Airworthiness Directives; The Boeing Company Airplanes, 16133-16137 [2021-06022]
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Federal Register / Vol. 86, No. 57 / Friday, March 26, 2021 / Proposed Rules
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (j)(2) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
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(1) For information about EASA AD 2020–
0219, contact EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49
221 8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may find
this EASA AD on the EASA website at
https://ad.easa.europa.eu. You may view this
material 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. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0192.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3223; email sanjay.ralhan@
faa.gov.
Issued on March 18, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–06236 Filed 3–25–21; 8:45 am]
BILLING CODE 4910–13–P
16:46 Mar 25, 2021
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0134; Project
Identifier AD–2020–01254–T]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model 777
airplanes. This proposed AD was
prompted by significant changes,
including new or more restrictive
requirements, made to the airworthiness
limitations (AWLs) and Critical Design
Configuration Control Limitations
(CDCCLs) related to fuel tank ignition
prevention, the engine fuel suction feed
system, and the nitrogen generation
system. This proposed AD would
require revising the existing
maintenance or inspection program, as
applicable, to incorporate new or more
restrictive airworthiness limitations.
The FAA is proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
The FAA must receive comments
on this proposed AD by May 10, 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
DATES:
(k) Related Information
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DEPARTMENT OF TRANSPORTATION
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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–
0134; 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:
Kevin Nguyen, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3555; email: kevin.nguyen@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–2021–0134; Project Identifier AD
AD–2020–01254–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
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
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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 Kevin Nguyen,
Aerospace Engineer, Propulsion
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3555; email:
kevin.nguyen@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’’) to 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
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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.
The FAA issued AD 2008–11–13,
Amendment 39–15536 (73 FR 30737,
May 29, 2008) (AD 2008–11–13), which
applies to certain The Boeing Company
Model 777–200, –200LR, –300, and
–300ER series airplanes. The
applicability of AD 2008–11–13 did not
include the Boeing Company Model
777F series airplane because those
airplanes were not yet type certificated.
AD 2008–11–13 requires incorporation
of fuel system AWLs and also requires
an initial inspection to phase in certain
repetitive inspections, and repair if
necessary. The fuel system AWLs were
developed to satisfy SFAR 88
requirements and were included in the
Airworthiness Limitations Section
(ALS) of the manufacturer’s Instructions
for Continued Airworthiness. Since the
FAA issued AD 2008–11–13, the ALS
has been significantly revised by the
manufacturer to correct technical and
editorial errors and also to add new or
more restrictive requirements. Many of
those changes are related to fuel tank
ignition prevention, the engine fuel
suction feed system, and the nitrogen
generation system. The FAA has
determined that the specific revisions of
the AWL mandated by AD 2008–11–13
(which applies to airplanes with an
original standard airworthiness
certificate or original export certificate
of airworthiness issued before December
5, 2007) and the revisions of the AWL
that have been delivered with airplanes
as part of the type design and
airworthiness certificate on or after
December 5, 2007, are inadequate to
provide information necessary to
maintain critical design features and
perform inspections.
The FAA also issued AD 2014–09–09,
Amendment 39–17844 (79 FR 30005,
May 27, 2014) (AD 2014–09–09), which
applies to all The Boeing Company
Model 777–200, –200LR, –300, –300ER,
and 777F series airplanes. AD 2014–09–
09 requires revising the maintenance
program to incorporate a revision to the
Airworthiness Limitations Section of
the maintenance planning data (MPD)
document. Since the FAA issued AD
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2014–09–09, 28–AWL–101 has been
revised, therefore, this proposed AD
would require the incorporation of the
revised 28–AWL–101. Incorporating the
revision required by this proposed AD
would terminate all the requirements of
AD 2014–09–09.
The FAA has received a report
indicating that significant changes,
including new or more restrictive
requirements, made to the AWLs and
CDCCLs related to fuel tank ignition
prevention, the engine fuel suction feed
system, and the nitrogen generation
system. The FAA is issuing this AD to
address ignition sources inside the fuel
tanks and the increased flammability
exposure of the center fuel tank caused
by latent failures, alterations, repairs, or
maintenance actions, which could result
in a fuel tank explosion and consequent
loss of an airplane; and to address
potential loss of engine fuel suction feed
capability, which could result in dual
engine flameouts, inability to restart
engines, and consequent forced landing
of the airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), of Boeing 777–200/200LR/300/
300ER/777F Maintenance Planning Data
(MPD) Document, D622W001–9, dated
November 2019. This service
information describes airworthiness
limitations and CDCCLs tasks related to
fuel tank ignition prevention, the engine
fuel suction feed system, 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 new or more restrictive
airworthiness limitations.
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
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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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Differences Between This Proposed AD
and the Service Information
Paragraph (g) of this proposed AD
would require operators to revise their
existing maintenance or inspection
program by incorporating, in part, AWL
No. 28–AWL–11, ‘‘Fuel Quantity
Indicating System (FQIS) and Auxiliary
Fuel Tank (Cell) Electronic Fuel Level
Indication System (EFLI)—Out Tank
Wiring Installation Separation
Requirement,’’ of Section 9,
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), of Boeing 777–200/200LR/300/
300ER/777F Maintenance Planning Data
(MPD) Document, D622W001–9, dated
November 2019.
Paragraph (h) of this proposed AD
would allow certain changes to be made
to the requirements specified in AWL
No. 28–AWL–11 as an option. Where
AWL No. 28–AWL–11 identifies certain
wire types for routing and installation of
any new wiring under certain
conditions, paragraph (h) of this
proposed AD provides acceptable
alternative wire types. Additionally,
where AWL No. 28–AWL–11 identifies
certain wiring sleeve material for new
wiring installed under certain
conditions, paragraph (h) of this
proposed AD provides acceptable
alternative wire sleeve materials.
Alternative Methods of Compliance
(AMOCs) Previously Approved for AD
2008–11–13
The FAA has previously issued
AMOC approvals for compliance with
paragraph (g)(2) of AD 2008–11–13 to
allow operators to incorporate
alternative versions of AWL No. 28–
AWL–11. AWL No. 28–AWL–11
includes the requirements for new
wiring introduced by any alterations or
changes to the type design, including
STC modifications, in proximity to
wiring that penetrates the fuel tank wall.
Certain STCs that introduced new
wiring near the fuel quantity indicating
system (FQIS) wiring utilized design
features that were different from the
critical design features for fuel tank
ignition prevention specified in the ADmandated version of AWL No. 28–
AWL–11. For those STCs, the FAA has
approved alternative versions of AWL
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No. 28–AWL–11 that specified critical
design features associated with STC
modifications. The FAA has determined
that certain critical design features
specified in the AMOC-approved
versions of AWL No. 28–AWL–11 are
not acceptable to meet the intent of this
AWL. Therefore, this proposed AD does
not allow credit for AMOCs previously
approved under AD 2008–11–13.
However, based on the agency’s
assessment of critical design features,
the FAA has provided options under
paragraph (h) of this proposed AD to
allow certain changes to be made to the
requirements specified in AWL No. 28–
AWL–11.
The requirements for new wiring
versus existing wiring are specified in
AWL No. 28–AWL–11. Based on these
requirements, any STC modifications
that are installed after the incorporation
of the version of AWL No. 28–AWL–11
required by paragraph (g) of this
proposed AD must comply with AWL
No. 28–AWL–11, including any
mandatory rework, or the operator must
request approval of an AMOC according
to paragraph (k) of this proposed AD.
Any STC modifications that are
installed prior to the incorporation of
the version of AWL No. 28 AWL–11
required by paragraph (g) of this
proposed AD are not required to be
reworked for compliance with the new
wiring requirements of AWL No. 28–
AWL–11, except that future repair and
replacement of existing wiring must
follow AWL No. 28–AWL–11.
Costs of Compliance
The FAA estimates that this proposed
AD affects 219 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).
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.
Authority for This Rulemaking
§ 39.13
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
■
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
The Boeing Company: Docket No. FAA–
2021–0134; Project Identifier AD–2020–
01254–T.
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Federal Register / Vol. 86, No. 57 / Friday, March 26, 2021 / Proposed Rules
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by May
10, 2021.
(b) Affected ADs
This AD affects the ADs specified in
paragraphs (b)(1) and (2) of this AD.
(1) AD 2008–11–13, Amendment 39–15536
(73 FR 30737, May 29, 2008) (AD 2008–11–
13).
(2) AD 2014–09–09, Amendment 39–17844
(79 FR 30005, May 27, 2014) (AD 2014–09–
09).
(c) Applicability
This AD applies to The Boeing Company
Model 777–200, –200LR, –300, –300ER, and
777F series airplanes having line numbers (L/
Ns) 1 through 1609 inclusive, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel; 47, Inert Gas System.
(e) Unsafe Condition
This AD was prompted by significant
changes, including new or more restrictive
requirements, made to the airworthiness
limitations (AWLs) and Critical Design
Configuration Control Limitations (CDCCLs)
related to fuel tank ignition prevention, the
engine fuel suction feed system, and the
nitrogen generation system. The FAA is
issuing this AD to address ignition sources
inside the fuel tanks and the increased
flammability exposure of the center fuel tank
caused by latent failures, alterations, repairs,
or maintenance actions, which could result
in a fuel tank explosion and consequent loss
of an airplane; and to address potential loss
of engine fuel suction feed capability, which
could result in dual engine flameouts,
inability to restart engines, and consequent
forced landing of the airplane.
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(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 D,
‘‘Airworthiness Limitations—Systems,’’
including Subsections D.1, D.2, and D.3, of
Section 9, Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements
(CMRs), of Boeing 777–200/200LR/300/
300ER/777F Maintenance Planning Data
(MPD) Document, D622W001–9, dated
November 2019; except as provided by
paragraph (h) of this AD. The initial
compliance time for doing the airworthiness
limitation instructions (ALI) tasks is at the
times specified in paragraphs (g)(1) through
(10) of this AD.
(1) For AWL 28–AWL–01, ‘‘External Wires
Over Center Fuel Tank’’: Within 16,000 flight
cycles or 3,000 days, whichever occurs first
after the date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
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airworthiness; or within 16,000 flight cycles
or 3,000 days, whichever occurs first after the
most recent inspection was performed as
specified in 28–AWL–01; whichever occurs
later.
(2) For AWL 28–AWL–03, ‘‘Fuel Quantity
Indicating System (FQIS)—Out of Tank
Wiring Lightning Shield to Ground
Termination’’: Within 16,000 flight cycles or
3,000 days, whichever occurs first after the
date of issuance of the original airworthiness
certificate or the date of issuance of the
original export certificate of airworthiness; or
within 16,000 flight cycles or 3,000 days,
whichever occurs first after the most recent
inspection was performed as specified in 28–
AWL–03; whichever occurs later.
(3) For AWL 28–AWL–18, ‘‘Over-Current
and Arcing Protection Electrical Design
Features Operation—AC Fuel Pump GFI and
GFP’’: Within 375 days after the date of
issuance of the original airworthiness
certificate or the date of issuance of the
original export certificate of airworthiness; or
within 375 days after accomplishment of the
actions specified in Boeing Service Bulletin
777–28A0037; or within 375 days after
accomplishment of the actions specified in
Boeing Service Bulletin 777–28A0038; or
within 375 days after the most recent
inspection was performed as specified in 28–
AWL–18; whichever occurs latest.
(4) For AWL 28–AWL–21, ‘‘External Wires
Over Auxiliary Fuel Tank (Cell)’’: Within
16,000 flight cycles or 3,000 days, whichever
occurs first after the date of issuance of the
original airworthiness certificate or date of
issuance of the original export certificate of
airworthiness; or within 16,000 flight cycles
or 3,000 days, whichever occurs first after the
most recent inspection was performed as
specified in 28–AWL–21; or within 365 days
after the effective date of this AD; whichever
occurs latest.
(5) For AWL 28–AWL–26, ‘‘Auxiliary Fuel
Tank (Cell) AC Fuel Pump Uncommanded
ON/Automatic Shutoff Circuit’’: Within 375
days after the date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness; or within 375 days after the
most recent inspection was performed as
specified in 28–AWL–26; or within 30 days
after the effective date of this AD; whichever
occurs latest.
(6) For AWL 28–AWL–32, ‘‘Cushion
Clamps and Teflon Sleeving Installed on Outof-Tank Wire Bundles Installed on Brackets
that are Mounted Directly on the Fuel
Tanks’’: For airplanes having L/N 1 through
503 inclusive, within 3,750 days after
accomplishment of the actions specified in
Boeing Service Bulletins 777–57A0050, or
within 60 months after the effective date of
this AD, whichever occurs later. For
airplanes having L/N 504 and subsequent,
within 3,750 days after the date of issuance
of the original airworthiness certificate or the
date of issuance of the original export
certificate of airworthiness; or within 60
months after the effective date of this AD;
whichever occurs later.
(7) For AWL 28–AWL–101, ‘‘Engine Fuel
Suction Feed Operational Test’’: Within
7,500 flight hours after the date of issuance
of the original airworthiness certificate or the
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date of issuance of the original export
certificate of airworthiness; or within 7,500
flight hours after the most recent inspection
was performed as specified in AWL No. 28–
AWL–101; whichever occurs later.
(8) For AWL 47–AWL–04, ‘‘NGS—Thermal
Switch’’: Within 108,000 flight hours after
the date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness; or within 108,000 flight hours
after accomplishment of the actions specified
in Boeing Service Bulletin 777–47–0002; or
within 108,000 flight hours after the most
recent inspection was performed as specified
in 47–AWL–04; whichever occurs latest.
(9) For 47–AWL–05, ‘‘NGS—Cross Vent
Check Valve’’: Within 10,682 flight hours
after the date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness; or within 10,682 flight hours
after accomplishment of the actions specified
in Boeing Service Bulletin 777–47–0002; or
within 10,682 flight hours after the most
recent inspection was performed as specified
in 47–AWL–05; whichever occurs latest.
(10) For AWL 47–AWL–06, ‘‘NGS—NEA
Distribution Ducting Integrity’’: Within
10,682 flight hours after the date of issuance
of the original airworthiness certificate or the
date of issuance of the original export
certificate of airworthiness; or within 10,682
flight hours after accomplishment of the
actions specified in Boeing Service Bulletin
777–47–0002; or within 10,682 flight hours
after the most recent inspection was
performed as specified in 47–AWL–06;
whichever occurs latest.
(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–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 (manufactured as
specified in MIL–I–23053) for wire sleeving,
the following sleeving materials are
acceptable: Roundit 2000NX and Varglas
Type HO, HP, or HM.
(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
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26MRP1
Federal Register / Vol. 86, No. 57 / Friday, March 26, 2021 / Proposed Rules
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.
DEPARTMENT OF TRANSPORTATION
(j) Terminating Actions
14 CFR Part 39
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
and (2) of this AD for that airplane.
(1) All requirements of AD 2008–11–13 for
Model 777–200, –200LR, –300, and –300ER
series airplanes only.
(2) All requirements of AD 2014–09–09.
[Docket No. FAA–2021–0191; Project
Identifier AD–2020–01492–E]
(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: 9ANM-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.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(l) Related Information
(1) For more information about this AD,
contact Kevin Nguyen, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3555;
email: kevin.nguyen@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 March 2, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–06022 Filed 3–25–21; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:46 Mar 25, 2021
Jkt 253001
Federal Aviation Administration
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to
supersede Airworthiness Directive (AD)
2019–21–11 and AD 2020–07–02. AD
2019–21–11 applies to all Pratt &
Whitney (PW) PW1519G, PW1521G,
PW1521G–3, PW1521GA, PW1524G,
PW1524G–3, PW1525G, PW1525G–3,
PW1919G, PW1921G, PW1922G,
PW1923G, and PW1923G–A model
turbofan engines. AD 2020–07–02
applies to all PW PW1519G, PW1521G,
PW1521G–3, PW1521GA, PW1524G,
PW1524G–3, PW1525G, and PW1525G–
3 model turbofan engines. AD 2019–21–
11 requires initial and repetitive
borescope inspections (BSIs) of the lowpressure compressor (LPC) rotor 1 (R1)
and, depending on the results of the
inspections, replacement of the LPC. AD
2020–07–02 requires the removal from
service of certain electronic engine
control (EEC) full authority digital
electronic control (FADEC) software and
the installation of a software version
eligible for installation. Since the FAA
issued AD 2019–21–11 and AD 2020–
07–02, the manufacturer developed a
new version of EEC FADEC software,
which terminates the need for repetitive
BSIs of the LPC R1. This proposed AD
would continue to require repetitive
BSIs of certain LPC R1s until
replacement of EEC FADEC software
with the updated software. This
proposed AD would require a BSI after
installation of the updated EEC FADEC
software if certain Onboard
Maintenance Message fault codes are
displayed and meet specified criteria.
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 May 10, 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.
SUMMARY:
PO 00000
Frm 00053
Fmt 4702
Sfmt 4702
16137
• 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 Pratt & Whitney,
400 Main Street, East Hartford, CT
06118; phone: (800) 565–0140; email:
help24@pw.utc.com; website: https://
fleetcare.pw.utc.com. You may view this
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.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0191; 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:
Nicholas Paine, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7116; fax: (781) 238–
7199; email: nicholas.j.paine@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–2021–0191; Project Identifier AD–
2020–01492–E’’ 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
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
E:\FR\FM\26MRP1.SGM
26MRP1
]]>Agencies
[Federal Register Volume 86, Number 57 (Friday, March 26, 2021)]
[Proposed Rules]
[Pages 16133-16137]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-06022]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0134; Project Identifier AD-2020-01254-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 777 airplanes. This proposed AD
was prompted by significant changes, including new or more restrictive
requirements, made to the airworthiness limitations (AWLs) and Critical
Design Configuration Control Limitations (CDCCLs) related to fuel tank
ignition prevention, the engine fuel suction feed system, and the
nitrogen generation system. This proposed AD would require revising the
existing maintenance or inspection program, as applicable, to
incorporate new or more restrictive airworthiness limitations. 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 May 10,
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-
0134; 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: Kevin Nguyen, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3555; email:
[email protected].
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-2021-0134; Project Identifier
AD AD-2020-01254-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
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
[[Page 16134]]
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 Kevin Nguyen, Aerospace Engineer, Propulsion Section,
FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198;
phone and fax: 206-231-3555; email: [email protected]. 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'') to 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.
The FAA issued AD 2008-11-13, Amendment 39-15536 (73 FR 30737, May
29, 2008) (AD 2008-11-13), which applies to certain The Boeing Company
Model 777-200, -200LR, -300, and -300ER series airplanes. The
applicability of AD 2008-11-13 did not include the Boeing Company Model
777F series airplane because those airplanes were not yet type
certificated. AD 2008-11-13 requires incorporation of fuel system AWLs
and also requires an initial inspection to phase in certain repetitive
inspections, and repair if necessary. The fuel system AWLs were
developed to satisfy SFAR 88 requirements and were included in the
Airworthiness Limitations Section (ALS) of the manufacturer's
Instructions for Continued Airworthiness. Since the FAA issued AD 2008-
11-13, the ALS has been significantly revised by the manufacturer to
correct technical and editorial errors and also to add new or more
restrictive requirements. Many of those changes are related to fuel
tank ignition prevention, the engine fuel suction feed system, and the
nitrogen generation system. The FAA has determined that the specific
revisions of the AWL mandated by AD 2008-11-13 (which applies to
airplanes with an original standard airworthiness certificate or
original export certificate of airworthiness issued before December 5,
2007) and the revisions of the AWL that have been delivered with
airplanes as part of the type design and airworthiness certificate on
or after December 5, 2007, are inadequate to provide information
necessary to maintain critical design features and perform inspections.
The FAA also issued AD 2014-09-09, Amendment 39-17844 (79 FR 30005,
May 27, 2014) (AD 2014-09-09), which applies to all The Boeing Company
Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. AD
2014-09-09 requires revising the maintenance program to incorporate a
revision to the Airworthiness Limitations Section of the maintenance
planning data (MPD) document. Since the FAA issued AD 2014-09-09, 28-
AWL-101 has been revised, therefore, this proposed AD would require the
incorporation of the revised 28-AWL-101. Incorporating the revision
required by this proposed AD would terminate all the requirements of AD
2014-09-09.
The FAA has received a report indicating that significant changes,
including new or more restrictive requirements, made to the AWLs and
CDCCLs related to fuel tank ignition prevention, the engine fuel
suction feed system, and the nitrogen generation system. The FAA is
issuing this AD to address ignition sources inside the fuel tanks and
the increased flammability exposure of the center fuel tank caused by
latent failures, alterations, repairs, or maintenance actions, which
could result in a fuel tank explosion and consequent loss of an
airplane; and to address potential loss of engine fuel suction feed
capability, which could result in dual engine flameouts, inability to
restart engines, and consequent forced landing of the airplane.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Section 9, Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), of Boeing 777-200/200LR/
300/300ER/777F Maintenance Planning Data (MPD) Document, D622W001-9,
dated November 2019. This service information describes airworthiness
limitations and CDCCLs tasks related to fuel tank ignition prevention,
the engine fuel suction feed system, 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 new or more
restrictive airworthiness limitations.
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
[[Page 16135]]
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.
Differences Between This Proposed AD and the Service Information
Paragraph (g) of this proposed AD would require operators to revise
their existing maintenance or inspection program by incorporating, in
part, AWL No. 28-AWL-11, ``Fuel Quantity Indicating System (FQIS) and
Auxiliary Fuel Tank (Cell) Electronic Fuel Level Indication System
(EFLI)--Out Tank Wiring Installation Separation Requirement,'' of
Section 9, Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), of Boeing 777-200/200LR/300/300ER/777F
Maintenance Planning Data (MPD) Document, D622W001-9, dated November
2019.
Paragraph (h) of this proposed AD would allow certain changes to be
made to the requirements specified in AWL No. 28-AWL-11 as an option.
Where AWL No. 28-AWL-11 identifies certain wire types for routing and
installation of any new wiring under certain conditions, paragraph (h)
of this proposed AD provides acceptable alternative wire types.
Additionally, where AWL No. 28-AWL-11 identifies certain wiring sleeve
material for new wiring installed under certain conditions, paragraph
(h) of this proposed AD provides acceptable alternative wire sleeve
materials.
Alternative Methods of Compliance (AMOCs) Previously Approved for AD
2008-11-13
The FAA has previously issued AMOC approvals for compliance with
paragraph (g)(2) of AD 2008-11-13 to allow operators to incorporate
alternative versions of AWL No. 28-AWL-11. AWL No. 28-AWL-11 includes
the requirements for new wiring introduced by any alterations or
changes to the type design, including STC modifications, in proximity
to wiring that penetrates the fuel tank wall. Certain STCs that
introduced new wiring near the fuel quantity indicating system (FQIS)
wiring utilized design features that were different from the critical
design features for fuel tank ignition prevention specified in the AD-
mandated version of AWL No. 28-AWL-11. For those STCs, the FAA has
approved alternative versions of AWL No. 28-AWL-11 that specified
critical design features associated with STC modifications. The FAA has
determined that certain critical design features specified in the AMOC-
approved versions of AWL No. 28-AWL-11 are not acceptable to meet the
intent of this AWL. Therefore, this proposed AD does not allow credit
for AMOCs previously approved under AD 2008-11-13. However, based on
the agency's assessment of critical design features, the FAA has
provided options under paragraph (h) of this proposed AD to allow
certain changes to be made to the requirements specified in AWL No. 28-
AWL-11.
The requirements for new wiring versus existing wiring are
specified in AWL No. 28-AWL-11. Based on these requirements, any STC
modifications that are installed after the incorporation of the version
of AWL No. 28-AWL-11 required by paragraph (g) of this proposed AD must
comply with AWL No. 28-AWL-11, including any mandatory rework, or the
operator must request approval of an AMOC according to paragraph (k) of
this proposed AD. Any STC modifications that are installed prior to the
incorporation of the version of AWL No. 28 AWL-11 required by paragraph
(g) of this proposed AD are not required to be reworked for compliance
with the new wiring requirements of AWL No. 28-AWL-11, except that
future repair and replacement of existing wiring must follow AWL No.
28-AWL-11.
Costs of Compliance
The FAA estimates that this proposed AD affects 219 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 work-hours 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 x $85 per work-hour).
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
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
The Boeing Company: Docket No. FAA-2021-0134; Project Identifier AD-
2020-01254-T.
[[Page 16136]]
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by May 10, 2021.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) and (2)
of this AD.
(1) AD 2008-11-13, Amendment 39-15536 (73 FR 30737, May 29,
2008) (AD 2008-11-13).
(2) AD 2014-09-09, Amendment 39-17844 (79 FR 30005, May 27,
2014) (AD 2014-09-09).
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes having line numbers (L/Ns) 1
through 1609 inclusive, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel; 47,
Inert Gas System.
(e) Unsafe Condition
This AD was prompted by significant changes, including new or
more restrictive requirements, made to the airworthiness limitations
(AWLs) and Critical Design Configuration Control Limitations
(CDCCLs) related to fuel tank ignition prevention, the engine fuel
suction feed system, and the nitrogen generation system. The FAA is
issuing this AD to address ignition sources inside the fuel tanks
and the increased flammability exposure of the center fuel tank
caused by latent failures, alterations, repairs, or maintenance
actions, which could result in a fuel tank explosion and consequent
loss of an airplane; and to address potential loss of engine fuel
suction feed capability, which could result in dual engine
flameouts, inability to restart engines, and consequent forced
landing 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 D, ``Airworthiness
Limitations--Systems,'' including Subsections D.1, D.2, and D.3, of
Section 9, Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), of Boeing 777-200/200LR/300/300ER/
777F Maintenance Planning Data (MPD) Document, D622W001-9, dated
November 2019; except as provided by paragraph (h) of this AD. The
initial compliance time for doing the airworthiness limitation
instructions (ALI) tasks is at the times specified in paragraphs
(g)(1) through (10) of this AD.
(1) For AWL 28-AWL-01, ``External Wires Over Center Fuel Tank'':
Within 16,000 flight cycles or 3,000 days, whichever occurs first
after the date of issuance of the original airworthiness certificate
or the date of issuance of the original export certificate of
airworthiness; or within 16,000 flight cycles or 3,000 days,
whichever occurs first after the most recent inspection was
performed as specified in 28-AWL-01; whichever occurs later.
(2) For AWL 28-AWL-03, ``Fuel Quantity Indicating System
(FQIS)--Out of Tank Wiring Lightning Shield to Ground Termination'':
Within 16,000 flight cycles or 3,000 days, whichever occurs first
after the date of issuance of the original airworthiness certificate
or the date of issuance of the original export certificate of
airworthiness; or within 16,000 flight cycles or 3,000 days,
whichever occurs first after the most recent inspection was
performed as specified in 28-AWL-03; whichever occurs later.
(3) For AWL 28-AWL-18, ``Over-Current and Arcing Protection
Electrical Design Features Operation--AC Fuel Pump GFI and GFP'':
Within 375 days after the date of issuance of the original
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness; or within 375 days after
accomplishment of the actions specified in Boeing Service Bulletin
777-28A0037; or within 375 days after accomplishment of the actions
specified in Boeing Service Bulletin 777-28A0038; or within 375 days
after the most recent inspection was performed as specified in 28-
AWL-18; whichever occurs latest.
(4) For AWL 28-AWL-21, ``External Wires Over Auxiliary Fuel Tank
(Cell)'': Within 16,000 flight cycles or 3,000 days, whichever
occurs first after the date of issuance of the original
airworthiness certificate or date of issuance of the original export
certificate of airworthiness; or within 16,000 flight cycles or
3,000 days, whichever occurs first after the most recent inspection
was performed as specified in 28-AWL-21; or within 365 days after
the effective date of this AD; whichever occurs latest.
(5) For AWL 28-AWL-26, ``Auxiliary Fuel Tank (Cell) AC Fuel Pump
Uncommanded ON/Automatic Shutoff Circuit'': Within 375 days after
the date of issuance of the original airworthiness certificate or
the date of issuance of the original export certificate of
airworthiness; or within 375 days after the most recent inspection
was performed as specified in 28-AWL-26; or within 30 days after the
effective date of this AD; whichever occurs latest.
(6) For AWL 28-AWL-32, ``Cushion Clamps and Teflon Sleeving
Installed on Out-of-Tank Wire Bundles Installed on Brackets that are
Mounted Directly on the Fuel Tanks'': For airplanes having L/N 1
through 503 inclusive, within 3,750 days after accomplishment of the
actions specified in Boeing Service Bulletins 777-57A0050, or within
60 months after the effective date of this AD, whichever occurs
later. For airplanes having L/N 504 and subsequent, within 3,750
days after the date of issuance of the original airworthiness
certificate or the date of issuance of the original export
certificate of airworthiness; or within 60 months after the
effective date of this AD; whichever occurs later.
(7) For AWL 28-AWL-101, ``Engine Fuel Suction Feed Operational
Test'': Within 7,500 flight hours after the date of issuance of the
original airworthiness certificate or the date of issuance of the
original export certificate of airworthiness; or within 7,500 flight
hours after the most recent inspection was performed as specified in
AWL No. 28-AWL-101; whichever occurs later.
(8) For AWL 47-AWL-04, ``NGS--Thermal Switch'': Within 108,000
flight hours after the date of issuance of the original
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness; or within 108,000 flight hours
after accomplishment of the actions specified in Boeing Service
Bulletin 777-47-0002; or within 108,000 flight hours after the most
recent inspection was performed as specified in 47-AWL-04; whichever
occurs latest.
(9) For 47-AWL-05, ``NGS--Cross Vent Check Valve'': Within
10,682 flight hours after the date of issuance of the original
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness; or within 10,682 flight hours
after accomplishment of the actions specified in Boeing Service
Bulletin 777-47-0002; or within 10,682 flight hours after the most
recent inspection was performed as specified in 47-AWL-05; whichever
occurs latest.
(10) For AWL 47-AWL-06, ``NGS--NEA Distribution Ducting
Integrity'': Within 10,682 flight hours after the date of issuance
of the original airworthiness certificate or the date of issuance of
the original export certificate of airworthiness; or within 10,682
flight hours after accomplishment of the actions specified in Boeing
Service Bulletin 777-47-0002; or within 10,682 flight hours after
the most recent inspection was performed as specified in 47-AWL-06;
whichever occurs latest.
(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-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
(manufactured as specified in MIL-I-23053) for wire sleeving, the
following sleeving materials are acceptable: Roundit 2000NX and
Varglas Type HO, HP, or HM.
(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
[[Page 16137]]
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 Actions
Accomplishment of the revision required by paragraph (g) of this
AD terminates the requirements specified in paragraphs (j)(1) and
(2) of this AD for that airplane.
(1) All requirements of AD 2008-11-13 for Model 777-200, -200LR,
-300, and -300ER series airplanes only.
(2) All requirements of AD 2014-09-09.
(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: [email protected].
(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 Kevin Nguyen,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3555; email: [email protected].
(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 March 2, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-06022 Filed 3-25-21; 8:45 am]
BILLING CODE 4910-13-P
