24404 Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 

email: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on April 15, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–08797 Filed 4–25–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0102; Project 

Identifier MCAI–2021–00841–R; Amendment 

39–22024; AD 2022–09–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

airworthiness directive (AD) for 2021– 

05–05 which applied to all Airbus 

Helicopters Model SA–365N1, AS– 

365N2, AS 365 N3, SA–366G1, EC 155B, 

and EC155B1 helicopters. AD 2021–05– 

05 required modifying the helicopter by 

replacing the tail rotor gearbox (TGB) 

control shaft guide bushes; repetitive 

inspections (checks) of the oil level of 

the TGB and, if necessary, filling the oil 

to the maximum level; repetitive 

inspections of the TGB magnetic plug 

and corrective actions if necessary; 

repetitive replacements of a certain 

control rod double bearing (bearing); 

and modifying the helicopter by 

replacing the TGB. This AD was 

prompted by a report where during a 

landing phase, a helicopter lost tail rotor 

pitch control, which was caused by 

significant damage to the TGB bearing. 

This AD retains some of the 

requirements of AD 2021–05–05, and 

reduces the intervals of the magnetic 

plug inspection, revises the corrective 

actions if particles are detected, and 

revises the compliance time for 

replacement of the affected part, 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 May 31, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 31, 2022. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find the 

EASA material on the EASA website at 

https://ad.easa.europa.eu. For Airbus 

Helicopters and Eurocopter service 

information identified in this final rule, 

contact Airbus Helicopters, 2701 North 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at https:// 

www.airbus.com/helicopters/services/ 

technical-support.html. You may view 

this material at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. For information 

on the availability of this material at the 

FAA, call (817) 222–5110. Service 

information that is IBRed is also 

available in the AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0102. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0102; 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: Hal 

Jensen, Aerospace Engineer, Operational 

Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 

L’Enfant Plaza N SW, Washington, DC 

20024; telephone (202) 267–9167; email 

hal.jensen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2021–05–05, 

Amendment 39–21448 (86 FR 13972, 

March 12, 2021) (AD 2021–05–05). AD 

2021–05–05 applied to all Airbus 

Helicopters Model SA–365N1, AS– 

365N2, AS 365 N3, SA–366G1, EC 155B, 

and EC155B1 helicopters. AD 2021–05– 

05 required repetitive checks of the oil 

level of the TGB and if necessary, filling 

the oil to the maximum level. AD 2021– 

05–05 also required modifying the 

helicopter by replacing the TGB control 

shaft guide bushes; repetitive 

inspections of the TGB magnetic plug 

and corrective actions if necessary; 

repetitive replacements of the bearing; 

and modifying the helicopter by 

replacing the TGB. The NPRM 

published in the Federal Register on 

February 18, 2022 (87 FR 9277). The 

NPRM was prompted by a report where 

during a landing phase, a helicopter lost 

tail rotor pitch control, which was 

caused by significant damage to the TGB 

bearing. The NPRM was also prompted 

by the determination that reduced 

inspection intervals, updated corrective 

actions, and a revised compliance time 

for replacement of affected parts are 

necessary to address the unsafe 

condition. Furthermore, the FAA 

determined that the magnetic plug 

inspection interval must be reduced 

based on additional testing of the 

affected part by the manufacturer, and 

the compliance time for replacement of 

the affected part must be reduced. 

The NPRM proposed to retain certain 

actions in AD 2021–05–05; reduce the 

intervals of the magnetic plug 

inspection; revise the corrective actions 

if particles are detected; and revise the 

compliance time for replacement of the 

affected part. The NPRM also proposed 

to allow the oil level inspections 

(checks) to be performed by the owner/ 

operator (pilot) holding at least a private 

pilot certificate and must be entered 

into the aircraft records showing 

compliance with the proposed AD in 

accordance with 14 CFR 43.9 (a)(1) 

through (4) and 14 CFR 91.417(a)(2)(v). 

The record must be maintained as 

required by 14 CFR 91.417 or 135.439. 

The NPRM was prompted by EASA 

AD 2021–0171, dated July 19, 2021 

(EASA AD 2021–0171), issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for Airbus Helicopters (AH), formerly 

Eurocopter (EC), Eurocopter France, 

Aerospatiale, Sud Aviation, Model SA 

365 N1, AS 365 N2, AS 365 N3, EC 155 

B, and EC 155 B1 helicopters, all serial 

numbers. 

The FAA is issuing this AD to prevent 

damage to the bearing, which if not 

addressed, could result in loss of yaw 

control of the helicopter. See EASA AD 

2021–0171 for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 


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Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 24405 

Conclusion 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about the unsafe condition 

described in its AD. 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 helicopters. This AD 

is adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0171 specifies 

procedures for modifying the helicopter 

by replacing TGB control shaft guide 

bushes, and specifies procedures for 

repetitive inspections of the oil level of 

the TGB, and if necessary, filling the oil 

to the maximum level. EASA AD 2021– 

0171 also describes procedures for 

repetitive inspections of the TGB 

magnetic plug for the presence of 

particles and updated corrective actions 

if necessary (corrective actions include 

removing the TGB; complying with 

certain work cards to address any 

particles found, and other conditions 

such as abrasions, scales, flakes, and 

splinters; placing the helicopter under 

close monitoring; and if required 

replacing any affected bearing); initial 

and repetitive replacements of the 

bearing with an improved part; and 

modifying the helicopter by replacing 

the TGB bearing or replacing the TGB. 

EASA AD 2021–0171 specifies replacing 

the TGB bearing is a terminating action 

for the repetitive inspections of the 

magnetic plug; and replacing the TGB is 

a terminating action for the repetitive 

inspections of the magnetic plug, and 

the repetitive replacements of the 

bearing. EASA AD 2021–0171 also 

prohibits installing a certain bearing or 

a certain TGB on any helicopter. 

This material 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 reviewed Airbus Helicopters 

Alert Service Bulletin No. AS365– 

01.00.67 (ASB AS365–01.00.67 Rev 6) 

and Airbus Helicopters Alert Service 

Bulletin No. EC155–04A014 (ASB 

EC155–04A014 Rev 6), both Revision 6, 

and both dated June 14, 2021. ASB 

AS365–01.00.67 Rev 6 and ASB EC155– 

04A014 Rev 6 both specify procedures 

for replacement of the TGB bearing 

before mod 07 65B63 installation, 

inspection of the TGB magnetic plug, 

removing the control shaft/rod assembly 

to inspect the bearing, and maintaining 

the TGB operating oil at the maximum 

level, and specify the monitoring 

criteria of the bearing. 

The FAA also reviewed Eurocopter 

Service Bulletin AS365 No. 65.00.17, 

and Eurocopter Service Bulletin EC155 

No. 65–006, both Revision 1 and both 

dated February 23, 2011. Both service 

bulletins specify instructions for 

introducing Eurocopter (EC) mod 07 

65B58. 

Differences Between This AD and EASA 

AD 2021–0171 

EASA AD 2021–0171 revises the 

applicability by removing the reference 

to Model SA 366 G1 helicopters because 

the EASA type certificate has been 

surrendered. However, Model SA– 

366G1 helicopters are still on the U.S. 

type certificate data sheet, even though 

there are no current U.S. operators. 

Therefore, this AD includes Model SA– 

366G1 helicopters. 

Costs of Compliance 

The FAA estimates that this AD 

affects 50 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR RETAINED REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

fleet 

Replace guide bushes ............ 4.00 work-hours × $85 per hour = $340 ........ $1,586 $1,926 per replacement ......... $96,300 

Daily oil level inspection ......... 1.00 work-hour × $85 per hour = $85 ............ 0 $85 per inspection cycle ........ 4,250 

Recurring plug inspection ....... 1.00 work-hour × $85 per hour = $85 ............ 0 $85 per inspection cycle ........ 4,250 

Inspect bearing ....................... 8.00 work-hours × $85 per hour = $680 ........ 0 $680 per inspection ............... 34,000 

Replace bearing ..................... 48.00 work-hours × $85 per hour = $4,080 ... 377 $4,457 per replacement ......... 222,850 

Replace TGB .......................... 8.00 work-hours × $85 per hour = $680 ........ 155,302 $155,982 per replacement ..... 7,799,100 

This AD does not add new required 

actions; however, the compliance times 

for certain actions have been reduced 

and a certain on-condition action has 

been revised. 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per product 

Up to 4 work-hours $85 per hour = $340 ............................................... Up to $1,395 .................................. Up to $1,735. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. The 

FAA does not control warranty coverage 

for affected individuals. As a result, the 

FAA has included all costs in the cost 

estimate. 

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. 


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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: 

■ a. Removing Airworthiness Directive 

(AD) 2021–05–05, Amendment 39– 

21448 (86 FR 13972, March 12, 2021); 

and 

■ b. Adding the following new AD: 

2022–09–04 Airbus Helicopters: 

Amendment 39–22024; Docket No. 

FAA–2022–0102; Project Identifier 

MCAI–2021–00841–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 31, 2022. 

(b) Affected ADs 

This AD replaces AD 2021–05–05, 

Amendment 39–21448 (86 FR 13972, March 

12, 2021) (AD 2021–05–05). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model SA–365N1, AS–365N2, AS 365 N3, 

SA–366G1, EC 155B, and EC155B1 

helicopters, all serial numbers, certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 6500, Tail Rotor Drive System. 

(e) Unsafe Condition 

This AD was prompted by a report where 

during a landing phase, a helicopter lost tail 

rotor pitch control, which was caused by 

significant damage to the tail rotor gearbox 

(TGB) control rod double bearing (bearing). 

This AD was also prompted by the 

determination that reduced inspection 

intervals, updated corrective actions, and 

increased compliance time for replacement of 

affected parts are necessary to address the 

unsafe condition. The FAA is issuing this AD 

to prevent damage to the bearing, which if 

not addressed, could result in loss of yaw 

control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For Model SA–365N1, AS–365N2, AS 

365 N3, EC 155B, and EC155B1 helicopters: 

Except as specified in paragraph (h) of this 

AD, comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2021–0171, dated 

July 19, 2021 (EASA AD 2021–0171). 

(2) For Model SA–366G1 helicopters: 

Before further flight after the effective date of 

this AD, accomplish the actions (e.g., modify 

the helicopter by replacing the TGB control 

shaft guide bushes, do repetitive inspections 

of the TGB magnetic plug and applicable 

corrective actions; do repetitive replacements 

of a certain bearing; and modify the 

helicopter by replacing the TGB) specified in 

paragraph (g)(l) of this AD using a method 

approved by the FAA. 

(h) Exceptions to EASA AD 2021–0171 

(1) Where EASA AD 2021–0171 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2021–0171 refers to 

flight hours (FH), this AD requires using 

hours time-in-service. 

(3) Where EASA AD 2021–0171 requires 

action after the last flight of the day or 

‘‘ALF,’’ this AD requires those actions before 

the first flight of the day. 

(4) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0171. 

(5) Where paragraph (2) of EASA AD 2021– 

0171 requires inspections (checks) to be done 

‘‘in accordance with the instructions of 

Paragraph 3.B.1 of the applicable inspection 

ASB,’’ for this AD, those instructions are for 

reference only and are not required for the 

actions in paragraph (2) of EASA AD 2021– 

0171. The inspections (checks) required by 

paragraph (2) of EASA AD 2021–0171 may be 

performed by the owner/operator (pilot) 

holding at least a private pilot certificate and 

must be entered into the aircraft records 

showing compliance with this AD in 

accordance with 14 CFR 43.9 (a)(1) through 

(4) and 14 CFR 91.417(a)(2)(v). The record 

must be maintained as required by 14 CFR 

91.417 or 135.439. 

(6) Where paragraph (5) of EASA AD 2021– 

0171 specifies ‘‘if any discrepancy is 

detected, as defined in the applicable 

inspection ASB, before next flight, 

accomplish the applicable corrective 

action(s) in accordance with the instructions 

of Paragraph 3.B.1 of the applicable 

inspection ASB,’’ for this AD, a qualified 

mechanic must add oil to the TGB to the 

‘‘max’’ level if the oil level is not at 

maximum. The instructions are for reference 

only and are not required for the actions in 

paragraph (5) of EASA AD 2021–0171. 

(7) Where paragraph (6) of EASA AD 2021– 

0171 refers to ‘‘any discrepancy,’’ for this AD, 

discrepancies include the presence of 

particles and other conditions such as 

abrasions, scales, flakes, and splinters. 

(8) Where the service information referred 

to in EASA AD 2021–0171 specifies to 

perform a metallurgical analysis and contact 

the manufacturer if collected particles are not 

clearly characterized, this AD does not 

require contacting the manufacturer to 

determine the characterization of the 

particles collected. 

(9) Although service information 

referenced in EASA AD 2021–0171 specifies 

to scrap parts, this AD does not include that 

requirement. 

(10) Although service information 

referenced in EASA AD 2021–0171 specifies 

reporting information to Airbus Helicopters, 

filling in a ‘‘particle detection’’ follow-up 

sheet, and returning a ‘‘bearing monitoring 

sheet’’ to Airbus Helicopters, this AD does 

not include those requirements. 

(11) Although service information 

referenced in EASA AD 2021–0171 specifies 

returning certain parts to an approved 

workshop and returning certain parts to 

Airbus Helicopters, this AD does not include 

those requirements. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0171 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

provided that there are no passengers 

onboard. 

(k) 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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (l) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 


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Federal Register / Vol. 87, No. 80 / Tuesday, April 26, 2022 / Rules and Regulations 24407 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 L’Enfant 

Plaza N SW, Washington, DC 20024; 

telephone (202) 267–9167; email hal.jensen@

faa.gov. 

(m) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0171, dated July 19, 2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0171, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find the 

EASA material on the EASA website at 

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

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

This material may be found in the AD docket 

at https://www.regulations.gov by searching 

for and locating Docket No. FAA–2022–0102. 

(5) You may view this material 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/ibrlocations.html. 

Issued on April 14, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–08803 Filed 4–25–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1164; Project 

Identifier MCAI–2021–00975–E; Amendment 

39–22019; AD 2022–08–16] 

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 superseding 

Airworthiness Directive (AD) 2020–20– 

07 for certain Rolls-Royce Deutschland 

Ltd & Co KG (RRD) Trent 1000–AE3, 

Trent 1000–CE3, Trent 1000–D3, Trent 

1000–G3, Trent 1000–H3, Trent 1000– 

J3, Trent 1000–K3, Trent 1000–L3, Trent 

1000–M3, Trent 1000–N3, Trent 1000– 

P3, Trent 1000–Q3, Trent 1000–R3, 

Trent 7000–72, and Trent 7000–72C 

model turbofan engines. AD 2020–20– 

07 required initial and repetitive 

borescope inspections (BSIs) or visual 

inspections of the intermediate-pressure 

compressor (IPC) shaft assembly and, 

depending on the results of the 

inspection, replacement of the IPC shaft 

assembly. This AD was prompted by the 

manufacturer providing optional 

terminating actions for the required 

repetitive inspections and alternative 

inspection instructions. This AD 

continues to require initial and 

repetitive BSIs but allows modification 

of the engine in accordance with RRD 

service information as a terminating 

action to these inspections, 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 May 31, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 31, 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– 

1164. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1164; 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 2019– 

0282R1, dated August 25, 2021 (EASA 

AD 2019–0282R1), to address an unsafe 

condition for all RRD Trent 1000–AE3, 

Trent 1000–CE3, Trent 1000–D3, Trent 

1000–G3, Trent 1000–H3, Trent 1000– 

J3, Trent 1000–K3, Trent 1000–L3, Trent 

1000–M3, Trent 1000–N3, Trent 1000– 

P3, Trent 1000–Q3, Trent 1000–R3, 

Trent 7000–72, and Trent 7000–72C 

model turbofan engines. The EASA AD 

includes exceptions that limit the 

applicability for certain engines. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–20–07, 

Amendment 39–21263 (85 FR 62975, 

October 6, 2020), (AD 2020–20–07). AD 

2020–20–07 applied to all RRD Trent 

1000–AE3, Trent 1000–CE3, Trent 

1000–D3, Trent 1000–G3, Trent 1000– 

H3, Trent 1000–J3, Trent 1000–K3, 

Trent 1000–L3, Trent 1000–M3, Trent 

1000–N3, Trent 1000–P3, Trent 1000– 

Q3, Trent 1000–R3, Trent 7000–72, and 

Trent 7000–72C model turbofan 

engines. The NPRM published in the 

Federal Register on December 28, 2021 

(86 FR 73690). The NPRM was 

prompted by a report of crack findings 

in the front air seal on the IPC shaft 

assembly during the stripping of a flight 

test engine. The NPRM was also 

prompted by the manufacturer’s 

publication of service information that 

provides optional terminating actions 

for the required repetitive inspections 

and alternative inspection instructions. 

In the NPRM, the FAA proposed to 

continue to require initial and repetitive 

BSIs of the IPC shaft assembly. In the 

NPRM, the FAA also proposed to 

require compliance with the required 

actions from November 10, 2020, the 

effective date of AD 2020–20–07. In the 

NPRM, the FAA also proposed to allow 

modification of the engine in 

accordance with Rolls-Royce service 

information as a terminating action to 

the initial and repetitive BSIs of the IPC 

shaft assembly. In the NPRM, the FAA 

also proposed to require accomplishing 


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