch, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, NY 

11590; phone: (516) 228–7323; email: 9-avsnyaco-cos@faa.gov. 

(2) Refer to Transport Canada AD CF– 

1972–06R5, dated June 22, 2018, for more 

information. You may examine the Transport 

Canada AD at https://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2022–0099. 

(k) 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) Viking DHC–6 (Twin Otter) Service 

Bulletin 6–511, Revision A, dated June 22, 

1990. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Viking Air Ltd., 1959 de 

Havilland Way, Sidney British Columbia, 

Canada V8L 5V5; phone: (800) 663–8444; 

email: continuing.airworthiness@

vikingair.com; website: https://

www.vikingair.com. 

(4) 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 (817) 222–5110. 

(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 May 5, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–10758 Filed 5–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0217; Project 

Identifier MCAI–2020–01486–A; Amendment 

39–22041; AD 2022–10–03] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate Previously 

Held by Bombardier, Inc. and de 

Havilland, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Viking Air Limited (type certificate 

previously held by Bombardier, Inc. and 

de Havilland, Inc.) Model DHC–6–1, 

DHC–6–100, DHC–6–200, DHC–6–300, 

and DHC–6–400 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 loose quadrants on the 

rudder pedal torque tube and signs of 

loose rivets or rivet joint wear due to 

inadequate manufacturing tolerances. 

This AD requires inspecting the rudder 

pedal torque tube quadrant for looseness 

and taking corrective action as 

necessary. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective June 23, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 23, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Viking Air Ltd., 1959 de Havilland Way, 

Sidney British Columbia, Canada V8L 

5V5; phone: (800) 663–8444; email: 

continuing.airworthiness@

vikingair.com; website: https://

www.vikingair.com. 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 (817) 222–5110. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0217. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 


jspears on DSK121TN23PROD with RULES1
Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 30409 

searching for and locating Docket No. 

FAA–2021–0217; 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: 

Deep Gaurav, Aviation Safety Engineer, 

New York ACO Branch, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; phone: (516) 228–7300; 

email: deep.gaurav@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 certain serial-numbered Viking 

Air Limited Model DHC–6–1, DHC–6– 

100, DHC–6–200, DHC–6–300, and 

DHC–6–400 airplanes. The NPRM 

published in the Federal Register on 

February 7, 2022 (87 FR 6802). The 

NPRM was prompted by MCAI 

originated by Transport Canada, which 

is the aviation authority for Canada. 

Transport Canada has issued AD CF– 

2020–45R1, dated April 16, 2021 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition on Viking 

Air Limited Model DHC–6 series 1, 

DHC–6 series 100, DHC–6 series 110, 

DHC–6 series 200, DHC–6 series 210, 

DHC–6 series 300, DHC–6 series 310, 

DHC–6 series 320, and DHC–6 series 

400 airplanes, serial numbers 001 

through 987. The MCAI states: 

There have been in-service reports of loose 

quadrants on the rudder pedal torque tube 

and signs of loose rivets or rivet joint wear, 

such as dark areas or streaks around the rivet 

heads and quadrant to torque tube interface. 

Viking Air Ltd. has determined that 

inadequate manufacturing tolerances may 

result in this condition. This defect, if not 

detected and corrected, could result in the 

affected parts deteriorating until the rivets 

fail, leading to loss of control of the rudder 

and possible loss of control of the aeroplane. 

To detect and correct this condition, 

[Transport Canada] AD CF–2020–45 

mandated a one-time detailed inspection of 

the rudder pedal torque tube quadrant 

assembly, and rectification, as required, of 

the affected parts. 

Viking Air Ltd. had published Service 

Bulletin (SB) V6/0067, Revision NC, dated 16 

July 2020, providing Accomplishment 

Instructions for the one-time detailed 

inspection for looseness of the affected parts. 

Since [Transport Canada] AD CF–2020–45 

was issued, Viking Air Ltd. has introduced a 

new rudder pedal torque tube assembly in 

production that is not subject to the unsafe 

condition of this [Transport Canada] AD. As 

a result, Viking Air Ltd. has revised the SB 

V6/0067 at Revision A, dated 26 January 

2021 (referred to as ‘‘the SB’’ in this 

[Transport Canada] AD) to update the 

aeroplane serial number applicability. 

This [Transport Canada] AD revision, CF– 

2020–45R1, is issued to modify the aeroplane 

serial number applicability in accordance 

with the SB. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0217. 

In the NPRM, the FAA proposed to 

require inspecting the rudder pedal 

torque tube quadrant for looseness and 

taking corrective action as necessary. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received one comment from 

the Airline Pilots Association, 

International (ALPA). ALPA supported 

the NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, 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. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Viking DHC–6 

Twin Otter Service Bulletin V6/0067, 

Revision A, dated January 26, 2021. 

This service information specifies 

procedures for inspecting the rudder 

pedal torque tube quadrant for looseness 

and performing a detailed visual 

inspection of the rudder torque tube 

assembly for signs of loose rivets or rivet 

joint wear. 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 the 

ADDRESSES section. 

Other Related Service Information 

The FAA also reviewed Viking DHC– 

6 Twin Otter Service Bulletin V6/0067, 

Revision NC, dated July 16, 2020. This 

service information specifies procedures 

for inspecting the rudder pedal torque 

tube quadrant for looseness and visually 

inspecting for signs of loose or smoking 

rivets. 

Differences Between This AD and the 

MCAI 

The MCAI applies to Viking Air 

Limited Model DHC–6 series 110, DHC– 

6 series 210, DHC–6 series 310, and 

DHC–6 series 320 airplanes, and this AD 

would not because these models do not 

have an FAA type certificate. Transport 

Canada Models DHC–6 series 1, DHC– 

6 series 100, DHC–6 series 200, DHC–6 

series 300, and DHC–6 series 400 

airplanes correspond to FAA Model 

DHC–6–1, DHC–6–100, DHC–6–200, 

DHC–6–300, and DHC–6–400 airplanes, 

respectively. 

Costs of Compliance 

The FAA estimates that this AD 

affects 33 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

airplane 

Cost on U.S. 

operators 

Inspection ....................................... 1 work-hour × $85 per hour = $85 Not Applicable ................................ $85 $2,805 

The FAA estimates the following 

costs to replace the rudder pedal torque 

tube quadrant assembly based on the 

results of the inspection. The agency has 

no way of determining the number of 

airplanes that might need this 

replacement: 


jspears on DSK121TN23PROD with RULES1
30410 Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

airplane 

Rudder pedal torque tube quadrant assembly replacement.10 work-hours × $85 per hour = $850 ......................... $9,256 $10,106 

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: 

2022–10–03 Viking Air Limited (Type 

Certificate Previously Held by 

Bombardier, Inc. and de Havilland, 

Inc.): Amendment 39–22041; Docket No. 

FAA–2021–0217; Project Identifier 

MCAI–2020–01486–A. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 23, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Viking Air Limited 

(type certificate previously held by 

Bombardier, Inc. and de Havilland, Inc.) 

Model DHC–6–1, DHC–6–100, DHC–6–200, 

DHC–6–300, and DHC–6–400 airplanes, 

serial numbers 001 through 987, certificated 

in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2700, Flight 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 

identifies the unsafe condition as loose 

quadrants on the rudder pedal torque tube 

and signs of loose rivets or rivet joint wear 

due to inadequate manufacturing tolerances. 

The FAA is issuing this AD to detect and 

correct loose rivets or rivet joint wear and 

signs of loose or smoking rivets. The unsafe 

condition, if not addressed, could result in 

the rudder pedal torque tube quadrant 

assembly deteriorating until the rivets fail, 

leading to loss of rudder control with 

consequent loss of airplane control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Action 

Within 3 months after the effective date of 

this AD, inspect the rudder pedal torque tube 

quadrant assembly for looseness and, if there 

is any looseness of the rudder pedal torque 

tube quadrant assembly, a loose rivet, any 

rivet joint wear, or a smoking rivet, before 

further flight, repair or replace the rudder 

pedal torque tube or quadrant assembly. Do 

these actions by following the 

Accomplishment Instructions, steps A.1. 

through A.9., in Viking DHC–6 Twin Otter 

Service Bulletin No. V6/0067, Revision A, 

dated January 26, 2021, except for any 

requirement to obtain repair instructions 

from Viking Customer Support, the repair 

must be accomplished using a method 

approved by the Manager, New York ACO 

Branch, FAA; Transport Canada; or Viking 

Air Limited’s Transport Canada Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(h) Credit for Previous Actions 

You may take credit for the actions 

required by paragraph (g) of this AD if you 

performed those actions before the effective 

date of this AD using Viking DHC–6 Twin 

Otter Service Bulletin V6/0067, Revision NC, 

dated July 16, 2020. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, New York ACO 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 address identified in paragraph (j)(1) of 

this AD. 

(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Deep Gaurav, Aviation Safety 

Engineer, New York ACO Branch, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, NY 

11590; phone: (516) 228–7300; email: 

deep.gaurav@faa.gov. 

(2) Refer to Transport Canada AD CF– 

2020–45R1, dated April 16, 2021, for related 

information. You may examine the Transport 

Canada AD in the AD docket at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2021–0217. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (4) of this AD. 


jspears on DSK121TN23PROD with RULES1
Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 30411 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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) Viking DHC–6 Twin Otter Service 

Bulletin V6/0067, Revision A, dated January 

26, 2021. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Viking Air Ltd., 1959 de 

Havilland Way, Sidney British Columbia, 

Canada V8L 5V5; phone: (800) 663–8444; 

email: continuing.airworthiness@

vikingair.com; website: https://

www.vikingair.com. 

(4) 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 (817) 222–5110. 

(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 April 30, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–10760 Filed 5–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1004; Project 

Identifier MCAI–2021–00480–E; Amendment 

39–22030; AD 2022–09–10] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (Type 

Certificate Previously Held by RollsRoyce plc) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) RB211 Trent 875–17, 877–17, 

884–17, 884B–17, 892–17, 892B–17, and 

895–17 model turbofan engines. This 

AD was prompted by findings during 

engine overhaul of corrosion on the lowpressure compressor (LPC) front case 

assembly. This AD requires inspection 

of the LPC front case assembly and, 

depending on the result of the 

inspection, accomplishment of the 

applicable corrective action(s), as 

specified in a European Union Aviation 

Safety Agency (EASA) 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 June 23, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 23, 2022. 

ADDRESSES: For material incorporated 

by reference in this AD, contact EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +49 221 8999 

000; email: ADs@easa.europa.eu. You 

may find this material on the EASA 

website at https://ad.easa.europa.eu. 

You may view this material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (817) 222– 

5110. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

1004. For RRD service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, DE24 8BJ, United 

Kingdom; phone: +44 (0)1332 242424 

fax: +44 (0)1332 249936; website: 

https://www.rolls-royce.com/contactus.aspx. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1004; 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 EASA AD, 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: 

Nicholas Paine, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7116; email: 

nicholas.j.paine@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0114, 

dated April 23, 2021 (EASA AD 2021– 

0114), to address an unsafe condition 

for certain RRD RB211 Trent 875–17, 

877–17, 884–17, 884B–17, 892–17, 

892B–17, and 895–17 model turbofan 

engines. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to RRD RB211 Trent 875–17, 877– 

17, 884–17, 884B–17, 892–17, 892B–17, 

and 895–17 model turbofan engines. 

The NPRM published in the Federal 

Register on November 16, 2021 (86 FR 

63319). The NPRM was prompted by 

findings during engine overhaul of 

corrosion on the LPC front case 

assembly caused by excessive 

movement between the Kevlar wrap and 

the fan case, which resulted in the anticorrosion paint fretting away. In the 

NPRM, the FAA proposed to require the 

performance of all required actions 

within the compliance times specified 

in, and in accordance with EASA AD 

2021–0114, except for any differences 

identified as exceptions in the 

regulatory text of this AD and except as 

discussed under ‘‘Differences Between 

this Proposed AD and the EASA AD.’’ 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

See EASA AD 2021–0114 for additional 

background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

three commenters. The commenters 

were American Airlines (American), 

The Boeing Company (Boeing), and 

Rolls-Royce plc (RR). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Request To Revise Applicability 

American requested that the FAA 

revise paragraph (c), Applicability, of 

this AD to replace ‘‘as identified in 

EASA AD 2021–0114’’ with ‘‘RB211 

Trent 875–17, 877–17, 884–17, 884B– 

17, 892–17, 892B–17 and 895–17 

engines with Low Pressure (LP) 

Compressor front (fan) case assemblies 

having Part Number (P/N) FK33097, P/ 

N FK26850, P/N FK26853, P/N 

FK26915, P/N FK26692 or P/N 

FK28577.’’ American stated that certain 

engines identified in the EASA AD 

applicability section have already 

performed rework on the LPC front case 

assembly to provide additional 

corrosion protection using RR RB211 

Trent 800 Series Propulsion Systems 

Service Bulletin (SB) RB.211–72–G634 


jspears on DSK121TN23PROD with RULES1