4826 Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Proposed Rules 

even if new, unless the actions required by 

paragraph (g)(1) of this AD have been 

accomplished. 

(2) For any post-HG mod 20–040 

helicopter: As of the effective date of this AD, 

do not install an MRH or swashplate guide, 

with rotating or non-rotating scissor fitting 

P/N G12–00–200 installed, respectively, on 

any helicopter. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD if you accomplished Guimbal Service 

Bulletin SB 20–012, Revision A, dated 

September 1, 2020, before February 22, 2021 

(the effective date of AD 2021–02–20). 

(2) This paragraph provides credit for the 

first instance of the actions required by 

paragraph (g)(2) of this AD if you 

accomplished Guimbal Service Bulletin SB 

20–011, Revision B, dated September 1, 2020, 

before February 22, 2021 (the effective date 

of AD 2021–02–20). 

(3) This paragraph provides credit for the 

actions required by paragraph (g)(2) of this 

AD if you accomplished Guimbal Service 

Bulletin SB 20–011, Revision C, dated 

October 5, 2020, before the effective date of 

this AD. 

(4) This paragraph provides credit for the 

actions required by paragraph (g)(3) of this 

AD if you accomplished Guimbal Service 

Bulletin SB 21–007, Revision B, dated April 

4, 2021, before the effective date of this AD. 

(j) Special Flight Permits 

A special flight permit may be permitted 

provided that there are no passengers 

onboard, and the flight is operating under 

day Visual Flight Rules, for the purpose of 

ferrying the helicopter to an authorized 

maintenance facility. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (l)(1) of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

(1) For more information about this AD, 

contact Darren Gassetto, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7323; email 

Darren.Gassetto@faa.gov. 

(2) For service information identified in 

this AD, contact He ́licopte`res Guimbal, 1070, 

rue du Lieutenant Parayre, Ae ́rodrome d’Aixen-Provence, 13290 Les Milles, France; 

telephone 33–04–42–39–10–88; email 

support@guimbal.com; web https://

www.guimbal.com. You may view this 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 6N– 

321, Fort Worth, TX 76177. For information 

on the availability of this material at the 

FAA, call (817) 222–5110. 

(3) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2021–0155, dated July 2, 2021. 

You may view the EASA AD on the internet 

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

FAA–2022–0020. 

Issued on January 25, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01829 Filed 1–28–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1173; Project 

Identifier AD–2021–00917–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

The Boeing Company Model 747–8F 

series airplanes. This proposed AD was 

prompted by reports of fuselage crown 

stringer cracking between station (STA) 

740 and STA 1000, stringer (S)–7 to S– 

12. This proposed AD would require 

repetitive detailed inspections for 

cracking of fuselage crown stringers and 

applicable on-condition actions. The 

FAA is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this proposed AD by March 17, 2022. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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. You may view 

this referenced 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– 

1173. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1173; 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 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Stefanie Roesli, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3964; email: stefanie.n.roesli@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2021–1173; Project Identifier AD– 

2021–00917–T’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Proposed Rules 4827 

summarizing each substantive verbal 

contact received about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Stefanie Roesli, 

Aerospace Engineer, Airframe Section, 

FAA, Seattle ACO Branch, 2200 South 

216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3964; email: 

stefanie.n.roesli@faa.gov. Any 

commentary that the FAA receives 

which is not specifically designated as 

CBI will be placed in the public docket 

for this rulemaking. 

Background 

The FAA has received reports of 

fuselage crown stringer cracking located 

on the left and right sides at S–7, S–8, 

S–9, S–10, S–11, and S–12, between 

STA 740 and STA 1000. Some of these 

reports were made during airplane 

production, and others were found on 

airplanes currently in operation. The 

existing maintenance inspections 

cannot reliably detect cracking at 

multiple stringers and bay frames. Any 

crack in these locations must be found 

and repaired before reaching a critical 

length. Without an inspection, any crack 

may grow in length and go undetected. 

This condition, if not addressed, could 

result in the inability of a structural 

element to sustain limit load, and could 

adversely affect the structural integrity 

of the airplane. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Boeing Alert 

Requirements Bulletin 747–53A2906 

RB, dated July 16, 2021. This service 

information specifies procedures for 

repetitive detailed inspections for 

cracking of fuselage crown stringers, 

repair of cracks, and a high frequency 

eddy current (HFEC) inspection for 

cracking of repaired areas. 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. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

accomplishing the actions specified in 

the service information already 

described, except as discussed under 

‘‘Difference Between this Proposed AD 

and the Service Information’’ and except 

for any differences identified as 

exceptions in the regulatory text of this 

proposed AD. For information on the 

procedures and compliance times, see 

this service information at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

1173. 

Clarification of Proposed Inspection 

Requirements 

Table 1 of Boeing Alert Requirements 

Bulletin 747–53A2906 RB, dated July 

16, 2021, specifies repetitive detailed 

inspections to detect cracking of the 

side crown stringers on all airplanes. 

Table 1 of the service information does 

not specifically state that airplanes with 

no crack found (‘‘Condition 1’’) may 

have additional work. However, for 

airplanes with Condition 1 that have 

any repairs in the inspection area, the 

HFEC inspection specified in Table 2 of 

the service information would also be 

required. 

Difference Between This Proposed AD 

and the Service Information 

The applicability in this proposed AD 

does not refer to paragraph 1., 

‘‘Effectivity,’’ of Boeing Alert 

Requirements Bulletin 747–53A2906 

RB, dated July 16, 2021, because this 

service information does not contain a 

comprehensive list of the airplanes 

affected by the identified unsafe 

condition. Therefore, the applicability 

of this proposed AD is all Model 747– 

8F series airplanes. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 33 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Repetitive detailed inspections.84 work-hours × $85 per hour = $7,140 per 

inspection cycle.

$0 $7,140 per inspection 

cycle.

$235,620 per inspection 

cycle. 

The FAA estimates the following 

costs to do any necessary repairs that 

would be required based on the results 

of the proposed inspection. The agency 

has no way of determining the number 

of aircraft that might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

HFEC inspection ... 1 work-hour × $85 per hour = $85 ................................................................................ $0 $85. 

Repair .................... Up to 550 work-hours × $85 per hour = $46,750 (per repaired area) .......................... 2,400 Up to $49,150. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some or all 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


khammond on DSKJM1Z7X2PROD with PROPOSALS
4828 Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Proposed Rules 

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 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

The Boeing Company: Docket No. FAA– 

2021–1173; Project Identifier AD–2021– 

00917–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 17, 

2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–8F series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fuselage crown stringer cracking between 

STA 740 and STA 1000, S–7 to S–12. The 

FAA is issuing this AD to address cracking 

in fuselage crown stringers. This condition, 

if not addressed, could result in the inability 

of a structural element to sustain limit load, 

and could adversely affect the structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as specified by paragraph (h) of this 

AD: At the applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 747–53A2906 RB, 

dated July 16, 2021, do all applicable actions 

identified in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Requirements Bulletin 747–53A2906 RB, 

dated July 16, 2021. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 747–53A2906, dated July 16, 2021, 

which is referred to in Boeing Alert 

Requirements Bulletin 747–53A2906 RB, 

dated July 16, 2021. 

(h) Exception to Service Information 

Specifications 

Where the Compliance Time columns of 

the tables in the ‘‘Compliance’’ paragraph of 

Boeing Alert Requirements Bulletin 747– 

53A2906 RB, dated July 16, 2021, use the 

phrase ‘‘the original issue date of 

Requirements Bulletin 747–53A2906 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(i) 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 (j)(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO Branch, FAA, to make 

those findings. To be approved, the repair 

method, modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Stefanie Roesli, Aerospace Engineer, 

Airframe Section, FAA, Seattle ACO Branch, 

2200 South 216th St., Des Moines, WA 

98198; phone and fax: 206–231–3964; email: 

stefanie.n.roesli@faa.gov. 

(2) For 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. You may view this 

referenced 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. 

Issued on December 29, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01860 Filed 1–28–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1177; Project 

Identifier AD–2021–00570–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain The Boeing Company Model 

767–200, –300, –300F, and –400ER 

airplanes. This proposed AD was 

prompted by reports of burned Boeing 

Material Specification (BMS) 8–39 

urethane foam, which is a material with 

fire-retardant properties that deteriorate 

with age. This proposed AD would 


khammond on DSKJM1Z7X2PROD with PROPOSALS