This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

33451 

Vol. 87, No. 106 

Thursday, June 2, 2022 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0520; Project 

Identifier AD–2021–00683–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 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747SR, 

and 747SP series airplanes. This 

proposed AD was prompted by 

significant changes, including new or 

more restrictive requirements, made to 

the airworthiness limitations (AWLs) 

related to fuel tank ignition prevention. 

This proposed AD would require 

revising the existing maintenance or 

inspection program, as applicable, to 

incorporate the latest revision of the 

AWLs. 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 July 18, 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; phone: 562–797–1717; 

internet: https://

www.myboeingfleet.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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0520; 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: Rose 

Len, Aerospace Engineer, Propulsion 

Section, FAA, Seattle ACO Branch, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3604; email: 

rose.len@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–2022–0520; Project Identifier AD– 

2021–00683–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 

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 Rose Len, Aerospace 

Engineer, Propulsion Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and 

fax: 206–231–3604; email: rose.len@

faa.gov. Any commentary that the FAA 

receives that is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

the FAA issued a final rule titled 

‘‘Transport Airplane Fuel Tank System 

Design Review, Flammability 

Reduction, and Maintenance and 

Inspection Requirements’’ (66 FR 23086, 

May 7, 2001). In addition to new 

airworthiness standards for transport 

airplanes and new maintenance 

requirements that rule included 

Amendment 21–78, which established 

Special Federal Aviation Regulation No. 

88 (SFAR 88) at 14 CFR part 21. 

Subsequently, SFAR 88 was amended 

by Amendment 21–82 (67 FR 57490, 

September 10, 2002; corrected at 67 FR 

70809, November 26, 2002), 

Amendment 21–83 (67 FR 72830, 

December 9, 2002; corrected at 68 FR 

37735, June 25, 2003, to change ‘‘21–82’’ 

to ‘‘21–83’’), and Amendment 21–101 

(83 FR 9162, March 5, 2018). 


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33452 Federal Register / Vol. 87, No. 106 / Thursday, June 2, 2022 / Proposed Rules 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule published on May 7, 2001, 

the FAA intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, 

the FAA established four criteria 

intended to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, combination of failures, 

and unacceptable (failure) experience. 

For all three criteria, the evaluations 

included consideration of previous 

actions taken that may mitigate the need 

for further action. 

This proposed AD was prompted by 

significant changes, including new or 

more restrictive requirements, made to 

the AWL related to fuel tank ignition 

prevention. This condition, if not 

addressed, could result in the potential 

for ignition sources inside fuel tanks 

caused by latent failures, alterations, 

repairs, or maintenance actions, which, 

in combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

FAA’s Determination 

The FAA is proposing this AD 

because the agency evaluated all the 

relevant information and determined 

the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Boeing 747–100/ 

200/300/SP/SR Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), D6– 

13747–CMR, dated September 2020. 

This service information describes 

AWLs that include airworthiness 

limitation instructions (ALIs) and 

critical design configuration control 

limitations (CDCCLs) tasks related to 

fuel tank ignition prevention. 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 

revising the existing maintenance or 

inspection program, as applicable, to 

incorporate the latest revision of the 

AWLs. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections) and CDCCLs. 

Compliance with these actions and 

CDCCLs is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this proposed 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (l) of this proposed AD. 

Other Relevant Rulemaking 

The proposed revisions will affect 

several existing AWL provisions in 

various ADs. The FAA has determined 

that accomplishing the revision required 

by paragraph (g) of this proposed AD 

would terminate the following AWL 

requirements for that airplane: 

• The revision required by paragraphs 

(g) and (h) of AD 2008–10–07 R1, 

Amendment 39–16070 (74 FR 56098, 

October 30, 2009). 

• The revision required by paragraph 

(g)(1) of AD 2008–18–09, Amendment 

39–15666 (73 FR 52911, September 12, 

2008). 

• The revision required by paragraph 

(h)(2) of AD 2010–13–12, Amendment 

39–16343 (75 FR 37997, July 1, 2010). 

• The revision required by paragraph 

(h) of AD 2010–24–13, Amendment 39– 

16532 (75 FR 78591, December 16, 2010; 

corrected May 25, 2011 (76 FR 30253)). 

• The revision required by paragraph 

(k) of AD 2011–06–03, Amendment 39– 

16627 (76 FR 15814, March 22, 2011). 

• The revision required by paragraph 

(h)(2) of AD 2014–15–14, Amendment 

39–17916 (79 FR 45324, August 5, 

2014). 

• The revision required by paragraph 

(h) of AD 2016–19–03, Amendment 39– 

18652 (81 FR 65872, September 26, 

2016). 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 39 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

The FAA has determined that revising 

the existing maintenance or inspection 

program takes an average of 90 workhours per operator, although the agency 

recognizes that this number may vary 

from operator to operator. Since 

operators incorporate maintenance or 

inspection program changes for their 

affected fleet(s), the FAA has 

determined that a per-operator estimate 

is more accurate than a per-airplane 

estimate. Therefore, the FAA estimates 

the average total cost per operator to be 

$7,650 (90 work-hours × $85 per workhour). 

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 

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. 


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Federal Register / Vol. 87, No. 106 / Thursday, June 2, 2022 / Proposed Rules 33453 

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– 

2022–0520; Project Identifier AD–2021– 

00683–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by July 18, 2022. 

(b) Affected ADs 

This AD affects the ADs specified in 

paragraphs (b)(1) through (7) of this AD. 

(1) AD 2008–10–07 R1, Amendment 39– 

16070 (74 FR 56098, October 30, 2009) (AD 

2008–10–07 R1). 

(2) AD 2008–18–09, Amendment 39–15666 

(73 FR 52911, September 12, 2008) (AD 

2008–18–09). 

(3) AD 2010–13–12, Amendment 39–16343 

(75 FR 37997, July 1, 2010) (AD 2010–13–12). 

(4) AD 2010–24–13, Amendment 39–16532 

(75 FR 78591, December 16, 2010; corrected 

May 25, 2011 (76 FR 30253)) (AD 2010–24– 

13). 

(5) AD 2011–06–03, Amendment 39–16627 

(76 FR 15814, March 22, 2011) (AD 2011–06– 

03). 

(6) AD 2014–15–14, Amendment 39–17916 

(79 FR 45324, August 5, 2014) (AD 2014–15– 

14). 

(7) AD 2016–19–03, Amendment 39–18652 

(81 FR 65872, September 26, 2016) (AD 

2016–19–03). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by significant 

changes, including new or more restrictive 

requirements, made to the airworthiness 

limitations (AWLs) related to fuel tank 

ignition prevention. The FAA is issuing this 

AD to address the potential for ignition 

sources inside fuel tanks caused by latent 

failures, alterations, repairs, or maintenance 

actions, which, in combination with 

flammable fuel vapors, could result in a fuel 

tank explosion and consequent loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 60 days after the effective date of 

this AD, revise the existing maintenance or 

inspection program, as applicable, to 

incorporate the information specified in 

Boeing 747–100/200/300/SP/SR 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D6–13747–CMR, dated September 

2020, except as specified in paragraphs (h) 

and (i) of this AD. The initial compliance 

times for the airworthiness limitation 

instruction (ALI) tasks are within the 

applicable compliance times for each AWL 

number specified in paragraphs (g)(1) 

through (8) of this AD: 

(1) For AWL No. 28–AWL–01, ‘‘External 

Wires Over Center Fuel Tank’’: At the 

applicable time specified in paragraph 

(g)(1)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–01 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

144 months since issuance of the original 

airworthiness certificate or original export 

certificate, or within 12 months after the 

effective date of this AD, whichever occurs 

later. 

(ii) For airplanes not identified in 

paragraph (g)(1)(i) of this AD: Within 144 

months since AWL No. 28–AWL–01 was 

incorporated into the existing maintenance or 

inspection program, or within 144 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–01, whichever occurs later. 

(2) For 28–AWL–03, ‘‘Fuel Quantity 

Indicating System (FQIS)—Out Tank Wiring 

Lightning Shield to Ground Termination’’: At 

the applicable time specified in paragraph 

(g)(2)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–03 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

144 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 12 

months after the effective date of this AD, 

whichever occurs later. 

(ii) For airplanes not identified in 

paragraph (g)(2)(i) of this AD: Within 144 

months since AWL No. 28–AWL–03 was 

incorporated into the existing maintenance or 

inspection program, or within 144 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–03, whichever occurs later. 

(3) For 28–AWL–09, ‘‘Over-Current and 

Arcing Protection Electrical Design Features 

Operation—Fault Current Detector for Center 

Tank Override/Jettison (O/J) Pumps’’: At the 

applicable time specified in paragraph 

(g)(3)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–09 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

18 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 90 days 

after the effective date of this AD, whichever 

occurs later. 

(ii) For airplanes not identified in 

paragraph (g)(3)(i) of this AD: Within 18 

months since AWL No. 28–AWL–09 was 

incorporated into the existing maintenance or 

inspection program, or within 18 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–09, whichever occurs later. 

(4) For AWL No. 28–AWL–13, ‘‘Main Tank, 

Center Wing Tank, Body Tank (if installed), 

and Auxiliary Tank (if installed) Refuel Valve 

Installation—Fault Current Bond’’: At the 

applicable time specified in paragraph 

(g)(4)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–13 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

144 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 12 

months after the effective date of this AD, 

whichever occurs later. 

(ii) For airplanes not identified in 

paragraph (g)(4)(i) of this AD: Within 144 

months since AWL No. 28–AWL–13 was 

incorporated into the existing maintenance or 

inspection program, or within 144 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–13, whichever occurs later. 

(5) For AWL No. 28–AWL–22, ‘‘Center 

Tank Override/Jettison Fuel Pump Inlet 

Protection and Power Failed On Protection 

System’’: At the applicable time specified in 

paragraph (g)(5)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–22 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

12 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 90 days 

after the effective date of this AD, whichever 

occurs later. 

(ii) For airplanes not identified in 

paragraph (g)(5)(i) of this AD: Within 12 

months since AWL No. 28–AWL–22 was 

incorporated into the existing maintenance or 

inspection program, or within 12 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–22, whichever occurs later. 

(6) For AWL No. 28–AWL–23, ‘‘OverCurrent and Arcing Protection Electrical 

Design Features Operation—Main Tank AC 

Fuel Pump and Center Tank Scavenge AC 

Fuel Pump Ground Fault Interrupter (GFI)’’: 

At the applicable time specified in paragraph 

(g)(6)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–23 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

12 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, within 12 months 


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since Boeing Service Bulletin 747–28A2261 

was incorporated, or within 90 days after the 

effective date of this AD, whichever occurs 

latest. 

(ii) For airplanes not identified in 

paragraph (g)(6)(i) of this AD: Within 12 

months since AWL No. 28–AWL–23 was 

incorporated into the existing maintenance or 

inspection program, or within 12 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–23, whichever occurs later. 

(7) For AWL No. 28–AWL–25, ‘‘Cushion 

Clamps and Teflon Sleeving Installed on Outof-Tank Wire Bundles Installed on Brackets 

that are Mounted Directly on the Fuel 

Tanks’’: At the applicable time specified in 

paragraph (g)(7)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–25 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

144 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 12 

months after the effective date of this AD, 

whichever occurs later. 

(ii) For airplanes not identified in 

paragraph (g)(7)(i) of this AD: Within 144 

months since AWL No. 28–AWL–25 was 

incorporated into the existing maintenance or 

inspection program, within 144 months since 

Boeing Special Attention Service Bulletin 

747–57–2327 was incorporated, or within 

144 months after the most recent inspection 

was performed as specified in AWL No. 28– 

AWL–25, whichever occurs latest. 

(8) For AWL No. 28–AWL–31, ‘‘Reserve 

Tank Refuel Valve Installation—Lightning 

Protection Electrical Bond’’: At the 

applicable time specified in paragraph 

(g)(8)(i) or (ii) of this AD. 

(i) For airplanes that did not have any 

version of AWL No. 28–AWL–31 in the 

existing maintenance or inspection program 

before the effective date of this AD: Within 

72 months since issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 6 

months after the effective date of this AD, 

whichever occurs later. 

(ii) For airplanes not identified in 

paragraph (g)(8)(i) of this AD: Within 72 

months since AWL No. 28–AWL–31 was 

incorporated into the existing maintenance or 

inspection program, or within 72 months 

after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–31, whichever occurs later. 

(h) Differences From the Required Service 

Information 

(1) Where the ‘‘Applicability’’ column of 

AWL Nos. 28–AWL–25 and 28–AWL–27 

specifies ‘‘ALL’’ and ‘‘NOTE,’’ replace that 

text with ‘‘Airplanes L/N 645 and on.’’ 

(2) In the ‘‘Description’’ column of AWL 

Nos. 28–AWL–25 and 28–AWL–27, remove 

the Applicability Note. 

(i) Additional Acceptable Wire Types and 

Sleeving 

(1) Where AWL No. 28–AWL–11 identifies 

wire types BMS 13–48, BMS 13–58, and BMS 

13–60, the following wire types are 

acceptable: MIL–W–22759/16, SAE 

AS22759/16 (M22759/16), MIL–W–22759/32, 

SAE AS22759/32 (M22759/32), MIL–W– 

22759/34, SAE AS22759/34 (M22759/34), 

MIL–W–22759/41, SAE AS22759/41 

(M22759/41), MIL–W–22759/86, SAE 

AS22759/86 (M22759/86), MIL–W–22759/87, 

SAE AS22759/87 (M22759/87), MIL–W– 

22759/92, and SAE AS22759/92 (M22759/ 

92); and MIL–C–27500 and NEMA WC 27500 

cables constructed from these military or 

SAE specification wire types, as applicable. 

(2) Where AWL No. 28–AWL–11 identifies 

TFE–2X Standard wall for wire sleeving, the 

following sleeving materials are acceptable: 

Roundit 2000NX and Varglas Type HO, HP, 

or HM. 

(j) No Alternative Actions, Intervals, or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After the existing maintenance or 

inspection program has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), 

intervals, or CDCCLs may be used unless the 

actions, intervals, and CDCCLs are approved 

as an alternative method of compliance 

(AMOC) in accordance with the procedures 

specified in paragraph (l) of this AD. 

(k) Terminating Action for Certain ADs 

Accomplishment of the revision required 

by paragraph (g) of this AD terminates the 

requirements specified in paragraphs (k)(1) 

through (7) of this AD for that airplane: 

(1) The revision required by paragraphs (g) 

and (h) of AD 2008–10–07 R1. 

(2) The revision required by paragraph 

(g)(1) of AD 2008–18–09. 

(3) The revision required by paragraph 

(h)(2) of AD 2010–13–12. 

(4) The revision required by paragraph (h) 

of AD 2010–24–13. 

(5) The revision required by paragraph (k) 

of AD 2011–06–03. 

(6) The revision required by paragraph 

(h)(2) of AD 2014–15–14. 

(7) The revision required by paragraph (h) 

of AD 2016–19–03. 

(l) 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 (m)(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. 

(m) Related Information 

(1) For more information about this AD, 

contact Rose Len, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des Moines, 

WA 98198; phone and fax: 206–231–3604; 

email: rose.len@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; 

phone: 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 May 9, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–11750 Filed 6–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0592; Project 

Identifier MCAI–2021–01023–T] 

RIN 2120–AA64 

Airworthiness Directives; MHI RJ 

Aviation ULC (Type Certificate 

Previously Held by Bombardier, Inc.) 

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 MHI RJ Aviation ULC Model 

CL–600–2D24 (Regional Jet Series 900) 

airplanes. This proposed AD was 

prompted by a report of a manufacturing 

error that can create dents on the lower 

wing plank, close to the flap arm 

locations at certain wing stations; as a 

result, cracks could develop and weaken 

the structural integrity of the wings 

before being detected by any existing 

required inspections. This proposed AD 

would require an inspection for damage 

(including dents, cracks, discoloration, 

gouges, scratches, or other surface 

damage) of the lower wing plank in the 

flap arm areas at certain wing stations, 

and repair if necessary. The FAA is 


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