[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]
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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).
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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