42308 Federal Register / Vol. 87, No. 135 / Friday, July 15, 2022 / Rules and Regulations 

16 ‘‘Energy Conservation Standards Rulemaking 

Peer Review Report.’’ 2007. Available at 

www.energy.gov/eere/buildings/downloads/energyconservation-standards-rulemaking-peer-reviewreport-0. 

17The report is available at 

www.nationalacademies.org/our-work/review-ofmethods-for-setting-building-and-equipmentperformance-standards. 

development process and the analyses 

that are typically used and has prepared 

a Peer Review report pertaining to the 

energy conservation standards 

rulemaking analyses.16 Generation of 

this report involved a rigorous, formal, 

and documented evaluation using 

objective criteria and qualified and 

independent reviewers to make a 

judgment as to the technical/scientific/ 

business merit, the actual or anticipated 

results, and the productivity and 

management effectiveness of programs 

and/or projects. Because available data, 

models, and technological 

understanding have changed since 2007, 

DOE has engaged with the National 

Academy of Sciences to review DOE’s 

analytical methodologies to ascertain 

whether modifications are needed to 

improve the Department’s analyses. 

DOE is in the process of evaluating the 

resulting report.17

M. Congressional Notification 

As required by 5 U.S.C. 801, DOE will 

report to Congress on the promulgation 

of this final determination prior to its 

effective date. The report will state that 

it has been determined that the final 

determination is not a ‘‘major rule’’ as 

defined by 5 U.S.C. 804(2). 

VI. Approval of the Office of the 

Secretary 

The Secretary of Energy has approved 

publication of this final determination. 

List of Subjects in 10 CFR Part 430 

Administrative practice and 

procedure, Confidential business 

information, Energy conservation, 

Intergovernmental relations, Reporting 

and recordkeeping requirements, Small 

businesses. 

Signing Authority 

This document of the Department of 

Energy was signed on June 21, 2022, by 

Kelly J. Speakes-Backman, Principal 

Deputy Assistant Secretary for Energy 

Efficiency and Renewable Energy, 

pursuant to delegated authority from the 

Secretary of Energy. That document 

with the original signature and date is 

maintained by DOE. For administrative 

purposes only, and in compliance with 

requirements of the Office of the Federal 

Register, the undersigned DOE Federal 

Register Liaison Officer has been 

authorized to sign and submit the 

document in electronic format for 

publication, as an official document of 

the Department of Energy. This 

administrative process in no way alters 

the legal effect of this document upon 

publication in the Federal Register. 

Signed in Washington, DC, on June 22, 

2022. 

Treena V. Garrett, 

Federal Register Liaison Officer, U.S. 

Department of Energy. 

For the reasons stated in the 

preamble, DOE amends part 430 of 

Chapter II of Title 10, Code of Federal 

Regulations as set forth below: 

PART 430—ENERGY CONSERVATION 

PROGRAM FOR CONSUMER 

PRODUCTS 

■ 1. The authority citation for part 430 

continues to read as follows: 

Authority: 42 U.S.C. 6291–6309; 28 U.S.C. 

2461 note. 

■ 2. Section 430.2 is amended by adding 

in alphabetical order the definition of 

‘‘air cleaner’’ to read as follows: 

§ 430.2 Definitions. 

* * * * * 

Air cleaner means a product for 

improving indoor air quality, other than 

a central air conditioner, room air 

conditioner, portable air conditioner, 

dehumidifier, or furnace, that is an 

electrically-powered, self-contained, 

mechanically encased assembly that 

contains means to remove, destroy, or 

deactivate particulates, VOC, and/or 

microorganisms from the air. It excludes 

products that operate solely by means of 

ultraviolet light without a fan for air 

circulation. 

* * * * * 

[FR Doc. 2022–13655 Filed 7–14–22; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0384; Project 

Identifier AD–2022–00027–E; Amendment 

39–22122; AD 2022–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2021–14– 

06 for all Pratt & Whitney (PW) 

PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, PW1525G–3, PW1919G, 

PW1921G, PW1922G, PW1923G, and 

PW1923G–A model turbofan engines. 

AD 2021–14–06 required repetitive 

borescope inspections (BSI) of certain 

low-pressure compressor (LPC) rotor 1 

(R1) until replacement of electronic 

engine control (EEC) full authority 

digital electronic control (FADEC) 

software with updated software. AD 

2021–14–06 also required a BSI after 

installation of the updated EEC FADEC 

software if certain Onboard 

Maintenance Message fault codes are 

displayed and meet specified criteria. 

AD 2021–14–06 also required, 

depending on the results of the BSI, 

replacement of the LPC R1. Since the 

FAA issued AD 2021–14–06, the 

manufacturer redesigned the 

compressor intermediate case (CIC) 

assembly to incorporate a shortened 

bleed duct configuration and updated 

the EEC FADEC software. This AD 

continues to require repetitive BSI of 

certain LPC R1s until replacement of 

EEC FADEC software with updated 

software and also a BSI after installation 

of the updated EEC FADEC software if 

certain Onboard Maintenance Message 

fault codes are displayed and meet 

specified criteria. This AD continues to 

require, depending on the results of the 

BSI, replacement of the LPC R1. This 

AD also requires removal and 

replacement of the existing CIC 

assembly with a CIC assembly eligible 

for installation. The FAA is issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective August 19, 

2022. 

ADDRESSES: For service information 

identified in this final rule, contact Pratt 

& Whitney, 400 Main Street, East 

Hartford, CT 06118; phone: (800) 565– 

0140; email: help24@pw.utc.com; 

website: http://fleetcare.pw.utc.com. 

You may view this service information 

at the Airworthiness Products Section, 

FAA, 1200 District Avenue, Burlington, 

MA 01803. 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–2022–0384; 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 


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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: 

Mark Taylor, Aviation Safety Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

(781) 238–7229; email: Mark.Taylor@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2021–14–06, 

Amendment 39–21633 (86 FR 36061, 

July 8, 2021), (AD 2021–14–06). AD 

2021–14–06 applied to all PW 

PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, PW1525G–3, PW1919G, 

PW1921G, PW1922G, PW1923G, and 

PW1923G–A model turbofan engines. 

The NPRM published in the Federal 

Register on April 04, 2022 (87 FR 

19405). The NPRM was prompted by 

reports of inflight shutdowns due to 

failure of the LPC R1 and by subsequent 

findings of cracked LPC R1s during 

inspection. Additionally, the 

manufacturer redesigned the CIC 

assembly to incorporate a shortened 

bleed duct configuration. The shortened 

bleed duct addresses the unsafe 

condition by preventing the coincidence 

between bleed and the acoustic 

excitation. The manufacturer also 

updated the EEC FADEC software to 

provide compatibility with both current 

and future operation of engines and 

airplanes with the redesigned CIC 

assembly installed. In the NPRM, the 

FAA proposed to continue to require 

removal from service of certain EEC 

FADEC software and the installation of 

a software version eligible for 

installation. The NPRM proposed to 

require a BSI of LPC R1 for damage and 

cracks after replacing certain EEC 

FADEC software versions. The NPRM 

proposed to continue to require a BSI of 

LPC R1 after installation of an eligible 

EEC FADEC software version if certain 

Onboard Maintenance Message fault 

codes are displayed and meet specified 

criteria. The NPRM proposed to 

continue to require, depending on the 

results of the BSI, replacement of the 

LPC R1. The NPRM also proposed to 

require removal and replacement of 

certain CIC assemblies, identified by 

part number, with a CIC assembly 

eligible for installation. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

three commenters. The commenters 

were Air Line Pilots Association, 

International (ALPA), Delta Air Lines, 

Inc, (DAL), and an individual 

commenter. One commenter, ALPA, 

supported the proposal without change. 

Two commenters, DAL and an 

individual commenter, requested 

changes. The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 

Request To Revise the Required Action 

Proposed in Paragraph (g)(3) 

DAL requested that the FAA remove 

the following language as proposed in 

paragraph (g)(3) of the NPRM: ‘‘after 

installation of the EEC FADEC software 

version eligible for installation as 

required by paragraphs (g)(1) and (g)(2) 

of this AD.’’ DAL noted that this 

requirement would create an 

unnecessary restriction on when the BSI 

of the LPC R1 can be accomplished and 

may cause operators to perform a 

second BSI if the BSI of the LPC R1 was 

performed prior to the software upgrade. 

The FAA agrees and has revised 

paragraph (g)(3) of this AD as requested 

by DAL. 

DAL also requested that the FAA 

revise paragraph (g)(3) of this AD by 

changing the language from ‘‘For the 

model turbofan engines identified in 

paragraphs (g)(1) and (g)(2) . . .’’ to 

‘‘For the model turbofan engines 

identified in paragraphs (g)(1) or 

(g)(2). . . .’’ DAL noted that there is no 

overlap in turbofan engine models 

between paragraphs (g)(1) and (g)(2), 

thus it is not possible for an engine 

model to be identified in both 

paragraphs. 

The FAA disagrees with changing this 

AD as requested by DAL. Paragraph 

(g)(3) of this AD applies to the model 

turbofan engines identified in paragraph 

(g)(1) and the model turbofan engines 

identified in paragraph (g)(2). The FAA 

did not change the AD as a result of this 

comment. 

Request To Include Future Revisions to 

Service Information 

DAL requested that the FAA add ‘‘or 

later’’ to Note 1 to paragraph (g)(4) to 

allow for the use of future revisions to 

PW Service Bulletins (SBs) PW1000G– 

A–72–00–0125–00A–930A–D, Issue No. 

004, dated October 13, 2021, and 

PW1000G–A–72–00–0075–00B–930A– 

D, Issue No. 004, dated July 21, 2021. 

DAL noted that this would ensure that 

any LPC R1 serial numbers added in 

subsequent revisions to these SBs would 

be included in the applicability of this 

AD. DAL also requested that the FAA 

add ‘‘or later’’ to Note 2 to paragraph 

(g)(5) to allow for the use of future 

revisions to PW engine maintenance 

manual (EMM) PW1000G–A–72–00–00– 

02A–0B5A–A. DAL noted that this 

would ensure that any changes made to 

the guidance on determining N1 

exceedance duration would be 

applicable within the AD. DAL also 

requested that the FAA add ‘‘or later’’ to 

Note 3 to paragraph (g)(5) to allow for 

the use of future revisions to PW EMM 

PW1000G–A–72–31–00–00A–312A–D, 

Issue No. 017, dated March 19, 2021. 

DAL noted that this would ensure that 

any changes made to the guidance on 

performing the BSI of the LPC R1 will 

be applicable within the AD. DAL also 

requested that the FAA add a reference 

to A220 aircraft maintenance 

publication (AMP) Task BD500–A–J72– 

00–00–02AAA–0B5A–A to help ensure 

consistency across different manuals 

used by on-wing maintenance 

personnel. 

The FAA disagrees with adding ‘‘or 

later’’ to the service information 

referenced in notes to paragraph (g) of 

this AD. The use of notes in the 

regulatory text is for informational 

purposes only, and the use of this 

service information is not required by 

this AD, but may assist the operator 

while complying with this AD. 

Therefore, including future revisions of 

the service information referenced in 

the notes would not affect the 

applicability of this AD. Additionally, 

future revisions of the service 

information have not yet been published 

by the manufacturer or reviewed by the 

FAA. The FAA disagrees with the need 

to add reference to future PW EMM 

revisions within Note 2 to paragraph 

(g)(5) of this AD, as the currently cited 

documents provide the appropriate 

guidance. The FAA did not change the 

AD as a result of these comments. 

Request To Correct Reference to EEC 

FADEC Software Version 

DAL and an individual commenter 

requested that the FAA revise paragraph 

(h)(1) of this AD to change the EEC 

FADEC software version eligible for 

installation from version V2.11.12.4 to 

version V2.11.12.1. Both commenters 

noted that PW SB PW1000G–A–73–00– 

0052–00A–930A–D, Issue No. 001, 

dated October 7, 2021, defines EEC 

FADEC software version V2.11.12.1 as 

the software version that is eligible for 

installation on PW1519G, PW1521G, 

PW1521G–3, PW1521GA, PW1524G–3, 

PW1525G, and PW1525G–3 model 

turbofan engines. 


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The FAA agrees and has updated 

paragraph (h)(1) of this AD. 

Conclusion 

The FAA reviewed the relevant data, 

considered any 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, and any other changes 

described previously, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information 

The FAA reviewed PW SB PW1000G– 

A–73–00–0025–00B–930A–D, Issue No. 

001, dated November 23, 2021; PW SB 

PW1000G–A–72–00–0125–00A–930A– 

D, Issue No. 004, dated October 13, 

2021; PW SB PW1000G–A–72–00– 

0075–00B–930A–D, Issue No. 004, dated 

July 21, 2021; PW SB PW1000G–A–73– 

00–0052–00A–930A–D, Issue No. 001, 

dated October 7, 2021; PW SB 

PW1000G–A–72–00–0121–00B–930A– 

D, Issue No. 001, dated July 9, 2021; PW 

SB PW1000G–A–72–00–0175–00A– 

930A–D, Issue No. 001, dated July 1, 

2021. 

PW SB PW1000G–A–73–00–0025– 

00B–930A–D, Issue No. 001, dated 

November 23, 2021, describes 

procedures for replacing or modifying 

the EEC to incorporate EEC FADEC 

software version V9.6.5.6 in PW1919G, 

PW1921G, PW1922G, PW1923G, and 

PW1923G–A model turbofan engines. 

PW SBs PW1000G–A–72–00–0125– 

00A–930A–D, Issue No. 004, dated 

October 13, 2021, and PW1000G–A–72– 

00–0075–00B–930A–D, Issue No. 004, 

dated July 21, 2021, describe procedures 

for performing repetitive BSIs of LPC 

R1s. PW SB PW1000G–A–73–00–0052– 

00A–930A–D, Issue No. 001, dated 

October 7, 2021, describes procedures 

for replacing or modifying the EEC to 

incorporate EEC FADEC software 

version V2.11.12 in PW1519G, 

PW1521G, PW1521G–3, PW1521GA, 

PW1524G, PW1524G–3, PW1525G, 

PW1525G–3 model turbofan engines. 

PW SBs PW1000G–A–72–00–0121– 

00B–930A–D, Issue No. 001, dated July 

9, 2021, and PW1000G–A–72–00–0175– 

00A–930A–D, Issue No. 001, dated July 

1, 2021, describe procedures for 

replacing or modifying the CIC 

assembly. 

The FAA also reviewed Section 

PW1000G–A–72–00–00–02A–0B5A–A 

of PW EMM, Issue No. 016, dated 

January 15, 2021; and Section 

PW1000G–A–72–31–00–00A–312A–D 

of PW EMM, Issue No. 017, dated March 

19, 2021. Section PW1000G–A–72–00– 

00–02A–0B5A–A of PW EMM, Issue No. 

016, dated January 15, 2021, describes 

procedures for inspecting the engine for 

possible engine damage after receiving 

notification of an N1 or N2 overspeed 

operation. Section PW1000G–A–72–31– 

00–00A–312A–D of PW EMM, Issue No. 

017, dated March 19, 2021, describes 

procedures for performing a BSI of the 

LPC. 

Costs of Compliance 

The FAA estimates that this AD 

affects 114 engines installed on 

airplanes of U.S. registry. The FAA 

estimates that five percent of engines 

installed on airplanes of U.S. registry 

will require EEC FADEC software 

upgrade and BSI of the LPC R1. 

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 

Replace EEC FADEC software ...................... 2 work-hours × $85 per hour = $170 ............. $0 $170 $19,380 

BSI of the LPC R1 .......................................... 2 work-hours × $85 per hour = $170 ............. 0 170 969 

Replace CIC assembly ................................... 428 work-hours × $85 per hour = $36,380 .... 124,522 160,902 18,342,828 

The FAA estimates the following 

costs to do any necessary inspection if 

certain Onboard Maintenance Message 

fault codes are displayed or if any 

necessary replacement is required based 

on the results of the inspection. The 

agency has no way of determining the 

number of aircraft that might need these 

replacements or inspections: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace LPC R1 ............................ 40 work-hours × $85 per hour = 

$3,400.

$156,000 ....................................... $159,400 

BSI of the LPC R1 if Onboard 

Maintenance Message fault 

codes are displayed and meet 

specified criteria.

2 work-hours × $85 per hour = 

$170.

$0 .................................................. $170 

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. 


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Federal Register / Vol. 87, No. 135 / Friday, July 15, 2022 / Rules and Regulations 42311 

Regulatory Findings 

The FAA has determined that 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 

2021–14–06, Amendment 39–21633 (86 

FR 36061, July 8, 2021); and 

■ b. Adding the following new 

airworthiness directive: 

2022-15–03 Pratt & Whitney: Amendment 

39–22122; Docket No. FAA–2022–0384; 

Project Identifier AD–2022–00027–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 19, 2022. 

(b) Affected ADs 

This AD replaces AD 2021–14–06, 

Amendment 39–21633 (86 FR 36061, July 8, 

2021). 

(c) Applicability 

This AD applies to Pratt & Whitney 

PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, PW1525G–3, PW1919G, 

PW1921G, PW1922G, PW1923G, and 

PW1923G–A model turbofan engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by reports of inflight shutdowns due to failure of the lowpressure compressor (LPC) rotor 1 (R1) and 

by subsequent findings of cracked LPC R1s 

during inspection. The FAA is issuing this 

AD to prevent failure of the LPC R1. The 

unsafe condition, if not addressed, could 

result in an uncontained release of the LPC 

R1, 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 PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, and PW1525G–3 model turbofan 

engines with installed electronic engine 

control (EEC) full authority digital electronic 

control (FADEC) software earlier than EEC 

FADEC software version V2.11.10.4, before 

further flight, remove the EEC FADEC 

software and install EEC FADEC software 

version eligible for installation. 

(2) For PW1919G, PW1921G, PW1922G, 

PW1923G, and PW1923G–A model turbofan 

engines with installed EEC FADEC software 

earlier than EEC FADEC software version 

V9.5.6.7, before further flight, remove the 

EEC FADEC software and install EEC FADEC 

software version eligible for installation. 

(3) For the model turbofan engines 

identified in paragraphs (g)(1) and (g)(2) of 

this AD, before further flight, perform a onetime borescope inspection (BSI) of the LPC 

R1 for damage and cracks at the following 

LPC R1 locations: 

(i) The blade tip; 

(ii) The leading edge; 

(iii) The leading edge fillet to rotor 

platform radius; and 

(iv) The airfoil convex side root fillet to 

rotor platform radius. 

(4) Based on the results of the BSI required 

by paragraph (g)(3) of this AD, before further 

flight, remove and replace the LPC R1 if: 

(i) There is damage on an LPC R1 that 

exceeds serviceable limits; or 

(ii) Any crack in the LPC R1 exists. 

Note 1 to paragraph (g)(4): Guidance on 

determining the serviceable limits in 

paragraphs (g)(4) and (6) of this AD can be 

found in Pratt & Whitney (PW) Service 

Bulletin (SB) PW1000G–A–72–00–0125– 

00A–930A–D, Issue No. 004, dated October 

13, 2021, and PW SB PW1000G–A–72–00– 

0075–00B–930A–D, Issue No. 004, dated July 

21, 2021. 

(5) For PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, and PW1525G–3 model turbofan 

engines with EEC FADEC software version 

V2.11.10.4 or later installed, within 15 flight 

cycles after receipt of Onboard Maintenance 

Message fault code 7100F0029 or 7100F0030, 

perform a BSI of the LPC R1 for damage and 

cracks at the locations specified in paragraph 

(g)(3) of this AD if the fault code is displayed 

on the Active Failure Messages and meets the 

following criteria: 

(i) N1 Exceedance is above 95.2%; 

(ii) N1 Exceedance occurred above 29,100 

feet; 

(iii) N1 Exceedance occurs for a duration 

of 40 seconds (15 seconds of cockpit display) 

or more during any flight; and 

(iv) Compressor intermediate case (CIC) 

assembly installed has part number (P/N) 

5379926, P/N 5379940, P/N 5379946, or P/N 

5379926–001. 

Note 2 to paragraph (g)(5): Guidance on 

determining the N1 Exceedance duration can 

be found in Section PW1000G–A–72–00–00– 

02A–0B5A–A of PW engine maintenance 

manual (EMM), Issue No. 016, dated January 

15, 2021. 

Note 3 to paragraph (g)(5): Guidance on 

performing the BSI can be found in Section 

PW1000G–A–72–31–00–00A–312A–D of PW 

EMM, Issue No. 017, dated March 19, 2021. 

(6) Based on the results of the BSI required 

by paragraph (g)(5) of this AD, before further 

flight, remove and replace the LPC R1 if: 

(i) There is damage on an LPC R1 that 

exceeds serviceable limits; or 

(ii) Any crack in the LPC R1 exists. 

(7) For all affected model turbofan engines, 

at the next engine shop visit after the 

effective date of this AD, remove CIC 

assembly with P/N 5379926, P/N 5379940, P/ 

N 5379946, or P/N 5379926–001 and replace 

with a CIC assembly eligible for installation. 

(8) For PW1519G, PW1521G, PW1521G–3, 

PW1521GA, PW1524G, PW1524G–3, 

PW1525G, and PW1525G–3 model turbofan 

engines with installed EEC FADEC software 

version V2.11.10.4, at the next engine shop 

visit after the effective date of this AD, 

remove the EEC FADEC software and install 

EEC FADEC software version eligible for 

installation. 

(9) For PW1919G, PW1921G, PW1922G, 

PW1923G, and PW1923G–A model turbofan 

engines with installed EEC FADEC software 

version V9.5.6.7, at the next engine shop visit 

after the effective date of this AD, remove the 

EEC FADEC software and install EEC FADEC 

software version eligible for installation. 

(h) Definitions 

(1) For the purpose of this AD, ‘‘EEC 

FADEC software version eligible for 

installation’’ is EEC FADEC software version 

V2.11.12.1 or later for PW1519G, PW1521G, 

PW1521G–3, PW1521GA, PW1524G, 

PW1524G–3, PW1525G, and PW1525G–3 

model turbofan engines, and EEC FADEC 

software version V9.6.5.6 or later for 

PW1919G, PW1921G, PW1922G, PW1923G, 

and PW1923G–A model turbofan engines. 

(2) 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 the LPC Flange 1 or separation 

of the LPC Flange 4, 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) Separation of engine flanges solely for 

the purpose of replacing the fan without 

subsequent maintenance. 

(3) For the purpose of this AD, a ‘‘CIC 

assembly eligible for installation’’ is any CIC 

assembly that does not have P/N 5379926, P/ 

N 5379940, P/N 5379946, or P/N 5379926– 

001. 


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42312 Federal Register / Vol. 87, No. 135 / Friday, July 15, 2022 / Rules and Regulations 

(i) 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 (j)(1) of this AD and 

email 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Mark Taylor, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7229; email: Mark.Taylor@faa.gov. 

(2) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

Street, East Hartford, CT 06118; phone: (800) 

565–0140; email: help24@pw.utc.com; 

website: http://fleetcare.pw.utc.com. 

(3) 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. 

(k) Material Incorporated by Reference 

None. 

Issued on July 7, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–15131 Filed 7–14–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0470; Project 

Identifier MCAI–2021–01002–T; Amendment 

39–22112; AD 2022–14–07] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Bombardier, Inc., Model BD–700–1A10 

and BD–700–1A11 airplanes. This AD 

was prompted by reports that some 

oxygen box assemblies had their piston 

ejected during the mask deployment 

test. This AD requires a one-time 

inspection of each passenger oxygen box 

dual manifold assembly to find and 

replace affected parts. This AD also 

prohibits installing affected parts. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 19, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier Business Aircraft Customer 

Response Center, 400 Coˆte-Vertu Road 

West, Dorval, Que ́bec H4S 1Y9, Canada; 

telephone 514–855–2999; email ac.yul@

aero.bombardier.com; internet https://

www.bombardier.com. You may view 

this service information 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 on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0470. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0470; 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: 

Elizabeth Dowling, Aerospace Engineer, 

Mechanical Systems and Administrative 

Services Section, FAA, New York ACO 

Branch, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 

516–228–7300; email 9-avs-nyaco-cos@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued TCCA AD CF– 

2021–30, dated September 7, 2021 

(TCCA AD CF–2021–30) (also referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or the MCAI), to correct an unsafe 

condition for all Bombardier, Inc., 

Model BD–700–1A10 and BD–700– 

1A11 airplanes. You may examine the 

MCAI in the AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0470. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Bombardier, Inc., Model 

BD–700–1A10 and BD–700–1A11 

airplanes. The NPRM published in the 

Federal Register on April 26, 2022 (87 

FR 24476). The NPRM was prompted by 

reports that some oxygen box assemblies 

had their piston ejected during the mask 

deployment test. The NPRM proposed 

to require a one-time inspection of each 

passenger oxygen box dual manifold 

assembly to find and replace affected 

parts. The NPRM also proposed to 

prohibit installing affected parts. The 

FAA is issuing this AD to address a 

possible in-service piston ejection when 

used for emergency descent, smoke, or 

fire that may result in a high rate of 

oxygen leakage, which could 

prematurely deplete the oxygen for all 

passengers. See the MCAI for additional 

background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the cost to the public. 

Conclusion 

The FAA reviewed the relevant data 

and determined that air safety requires 

adopting this AD as proposed. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Related Service Information Under 1 

CFR Part 51 

Bombardier, Inc., has issued the 

following service information. 

• Service Bulletin 700–35–5004, 

Revision 02, dated August 27, 2021. 

• Service Bulletin 700–35–5502, 

dated August 27, 2021. 

• Service Bulletin 700–35–6004, 

Revision 05, dated August 27, 2021. 

• Service Bulletin 700–35–6502, 

dated August 27, 2021. 

This service information describes 

procedures for inspecting each 

passenger oxygen box dual manifold 

assembly to find affected parts, and 

replacing affected parts. These 

documents are distinct because they 


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