Federal Register / Vol. 87, No. 44 / Monday, March 7, 2022 / Rules and Regulations 12561 

and before further flight, repair or replace the 

affected part, as applicable, in accordance 

with Action 2 in Schempp-Hirth 

Flugzeugbau GmbH Working Instructions for 

Technical Note No. 349–42/825–57, Revision 

4, dated August 31, 2020. 

(h) Credit for Previous Actions 

You may take credit for the actions 

required by paragraph (g) of this AD if you 

performed those actions before the effective 

date of this AD using Schempp-Hirth 

Flugzeugbau GmbH Working Instructions for 

Technical Note No. 349–42/825–57, Revision 

2, dated February 24, 2020; or SchemppHirth Flugzeugbau GmbH Working 

Instructions for Technical Note No. 349–42/ 

825–57, Revision 3, dated March 31, 2020. 

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

email to: 9-AVS-AIR-730-AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(j) Related Information 

(1) For more information about this AD, 

contact Jim Rutherford, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation Branch, 

FAA, 901 Locust, Room 301, Kansas City, 

MO 64106; phone: (816) 329–4165; email: 

jim.rutherford@faa.gov. 

(2) Refer to European Union Aviation 

Safety Agency (EASA) AD 2020–0063, dated 

March 18, 2020, for more information. You 

may examine the EASA AD in the AD docket 

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

for and locating Docket No. FAA–2021–1019. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Schempp-Hirth Flugzeugbau GmbH 

Working Instructions for Technical Note No. 

349–42/825–57, Revision 4, dated August 31, 

2020. 

Note 1 to paragraph (k)(2)(i): This service 

information contains German to English 

translation. EASA used the English 

translation in referencing the document from 

Schempp-Hirth Flugzeugbau GmbH. For 

enforceability purposes, the FAA will cite 

references to the service information in 

English as it appears on the document. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Schempp-Hirth Flugzeugbau 

GmbH, Krebenstrasse 25, 73230 Kirchheim/ 

Teck, Germany; phone: +49 7021 7298–0; fax: 

+49 7021 7298–199; email: info@schempphirth.com; website: https://www.schempphirth.com. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. 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 February 17, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–04650 Filed 3–4–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0664; Project 

Identifier AD–2021–00158–T; Amendment 

39–21938; AD 2022–03–21] 

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 787–8, 

787–9, and 787–10 airplanes. 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 and the nitrogen 

generation system. This AD requires 

revising the existing maintenance or 

inspection program, as applicable, to 

incorporate new or more restrictive 

airworthiness limitations. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective April 11, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 11, 2022. 

ADDRESSES: For service information 

identified in this final rule, 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. 

It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0664. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0664; 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: Tak 

Kobayashi, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA; phone: 206–231–3553; 

email: Takahisa.Kobayashi@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 787–8, 787–9, and 787–10 

airplanes. The NPRM published in the 

Federal Register on October 6, 2021 (86 

FR 55538). The NPRM was prompted by 

significant changes, including new or 

more restrictive requirements, made to 

the AWLs related to fuel tank ignition 

prevention and the nitrogen generation 

system. In the NPRM, the FAA proposed 

to require revising the existing 

maintenance or inspection program, as 

applicable, to incorporate new or more 

restrictive airworthiness limitations. 

The FAA is issuing this AD to address 

ignition sources inside the fuel tanks 

and increased flammability exposure of 

the fuel tanks caused by latent failures, 

alterations, repairs, or maintenance 

actions, which could result in a fuel 


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tank explosion and consequent loss of 

an airplane. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from the 

Air Line Pilots Association, 

International (ALPA) and United 

Airlines who supported the NPRM 

without change. 

The FAA received additional 

comments from two commenters, 

including Boeing and American Airlines 

(AA). The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 

Request To Clarify Applicability 

Boeing asked for clarification that the 

applicability specified in the proposed 

AD is the same as the effectivity 

specified in the referenced service 

information. Boeing stated that the 

effectivity in the service information 

mandated by the proposed AD does not 

apply to Model 787–8 airplanes having 

line numbers 1 through 5. 

The FAA agrees that this AD does not 

apply to Model 787–8 airplanes having 

line numbers 1 through 5. The FAA has 

changed paragraph (c) of this AD 

accordingly. 

Request To Clarify Applicability for 

AWL No. 57–AWL–13 

Boeing and AA asked for clarification 

that the initial compliance time 

specified in paragraph (g)(11)(ii)(B) of 

the proposed AD is applicable only to 

Model 787 airplanes having line 

numbers 10, 13, and 15 through 19 

inclusive. Boeing stated that AWL No. 

57–AWL–13 explicitly identifies those 

specific line numbers instead of 

referring to Boeing Service Bulletin 

B787–81205–SB570030–00. AA stated 

that for airplanes not included in the 

effectivity of the referenced service 

bulletin, operators could misinterpret 

the actions required by paragraph 

(g)(11)(ii)(B) for those airplanes, 

regardless of the applicability specified 

in AWL No. 57–AWL–13. 

The FAA agrees that the initial 

compliance time specified in paragraph 

(g)(11)(ii)(B) of this AD is applicable 

only to Model 787 airplanes having line 

numbers 10, 13, and 15 through 19 

inclusive. The FAA has revised 

paragraph (g)(11)(ii)(B) accordingly. 

Request To Clarify Applicability in 

Airworthiness Limitation Instruction 

(ALI) 

Boeing asked for clarification that the 

initial compliance time for performing 

an inspection in accordance with each 

ALI task specified in paragraphs (g)(1) 

through (14) of the proposed AD is 

applicable only to the airplanes 

specified in the applicability of each 

ALI task. Boeing also asked for 

clarification that the proposed AD does 

not supersede the applicability of the 

ALI tasks. Boeing stated that each ALI 

task has a unique applicability, and 

some of these tasks only apply to a 

subset of the airplanes affected by the 

proposed AD. 

The FAA agrees to provide 

clarification. This AD requires 

incorporation of the service information 

into the maintenance or inspection 

program. After this action is done, 

compliance with each ALI or critical 

design configuration control limitation 

(CDCCL) task incorporated into the 

maintenance or inspection program is 

required by the operating rules in 14 

CFR 91.403(c) and 43.16. This AD does 

not change or supersede any ALI or 

CDCCL task or its applicability. 

Compliance is based on the 

applicability specified in each ALI or 

CDCCL task. Therefore, the FAA has not 

changed this AD in this regard. 

Request To Clarify ‘‘Recent Inspection’’ 

Boeing asked for clarification 

regarding a recent inspection referenced 

in the sub-paragraphs to paragraphs 

(g)(1) through (14) of the proposed AD. 

Boeing asked that the FAA clarify that 

a recent inspection performed on an 

airplane can be the inspection done in 

accordance with an ALI task of the 

existing maintenance or inspection 

program applicable to that airplane. 

Boeing stated that without clarification, 

its interpretation is that the initial 

inspections are required to be performed 

in accordance with the ALI tasks 

provided in the service information 

mandated by paragraph (g) of the AD. 

The FAA agrees to provide 

clarification. The initial compliance 

time specified in the sub-paragraphs to 

paragraph (g)(1) through (14) of this AD 

is the compliance time to perform the 

first inspection in accordance with each 

ALI task, after incorporation of the 

service information into the 

maintenance or inspection program as 

required by paragraph (g) of this AD. 

The ‘‘most recent’’ inspection 

referenced in those paragraphs is the 

inspection performed in accordance 

with an ALI task of the operator’s 

existing maintenance or inspection 

program prior to incorporation of the 

service information mandated by 

paragraph (g) of this AD. Certain ALI 

tasks from the same or earlier revisions 

of the service information mandated by 

paragraph (g) of this AD should already 

exist in the maintenance or inspection 

program. The requirements of 

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

are intended to address the transition to 

the ALI tasks after accomplishment of 

the actions required by paragraph (g) of 

this AD, without disrupting the existing 

inspection intervals. Therefore, the FAA 

has not changed this AD in this regard. 

Request To Extend Compliance Time 

Boeing asked that the compliance 

time to revise the maintenance/ 

inspection program required by 

paragraph (g) of the proposed AD be 

changed from 180 to 240 days. Boeing 

stated that the majority of the 

inspections require entry into a wet fuel 

cell to access and possibly repair 

structural sealant applications, at 

unique facilities and with significant 

aircraft downtime. Boeing added that an 

extension of the compliance time to 240 

days would allow additional flexibility 

to operators. Boeing also asked whether 

an initial inspection done within 180 

days after the effective date of the AD 

must be performed in accordance with 

the service information mandated by 

this AD or if it is allowed to be 

performed under the existing 

maintenance or inspection program 

applicable to that airplane. Boeing 

stated that performing the initial 

inspection within 180 days after the 

effective date of the AD seems to 

conflict with the requirement to revise 

the maintenance or inspection program 

within 180 days after the effective date 

of the AD. 

The FAA does not agree to extend the 

compliance time to revise the 

maintenance/inspection program 

required by paragraph (g) of this AD 

from 180 to 240 days because the FAA 

has determined that this compliance 

time is adequate for operators to 

incorporate maintenance or inspection 

program changes for their affected fleet. 

The 180-day compliance time required 

by paragraph (g) is unrelated to the 

initial compliance time for performing 

the inspections in accordance with each 

ALI task specified in the service 

information mandated by this AD. 

Paragraph (g) requires incorporation of 

the service information into the 

maintenance or inspection program 

within 180 days after the effective date 

of this AD. Once the maintenance/ 

inspection program has been revised, 

compliance with each ALI or CDCCL 

task of the maintenance or inspection 

program is required by the operating 

rules in 14 CFR 91.403(c) and 43.16. For 

clarification, the initial compliance time 

to perform an inspection after 

incorporation of the service information 

into the maintenance or inspection 

program is specified in paragraphs (g)(1) 

through (14) of this AD. Therefore, the 


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FAA has not changed this AD in this 

regard. 

Request To Add Revision Level to a 

Certain Service Bulletin Reference 

AA asked that the FAA specify the 

revision level of Boeing Service Bulletin 

B787–81205–SB570030–00, referenced 

in paragraph (g)(11)(ii)(A) of the 

proposed AD. AA stated that specifying 

the revision level of the service bulletin 

will reduce any ambiguity for the 

requirements associated with that 

revision level. 

The FAA does not agree to include 

the revision level of Boeing Service 

Bulletin B787–81205–SB570030–00. 

Including the revision level of the 

referenced service bulletin could 

potentially conflict with another AD 

that mandates that service bulletin. 

Boeing Service Bulletin B787–81205– 

SB570030–00, Issue 001, dated March 

17, 2017, is required by AD 2018–11–13, 

Amendment 39–19301 (83 FR 25894, 

June 5, 2018) (AD 2018–11–13). If a later 

revision of that service bulletin is issued 

in the future as an (alternative method 

of compliance) AMOC to AD 2018–11– 

13, the actions in the later revision can 

be done equivalent to Issue 001. 

Specifying ‘‘Issue 001 or later’’ in 

paragraph (g)(11)(ii)(A) of this AD 

would make it consistent with the 

requirements in AD 2018–11–13; 

however, if AD 2018–11–13 must be 

superseded to mandate a later revision 

of the service bulletin, this AD would 

also have to be superseded if the 

revision level of the service bulletin is 

specified. Therefore, the FAA has 

determined that the revision level of the 

referenced service bulletin will not be 

included in this AD, and has not 

changed this AD in this regard. 

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 Boeing 787 

Special Compliance Items/ 

Airworthiness Limitations, D011Z009– 

03–04, dated August 2018. This service 

information specifies AWLs that include 

ALIs and CDCCLs 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 ADDRESSES. 

Costs of Compliance 

The FAA estimates that this AD 

affects 121 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this 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 

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: 

2022–03–21 The Boeing Company: 

Amendment 39–21938; Docket No. 

FAA–2021–0664; Project Identifier AD– 

2021–00158–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 11, 2022. 

(b) Affected ADs 

This AD affects AD 2018–11–13, 

Amendment 39–19301 (83 FR 25894, June 5, 

2018) (AD 2018–11–13). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8, 787–9, and 787–10 airplanes, 

certificated in any category, having line 

numbers (L/Ns) 6 through 871 inclusive, 

excluding L/N 688; and L/Ns 873, 875, 877, 

878, 879, 881, and 883. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by significant 

changes, including new and more restrictive 

requirements, 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 ignition sources inside the fuel 

tanks and increased flammability exposure of 

the fuel tanks caused by latent failures, 

alterations, repairs, or maintenance actions, 

which could result in a fuel tank explosion 

and consequent loss of an airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 180 days after the effective date of 

this AD, revise the existing maintenance or 


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inspection program, as applicable, to 

incorporate the information specified in 

Sections C through F of Boeing 787 Special 

Compliance Items/Airworthiness 

Limitations, D011Z009–03–04, dated August 

2018. The initial compliance time for doing 

the airworthiness limitation instruction (ALI) 

tasks specified in Sections C through F of 

Boeing 787 Special Compliance Items/ 

Airworthiness Limitations, D011Z009–03–04, 

dated August 2018, as applicable for each 

airplane, is at the times specified in 

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

(1) For AWL No. 28–AWL–89, ‘‘Fuel 

Quantity Data Concentrator (FQDC) Bracket 

Inspections,’’ at the applicable time in 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 28– 

AWL–89: Within 5 years or 10,000 flight 

cycles, whichever occur first after the most 

recent inspection was performed as specified 

in AWL No. 28–AWL–89. 

(ii) For airplanes on which no initial 

inspection was performed: Within 5 years or 

10,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(2) For AWL No. 57–AWL–01, ‘‘Edge and 

Fillet Seals at Stringer and Spar Locations 

(Zone 2),’’ at the applicable time in paragraph 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–01: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–01. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(3) For AWL No. 57–AWL–02, ‘‘Fasteners 

on Bare Carbon Fiber Reinforced Plastic 

(CFRP) Stripes,’’ at the applicable time in 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–02: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–02. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(4) For AWL No. 57–AWL–03, ‘‘Head-intank Thin-Sleeved Interference-Fit Fasteners 

with Heads in the Fuel Tank’’ at the 

applicable time in paragraph (g)(4)(i) or (ii) 

of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–03: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–03. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(5) For AWL No. 57–AWL–05, ‘‘Titanium 

Collars—BACC30CT Fasteners (Clearance 

Fit).’’ at the applicable time in paragraph 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–05: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–05. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(6) For AWL No. 57–AWL–06, ‘‘Titanium 

Collars—BACC30CY Collars (Interference-Fit 

with Swaged Collars)’’ at the applicable time 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–06: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–06. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(7) For AWL No. 57–AWL–07, ‘‘Tensionrated Bolt Locations at Side of Body (SOB) 

and Nacelle Fittings’’ at the applicable time 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–07: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–07. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(8) For AWL No. 57–AWL–08, ‘‘Dielectric 

Top on Wing Surface,’’ at the applicable time 

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

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–08: Within 6 years or 12,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–08. 

(ii) For airplanes on which no initial 

inspection was performed: Within 6 years or 

12,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(9) For AWL No. 57–AWL–09, ‘‘Inspection 

Requirements for Class 1A Seal Installations 

created as a result of Boeing Material Review 

Board,’’ at the applicable time in paragraph 

(g)(9)(i) or (ii) of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–09: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–09. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(10) For AWL No. 57–AWL–10, 

‘‘Inspection Requirements for In-Tank 

Fasteners near Side of Body (SOB) Rib and 

between Ribs 7 and 18,’’ at the applicable 

time in paragraph (g)(10)(i) or (ii) of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–10: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–10. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(11) For AWL No. 57–AWL–13, 

‘‘Inspection Requirements for In-Tank 

Fasteners and Edge Seal near Disbond 

Arrestment (DBA) Fastener Installations in 

Lightning Zone 2,’’ at the applicable time in 

paragraph (g)(11)(i) or (ii) of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–13: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–13. 

(ii) For airplanes on which no initial 

inspection was performed: At the applicable 

time in paragraph (g)(11)(ii)(A) or (B) of this 

AD. 

(A) For airplanes on which Boeing Service 

Bulletin B787–81205–SB570030–00 is 

applicable: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the 

incorporation of Boeing Service Bulletin 

B787–81205–SB570030–00. 

(B) For airplanes having line numbers 10, 

13, and 15 through 19 inclusive: Within 12 

years or 24,000 flight cycles, whichever 

occurs first after the date of issuance of the 

original standard airworthiness certificate or 

the date of issuance of the original export 

certificate of airworthiness. 

(12) For AWL No. 57–AWL–14, 

‘‘Supplemental Inspection Requirements for 

Pre-cured Sealant Caps, Fillet Seals, and 

Edge Seals associated Stringer Splice Fitting 

Installation located at Right Wing Upper 

Panel Stringer No. 3, just Outboard of the 

Side of Body Rib,’’ at the applicable time in 

paragraph (g)(12)(i) or (ii) of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–14: Within 12 years or 24,000 flight 

cycles whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–14. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 


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24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(13) For AWL No. 57–AWL–15, 

‘‘Inspection Requirements for Pre-cured 

Sealant Caps, Injection Seals, Fillet Seals, 

and Edge Seals associated with the Wing 

Lower Panel Stringer Attachments to the 

Lower Side of Body (SOB) Chord,’’ at the 

applicable time in paragraph (g)(13)(i) or (ii) 

of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–15: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–15. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(14) For AWL No. 57–AWL–16, 

‘‘Supplemental Inspection Requirements for 

Edge Seals located at Left Wing Upper Panel 

Stringer No. 19, Between Ribs 8 and 9,’’ at 

the applicable time in paragraph (g)(14)(i) or 

(ii) of this AD. 

(i) For airplanes on which an inspection 

was performed as specified in AWL No. 57– 

AWL–16: Within 12 years or 24,000 flight 

cycles, whichever occurs first after the most 

recent inspection was performed as specified 

in AWL No. 57–AWL–16. 

(ii) For airplanes on which no initial 

inspection was performed: Within 12 years or 

24,000 flight cycles, whichever occurs first 

after the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

(h) No Alternative Actions, Intervals, or 

Critical Design Configuration Control 

Limitations 

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 critical design configuration 

control limitation (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 (j) of this 

AD. 

(i) Terminating Actions 

Accomplishment of the revision required 

by paragraph (g) of this AD terminates the 

requirements specified in paragraph (h) of 

AD 2018–11–13, for Model 787–8 airplanes 

only. 

(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 Related Information. 

Information may be emailed to: 9-ANMSeattle-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. 

(k) Related Information 

For more information about this AD, 

contact Tak Kobayashi, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

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

WA; phone: 206–231–3553; email: 

Takahisa.Kobayashi@faa.gov. 

(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) Boeing 787 Special Compliance Items/ 

Airworthiness Limitations, D011Z009–03–04, 

dated August 2018. 

(ii) [Reserved] 

(3) 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. 

(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 January 28, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–04662 Filed 3–4–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0883; Project 

Identifier AD–2021–00307–T; Amendment 

39–21950; AD 2022–04–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–16– 

01, which applied to all Airbus SAS 

Model A318, A319, A320, and A321 

series airplanes. AD 2020–16–01 

required repetitive cleaning and 

greasing of affected cargo door seals 

(both original equipment manufacturer 

(OEM) and parts manufacturer approval 

(PMA) parts). This AD was prompted by 

reports of low halon concentration in 

the forward and aft cargo compartments 

due to air leakage through cargo 

compartment door seals, and the FAA’s 

determination that improved cargo door 

seals must be installed and that certain 

flight operations must be limited until 

the improved cargo door seals are 

installed. This AD retains certain 

actions required by AD 2020–16–01 and 

requires replacing certain forward and 

aft cargo compartment door seals with 

new seals and installing a placard on 

the cargo compartment doors; and for 

certain airplanes, revising the existing 

airplane flight manual (AFM) to 

implement an operational limitation for 

certain routes. The FAA is issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective April 11, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 11, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 20, 2021 (86 FR 

51265, September 15, 2021). 

ADDRESSES: For Airbus service 

information identified in this final rule, 

contact Airbus SAS, Airworthiness 

Office—EIAS, Rond-Point Emile 

Dewoitine No: 2, 31700 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax 

+33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

internet http://www.airbus.com. For 

European Union Aviation Safety Agency 


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