Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 49909 

cracks would take about 0.5 work-hours 

for an estimated cost of $43 per 

inspection cycle. 

Installing each plastic bushing, 

coating with compound, re-installing 

the bellcrank, and applying torque 

would take about 0.5 work-hours and 

parts would cost about $10 for an 

estimated cost of $53 per helicopter. 

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 helicopters 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: 

2021–19–04 He ́licopte`res Guimbal: 

Amendment 39–21722; Docket No. 

FAA–2021–0498; Project Identifier 

2019–SW–072–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 12, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to He ́licopte`res Guimbal 

(HG) Model Cabri G2 helicopters, certificated 

in any category, with any metal bushings 

installed on the main rotor (M/R) swashplate 

guide bellcrank and without plastic bushing 

part number HG22–1001 or HG modification 

16–009. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Rotorcraft Flight Control. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks on the M/R scissor link. The FAA is 

issuing this AD to replace the metal bushings 

installed on the M/R swashplate guide 

bellcrank with plastic bushings. The unsafe 

condition, if not addressed, could result in 

failure of the M/R swashplate guide bellcrank 

and reduced control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 50 hours time-in-service (TIS) or 

2 months, whichever occurs first after the 

effective date of this AD: 

(i) Disconnect the bellcrank from the 

swashplate guide by removing each bolt and, 

ensuring that the bellcrank remains attached 

to the flight control rod, remove each metal 

bushing from service using a bushing 

disassembly tool. 

(ii) Visually inspect the lug bore area for 

any corrosion and any cracks. If there is any 

corrosion or any cracks, before further flight, 

remove the swashplate guide from service or 

repair it using an FAA-approved method. If 

there is no corrosion and no cracks, install 

plastic bushing part number HG22–1001, 

coat plastic bushing with isolation 

compound, re-install the bellcrank, torque 

each bolt to 7.5 Nm–9 Nm (5.5 ft-lbs–6.6 ftlbs), and install cotter pins. 

(2) As of the effective date of this AD, do 

not install any metal bushing on any 

helicopter. 

(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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (i)(1) 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, 

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 Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave, Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2019–0185, dated July 30, 2019. 

You may view the EASA AD on the internet 

at https://www.regulations.gov in Docket No. 

FAA–2021–0498. 

(j) Material Incorporated by Reference 

None. 

Issued on August 30, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19037 Filed 9–3–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0497; Project 

Identifier 2019–SW–043–AD; Amendment 

39–21711; AD 2021–18–10] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bell Textron Canada Limited Model 429 

helicopters. This AD was prompted by 

three reports of unexpected forces or 

uncommanded inputs to the directional 

(yaw) control system. This AD requires 

revising the existing Rotorcraft Flight 


lotter on DSK11XQN23PROD with RULES1
49910 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 

Manual (RFM) for your helicopter. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective October 12, 

2021. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4, 

Canada; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or 

at https://www.bellcustomer.com. You 

may view the referenced 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0497; 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 Transport Canada AD, any 

comments received, and other 

information. The street 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: 

Mitch Soth, Flight Test Engineer, 

Southwest Section, Flight Test Branch, 

Compliance & Airworthiness Division, 

FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222– 

5110; email mitch.soth@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 Bell Textron Canada Limited 

Model 429 helicopters, serial numbers 

57001 and subsequent. The NPRM 

published in the Federal Register on 

July 7, 2021 (86 FR 35692). In the 

NPRM, the FAA proposed to require 

revising the existing RFM for your 

helicopter by adding procedures in 

Section 2, Normal Procedures, under 2– 

4. INTERIOR AND PRESTART CHECK, 

2–5. ENGINE START, and 2–8. 

TAKEOFF; Section 3, Emergency and 

Malfunction Procedures, under 3–9. 

AUTOMATIC FLIGHT CONTROL 

SYSTEM; and Section 4, Performance, 

under 4–2. POWER ASSURANCE 

CHECK. The owner/operator (pilot) may 

revise the existing RFM for your 

helicopter, and the owner/operator must 

enter compliance with the applicable 

paragraphs of the AD into the aircraft 

records in accordance with § 43.9(a)(1) 

through (4) and § 91.417(a)(2)(v). This is 

an exception to the FAA’s standard 

maintenance regulations. 

The NPRM was prompted by 

Transport Canada Emergency AD CF– 

2019–16, dated May 6, 2019 (Transport 

Canada AD CF–2019–16), issued by 

Transport Canada, which is the aviation 

authority for Canada to correct an 

unsafe condition for Bell Helicopter 

Textron Canada Limited (now Bell 

Textron Canada Limited) Model 429 

helicopters, serial numbers 57001 and 

subsequent. Transport Canada advises 

of three reports of unexpected forces or 

uncommanded inputs to the directional 

(yaw) control system during ground 

operations. Investigation revealed that a 

yaw trim runaway can occur while the 

automatic pedal trim function is 

operating. This condition, if not 

addressed, could result in loss of control 

of the helicopter. Accordingly, 

Transport Canada AD CF–2019–16 

requires revising Bell RFM BHT–429– 

FM–1 by incorporating revision 14, 

dated April 18, 2019. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received one comment from 

an individual who supported the NPRM 

without change. 

Conclusion 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified the FAA of the unsafe condition 

described in its AD. 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 helicopters. 

Related Service Information 

The FAA reviewed Section 2—Normal 

Procedures, Section 3—Emergency and 

Malfunction Procedures, and Section 

4—Performance, of Bell RFM BHT–429– 

FM–1, Revision 14, dated April 18, 

2019. This revision of the service 

information adds a procedure to reduce 

the risk of trim runaway during start 

sequence, cautions to reduce the risk of 

uncommanded control movement 

during engine start and takeoff and resetting force trim detent instructions 

during engine start and takeoff, and an 

emergency procedure to assist flight 

crew to recognize trim runaway and 

response instructions. 

Costs of Compliance 

The FAA estimates that this AD 

affects 120 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. 

Revising the existing RFM for your 

helicopter takes about 0.50 work-hour 

for an estimated cost of $43 per 

helicopter and $5,160 for the U.S. fleet. 

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 helicopters 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, 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 49911 

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: 

2021–18–10 Bell Textron Canada Limited: 

Amendment 39–21711; Docket No. 

FAA–2021–0497; Project Identifier 

2019–SW–043–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 12, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bell Textron Canada 

Limited Model 429 helicopters, certificated 

in any category, serial numbers 57001 and 

subsequent. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Control System. 

(e) Unsafe Condition 

This AD was prompted by three reports of 

unexpected forces or uncommanded inputs 

to the directional (yaw) control system. The 

FAA is issuing this AD to prevent yaw trim 

runaway. The unsafe condition, if not 

addressed, could result in loss of control of 

the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 30 days after the effective date 

of this AD, revise the existing Rotorcraft 

Flight Manual for your helicopter as follows: 

(i) In Section 2, Normal Procedures, under 

2–4. INTERIOR AND PRESTART CHECK, 

add the following as item 25: ‘‘25. Depress 

the cyclic force TRIM REL button and 

collective FORCE REL button (4-axis only) to 

center actuators and extinguish any active 

out of detent indications.’’ 

(ii) In Section 2, Normal Procedures, under 

2–5. ENGINE START and under 2–8. 

TAKEOFF, add the following above item 1: 

‘‘CAUTION: WHEN MANIPULATING 

FLIGHT CONTROLS WITH FORCE TRIM 

SELECTED ON, DO NOT RELEASE 

AFFECTED FLIGHT CONTROL UNTIL THE 

OUT OF DETENT INDICATION 

EXTINGUISHES. THE FLIGHT CONTROLS 

MAY BE RESET BY DEPRESSING THE 

CYCLIC FORCE TRIM REL BUTTON AND 

COLLECTIVE FORCE REL BUTTON (4–AXIS 

ONLY) UNTIL THE OUT OF DETENT 

INDICATION EXTINGUISHES.’’ 

(iii) In Section 3, Emergency and 

Malfunction Procedures, under 3–9. 

AUTOMATIC FLIGHT CONTROL SYSTEM, 

add the information in Figure 1 to paragraph 

(g)(1)(iii) of this AD as item 3–9–D: 

(iv) In Section 4, Performance, under 4–2. 

POWER ASSURANCE CHECK, add the 

following above the instructions for 

performing a power assurance check: 

‘‘CAUTION: WHEN MANIPULATING 

FLIGHT CONTROLS WITH FORCE TRIM 

SELECTED ON, DO NOT RELEASE 

AFFECTED FLIGHT CONTROL UNTIL THE 

OUT OF DETENT INDICATION 

EXTINGUISHES. THE FLIGHT CONTROLS 

MAY BE RESET BY DEPRESSING THE 

CYCLIC FORCE TRIM REL BUTTON AND 

COLLECTIVE FORCE REL BUTTON (4–AXIS 

ONLY) UNTIL THE OUT OF DETENT 

INDICATION EXTINGUISHES.’’ 

(2) Using a document with information 

identical to the information in paragraph 

(g)(1) of this AD is acceptable for compliance 


lotter on DSK11XQN23PROD with RULES1ER07SE21.000</MATH>

3-9-D. TRIM RUNAWAY 

• INDICATIONS: 

Flight controls - Uncommanded movement. 

Flight control forces - High in axis of uncommanded movement, 

normal in other axes. 

Out of detent indication for affected axis 

• PROCEDURE: 

1. Cyclic force TRIM REL and/or collective FORCE REL button 

( 4-axis only) - Depress until the out of detent indication extinguishes. 

2. Flight controls - Do not release flight control if out of detent 

indication is present. 

3. Force TRIM switch- OFF; check TRM OFF illuminates on PFD. 

4. IfIMC, land as soon as practical. IfVMC, continue flight in SCAS. 

Figure 1 to paragraph (g)(l )(iii) 
49912 Federal Register / Vol. 86, No. 170 / Tuesday, September 7, 2021 / Rules and Regulations 

with the actions required by paragraph (g)(1) 

of this AD. 

(3) The actions required by paragraphs 

(g)(1) and (2) of this AD 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 § 43.9(a)(1) 

through (4) and § 91.417(a)(2)(v). The record 

must be maintained as required by § 91.417, 

§ 121.380, or § 135.439. 

(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 International Validation 

Branch, send it to the attention of the person 

identified in paragraph (i)(1) 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, 

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 Mitch Soth, Flight Test Engineer, 

Southwest Section, Flight Test Branch, 

Compliance & Airworthiness Division, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

mitch.soth@faa.gov. 

(2) The subject of this AD is addressed in 

Transport Canada Emergency AD CF–2019– 

16, dated May 6, 2019. You may view the 

Transport Canada AD on the internet at 

https://www.regulations.gov in Docket No. 

FAA–2021–0497. 

(j) Material Incorporated by Reference 

None. 

Issued on August 26, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–19049 Filed 9–3–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0381; Project 

Identifier MCAI–2020–01656–E; Amendment 

39–21694; AD 2021–17–11] 

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 certain 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) Trent XWB–75, Trent XWB–79, 

Trent XWB–79B, and Trent XWB–84 

model turbofan engines. This AD was 

prompted by reports of cracks in the 

intermediate-pressure compressor (IPC) 

rotor 1 (R1) blades installed on certain 

Trent XWB model turbofan engines. 

This AD requires initial and repetitive 

borescope inspections (BSIs) of the 

affected IPC R1 blades and, depending 

on the results of the inspections, 

replacement of all 34 IPC R1 blades. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective October 12, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 12, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Rolls-Royce 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.rollsroyce.com/contact-us.aspx. You may 

view this service information 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 (781) 238– 

7759. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0381. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0381; 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: 

Kevin Clark, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7088; fax: (781) 238–7199; 

email: kevin.m.clark@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 RRD Trent XWB–75, 

Trent XWB–79, Trent XWB–79B, and 

Trent XWB–84 model turbofan engines. 

The NPRM published in the Federal 

Register on May 28, 2021 (86 FR 28716). 

The NPRM was prompted by reports of 

cracks in the IPC R1 blades installed on 

certain Trent XWB model turbofan 

engines. The NPRM proposed to require 

initial and repetitive BSIs of the affected 

IPC R1 blades and, depending on the 

results of the inspections, replacement 

of all 34 IPC R1 blades with parts 

eligible for installation. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

AD 2020–0277, dated December 11, 

2020 (referred to after this as ‘‘the 

MCAI’’), to address the unsafe condition 

on these products. The MCAI states: 

Occurrences have been reported of finding 

cracked IPC R1 blades on certain Trent XWB 

engines that were close to their first planned 

refurbishment shop visit. 

This condition, if not corrected, could lead 

to blade failure and consequent engine inflight shut-down (IFSD), possibly resulting in 

reduced control of the aeroplane. 

To address this potential unsafe condition 

and avoid dual engine IFSD, Rolls-Royce 

issued the inspection NMSB to provide 

inspection instructions and the NMSB to 

provide information on threshold and 

intervals. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the affected parts and, depending on 

findings, accomplishment of applicable 

corrective action(s). 

You may obtain further information 

by examining the MCAI in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0381. 


lotter on DSK11XQN23PROD with RULES1