Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 7029 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2022–02–07 Airbus Canada Limited 

Partnership (Type Certificate Previously 

Held by C Series Aircraft Limited 

Partnership (CSALP); Bombardier, Inc.): 

Amendment 39–21904; Docket No. 

FAA–2021–0444; Project Identifier 

MCAI–2020–01601–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 15, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Canada Limited 

Partnership (type certificate previously held 

by C Series Aircraft Limited Partnership 

(CSALP); Bombardier, Inc.) Model BD–500– 

1A10 and BD–500–1A11 airplanes, 

certificated in any category, as identified in 

Transport Canada Civil Aviation (TCCA) AD 

CF–2019–19R1, issued November 1, 2019 

(TCCA AD CF–2019–19R1). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports of wear 

damage found between the bonding clamps 

and the fuel feed tubes inside the left- and 

right-hand fuel tanks. In one incident, the 

wear damage resulted in a hole in the main 

engine fuel feed tube located in the collector 

tank, and subsequent fuel imbalance during 

flight. The FAA is issuing this AD to address 

failure of certain fuel feed tubes, which could 

lead to a severe fuel imbalance or fuel 

starvation of one engine, or in the event of 

the failure of multiple fuel tubes feeding both 

engines, could result in an in-flight 

shutdown of both engines. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, TCCA AD CF–2019–19R1. 

(h) Exceptions to TCCA AD CF–2019–19R1 

(1) Where TCCA AD CF–2019–19R1 refers 

to the effective date of TCCA AD CF–2019– 

19 (May 27, 2019), this AD requires using the 

effective date of this AD. 

(2) Where TCCA AD CF–2019–19R1 refers 

to its effective date, this AD requires using 

the effective date of this AD. 

(3) Where TCCA AD CF–2019–19R1 refers 

to hours air time, this AD requires using 

flight hours. 

(4) Where TCCA AD CF–2019–19R1 

specifies rectifying ‘‘any noted discrepancy,’’ 

for this AD discrepancies are ‘‘damage, 

cracks, scores, scratches, nicks, and gouges.’’ 

(i) No Reporting Requirement 

Although the service information 

referenced in TCCA AD CF–2019–19R1 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 516– 

228–7300; fax: 516–794–5531. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, New York ACO Branch, 

FAA; or TCCA; or Airbus Canada Limited 

Partnership’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(k) Related Information 

For more information about this AD, 

contact Joseph Catanzaro, Aviation Safety 

Engineer, Airframe & Propulsion Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7366; fax 516–794–5531; 

email 9-avs-nyaco-cos@faa.gov. 

(l) 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) Transport Canada Civil Aviation (TCCA) 

AD CF–2019–19R1, issued November 1, 

2019. 

(ii) [Reserved] 

(3) For TCCA AD CF–2019–19R1, contact 

TCCA, Transport Canada National Aircraft 

Certification, 159 Cleopatra Drive, Nepean, 

Ontario K1A 0N5, Canada; telephone 888– 

663–3639; email AD-CN@tc.gc.ca; internet 

https://tc.canada.ca/en/aviation. 

(4) 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. 

(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 January 7, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–02546 Filed 2–7–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0835; Project 

Identifier AD–2021–00971–E; Amendment 

39–21906; AD 2022–02–09] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2021–11– 

15 for certain International Aero 

Engines AG (IAE) V2500 model turbofan 

engines. AD 2021–11–15 required 

performance of an ultrasonic inspection 

(USI) of the high-pressure turbine (HPT) 

1st-stage disk and HPT 2nd-stage disk 

and, depending on the results of the 

inspections, replacement of the HPT 1ststage disk or HPT 2nd-stage disk. Since 

the FAA issued AD 2021–11–15, the 

FAA determined the need to clarify the 

compliance time for inspection of any 

HPT 1st-stage disk or HPT 2nd-stage 

disk that is installed on a low-thrust 

model engine but had been previously 

operated on a high-thrust model engine. 

This AD requires performance of a USI 

of the HPT 1st-stage disk and HPT 2ndstage disk and, depending on the results 

of the inspections, replacement of the 

HPT 1st-stage disk or HPT 2nd-stage 

disk. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective March 15, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 15, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of July 13, 2021 (86 FR 

30380, June 8, 2021). 


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7030 Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 

ADDRESSES: For service information 

identified in this final rule, contact 

International Aero Engines AG, 400 

Main Street, East Hartford, CT 06118; 

phone: (800) 565–0140; email: help24@

prattwhitney.com; website: https://

connect.prattwhitney.com. You may 

view this referenced 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 (817) 222–5110. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0835. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0835; 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, 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: 

Alberto Hernandez, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7329; fax: (781) 238– 

7199; email: Alberto.J.Hernandez@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2021–11–15, 

Amendment 39–21577 (86 FR 30380, 

June 8, 2021), (AD 2021–11–15). AD 

2021–11–15 applied to all IAE V2522– 

A5, V2524–A5, V2525–D5, V2527–A5, 

V2527E–A5, V2527M–A5, V2528–D5, 

V2530–A5, V2531–E5, and V2533–A5 

model turbofan engines with a certain 

HPT 1st-stage disk or HPT 2nd stage 

disk installed. The NPRM published in 

the Federal Register on October 28, 

2021 (86 FR 59658). The NPRM was 

prompted by the FAA determining the 

need to clarify the compliance time for 

inspection of any HPT 1st-stage disk or 

HPT 2nd-stage disk that is installed on 

a V2500 low-thrust model engine but 

that had been previously operated on a 

V2500 high-thrust model engine. The 

manufacturer categorizes V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, 

and V2533–A5 model turbofan engines 

as high-thrust model engines and 

V2522–A5, V2524–A5, V2525–D5, and 

V2527–A model turbofan engines as 

low-thrust model engines. The FAA 

determined that any HPT 1st-stage disk 

and HPT 2nd-stage disk that was 

operated on a high-thrust model engine 

must follow shortened compliance 

thresholds. In the NPRM, the FAA 

proposed to require the performance of 

a USI of the HPT 1st-stage disk and HPT 

2nd-stage disk and, depending on the 

results of the inspections, replacement 

of the HPT 1st-stage disk or HPT 2ndstage disk. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

two commenters. Commenters included 

Air Line Pilots Association, 

International and United Airlines 

Engineering. All commenters supported 

the NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes, this AD is adopted as proposed 

in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed IAE NonModification Service Bulletin (NMSB) 

No. V2500–ENG–72–0713, Revision 1, 

dated January 26, 2021. This NMSB 

identifies the affected HPT 1st-stage 

disks and HPT 2nd-stage disks on IAE 

V2522–A5, V2524–A5, V2525–D5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 

model turbofan engines and specifies 

procedures for a USI of the HPT 1ststage disk and HPT 2nd-stage disk. The 

Director of the Federal Register 

approved IAE NMSB V2500–ENG–72– 

0713, Revision 1, dated January 26, 2021 

for incorporation by reference as of July 

13, 2021 (86 FR 30380, June 8, 2021). 

The FAA also reviewed IAE NMSB 

No. V2500–E5–72–0015, Revision 1, 

dated August 10, 2021. This NMSB 

identifies the affected HPT 1st-stage 

disks and HPT 2nd-stage disks on IAE 

V2531–E5 model turbofan engines and 

specifies procedures for a USI of the 

HPT 1st-stage disk and HPT 2nd-stage 

disk. 

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 1,100 engines installed on 

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 

product 

Cost on U.S. 

operators 

USI the HPT 1st-stage disk and HPT 2ndstage disk.20 work-hours × $85 per hour = $1,700 ........ $0 $1,700 $1,870,000 

The FAA estimates the following 

costs to do any necessary replacement 

that is required based on the results of 

the inspection. The agency has no way 

of determining the number of aircraft 

that might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace the HPT 1st-stage disk or HPT 2nd-stage 

disk.

0 work-hours × $85 per hour = $0 ............................... $300,000 $300,000 


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Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 7031 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this AD may be covered under 

warranty, thereby reducing the cost 

impact on affected individuals. 

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: 

■ a. Removing Airworthiness Directive 

2021–11–15, Amendment 39–21577 (86 

FR 30380, June 8, 2021); and 

■ b. Adding the following new 

airworthiness directive: 

2022–02–09 International Aero Engines 

AG: Amendment 39–21906; Docket No. 

FAA–2021–0835; Project Identifier AD– 

2021–00971–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 15, 2022. 

(b) Affected ADs 

This AD replaces AD 2021–11–15, 

Amendment 39–21577 (86 FR 30380, June 8, 

2021) (AD 2021–11–15). 

(c) Applicability 

This AD applies to International Aero 

Engines AG (IAE) V2522–A5, V2524–A5, 

V2525–D5, V2527–A5, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, V2531– 

E5, and V2533–A5 model turbofan engines 

with an installed: 

(1) High-pressure turbine (HPT) 1st-stage 

disk, part number (P/N) 2A5001, with a serial 

number (S/N) listed in Appendix A, Table 1, 

of IAE Non-Modification Service Bulletin 

(NMSB) No. V2500–ENG–72–0713, Revision 

1, dated January 26, 2021 (IAE NMSB V2500– 

ENG–72–0713, Revision 1) or IAE NMSB No. 

V2500–E5–72–0015, Revision 1, dated 

August 10, 2021 (IAE NMSB V2500–E5–72– 

0015, Revision 1); or 

(2) HPT 2nd-stage disk, P/N 2A4802, with 

an S/N listed in Appendix A, Table 2, of IAE 

NMSB V2500–ENG–72–0713, Revision 1, or 

IAE NMSB V2500–E5–72–0015, Revision 1. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by an analysis 

performed by the manufacturer after an event 

involving an uncontained failure of a HPT 

1st-stage disk that resulted in high-energy 

debris penetrating the engine cowling. The 

FAA is issuing this AD to prevent failure of 

the HPT 1st-stage disk and HPT 2nd-stage 

disk. The unsafe condition, if not addressed, 

could result in uncontained HPT disk failure, 

damage to the engine, damage to the airplane, 

and loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For IAE V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 model 

turbofan engines with an HPT 1st-stage disk, 

P/N 2A5001, with an S/N listed in Appendix 

A, Table 1, of IAE NMSB V2500–ENG–72– 

0713, Revision 1, within the compliance time 

specified in Figure 1 to paragraph (g)(1) of 

this AD, or within 10 flight cycles (FCs) after 

the effective date of this AD, whichever 

occurs later, perform an ultrasonic inspection 

(USI) of the HPT 1st-stage disk using the 

Accomplishment Instructions, paragraph 6, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1. 

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

required by paragraphs (g)(1) through (6) of 

this AD requires the HPT 1st-stage disk and 

HPT 2nd-stage disks to be removed from the 

engine allowing piece-part opportunity 

inspections. Per the Airworthiness 

Limitations Section of the manufacturer’s 

Instructions for Continued Airworthiness, the 

additional inspections are not required 

unless the part has more than 100 FCs since 

the last piece-part opportunity inspection, is 

damaged, or is the cause for the removal of 

the engine. Engine removal for the purposes 

of complying with this AD is not ‘‘cause’’ for 


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A 

B 

Figure 1 to Paragraph (g)(l)-Inspection threshold 

Compliance time: Whichever occurs first, Row A or B 

At the next engine shop visit after July 13, 2021 (the effective date of AD 

2021-11-15) 

Before the HPT 1st-stage disk or HPT 2nd-stage disk has accumulated 3,200 

FCs since July 13, 2021 
7032 Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 

removal as stated in the Airworthiness 

Limitations Section. 

(2) For IAE V2527E–A5, V2527M–A5, 

V2528–D5, V2530–A5, and V2533–A5 model 

turbofan engines with an HPT 2nd-stage disk, 

P/N 2A4802, with an S/N listed in Appendix 

A, Table 2, of IAE NMSB V2500–ENG–72– 

0713, Revision 1, within the compliance time 

specified in Figure 1 to paragraph (g)(1) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later, 

perform a USI of the HPT 2nd-stage disk 

using the Accomplishment Instructions, 

paragraph 7, of IAE NMSB V2500–ENG–72– 

0713, Revision 1. 

(3) For IAE V2522–A5, V2524–A5, V2525– 

D5, and V2527–A5 model turbofan engines 

with an HPT 1st-stage disk, P/N 2A5001, 

with an S/N listed in Appendix A, Table 1, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1, within the following compliance 

times, perform a USI of the HPT 1st-stage 

disk using the Accomplishment Instructions, 

paragraph 6, of IAE NMSB V2500–ENG–72– 

0713, Revision 1: 

(i) If the affected HPT 1st-stage disk has not 

operated at any time in an IAE V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, or 

V2533–A5 model turbofan engine, perform 

the inspection within the compliance time 

specified in Figure 2 to paragraph (g)(3)(i) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later; or 

(ii) If the affected HPT 1st-stage disk has 

operated at any time in an IAE V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, or 

V2533–A5 model turbofan engine, perform 

the inspection within the compliance time 

specified in Figure 1 to paragraph (g)(1) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later. 

(4) For IAE V2522–A5, V2524–A5, V2525– 

D5, and V2527–A5 model turbofan engines 

with an HPT 2nd-stage disk, P/N 2A4802, 

with an S/N listed in Appendix A, Table 2, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1, within the following compliance 

times, perform a USI of the HPT 2nd-stage 

disk using the Accomplishment Instructions, 

paragraph 7, of IAE NMSB V2500–ENG–72– 

0713, Revision 1: 

(i) If the affected HPT 2nd-stage disk has 

not operated at any time in an IAE V2527E– 

A5, V2527M–A5, V2528–D5, V2530–A5, or 

V2533–A5 model turbofan engine, perform 

the inspection within the compliance time 

specified in Figure 2 to paragraph (g)(3)(i) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later; or 

(ii) If the affected HPT 2nd-stage disk has 

operated at any time in an IAE V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, or 

V2533–A5 model turbofan engine, perform 

the inspection within the compliance time 

specified in Figure 1 to paragraph (g)(1) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later. 

(5) For IAE V2531–E5 model turbofan 

engines with an HPT 1st-stage disk, P/N 

2A5001, with an S/N listed in Appendix A, 

Table 1, of IAE NMSB V2500–E5–72–0015, 

Revision 1, within the compliance time 

specified in Figure 1 to paragraph (g)(1) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later, 

perform a USI of the HPT 1st-stage disk using 

the Accomplishment Instructions, paragraph 

6, of IAE NMSB V2500–E5–72–0015, 

Revision 1. 

(6) For IAE V2531–E5 model turbofan 

engines with an HPT 2nd-stage disk, P/N 

2A4802, with an S/N listed in Appendix A, 

Table 2, of IAE NMSB V2500–E5–72–0015, 

Revision 1, within the compliance time 

specified in Figure 1 to paragraph (g)(1) of 

this AD, or within 10 FCs after the effective 

date of this AD, whichever occurs later, 

perform a USI of the HPT 2nd-stage disk 

using the Accomplishment Instructions, 

paragraph 7, of IAE NMSB V2500–E5–72– 

0015, Revision 1. 

(7) If, during the USI required by 

paragraphs (g)(1) through (6) of this AD, an 

HPT 1st-stage disk or HPT 2nd-stage disk 

does not pass the inspection as specified in 

the Accomplishment Instructions, paragraph 

8, of IAE NMSB V2500–ENG–72–0713, 

Revision 1, or IAE NMSB V2500–E5–72– 

0015, Revision 1, as applicable, before further 

flight, remove the HPT 1st-stage disk or HPT 

2nd-stage disk, as applicable, from service 

and replace with a part eligible for 

installation. 

(h) Definitions 

(1) For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, H–P, except for the following 

situations, which do not constitute an engine 

shop visit. 

(i) Separation of engine flanges solely for 

the purposes of transportation without 

subsequent engine maintenance. 

(ii) Engine removal for the purpose of 

performing field maintenance activities at a 

maintenance facility in lieu of performing 

them on-wing. 

(2) For the purpose of this AD, a ‘‘part 

eligible for installation’’ is: 

(i) An HPT 1st-stage disk or HPT 2nd-stage 

disk listed in Appendix A, Tables 1 and 2, 

of IAE NMSB V2500–ENG–72–0713, 

Revision 1, or Appendix A, Tables 1 and 2, 

of IAE NMSB V2500–E5–72–0015, Revision 

1, that passed the USI required by paragraphs 

(g)(1) through (6) of this AD; or 

(ii) An HPT 1st-stage disk or HPT 2nd-stage 

disk that is not listed in Appendix A, Tables 

1 and 2, of IAE NMSB V2500–ENG–72–0713, 

Revision 1, or Appendix A, Tables 1 and 2, 

of IAE NMSB V2500–E5–72–0015, Revision 

1. 

(i) Credit for Previous Actions 

You may take credit for the USI of the HPT 

1st-stage disk and HPT 2nd-stage disk 

required by paragraphs (g)(5) and (6) of this 

AD and the replacement of the HPT 1st-stage 

disk and HPT 2nd-stage disk required by 

paragraph (g)(7) of this AD, if you performed 

these actions before the effective date of this 

AD in accordance with IAE NMSB No. 

V2500–E5–72–0015, original issue, dated 

December 15, 2020. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 (k) of this AD. You 

may email your request to: ANE-AD-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. 

(k) Related Information 

For more information about this AD, 

contact Alberto Hernandez, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7329; fax: (781) 238–7199; email: 

Alberto.J.Hernandez@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 


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A 

B 

Figure 2 to Paragraph (g)(3)(i) - Inspection threshold 

Compliance time: Whichever occurs first, Row A or B 

At the next HPT rotor and stator assembly (HPT module) removal after July 

13, 2021 (the effective date of AD 2021-11-15) 

Before the HPT 1st-stage disk or HPT 2nd-stage disk has accumulated 6,700 

FCs since July 13, 2021 
Federal Register / Vol. 87, No. 26 / Tuesday, February 8, 2022 / Rules and Regulations 7033 

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. 

(3) The following service information was 

approved for IBR on March 15, 2022. 

(i) International Aero Engines AG (IAE) 

Non-Modification Service Bulletin (NMSB) 

No. V2500–E5–72–0015, Revision 1, dated 

August 10, 2021. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on July 13, 2021 (86 FR 

30380, June 8, 2021). 

(i) IAE NMSB No. V2500–ENG–72–0713, 

Revision 1, dated January 26, 2021. 

(ii) [Reserved] 

(5) For service information identified in 

this AD, contact International Aero Engines 

AG, 400 Main Street, East Hartford, CT 

06118; phone: (800) 565–0140; email: 

help24@prattwhitney.com; website: https://

connect.prattwhitney.com. 

(6) You may view this referenced 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 (817) 222–5110. 

(7) 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 January 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–02574 Filed 2–7–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0501; Project 

Identifier MCAI–2021–00168–T; Amendment 

39–21908; AD 2022–02–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–20– 

10, which applied to certain Airbus SAS 

Model A318 series airplanes; Model 

A319–111, –112,–113, –114, –115, –131, 

–132, and –133 airplanes; Model A320– 

211, –212, –214, –216, –231, –232, and 

–233 airplanes; and Model A321–111, 

–112, –131, –211, –212, –213, –231, and 

–232 airplanes. AD 2019–20–10 

required repetitive rototest inspections 

of the holes at the door stop fittings for 

any cracking, and corrective actions if 

necessary. Since the FAA issued AD 

2019–20–10, a clarification of a certain 

compliance time for the rototest 

inspection was added. This AD clarifies 

a certain compliance time and continues 

to require repetitive rototest inspections 

of the holes at the door stop fittings for 

any cracking, and repair if necessary, 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 March 15, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 15, 2022. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, 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 this IBR 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, 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–2021–0501. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0501; 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: 

Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223; email 

Sanjay.Ralhan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2018– 

0289R1, dated February 10, 2021 (EASA 

AD 2018–0289R1) (also referred to as 

the MCAI), to correct an unsafe 

condition for certain Airbus SAS Model 

A318 series airplanes; Model A319–111, 

–112, –113, –114, –115, –131, –132, and 

–133 airplanes; Model A320–211, –212, 

–214, –215, –216, –231, –232, and –233 

airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes. EASA AD 2018–0289R1 

supersedes EASA AD 2018–0289 (which 

corresponds to FAA AD 2019–20–10, 

Amendment 39–19763 (84 FR 61526, 

November 13, 2019) (AD 2019–20–10). 

Model A320–215 airplanes are not 

certificated by the FAA and are not 

included on the U.S. type certificate 

data sheet; this AD therefore does not 

include those airplanes in the 

applicability. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–20–10. 

AD 2019–20–10 applied to certain 

Airbus SAS Model A318 series 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The NPRM published in the Federal 

Register on June 16, 2021 (86 FR 31989). 

The NPRM was prompted by a report 

that cracks were detected on frame 

(FR)16 and FR20 web holes and 

passenger door intercostal fitting holes 

at the door stop fitting locations, and a 

determination that a certain compliance 

time needs to be clarified. The NPRM 

proposed to clarify a certain compliance 

time and continue to require repetitive 

rototest inspections of the holes at the 

door stop fittings for any cracking, and 

repair if necessary as specified in EASA 

AD 2018–0289R1. 

The FAA is issuing this AD to address 

cracking of the web holes at the door 

stop fittings, which could affect the 

structural integrity of the airplane. See 

the MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

two commenters, including Delta 

Airlines (DAL) and United Airlines 

(UAL). The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 


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