13926 Federal Register / Vol. 87, No. 48 / Friday, March 11, 2022 / Rules and Regulations 

blades that have zero CSN do not need to 

undergo the initial 1st-stage LPC blade flow 

path and mid span UT inspection required by 

paragraph (g)(1)(i) of this AD, but must 

undergo the repetitive inspections of 

paragraph (g)(2) of this AD. 

(ii) Within the following compliance times 

after the effective date of this AD, perform a 

thermal acoustic image (TAI) inspection of 

the 1st-stage LPC blades for cracks using a 

method approved by the FAA: 

(A) For 1st-stage LPC blades with 1,000 

CSN or more, with no prior TAI inspection, 

inspect before further flight. 

(B) For 1st-stage LPC blades with 1,000 

flight cycles (FCs) or more since the last TAI 

inspection, inspect before further flight. 

(C) For 1st-stage LPC blades with fewer 

than 1,000 CSN, with no prior TAI 

inspection, inspect before accumulating 

1,000 CSN. 

(D) For 1st-stage LPC blades with fewer 

than 1,000 FCs since the last TAI inspection, 

inspect before accumulating 1,000 FCs since 

the last TAI inspection. 

Note 1 to paragraph (g)(1)(ii): The FAAapproved TAI inspection method and the 

vendors that can perform the FAA-approved 

TAI inspection are specified in the 

Accomplishment Instructions section and the 

Vendor Services section of PW4G–112–A72– 

361, respectively. 

(2) Repetitive 1st-Stage LPC Blade 

Inspections 

(i) Before exceeding 275 FCs since the last 

flow path UT inspection, and thereafter at 

intervals not exceeding 275 FCs since the last 

flow path UT inspection, perform a flow path 

UT inspection of the 1st-stage LPC blades in 

accordance with the Accomplishment 

Instructions, Part B—Repetitive Inspection of 

All LPC Fan Blades After Their Return to 

Service, paragraph 1.A., of PW4G–112–A72– 

361. 

(ii) Before exceeding 550 FCs since the last 

mid span UT inspection, and thereafter at 

intervals not exceeding 550 FCs since the last 

mid span UT inspection, perform a mid span 

UT inspection of the 1st-stage LPC blades in 

accordance with the Accomplishment 

Instructions, Part B—Repetitive Inspection of 

All LPC Fan Blades After Their Return to 

Service, paragraphs 1.B. and C., of PW4G– 

112–A72–361. 

(iii) Before exceeding 1,000 FCs since the 

last TAI inspection, and thereafter at 

intervals not exceeding 1,000 FCs since the 

last TAI inspection, perform repetitive TAI 

inspections of the 1st-stage LPC blades using 

a method approved by the FAA. 

Note 2 to paragraph (g)(2)(iii): The FAAapproved TAI inspection method and the 

vendors that can perform the FAA-approved 

TAI inspection are specified in the 

Accomplishment Instructions section and the 

Vendor Services section of PW4G–112–A72– 

361, respectively. 

(3) Removal of the 1st-Stage LPC Blade 

If any 1st-stage LPC blade fails any 

inspection required by paragraphs (g)(1) or 

(2) of this AD, before further flight, remove 

the 1st-stage LPC blade from service and 

replace with a part eligible for installation. 

(h) Definition 

For the purpose of this AD, a ‘‘part eligible 

for installation’’ is a new, zero CSN 1st-stage 

LPC blade or a 1st-stage LPC blade that has 

passed the inspections required by 

paragraphs (g)(1) and (2) of this AD, as 

applicable. 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are permitted 

provided that the actions in paragraphs (i)(1) 

and (2) of this AD have first been 

accomplished. 

(1) A flow path UT inspection of the 1ststage LPC blades for cracking has been done 

within the last 275 FCs, as specified in the 

Accomplishment Instructions, Part A—Initial 

Inspection of All LPC Fan Blades Prior to 

their Return to Service, paragraph 1.A., of 

PW4G–112–A72–361, and the 1st-stage LPC 

blades have been found serviceable. This 

inspection is not required for 1st-stage LPC 

blades with 275 CSN or fewer. 

(2) A functional check of the left and right 

hydraulic pump shutoff valves to ensure they 

close in response to the corresponding engine 

fire handle input and all applicable 

corrective actions (i.e., repair) within 10 days 

prior to flight. 

Note 3 to paragraph (i)(2): Guidance for 

accomplishing the actions required by 

paragraph (i)(2) of this AD can be found in 

the ‘‘Engine-Driven Pump (EDP) Shutoff 

Valve Check’’ (Subtasks 26–21–00–200–018, 

26–21–00–200–019, 26–21–00–840–022, or 

Task 29–11–00–710–806) of Boeing 777–200/ 

300 Aircraft Maintenance Manual. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g)(1) and 

(i)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraph (j)(1), (2), or (3) of this AD. 

(1) Paragraph 2. of the Accomplishment 

Instructions of Pratt & Whitney Special 

Instruction No. 85F21, dated May 12, 2021, 

for a flow path UT inspection. 

(2) Paragraph 1.a) through c) of the 

Accomplishment Instructions of Pratt & 

Whitney Special Instruction No. 130F–21, 

dated July 1, 2021, for a flow path and a mid 

span UT inspection. 

(3) Paragraph 2.a) through c) of the 

Accomplishment Instructions of Pratt & 

Whitney Special Instruction No. 130F–21, 

Revision A, dated July 28, 2021, for a flow 

path and a mid span UT inspection. 

(k) 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 (l) 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. 

(l) Related Information 

For more information about this AD, 

contact Carol Nguyen, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7655; fax: (781) 238–7199; email: 

carol.nguyen@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Pratt & Whitney Alert Service Bulletin 

PW4G–112–A72–361, dated October 15, 

2021. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Pratt & Whitney Division, 

400 Main Street, East Hartford, CT 06118; 

phone: (860) 565–0140; email: help24@

prattwhitney.com; website: https://

connect.prattwhitney.com. 

(4) You may view this service information 

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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

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

ibr-locations.html. 

Issued on March 4, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–05296 Filed 3–9–22; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0963; Project 

Identifier AD–2021–01026–T; Amendment 

39–21977; AD 2022–06–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 


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Federal Register / Vol. 87, No. 48 / Friday, March 11, 2022 / Rules and Regulations 13927 

and –300 series airplanes. This AD was 

prompted by reports of three incidents 

involving in-flight fan blade failures on 

certain Pratt & Whitney engines (‘‘fan 

blades’’ are also known as ‘‘1st-stage 

low-pressure compressor (LPC) 

blades’’—these terms are used 

interchangeably in this AD). This AD 

requires modifying the engine inlet to 

withstand fan blade failure event loads. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective April 15, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 15, 2022. 

ADDRESSES: For Boeing service 

information identified in this AD, 

contact Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. For 

Pratt & Whitney service information 

identified in this AD contact Pratt & 

Whitney Division, 400 Main Street, East 

Hartford, CT 06118; phone: 860–565– 

0140; email: help24@prattwhitney.com; 

website: https://

connect.prattwhitney.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 at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0963. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0963; 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: Luis 

Cortez-Muniz, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 

(206) 231–3958; email: Luis.A.CortezMuniz@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 The Boeing Company 

Model 777–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on December 28, 2021 

(86 FR 73688). The NPRM was 

prompted by reports of three incidents 

involving in-flight fan blade failures on 

certain Pratt & Whitney engines. In the 

NPRM, the FAA proposed to require 

modifying the engine inlet to withstand 

fan blade failure event loads. The FAA 

is issuing this AD to address the 

airplane-level implications of the unsafe 

condition of engine fan blade failure. 

Fan blade failures can cause fan rotor 

imbalance and result in fan blade 

fragments penetrating the inner and 

outer barrel of the inlet. This condition, 

if not addressed could result in engine 

in-flight shutdown, and could result in 

separation of the inlet, the fan cowl 

doors, or the thrust reverser (T/R) cowl, 

or result in uncontrolled engine fire. 

Separation of the inlet, the fan cowl 

doors, or the T/R cowl could result in 

impact damage to the empennage and 

loss of control of the airplane, or to the 

fuselage or windows with potential 

injury to passengers; or it could result 

in significantly increased aerodynamic 

drag causing fuel exhaustion or the 

inability to maintain altitude above 

terrain during extended operations 

(ETOPS) flights, either of which could 

result in a forced off-airport landing and 

injury to passengers. Uncontrolled 

engine fire could result in loss of control 

of the airplane. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

The Air Line Pilots Association, 

International (ALPA), and two 

Anonymous commenters who 

supported the NPRM without change. 

The FAA received additional 

comments from five commenters, 

including an Anonymous commenter, 

All Nippon Airways (ANA), Boeing, 

Japan Airlines (JAL), and United 

Airlines (UAL). The following presents 

the comments received on the NPRM 

and the FAA’s response to each 

comment. 

Request To Clarify Certain Sentences in 

the Background Paragraph 

Boeing requested that the 

‘‘Background’’ paragraph in the NPRM 

be revised to clarify that the failed 

hydraulic pump shutoff valve was not 

the direct cause of the uncontained 

engine fire. Boeing stated that flight data 

indicates that while the hydraulic pump 

shutoff valve failed to close, no 

hydraulic fluid was leaked from the 

system until well after the engine fire 

initiated. 

Boeing proposed that two sentences 

in the ‘‘Background’’ paragraph of the 

NPRM be revised to, ‘‘Several 

flammable fluid lines, the engine 

accessory gearbox, and T/R structure 

were fractured and an uncontained 

engine fire occurred. The hydraulic 

pump shutoff valve failed to close when 

the fire handle was pulled, contributing 

additional flammable fluid to the T/R 

area.’’ Boeing commented that the 

proposed wording recognizes that the 

failure may have contributed additional 

flammable fluid to the T/R area, but that 

it did not directly cause the 

uncontained fire. 

The FAA agrees with the commenter’s 

clarification and did not intend to imply 

that the failed hydraulic pump shutoff 

valve was the direct cause of the 

uncontained engine fire. However, the 

detailed background information, which 

includes the sentences that the 

commenter proposed for the 

‘‘Background’’ paragraph, are not 

carried over into the final rule. The FAA 

has not changed this final rule in this 

regard. 

Request To Use Certain Service 

Information as a Method of Compliance 

ANA, an Anonymous commenter, 

Boeing, and UAL requested the use of 

Boeing Alert Service Bulletin 777– 

71A0085 and Boeing Alert Service 

Bulletin 777–71A0093, for doing the 

actions in paragraph (g) of the proposed 

AD. Boeing stated that the description of 

the modification in the proposed AD is 

vague. 

The FAA disagrees with allowing the 

use of Boeing Alert Service Bulletin 

777–71A0085 and Boeing Alert Service 

Bulletin 777–71A0093 for the actions 

specified in paragraph (g) of this AD. 

The service bulletins are not yet FAAapproved. However, under the 

provisions of paragraph (j) of this AD, 

the FAA will consider requests for 

approval of the use of the service 

bulletins if sufficient data are submitted 

to substantiate that the service bulletins 

would provide an acceptable level of 

safety. 

Request To Add Certain Exceptions for 

Ferry Flights 

JAL requested that the FAA revise the 

AD to include certain exceptions for 

ferry flights. JAL stated it is planning to 

ferry affected airplanes to a storage 

point in the United States. JAL 

commented that although the local 


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authority in Japan provides regulatory 

requirements for special flight 

permissions which are similar to 14 CFR 

21.197, the Japanese regulatory 

requirements do not include ‘‘to a point 

of storage’’ language for the purpose of 

the flights. JAL proposed to add the 

following wording to paragraphs (c) and 

(g) of the proposed AD, ‘‘except for ferry 

flights, without passenger and cargo, of 

the airplanes on which the actions 

specified in paragraphs (h)(1) and (2) of 

this AD have been done.’’ 

The FAA disagrees with revising 

paragraph (c) Applicability or paragraph 

(g) Modification of this AD in response 

to JAL’s comment. Paragraph (i), Special 

Flight Permit, provides that special 

flight permits, as described in 14 CFR 

21.197 and 21.199, are permitted 

provided that the actions in paragraphs 

(h)(1) and (2) of this AD have first been 

accomplished. 14 CFR 21.197(a)(1) 

provides, in relevant part, that a special 

flight permit may be issued for flying 

the aircraft to a base where repairs, 

alterations, or maintenance are to be 

performed, or to a point of storage. The 

requested change is already permitted 

by this AD. The FAA did not change 

this AD as a result of this comment. 

Request To Change the Initial 

Compliance Time to Before Revenue 

Flight 

ANA requested that in paragraph (g) 

of the proposed AD, the FAA update the 

initial compliance time of ‘‘before 

further flight after the effective date of 

this AD’’ to ‘‘before the next revenue 

flight’’ to clarify the ferry flight 

requirement. 

Similarly, JAL requested that in 

paragraph (g) of the proposed AD, the 

FAA update the initial compliance time 

of ‘‘before further flight after the 

effective of this AD’’ to ‘‘before the next 

revenue flight’’ or ‘‘before further flight 

except the ferry flight without passenger 

and cargos.’’ 

The FAA disagrees with revising the 

initial compliance time in paragraph (g) 

of this AD as requested by ANA and 

JAL. The FAA has determined it is 

necessary to require certain actions 

prior to any flight, except as permitted 

in paragraph (h), Special Flight Permit, 

of this AD. 

Request To Provide a Threshold for the 

Special Flight Permit 

UAL requested that the FAA provide 

a threshold in paragraph (h)(1) of the 

proposed AD for the flow path UT 

inspection. UAL stated that omitting a 

compliance time in paragraph (h) of the 

proposed AD for the special flight 

permits creates ambiguity regarding 

when and how often the flow path UT 

inspection is required for special flight 

permits. UAL suggested a threshold of 

275 flight cycles since the last flow path 

UT inspection. 

The FAA agrees to add a threshold of 

275 cycles to paragraph (h)(1) of this 

AD, which is specified in Pratt & 

Whitney Alert Service Bulletin PW4G– 

112–A72–361, dated October 15, 2021. 

This allows airplanes with 1st-stage LPC 

blades that have accumulated 275 cycles 

since new or fewer to be eligible for a 

special flight permit. 

Request for an Additional Method of 

Compliance 

UAL requested that the FAA revise 

paragraph (h)(1) of the proposed AD to 

add NPRM AD–2021–00830–E (86 FR 

73699, December 28, 2021), as a method 

of compliance for the flow path 

ultrasonic testing (UT) inspection of the 

1st-stage LPC blades. 

The FAA disagrees with the 

commenter’s request. The method of 

compliance in Pratt & Whitney Alert 

Service Bulletin PW4G–112–A72–361, 

dated October 15, 2021, is the same as 

paragraph (i)(1) of NPRM AD–2021– 

00830–E (86 FR 73699, December 28, 

2021) and paragraph (h)(1) of this AD. 

If the actions in the service information 

are accomplished, the requirements in 

paragraph (h)(1) of this AD will have 

been met, and therefore, no change to 

this AD has been made. 

Request To Add Aircraft Maintenance 

Manual Task to Special Flight Permit 

ANA and UAL requested that 

paragraph (h)(2) of the proposed AD 

include Task 29–11–00–710–806 of the 

Boeing 777–200/300 Aircraft 

Maintenance Manual as an acceptable 

method for accomplishing the 

functional check of the left and right 

hydraulic pump shutoff valves. 

The FAA agrees with the commenter’s 

request and has added Task 29–11–00– 

710–806 of Boeing 777–200/300 Aircraft 

Maintenance Manual to the ‘‘Other 

Related Service Information’’ paragraph 

and to Note (1) to paragraph (h)(2) of 

this AD as guidance for accomplishing 

the actions required by paragraph (h)(2) 

of this AD. 

Request To Delegate Alternative 

Methods of Compliance (AMOCs) 

UAL requested that if Boeing Alert 

Service Bulletin 777–71A0085 and 

Boeing Alert Service Bulletin 777– 

71A0093 become an FAA-approved 

method of compliance, the FAA should 

delegate The Boeing Company 

Organization Designation Authorization 

(ODA) authority to approve structural 

related AMOCs when deviations to the 

service documents are required. 

The FAA acknowledges UAL’s 

request, however as stated previously, 

the Boeing service bulletins are not yet 

FAA-approved, and therefore ODA 

authority is not granted at this time. In 

the future, should the service bulletins 

be approved as a method of compliance 

to this AD, the FAA may consider ODA 

authority delegation for approval of 

structural-related AMOCs for deviations 

to the approved method of compliance. 

Additional Change Made to This AD 

In the process of preparing this final 

rule, the FAA noticed that the unsafe 

condition statement could be improved 

regarding the initial effects of the fan 

blade failure and the airplane level 

unsafe outcomes that could result from 

each of those initial effects. Therefore, 

the FAA has updated the unsafe 

condition statement in this AD to clarify 

the specific causes and hazardous 

effects. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 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 Under 1 

CFR Part 51 

The FAA reviewed Pratt & Whitney 

Alert Service Bulletin PW4G–112–A72– 

361, dated October 15, 2021. This 

service information specifies procedures 

for performing thermal acoustic image 

and ultrasonic testing inspections of 1ststage LPC blades. 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. 

Other Related Service Information 

The FAA reviewed Subtasks 26–21– 

00–200–018, 26–21–00–200–019, and 

26–21–00–840–022, and Task 29–11– 

00–710–806, of Boeing 777–200/300 

Aircraft Maintenance Manual, dated 

September 5, 2021. The service 

information specifies procedures for 

performing a functional check of the 

engine-driven pump shutoff valve. 

Interim Action 

The FAA considers this AD to be an 

interim action. The manufacturer is 

currently developing other actions that 

will address the unsafe condition 

identified in this AD. Once these actions 


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Federal Register / Vol. 87, No. 48 / Friday, March 11, 2022 / Rules and Regulations 13929 

are developed, approved, and available, 

the FAA might consider additional 

rulemaking. 

Costs of Compliance 

The FAA estimates that this AD 

affects 54 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 

Modification ..................................................... 660 work-hours × $85 per hour = $56,100 .... $362,560 $418,660 $22,607,640 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition repairs that are part 

of the modification specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2022–06–11 The Boeing Company: 

Amendment 39–21977; Docket No. 

FAA–2021–0963; Project Identifier AD– 

2021–01026–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 15, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, as 

specified in paragraphs (c)(1) and (2) of this 

AD. 

(1) Model 777–200 series airplanes 

equipped with Pratt & Whitney PW4074, 

PW4074D, PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3 model turbofan 

engines. 

(2) Model 777–300 series airplanes 

equipped with Pratt & Whitney PW4090 and 

PW4098 model turbofan engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of three 

incidents involving in-flight fan blade 

failures on certain Pratt & Whitney engines. 

The FAA is issuing this AD to address engine 

fan blade failure, which could result in 

engine in-flight shutdown, and could result 

in separation of the inlet, the fan cowl doors, 

or the thrust reverser (T/R) cowl, or result in 

uncontrolled engine fire. Separation of the 

inlet, the fan cowl doors, or the T/R cowl 

could result in impact damage to the 

empennage and loss of control of the 

airplane, or to the fuselage or windows with 

potential injury to passengers; or it could 

result in significantly increased aerodynamic 

drag causing fuel exhaustion or the inability 

to maintain altitude above terrain during 

extended operations (ETOPS) flights, either 

of which could result in a forced off-airport 

landing and injury to passengers. 

Uncontrolled engine fire could result in loss 

of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Before further flight after the effective date 

of this AD, modify the engine inlet to 

withstand fan blade failure event loads, in 

accordance with a method approved by the 

Manager, Seattle ACO Branch, FAA. 

(h) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are permitted 

provided that the actions in paragraphs (h)(1) 

and (2) of this AD have first been 

accomplished. 

(1) A flow path ultrasonic testing (UT) 

inspection of the 1st-stage low-pressure 

compressor (LPC) blades for cracking has 

been done within the last 275 cycles, as 

specified in the Accomplishment 

Instructions, Part A—Initial Inspection of All 

LPC Fan Blades Prior to their Return to 

Service, paragraph 1.A., of Pratt & Whitney 

Alert Service Bulletin PW4G–112–A72–361, 

dated October 15, 2021, and the 1st-stage LPC 

blades have been found serviceable. This 

inspection is not required for 1st-stage LPC 

blades with 275 cycles since new or fewer. 

(2) A functional check of the left and right 

hydraulic pump shutoff valves to ensure they 

close in response to the corresponding engine 

fire handle input and all applicable 

corrective actions (i.e., repair) within 10 days 

prior to flight. 

Note (1) to paragraph (h)(2): Guidance for 

accomplishing the actions required by 

paragraph (h)(2) of this AD can be found in 

the ‘‘Engine-Driven Pump (EDP) Shutoff 

Valve Check’’ (Subtasks 26–21–00–200–018, 

26–21–00–200–019, and 26–21–00–840–022, 

or Task 29–11–00–710–806) of Boeing 777– 

200/300 Aircraft Maintenance Manual. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

information specified in paragraph (i)(1), (2), 

or (3) of this AD. 


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13930 Federal Register / Vol. 87, No. 48 / Friday, March 11, 2022 / Rules and Regulations 

(1) Paragraph 2. of the Accomplishment 

Instructions of Pratt & Whitney Special 

Instruction No. 85F–21, dated May 12, 2021, 

for a flow path UT inspection. 

(2) Paragraph 1.a) of the Accomplishment 

Instructions of Pratt & Whitney Special 

Instruction No. 130F–21, dated July 1, 2021, 

for a flow path UT inspection. 

(3) Paragraph 2.a) of the Accomplishment 

Instructions of Pratt & Whitney Special 

Instruction No. 130F–21, Revision A, dated 

July 28, 2021, for a flow path UT inspection. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 the attention of 

the person identified in paragraph (k)(1) of 

this AD. Information may be emailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(k) Related Information 

(1) For more information about this AD, 

contact Luis Cortez-Muniz, Aerospace 

Engineer, Airframe Section, FAA, Seattle 

ACO Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: (206) 

231–3958; email: Luis.A.Cortez-Muniz@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Pratt & Whitney Alert Service Bulletin 

PW4G–112–A72–361, dated October 15, 

2021. 

(ii) [Reserved] 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 2600 

Westminster Blvd., MC 110–SK57, Seal 

Beach, CA 90740–5600; telephone 562–797– 

1717; internet https://

www.myboeingfleet.com. For Pratt & Whitney 

service information identified in this AD 

contact Pratt & Whitney Division, 400 Main 

Street, East Hartford, CT 06118; phone: 860– 

565–0140; email: help24@prattwhitney.com; 

website: https://connect.prattwhitney.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on March 4, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–05295 Filed 3–9–22; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0962; Project 

Identifier AD–2021–00997–T; Amendment 

39–21976; AD 2022–06–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 

and –300 series airplanes. This AD was 

prompted by reports of three incidents 

involving in-flight fan blade failures on 

certain Pratt & Whitney engines (‘‘fan 

blades’’ are also known as ‘‘1st-stage 

low-pressure compressor (LPC) 

blades’’—these terms are used 

interchangeably in this AD). This AD 

requires installation of debris shields on 

the thrust reverser (T/R) inner wall at 

the left and right sides of the lower 

bifurcation, inspection of the fan cowl 

doors for moisture ingression, repetitive 

functional checks of the hydraulic 

pump shutoff valves to ensure they 

close in response to the fire handle 

input, and corrective actions if 

necessary. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective April 15, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 15, 2022. 

ADDRESSES: For Boeing service 

information identified in this AD, 

contact Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet 

https://www.myboeingfleet.com. For 

Pratt & Whitney service information 

identified in this AD contact Pratt & 

Whitney Division, 400 Main Street, East 

Hartford, CT 06118; phone: 860–565– 

0140; email: help24@prattwhitney.com; 

website: https://

connect.prattwhitney.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 at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0962. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0962; 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: 

James Laubaugh, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3622; email: james.laubaugh@

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 The Boeing Company 

Model 777–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on December 28, 2021 

(86 FR 73712). The NPRM was 

prompted by reports of three incidents 

involving in-flight fan blade failures on 

certain Pratt & Whitney engines. In the 

NPRM, the FAA proposed to require 

installation of debris shields on the T/ 

R inner wall at the left and right sides 

of the lower bifurcation, inspection of 

the fan cowl doors for moisture 

ingression, repetitive functional checks 

of the hydraulic pump shutoff valves to 

ensure they close in response to the fire 

handle input, and corrective actions if 

necessary. The FAA is issuing this AD 

to address the airplane-level 

implications of the unsafe condition of 

engine fan blade failure. Fan blade 


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