Federal Register / Vol. 86, No. 37 / Friday, February 26, 2021 / Proposed Rules 11653 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by a report from 

the manufacturer that the Automated Damage 

Tracking System (ADTS) may under-count 

the number of cycles accrued by the impeller 

and the high-pressure compressor (HPC) 

rotor, which could result in the failure of 

these components. The FAA is issuing this 

AD to prevent failure of the impeller and the 

HPC rotor. The unsafe condition, if not 

addressed, could result in the uncontained 

release of the impeller or the HPC rotor, 

damage to the engine, damage to the 

helicopter, and loss of control of the 

helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Before exceeding 7,000 starts or 14,000 

flight cycles since new (CSN) on the affected 

engine, or prior to removal of the engine from 

the aircraft for the purpose of sending the 

engine to a repair or overhaul facility, 

whichever occurs first after the effective date 

of this AD: 

(1) Use the manual low-cycle fatigue (LCF) 

counting method to determine the 

accumulated LCF cycles for the impeller and 

the HPC rotor using paragraph 3., 

Accomplishment Instructions, of P&WC Alert 

Service Bulletin (ASB) PW210–72–A57142, 

Revision 1, dated March 26, 2020 or PW210– 

72–A57143, Revision 1, dated March 26, 

2020, as applicable for the engine model. 

(2) After performing the actions required 

by paragraph (g)(1) of this AD, use the 

manual LCF counting method specified in 

paragraph (g)(1) of this AD to count 

subsequent LCF cycles on the impeller and 

HPC rotor. Do not use the ADTS to count 

subsequent LCF cycles on the impeller or the 

HPC rotor. 

(h) Definition 

For the purpose of this AD, a ‘‘start’’ is an 

engine start followed by one or more flights. 

(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 ECO Branch, send it to 

the attention of the person identified in 

Related Information. 

(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 Barbara Caufield, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7146; fax: (781) 238–7199; email: 

barbara.caufield@faa.gov. 

(2) Refer to Transport Canada Civil 

Aviation (TCCA) AD CF–2020–13, dated 

April 28, 2020, for more information. You 

may examine the TCCA AD in the AD docket 

at https://www.regulations.gov by searching 

for and locating it in Docket No. FAA–2021– 

0103. 

(3) For service information identified in 

this AD, contact Pratt & Whitney Canada 

Corp., 1000 Marie-Victorin, Longueuil, 

Quebec, J4G 1A1, Canada; phone: (800) 268– 

8000. 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 (781) 238–7759. 

Issued on February 19, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03814 Filed 2–25–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0099; Project 

Identifier AD–2020–01272–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 

series airplanes. This proposed AD was 

prompted by significant changes made 

to the airworthiness limitations (AWLs) 

related to fuel tank ignition prevention 

and the nitrogen generation system. 

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 April 12, 2021. 

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 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 on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0099; 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3556; email: rebel.nichols@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–2021–0099; Project Identifier AD– 

2020–01272–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 the 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 


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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 proposed 

AD. 

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 Rebel Nichols, 

Aerospace Engineer, Propulsion 

Section, FAA, Seattle ACO Branch, 2200 

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

phone and fax: 206–231–3556; email: 

rebel.nichols@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 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). 

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 final 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 has 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, single failures in 

combination with another latent 

condition(s), and in-service failure 

experience. For all four 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 made to the AWL 

related to fuel tank ignition prevention 

and the nitrogen generation system. 

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. 

The FAA has determined that 

accomplishing the revision required by 

paragraph (g) of this proposed AD 

would terminate the following 

requirements for that airplane: 

• The revision required by paragraphs 

(g) and (h) of AD 2008–11–01 R1, 

Amendment 39–16145 (74 FR 68515, 

December 28, 2009). 

• The revision required by paragraph 

(h) of AD 2010–06–10, Amendment 39– 

16234 (75 FR 15322, March 29, 2010) 

(AD 2010–06–10). 

• The revision required by paragraph 

(k) of AD 2011–25–05, Amendment 39– 

16881 (77 FR 2442, January 18, 2012) 

(AD 2011–25–05). 

• The revision required by paragraph 

(n) of AD 2013–25–02, Amendment 39– 

17698 (79 FR 24541, May 1, 2014) (AD 

2013–25–02). 

• The revision required by paragraph 

(g) of AD 2014–08–09, Amendment 39– 

17833 (79 FR 24546, May 1, 2014) (AD 

2014–08–09). 

• The revision required by paragraph 

(h) of AD 2014–20–02, Amendment 39– 

17975 (79 FR 59102, October 1, 2014) 

(AD 2014–20–02). 

• The revision required by paragraphs 

(i)(3)(i) and (ii) of AD 2018–20–13, 

Amendment 39–19447 (83 FR 52305, 

October 17, 2018) (AD 2018–20–13). 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Boeing 767–200/ 

300/300F/400ER Special Compliance 

Items/Airworthiness Limitations, 

D622T001–9–04, dated January 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 and the 

nitrogen generation system. 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 the ADDRESSES section. 

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. 

Proposed AD Requirements 

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 (k) of this proposed AD. 


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Costs of Compliance 

The FAA estimates that this proposed 

AD affects 500 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. 

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– 

2021–0099; Project Identifier AD–2020– 

01272–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) action by April 

12, 2021. 

(b) Affected ADs 

This AD affects the ADs specified in 

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

(1) AD 2008–11–01 R1, Amendment 39– 

16145 (74 FR 68515, December 28, 2009) (AD 

2008–11–01 R1). 

(2) AD 2010–06–10, Amendment 39–16234 

(75 FR 15322, March 29, 2010) (AD 2010–06– 

10). 

(3) AD 2011–25–05, Amendment 39–16881 

(77 FR 2442, January 18, 2012) (AD 2011–25– 

05). 

(4) AD 2013–25–02, Amendment 39–17698 

(79 FR 24541, May 1, 2014) (AD 2013–25– 

02). 

(5) AD 2014–08–09, Amendment 39–17833 

(79 FR 24546, May 1, 2014) (AD 2014–08– 

09). 

(6) AD 2014–20–02, Amendment 39–17975 

(79 FR 59102, October 1, 2014) (AD 2014–20– 

02). 

(7) AD 2018–20–13, Amendment 39–19447 

(83 FR 52305, October 17, 2018) (AD 2018– 

20–13). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, –300F, and –400ER 

series airplanes, certificated in any category, 

having line numbers (L/N) 1 through 1200 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by significant 

changes made to the airworthiness 

limitations (AWLs) related to fuel tank 

ignition prevention and the nitrogen 

generation system. 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 in Section A, 

including Subsections A.1, A.2, A.3, A.4, and 

A.5, of Boeing 767–200/300/300F/400ER 

Special Compliance Items/Airworthiness 

Limitations, D622T001–9–04, revision 

January 2020; except as provided by 

paragraph (h) of this AD. The initial 

compliance times for the airworthiness 

limitation instructions (ALI) tasks are within 

the applicable compliance times specified in 

paragraphs (g)(1) through (14) of this AD: 

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

Wires Over Auxiliary (Center) Fuel Tank’’: 

Within 144 months after the most recent 

inspection was performed as specified in 

AWL No. 28 AWL 01, or within 12 months 

after the effective date of this AD if no initial 

inspection has been performed or the last 

inspection date is unknown. 

(2) For AWL No. 28–AWL–05, ‘‘Lightning 

Protection—Hydraulic Line Fuel Tank 

Penetration Bonding Path’’: Within 25,000 

flight hours or 72 months, whichever occurs 

first, since the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–05, or within 30 days after the effective 

date of this AD if no initial inspection has 

been performed or the last inspection date is 

unknown. 

(3) For AWL No. 28–AWL–18, ‘‘Fuel 

Quantity Indicating System (FQIS)—Out of 

Tank Wiring Lightning Shield to Ground 

Termination’’: Within 144 months after the 

most recent inspection was performed as 

specified in AWL No. 28–AWL–18, or within 

12 months after the effective date of this AD 

if no initial inspection has been performed or 

the last inspection date is unknown. 

(4) For AWL No. 28–AWL–20, ‘‘Auxiliary 

(Center) Tank Override Fuel Pumps Auto 

Shutoff Circuit’’: Within 12 months after the 

most recent inspection was performed as 

specified in AWL No. 28–AWL–20; or within 

12 months after accomplishment of the 

actions specified in Boeing Service Bulletin 

767–28A0083, or Boeing Service Bulletin 

767–28A0084, as applicable; whichever is 

later. If no initial inspection was performed 

or the last inspection date is unknown, then 

within 30 days after the effective date of this 

AD. 

(5) For AWL No. 28–AWL–21, ‘‘AC and DC 

Fuel Pump Fault Current Bonding Jumper 

Installation’’: Within 72 months after the 

most recent inspection was performed as 

specified in AWL No. 28–AWL–21, or within 

6 months after the effective date of this AD 

if no initial inspection has been performed or 

the last inspection date is unknown. 


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(6) For AWL No. 28–AWL–27, ‘‘OverCurrent and Arcing Protection Electrical 

Design Features Operation—AC Fuel Pump 

Ground Fault Interrupter (GFI)’’: Within 12 

months after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–27, or within 12 months after 

accomplishment of the actions specified in 

Boeing Service Bulletin 767–28A0085, 

whichever is later. If no initial inspection 

was performed or the last inspection date is 

unknown, then within 30 days after the 

effective date of this AD. 

(7) For AWL No. 28–AWL–28, ‘‘Auxiliary 

(Center) Tank Override/Jettison Fuel Pump 

Failed On Protection System’’: Within 12 

months after the most recent inspection was 

performed as specified in AWL No. 28– 

AWL–28, or within 12 months after 

accomplishment of the actions specified in 

Boeing Service Bulletin 767–28A0085, 

whichever is later. If no initial inspection 

was performed or the last inspection date is 

unknown, then within 30 days after the 

effective date of this AD. 

(8) For AWL No. 28–AWL–35, ‘‘Cushion 

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

that are Mounted Directly on the Fuel 

Tanks’’: Within 144 months after the most 

recent inspection was performed as specified 

in AWL No. 28–AWL–35 or within 144 

months after accomplishment of the actions 

specified in Boeing Service Bulletin 767– 

57A0102, whichever is later. If no initial 

inspection was performed or the last 

inspection date is unknown, then within 12 

months after the effective date of this AD. 

(9) For AWL No. 28–AWL–37, ‘‘FQIS BITE 

Test (Auxiliary (Center) Tank Circuit Test)’’: 

For Model 767–300F airplanes L/N 1094 and 

subsequent, within 750 flight hours after the 

most recent inspection was performed as 

specified in AWL No. 28–AWL–37, or within 

30 days after the effective date of this AD if 

no initial inspection has been performed or 

the last inspection date is unknown. 

(10) For AWL No. 28–AWL–38, ‘‘Fuel 

Level Sensing System (FLSS) Dry 

Capacitance Test’’: For Model 767–300F 

airplanes L/N 1096 and subsequent, within 

750 flight hours after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–38, or within 30 days 

after the effective date of this AD if no initial 

inspection has been performed or the last 

inspection date is unknown. 

(11) For AWL No. 28–AWL–101, ‘‘Engine 

Fuel Suction Feed Operational Test’’: Within 

7,500 flight hours or 36 months, whichever 

occurs first since the most recent inspection 

was performed as specified in AWL No. 28– 

AWL–101, or within 30 days after the 

effective date of this AD if no initial 

inspection has been performed or the last 

inspection date is unknown. 

(12) For AWL No. 28–AWL–102, ‘‘Fuel 

Quantity Indicating System (FQIS)—Low 

Fuel and Fuel Config Indication Test’’: 

Within 750 flight hours after the most recent 

inspection was performed as specified in 

AWL No. 28–AWL–102; or within 750 flight 

hours after accomplishment of the actions 

specified in Boeing Service Bulletin 767–31– 

0295 or Boeing Service Bulletin 767–31– 

0302, as applicable; whichever is later. If no 

initial inspection was performed or the last 

inspection date is unknown, then within 30 

days after the effective date of this AD. 

(13) For AWL No. 47–AWL–04, ‘‘Nitrogen 

Generation System (NGS)—NitrogenEnriched Air (NEA) Distribution Ducting’’: 

For L/N 993 and subsequent and all airplanes 

that have incorporated Boeing Service 

Bulletin 767–47–0001, within the applicable 

interval specified in AWL No. 47–AWL–04 

since the most recent inspection was 

performed as specified in AWL No. 47– 

AWL–04. If no initial inspection was 

performed or the last inspection date is 

unknown, then within 4 months after the 

effective date of this AD. 

(14) For AWL No. 47–AWL–05, ‘‘Nitrogen 

Generation System (NGS)—Cross Vent Check 

Valve’’: For L/N 993 and subsequent and all 

airplanes that have incorporated Boeing 

Service Bulletin 767–47–0001, within the 

applicable interval specified in AWL No. 47– 

AWL–05 since the most recent inspection 

was performed as specified in AWL No. 47– 

AWL–05. If no initial inspection was 

performed or the last inspection date is 

unknown, then within 4 months after the 

effective date of this AD. 

(h) Additional Acceptable Wire Types and 

Sleeving 

As an option, when accomplishing the 

actions required by paragraph (g) of this AD, 

the changes specified in paragraphs (h)(1) 

and (2) of this AD are acceptable. 

(1) Where AWL No. 28–AWL–09 identifies 

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

13–60, the following acceptable wire types 

and cables can be added to AWL No. 28– 

AWL–09: MIL–W–22759/16, SAE AS22759/ 

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

SAE AS22759/32 (formerly M22759/32), 

MIL–W–22759/34, SAE AS22759/34 

(formerly M22759/34), MIL–W–22759/41, 

SAE AS22759/41 (formerly M22759/41), 

MIL–W–22759/86, SAE AS22759/86 

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

SAE AS22759/87 (formerly M22759/87), 

MIL–W–22759/92, and SAE AS22759/92 

(formerly M22759/92); and MIL–C–27500 

and NEMA WC 27500 cables that are 

constructed from these military or SAE 

specification wire types, as applicable. 

(2) Where AWL No. 28–AWL–09 identifies 

TFE–2X Standard wall for wire sleeving, the 

following sleeving materials are acceptable: 

Roundit 2000NX and Varglas Type HO, HP, 

or HM, Grade A. 

(i) 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 (k) of this AD. 

(j) Terminating Action for Certain AD 

Requirements 

Accomplishment of the revision required 

by paragraph (g) of this AD terminates the 

requirements specified in paragraphs (j)(1) 

through (7) of this AD for that airplane: 

(1) The revision required by paragraphs (g) 

and (h) of AD 2008–11–01 R1. 

(2) The revision required by paragraph (h) 

of AD 2010–06–10. 

(3) The revision required by paragraph (k) 

of AD 2011–25–05. 

(4) The revision required by paragraph (n) 

of AD 2013–25–02. 

(5) The revision required by paragraph (g) 

of AD 2014–08–09. 

(6) The revision required by paragraph (h) 

of AD 2014–20–02. 

(7) The revision required by paragraphs 

(i)(3)(i) and (ii) of AD 2018–20–13. 

(k) 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 (l)(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. 

(l) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

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

WA 98198; phone and fax: 206–231–3556; 

email: rebel.nichols@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 

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 February 12, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03858 Filed 2–25–21; 8:45 am] 

BILLING CODE 4910–13–P 


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