Airworthiness Directives; The Boeing Company Airplanes, 31604-31609 [2021-12436]
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Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations
(j) Definitions
(1) For the purpose of this AD, a ‘‘critical
part’’ is an engine part listed in paragraph
2.3.1, Table B—List of Critical Parts and the
Accelerating Factor, of the ASB.
(2) For the purpose of this AD,
‘‘recalculated life’’ is the consumed life of the
critical part using the recalculation required
by (g)(1) of this AD.
(3) For the purpose of this AD, where the
ASB says the ‘‘applicable Airworthiness
Limitation Section’’ use the following:
(i) For affected model engines M601D–1,
M601D–11, M601D–11NZ, M601D–2,
M601Z: ‘‘the ALS section of GE Aviation
Engine Maintenance Manual 0982309.’’
(ii) For affected model engines M601E–11,
M601E–11S, M601E–11A, M601E–11AS,
M601F, M601FS: ‘‘the ALS section of GE
Aviation Engine Maintenance Manual
0982302.’’
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO Branch, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to the attention of the person
identified in Related Information. You may
email your request to: ANE-AD-AMOC@
faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
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(l) Related Information
(1) For more information about this AD,
contact Barbara Caufield, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7146; fax: (781) 238–7199; email:
barbara.caufield@faa.gov.
(2) Refer to European Union Aviation
Safety Agency (EASA) Emergency AD 2021–
0125–E, dated May 7, 2021, for more
information. You may examine the EASA AD
in the AD docket at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2021–0499.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) GE Aviation Czech Alert Service
Bulletin (ASB) ASB–M601F–72–00–00–0057
[00], ASB–M601E–72–00–00–0106 [00],
ASB–M601D–72–00–00–0075 [00], and ASB–
M601Z–72–00–00–0057 [00] (single
document; formatted as service bulletin
identifier [revision number]), dated May 7,
2021.
(ii) [Reserved]
(3) For GE Aviation Czech service
information identified in this AD, contact GE
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Aviation Czech s.r.o., Beranovy´ch 65, 199 00
Praha 18, Letnany, Czech Republic; phone:
+420 222 538 111; fax: +420 222 538 222.
(4) You may view this service information
at 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet
https://www.myboeingfleet.com. You
may view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0341.
Issued on June 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0341; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
any comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Christopher Baker, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3552; email: Christopher.R.Baker@
faa.gov.
[FR Doc. 2021–12659 Filed 6–11–21; 11:15 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0341; Project
Identifier 2020–NM–017–AD; Amendment
39–21586; AD 2021–11–24]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUPPLEMENTARY INFORMATION:
Background
The FAA is adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–600,
–700, –700C, –800, –900, and –900ER
series airplanes. This AD was prompted
by significant changes made to the
airworthiness limitations (AWLs)
related to fuel tank ignition prevention
and the nitrogen generation system
(NGS). This AD requires revising the
existing maintenance or inspection
program, as applicable, to incorporate
the April 2019 or November 2020
revision of the airworthiness limitations
document. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective July 20,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 20, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Contractual & Data Services
SUMMARY:
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Examining the AD Docket
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–600, –700, –700C, –800,
–900, and –900ER series airplanes. The
NPRM published in the Federal
Register on May 6, 2020 (85 FR 26888).
The NPRM was prompted by significant
changes made to the AWLs related to
fuel tank ignition prevention and the
NGS. The NPRM proposed to require
revising the existing maintenance or
inspection program, as applicable, to
incorporate the April 2019 revision of
the airworthiness limitations document.
The FAA is issuing this AD to prevent
the potential for ignition sources inside
the fuel tanks and also to prevent
increasing the 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. In addition, the FAA
is issuing this AD to address the
potential loss of engine fuel suction feed
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capability, which could result in dual
engine flameouts, inability to restart
engines, and consequent forced landing
of the airplane.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
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Support for the NPRM
The Air Line Pilots Association,
International (ALPA), United Airlines,
and an individual stated support for the
NPRM.
Request To Delay Issuance of Final
Rule
All Nippon Airways (ANA) requested
that the FAA delay issuance of the final
rule until Boeing releases the next
revision of Boeing 737–600/700/700C/
800/900/900ER Special Compliance
Items/Airworthiness Limitations,
D626A001–9–04. The commenter
explained that in the current revision of
Boeing 737–600/700/700C/800/900/
900ER Special Compliance Items/
Airworthiness Limitations, D626A001–
9–04, dated April 2019 (Boeing
D626A001–9–04, dated April 2019), for
Airworthiness Limitation (AWL) No.
47–AWL–09, ‘‘Nitrogen Generation
System—Oxygen Sensor,’’ operators
must replace the NGS oxygen sensor
with a new oxygen sensor because
installation of an overhauled part is not
approved at this time. The commenter
stated that Boeing is working with the
FAA to allow testing of the oxygen
sensor using the component
maintenance manual, and on-wing
testing using the aircraft maintenance
manual, and Boeing plans to revise
AWL No. 47–AWL–09 to allow testing
and installation of an overhauled part.
The commenter anticipated that the
next revision of Boeing 737–600/700/
700C/800/900/900ER Special
Compliance Items/Airworthiness
Limitations, D626A001–9–04, would
include the revised AWL No. 47–AWL–
09.
The FAA acknowledges the
commenter’s request. Since publication
of the NPRM, Boeing has issued Boeing
737–600/700/700C/800/900/900ER
Special Compliance Items/
Airworthiness Limitations, D626A001–
9–04, dated November 2020 (Boeing
D626A001–9–04, dated November
2020), which limits the applicability of
AWL No. 47–AWL–09 to certain Model
737 airplanes and states that an oxygen
sensor can be replaced with a new
oxygen sensor or an oxygen sensor
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repaired per AWL No. 47–AWL–10
‘‘Nitrogen Generation System—Oxygen
Sensor Repair.’’ This AD requires
updating the existing maintenance/
inspection program to incorporate
Boeing D626A001–9–04, dated April
2019; or Boeing D626A001–9–04, dated
November 2020. In addition, based
upon requests from other commenters,
the FAA has extended the initial
compliance time for replacement of the
oxygen sensor due to a parts availability
issue. The FAA has revised the grace
period for the initial ALI task in
paragraph (g)(13) of this AD from 12
months to 36 months. This extended
grace period will still provide an
acceptable level of safety.
Request To Extend the Compliance
Time
Air China, ANA, China Eastern
Airlines (CEA), Delta Air lines (DAL),
Japan Airlines (JAL), Okay Airlines
(OKY), Southwest Airlines (SWA), and
Turkish Airlines (THY) requested that
the initial compliance time for the
replacement of the oxygen sensor as
specified in paragraph (g)(13) of the
proposed AD be extended because of a
parts availability issue. The commenters
contacted Boeing and determined that
there would be a shortage of parts,
which would prevent them from
complying with the proposed
requirement specified in paragraph
(g)(13) of the proposed AD within the
compliance time specified in the
proposed AD.
The FAA agrees with the commenters’
requests based on the information
provided by the commenters. The FAA
contacted Boeing and confirmed that
there is a parts availability issue, which
could create an undue burden on
operators because it could prevent them
from complying with the requirement
specified in paragraph (g)(13) of this
AD, subsequently grounding the
affected airplanes. The FAA has revised
the initial compliance time in paragraph
(g)(13) of this AD from 12 months to 36
months.
Request To Add an Off-Wing Inspection
for AWL No. 47–AWL–09
SWA requested that the FAA consider
coordinating this AD with Boeing to
allow for an off-wing inspection of the
oxygen sensor, and repair if necessary,
as opposed to a mandated time-limited
replacement. SWA stated that this
would mitigate the parts availability
impact across the industry as well the
cost of complying with AWL No. 47–
AWL–09.
The FAA agrees that an off-wing
inspection would reduce the burden on
operators. This AD allows operators to
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optionally incorporate Boeing
D626A001–9–04, dated November 2020,
which includes an off-wing inspection
as specified in AWL No. 47–AWL–10.
Boeing modified the requirement of
AWL No. 47–AWL–09 to allow the use
of repaired parts and added AWL No.
47–AWL–10 to describe the
requirements for the method of
inspection/repair in Boeing D626A001–
9–04, dated November 2020. This AD
still requires operators to use Boeing
D626A001–9–04, dated April 2019, but
provides an option for operators to
incorporate Boeing D626A001–9–04,
dated November 2020, into their
maintenance program. In addition, the
FAA has determined that an on-wing
inspection is currently being developed
by Boeing and that subject on-wing
inspection is expected to be
implemented in a future revision of the
Boeing D626A001–9–04 document.
Under the provisions of paragraph (k) of
this AD, the FAA will consider requests
for approval of an alternative method of
compliance (AMOC) if sufficient data
are submitted to substantiate that the
change would provide an acceptable
level of safety.
Request To Clarify the Applicability of
a Certain AWL Item
CEA, DAL, JAL, OKY, Ryan Air, and
THY requested clarification of the
applicability specified in AWL No. 47–
AWL–09, which addresses replacement
of the oxygen sensor in the NGS. The
commenters noted that in Boeing
D626A001–9–04, dated April 2019, the
other AWLs specific to the NGS show
the airplane applicability in terms of the
airplanes that have the NGS installed, or
incorporation of the actions in Boeing
Service Bulletin 737–47–1002 or Boeing
Service Bulletin 737–47–1003. The
commenters noted that all airplanes on
the U.S. registry are required to have the
NGS system installed, but the
commenters expected the applicability
of AWL No. 47–AWL–09 to be similar
to the other AWLs included in Boeing
D626A001–9–04, dated April 2019. In
addition, OKY noted that the
applicability in AWL No. 47–AWL–09
was listed as all airplanes, but in Boeing
Fleet Team Digest Document 737NG–
FTD–47–19003, created on May 8, 2020,
the applicability is Model 737NG
airplanes delivered after June 2019 or
modified with a new, improved ASM
(air separation module) using the
procedures in Boeing Service Bulletin
737–47–1015.
DAL and the other commenters
explained that they contacted Boeing
regarding this applicability issue. The
commenters stated that Boeing
confirmed that the applicability
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specified in AWL No. 47–AWL–09 is
incorrect and Boeing advised that in the
next revision of Boeing D626A001–9–
04, dated April 2019, the applicability
specified in AWL No. 47–AWL–09 will
be updated to include airplanes having
L/Ns 1820, 1831, 2517, 2620, and
subsequent, and all airplanes that have
incorporated the actions specified in
Boeing Service Bulletin 737–47–1003.
Several of the commenters stated that
paragraph (g)(13) of the proposed AD
should include additional text to clarify
the applicability of AWL No. 47–AWL–
09. The commenters stated that by
incorporating this information into the
final rule, the FAA would prevent the
need for operators to apply for an
AMOC in the future.
The FAA acknowledges the
commenters’ requests. As mentioned
previously, Boeing has published
Boeing D626A001–9–04, dated
November 2020, and in this revision the
applicability specified in AWL No. 47–
AWL–09 was updated and limited to
specify only airplanes having L/Ns
1820, 1831, 2517, 2620, and subsequent,
and all airplanes that have incorporated
the actions specified in Boeing Service
Bulletin 737–47–1003. The FAA has
changed the AD to allow the use of
Boeing D626A001–9–04, dated
November 2020, which correctly
identifies the applicability for AWL No.
47–AWL–09.
Request To Clarify the Unsafe
Condition
Boeing, DAL, and CEA requested
clarification of the unsafe condition
specified in the Discussion section of
the NPRM and paragraph (e) of the
proposed AD. The commenters
remarked that the wording implied that
increased flammability in the center fuel
tank leads to fuel tank explosion. The
commenters explained that increased
flammability alone does not lead to a
fuel tank explosion; there must also be
a concurrent ignition source in the
center fuel tank. The commenters
suggested that it would be more
accurate to state that the increased
flammability combined with an ignition
source could lead to a fuel tank
explosion.
In addition, the commenters
requested that the unsafe condition be
revised to address the potential loss of
engine fuel suction feed capability. The
commenters pointed out that paragraph
(g)(14) of the proposed AD specified
AWL No. 28–AWL–101, ‘‘Engine Fuel
Suction Feed Operational Test,’’ which
would be required to protect the
airplane from engine flameout during
suction feed operations. The
commenters observed that this proposed
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action is not associated with the
prevention of fuel tank ignition.
The FAA agrees with the commenters’
requests based on the reasons provided
by the commenters. The FAA has
revised the Background section in this
final rule and paragraph (e) of this AD
accordingly.
Request To Account for Indirect Costs
ANA, CEA, DAL, OKY, SWA, and
THY expressed concern regarding the
indirect financial burden associated
with accomplishing the actual on-wing
work resulting from the maintenance
program or inspection program changes
that would be required by the proposed
AD. DAL specifically noted that
accomplishment of the oxygen sensor
replacement specified in AWL No. 47–
AWL–09, would require replacement of
approximately 130 oxygen sensors with
new oxygen sensors, and based on price
quotes from the manufacturer of the
oxygen sensors, it would cost an
additional $7,000,000 over the
estimated $7,560 per operator specified
in the Costs of Compliance section of
the NPRM. DAL stated that once all
airplanes have reached the threshold for
replacing the oxygen sensor the
recurring cost would be approximately
$2,000,000 per year for this task.
The FAA disagrees with changing the
cost of compliance information for this
AD. The cost information provided in
this AD describes only the direct costs
of the specific actions required by this
AD. The FAA recognizes that, in doing
the actions required by an AD, operators
might incur incidental costs in addition
to the direct costs. The extended
compliance time previously mentioned
could alleviate some of these indirect
costs, as they would be spread out over
36 months instead of occurring within
12 months. Also, Boeing D626A001–9–
04, dated November 2020, was revised
to allow operators to use a repaired
oxygen sensor in AWL No. 47–AWL–09
and added AWL No. 47–AWL–10 to
describe the requirements for the
method of inspection/repair. As
identified above in a previous comment,
operators now have the option to
incorporate Boeing D626A001–9–04,
dated November 2020, into their
maintenance and inspection program,
thereby reducing the financial impact of
these requirements. The AD has not
been changed in this regard.
Request for Clarification of Compliance
Time Interval Units
DAL and CEA requested that the FAA
explain why paragraph (g) of the
proposed AD expressed compliance
time intervals in terms of months when
Boeing D626A001–9–04, dated April
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2019, specifies these intervals in terms
of years. The commenter mentioned it
was unclear if an AMOC would be
required if an operator incorporated the
compliance intervals in years, as
specified in Boeing D626A001–9–04,
dated April 2019, instead of months, as
specified in the proposed AD.
The FAA disagrees that there is a
difference in the calculated compliance
times described by the commenters. The
FAA uses compliance times defined in
months for required AD actions.
Operators have the capability of
converting years to months when
comparing the compliance times of
required AD actions and the times
specified in a manufacturer’s document.
The FAA has determined that operators
should not be confused when these
conversions take place and an operator
does not need to request an AMOC.
Regardless of how an operator records
the compliance time, within 36 months
or within 3 years after the effective date
of this AD, the compliance times in this
AD, Boeing D626A001–9–04, dated
April 2019, and Boeing D626A001–9–
04, dated November 2020, end at the
same time. The FAA has not changed
this AD in regard to this issue.
Request To Include Additional Affected
AD in Paragraph (b) of Proposed AD
DAL and CEA requested that AD
2018–20–13, Amendment 39–19447 (83
FR 52305, October 17, 2018) (AD 2018–
20–13), be included in the list of
affected ADs in paragraph (b) of the
proposed AD. DAL and CEA noted that
paragraphs (i)(1)(i) through (iii) of AD
2018–20–13 require incorporation of
AWL Nos. 28–AWL–21, 28–AWL–22,
and 28–AWL–24 that are included in
Boeing 737–600/700/700C/800/900/
900ER Special Compliance Items/
Airworthiness Limitations, D626A001–
9–04, dated June 2018, into an
operator’s maintenance or inspection
program as applicable. DAL and CEA
suggested that only the latter revision of
these AWLs that are included in Boeing
D626A001–9–04, dated April 2019,
should be mandated. DAL and CEA
stated that the requirements of
paragraphs (i)(1)(i) through (iii) of AD
2018–20–13 should be terminated when
the requirements of the proposed AD
become effective.
The FAA agrees with the commenter’s
request; paragraph (b) of this AD has
been revised to include AD 2018–20–13
in paragraph (b)(6) of this AD, and the
subsequent paragraph has been
redesignated as paragraph (b)(7) of this
AD. In addition, this AD has been
revised to include a new paragraph (j)(6)
of this AD to terminate the requirements
specified in paragraphs (i)(1)(i) through
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(iii) of AD 2018–20–13, and the
subsequent paragraph has been
redesignated as paragraph (j)(7) of this
AD.
Request To Change the Subject in
Paragraph (d) of the Proposed AD
DAL and CEA requested that the
Subject in paragraph (d) of the proposed
AD be changed from Air Transport
Association (ATA) of America Code 71,
Powerplant, to ATA Code 28, Fuel. DAL
and CEA noted that the unsafe
condition specified in the proposed AD
is associated with ignition sources in
the fuel tanks and flammability
exposure of the center fuel tank. The
fuel system is the subject of ATA Code
28. Previously issued ADs identified in
paragraph (b) of the proposed AD,
which are similar to the proposed AD,
have specified ATA Code 28 as the
subject in paragraph (d).
The FAA agrees with the commenter’s
request based on the reasons provided
by the commenter. Paragraph (d) of this
AD has been changed to ATA Code 28,
Fuel.
Effects of Winglets on Accomplishment
of the Proposed Actions
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing 737–600/
700/700C/800/900/900ER Special
Compliance Items/Airworthiness
Limitations, D626A001–9–04, dated
April 2019; and Boeing 737–600/700/
700C/800/900/900ER Special
Compliance Items/Airworthiness
Limitations, D626A001–9–04, dated
November 2020. This service
information describes AWLs that
include airworthiness limitation
instructions (ALIs) and critical design
configuration control limitations
(CDCCLs) tasks related to fuel tank
ignition prevention and the NGS. 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.
Conclusion
Differences Between This AD and the
Service Information
The ‘‘Description’’ column of AWL
No. 28–AWL–20 identifies certain
operational tests. However, the
operational test for left center tank fuel
boost pump relay R54 and right center
tank fuel boost pump relay R55 is not
required for airplanes on which the
actions specified in paragraph (g)(2)(ii)
of AD 2011–20–07, Amendment 39–
16818 (76 FR 60710, September 30,
2011), have been done, or airplanes that
have installed STC ST02076LA.
Paragraph (g) of this AD requires
operators to revise their existing
maintenance or inspection program by
incorporating, in part, AWL No. 28–
AWL–05, ‘‘Wire Separation
Requirements for New Wiring Installed
in Proximity to Wiring That Goes Into
the Fuel Tanks’’ in Boeing D626A001–
9–04, dated November 2020. Paragraph
(h) of this AD allows certain changes to
be made to the requirements specified
in AWL No. 28–AWL–05 as an option.
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
The FAA has determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
Costs of Compliance
The FAA estimates that this AD
affects 2,057 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
The FAA 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. In the past,
Aviation Partners Boeing stated that
the installation of blended or split
scimitar winglets per Supplemental
Type Certificated (STC) ST008300SE
does not affect compliance with the
proposed actions.
The FAA agrees that STC
ST008300SE does not affect compliance
with the actions required by this AD.
The FAA has not changed this AD in
this regard.
Reduction of Applicable Airplanes
Since NPRM Was Issued
The FAA has updated the
applicability, paragraph (c) of this AD,
to remove airplanes that were delivered
with Boeing 737–600/700/700C/800/
900/900ER Special Compliance Items/
Airworthiness Limitations, D626A001–
9–04, dated April 2019, thereby
reducing the scope of the affected
airplanes in this final rule.
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• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
The FAA also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
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the FAA estimated that this action takes
1 work-hour per airplane. Since
operators incorporate maintenance or
inspection program changes for their
affected fleet(s), the FAA determined
that a per-operator estimate is more
accurate than a per-airplane estimate.
Therefore, the FAA estimates the
average total cost per operator to be
$7,650 (90 work-hours × $85 per workhour).
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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address the 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.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–11–24 The Boeing Company:
Amendment 39–21586; Docket No.
FAA–2020–0341; Project Identifier
2020–NM–017–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective July 20, 2021.
(b) Affected (Airworthiness Directives) ADs
This AD affects the ADs specified in
paragraphs (b)(1) through (7) of this AD.
(1) AD 2008–06–03, Amendment 39–15415
(73 FR 13081, March 12, 2008) (AD 2008–06–
03).
(2) AD 2008–10–10 R1, Amendment 39–
16164 (75 FR 1529, January 12, 2010) (AD
2008–10–10 R1).
(3) AD 2008–17–15, Amendment 39–15653
(73 FR 50714, August 28, 2008) (AD 2008–
17–15).
(4) AD 2011–18–03, Amendment 39–16785
(76 FR 53317, August 26, 2011) (AD 2011–
18–03).
(5) AD 2013–15–17, Amendment 39–17533
(78 FR 52838, August 27, 2013) (AD 2013–
15–17).
(6) AD 2018–20–13, Amendment 39–19447
(83 FR 52305, October 17, 2018) (AD 2018–
20–13).
(7) AD 2018–20–24, Amendment 39–19458
(83 FR 51815, October 15, 2018) (AD 2018–
20–24).
(c) Applicability
This AD applies to The Boeing Company
Model 737–600, –700, –700C, –800, –900,
and –900ER series airplanes, certificated in
any category, Line Numbers (L/Ns) 1 through
7596 inclusive, except L/Ns 7352, 7362,
7377, 7417, 7457, 7522, 7587, and 7592.
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(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant
changes made to the airworthiness
limitations (AWLs) related to fuel tank
ignition prevention and the nitrogen
generation system (NGS). The FAA is issuing
this AD to address the development of an
ignition source inside the fuel tanks and also
to prevent increasing the flammability
exposure of the center fuel tank, which could
lead to fuel tank explosion and consequent
loss of the airplane. The FAA is also issuing
this AD to prevent increasing the
flammability exposure of the center fuel tank,
which together with an ignition source in the
fuel tank, could lead to a fuel tank explosion
and consequent loss of the airplane. In
addition, the FAA is issuing this AD to
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16:05 Jun 14, 2021
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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 applicable information
specified in Section A, including Subsections
A.1., A.2., and A.3, of Boeing 737–600/700/
700C/800/900/900ER Special Compliance
Items/Airworthiness Limitations, D626A001–
9–04, dated April 2019; or November 2020;
except as provided by paragraph (h) of this
AD. The initial compliance times for the
airworthiness limitation instruction (ALI)
tasks are within the applicable compliance
times specified in in paragraphs (g)(1)
through (14) of this AD.
(1) For AWL No. 28–AWL–01, ‘‘External
Wires Over Center Fuel Tank’’: Within 120
months after the date of issuance of the
original airworthiness certificate or the
original export certificate of airworthiness, or
within 120 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–01, whichever is later.
(2) For AWL No. 28–AWL–03, ‘‘Fuel
Quantity Indicating System (FQIS)—Out
Tank Wiring Lightning Shield to Ground
Termination’’: Within 120 months after the
date of issuance of the original airworthiness
certificate or the original export certificate of
airworthiness, or within 120 months after the
most recent inspection was performed as
specified in AWL No. 28–AWL–03,
whichever is later.
(3) For AWL No. 28–AWL–19, ‘‘Center
Tank Fuel Boost Pump Automatic Shutoff
System’’: Within 12 months after the date of
issuance of the original airworthiness
certificate or the original export certificate of
airworthiness, within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1206, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–19, whichever is latest.
This AWL does not apply to airplanes that
have complied with paragraph (s) of AD
2011–18–03.
(4) For AWL No. 28–AWL–20, ‘‘OverCurrent and Arcing Protection Electrical
Design Features Operation—Boost Pump
Ground Fault Interrupter (GFI)’’: Within 12
months after the date of issuance of the
original airworthiness certificate or the
original export certificate of airworthiness,
within 12 months after accomplishment of
the actions specified in Boeing Service
Bulletin 737–28A1201, or within 12 months
after the most recent inspection was
performed as specified in AWL No. 28–
AWL–20, whichever is latest.
(5) For AWL No. 28–AWL–23, ‘‘Center
Tank Fuel Boost Pump Power Failed On
Protection System’’: Within 12 months after
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Fmt 4700
Sfmt 4700
the date of issuance of the original
airworthiness certificate or the original
export certificate of airworthiness, within 12
months after accomplishment of the actions
specified in Boeing Service Bulletin 737–
28A1248, or within 12 months after the most
recent inspection was performed as specified
in AWL No. 28–AWL–23, whichever is latest.
This AWL does not apply to airplanes that
have complied with paragraph (s) of AD
2011–18–03.
(6) For AWL No. 28–AWL–24, ‘‘Spar Valve
Motor Operated Valve (MOV) Actuator—
Lightning and Fault Current Protection
Electrical Bond’’: Within 72 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1207, or
within 72 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–24, whichever is later.
(7) For AWL No. 28–AWL–29, ‘‘Full
Cushion Clamps and Teflon Sleeving (If
Installed) Installed on Out-of-Tank Wire
Bundles Installed on Brackets that are
Mounted Directly on the Fuel Tanks’’: For
airplanes having line numbers (L/N) 1
through 1754 inclusive, within 120 months
after accomplishment of the actions specified
in Boeing Service Bulletin 737–57A1279. For
airplanes having L/N 1755 and subsequent,
within 120 months after the date of issuance
of the original airworthiness certificate or the
original export certificate of airworthiness, or
within 48 months after the effective date of
this AD, whichever is later.
(8) For AWL No. 28–AWL–35, ‘‘Fuel
Quantity Indicating System (FQIS)—Center
Fuel Tank In-Tank Component and Wire
Harness Protection Features-Separation from
Center Tank Internal Structure’’: For
airplanes that have incorporated Boeing
Service Bulletin 737–28–1356, within 120
months after accomplishment of the actions
specified in Boeing Service Bulletin 737–28–
1356, or within 120 months after the most
recent inspection was performed as specified
in AWL No. 28–AWL–35, whichever is later.
(9) For AWL No. 28–AWL–37, ‘‘Fuel
Quantity Indicating System (FQIS)—Built in
Test Equipment (BITE) Test’’: For airplane
L/Ns 6987 and 7000 and subsequent, within
750 flight hours since the date the most
recent BITE test was accomplished as
specified in AWL No. 28–AWL–37, or within
750 flight hours after the effective date of this
AD, whichever is later.
(10) For AWL No. 47–AWL–04, ‘‘Nitrogen
Generation System—Thermal Switch’’:
Within 22,500 flight hours after the date of
issuance of the original airworthiness
certificate or the original export certificate of
airworthiness, within 22,500 flight hours
after accomplishment of the actions specified
in Boeing Service Bulletin 737–47–1003, or
within 22,500 flight hours after the most
recent inspection was performed as specified
in AWL No. 47–AWL–04, whichever is latest.
(11) For AWL No. 47–AWL–06, ‘‘Nitrogen
Generation System (NGS)—Cross Vent Check
Valve’’: Within 13,000 flight hours after the
date of issuance of the original airworthiness
certificate or the original export certificate of
airworthiness, within 13,000 flight hours
after accomplishment of the actions specified
in Boeing Service Bulletin 737–47–1003, or
within 13,000 flight hours after the most
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khammond on DSKJM1Z7X2PROD with RULES
recent inspection was performed as specified
in AWL No. 47–AWL–06, whichever is latest.
(12) For AWL No. 47–AWL–07, ‘‘Nitrogen
Generation System (NGS)—Nitrogen
Enriched Air (NEA) Distribution Ducting
Integrity’’: Within 6,500 flight hours after the
date of issuance of the original airworthiness
certificate or the original export certificate of
airworthiness, within 6,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1003, or
within 6,500 flight hours after the most
recent inspection was performed as specified
in AWL No. 47–AWL–07, whichever is latest.
(13) For AWL No. 47–AWL–09, ‘‘Nitrogen
Generation System—Oxygen Sensor’’: Within
18,000 flight hours after the date of issuance
of the original airworthiness certificate or the
original export certificate of airworthiness, or
within 18,000 flight hours after the most
recent replacement was performed as
specified in AWL No. 47–AWL–09, or within
36 months after the effective date of this AD,
whichever is latest.
(14) For AWL No. 28–AWL–101, ‘‘Engine
Fuel Suction Feed Operational Test’’: Within
7,500 flight hours or 36 months, whichever
occurs first, after the date of issuance of the
original airworthiness certificate or the
original export certificate of airworthiness; or
within 7,500 flight hours or 36 months,
whichever occurs first, after the most recent
inspection was performed as specified in
AWL No. 28–AWL–101; whichever is later.
(h) Additional Acceptable Exceptions to the
AWLs
As an option, when accomplishing the
actions required by paragraph (g) of this AD,
the changes specified in paragraphs (h)(1)
through (3) of this AD are acceptable.
(1) Where AWL No. 28–AWL–05 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–05 identifies
TFE–2X Standard wall for wire sleeving, the
following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP,
or HM.
(3) Where AWL No. 28–AWL–20 specifies
the operational test for left center tank fuel
boost pump relay R54 and right center tank
fuel boost pump relay R55, for airplanes that
have complied with paragraph (g)(2)(ii) of AD
2011–20–07, Amendment 39–16818 (76 FR
60710, September 30, 2011), or that have
installed Supplemental Type Certificate
(STC) ST02076LA, that action does not
apply.
(i) No Alternative Actions, Intervals, or
Critical Design Configuration Control
Limitations (CDCCLs)
Except as provided in paragraph (h) of this
AD, after the existing maintenance or
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16:05 Jun 14, 2021
Jkt 253001
inspection program has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections),
intervals, or CDCCLs may be used unless the
actions, intervals, and CDCCLs are approved
as an alternative method of compliance
(AMOC) in accordance with the procedures
specified in paragraph (k) of this AD.
(j) Terminating Action for Certain AD
Requirements
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (7) of this AD for that airplane.
(1) The revision required by the
introductory text to paragraph (h) and
paragraph (h)(1) of AD 2008–06–03.
(2) All requirements of AD 2008–10–10 R1.
(3) The revision required by paragraph (g)
of AD 2008–17–15.
(4) The revision required by paragraph (k)
of AD 2011–18–03.
(5) All requirements of AD 2013–15–17.
(6) The revisions required by paragraphs
(i)(1)(i) through (iii) of AD 2018–20–13.
(7) All requirements of AD 2018–20–24.
(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 local Flight Standards
District 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) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district 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
For more information about this AD,
contact Christopher Baker, Aerospace
Engineer, Propulsion Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3552; email: Christopher.R.Baker@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
PO 00000
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31609
(i) Boeing 737–600/700/700C/800/900/
900ER Special Compliance Items/
Airworthiness Limitations, D626A001–9–04,
dated April 2019.
(ii) Boeing 737–600/700/700C/800/900/
900ER Special Compliance Items/
Airworthiness Limitations, D626A001–9–04,
dated November 2020.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
St., Des Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on May 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–12436 Filed 6–14–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0314; Project
Identifier MCAI–2020–00599–R; Amendment
39–21592; AD 2021–12–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Helicopters Model EC155B1
helicopters. This AD was prompted by
a report of difficulties when jettisoning
the co-pilot door during non-scheduled
maintenance. This AD requires a
functional check of the pilot and copilot door jettisoning system and
corrective actions if necessary, as
specified in a European Aviation Safety
Agency (EASA) AD, which is
incorporated by reference. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 20,
2021.
SUMMARY:
E:\FR\FM\15JNR1.SGM
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]]>Agencies
[Federal Register Volume 86, Number 113 (Tuesday, June 15, 2021)]
[Rules and Regulations]
[Pages 31604-31609]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12436]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0341; Project Identifier 2020-NM-017-AD; Amendment
39-21586; AD 2021-11-24]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and
-900ER series airplanes. This AD was prompted by significant changes
made to the airworthiness limitations (AWLs) related to fuel tank
ignition prevention and the nitrogen generation system (NGS). This AD
requires revising the existing maintenance or inspection program, as
applicable, to incorporate the April 2019 or November 2020 revision of
the airworthiness limitations document. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective July 20, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 20,
2021.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the
FAA, Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability of
this material at the FAA, call 206-231-3195. It is also available on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0341.
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-2020-
0341; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Christopher Baker, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3552; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 737-600, -700, -700C, -800, -900, and -900ER series
airplanes. The NPRM published in the Federal Register on May 6, 2020
(85 FR 26888). The NPRM was prompted by significant changes made to the
AWLs related to fuel tank ignition prevention and the NGS. The NPRM
proposed to require revising the existing maintenance or inspection
program, as applicable, to incorporate the April 2019 revision of the
airworthiness limitations document.
The FAA is issuing this AD to prevent the potential for ignition
sources inside the fuel tanks and also to prevent increasing the
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. In
addition, the FAA is issuing this AD to address the potential loss of
engine fuel suction feed
[[Page 31605]]
capability, which could result in dual engine flameouts, inability to
restart engines, and consequent forced landing of the airplane.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Support for the NPRM
The Air Line Pilots Association, International (ALPA), United
Airlines, and an individual stated support for the NPRM.
Request To Delay Issuance of Final Rule
All Nippon Airways (ANA) requested that the FAA delay issuance of
the final rule until Boeing releases the next revision of Boeing 737-
600/700/700C/800/900/900ER Special Compliance Items/Airworthiness
Limitations, D626A001-9-04. The commenter explained that in the current
revision of Boeing 737-600/700/700C/800/900/900ER Special Compliance
Items/Airworthiness Limitations, D626A001-9-04, dated April 2019
(Boeing D626A001-9-04, dated April 2019), for Airworthiness Limitation
(AWL) No. 47-AWL-09, ``Nitrogen Generation System--Oxygen Sensor,''
operators must replace the NGS oxygen sensor with a new oxygen sensor
because installation of an overhauled part is not approved at this
time. The commenter stated that Boeing is working with the FAA to allow
testing of the oxygen sensor using the component maintenance manual,
and on-wing testing using the aircraft maintenance manual, and Boeing
plans to revise AWL No. 47-AWL-09 to allow testing and installation of
an overhauled part. The commenter anticipated that the next revision of
Boeing 737-600/700/700C/800/900/900ER Special Compliance Items/
Airworthiness Limitations, D626A001-9-04, would include the revised AWL
No. 47-AWL-09.
The FAA acknowledges the commenter's request. Since publication of
the NPRM, Boeing has issued Boeing 737-600/700/700C/800/900/900ER
Special Compliance Items/Airworthiness Limitations, D626A001-9-04,
dated November 2020 (Boeing D626A001-9-04, dated November 2020), which
limits the applicability of AWL No. 47-AWL-09 to certain Model 737
airplanes and states that an oxygen sensor can be replaced with a new
oxygen sensor or an oxygen sensor repaired per AWL No. 47-AWL-10
``Nitrogen Generation System--Oxygen Sensor Repair.'' This AD requires
updating the existing maintenance/inspection program to incorporate
Boeing D626A001-9-04, dated April 2019; or Boeing D626A001-9-04, dated
November 2020. In addition, based upon requests from other commenters,
the FAA has extended the initial compliance time for replacement of the
oxygen sensor due to a parts availability issue. The FAA has revised
the grace period for the initial ALI task in paragraph (g)(13) of this
AD from 12 months to 36 months. This extended grace period will still
provide an acceptable level of safety.
Request To Extend the Compliance Time
Air China, ANA, China Eastern Airlines (CEA), Delta Air lines
(DAL), Japan Airlines (JAL), Okay Airlines (OKY), Southwest Airlines
(SWA), and Turkish Airlines (THY) requested that the initial compliance
time for the replacement of the oxygen sensor as specified in paragraph
(g)(13) of the proposed AD be extended because of a parts availability
issue. The commenters contacted Boeing and determined that there would
be a shortage of parts, which would prevent them from complying with
the proposed requirement specified in paragraph (g)(13) of the proposed
AD within the compliance time specified in the proposed AD.
The FAA agrees with the commenters' requests based on the
information provided by the commenters. The FAA contacted Boeing and
confirmed that there is a parts availability issue, which could create
an undue burden on operators because it could prevent them from
complying with the requirement specified in paragraph (g)(13) of this
AD, subsequently grounding the affected airplanes. The FAA has revised
the initial compliance time in paragraph (g)(13) of this AD from 12
months to 36 months.
Request To Add an Off-Wing Inspection for AWL No. 47-AWL-09
SWA requested that the FAA consider coordinating this AD with
Boeing to allow for an off-wing inspection of the oxygen sensor, and
repair if necessary, as opposed to a mandated time-limited replacement.
SWA stated that this would mitigate the parts availability impact
across the industry as well the cost of complying with AWL No. 47-AWL-
09.
The FAA agrees that an off-wing inspection would reduce the burden
on operators. This AD allows operators to optionally incorporate Boeing
D626A001-9-04, dated November 2020, which includes an off-wing
inspection as specified in AWL No. 47-AWL-10. Boeing modified the
requirement of AWL No. 47-AWL-09 to allow the use of repaired parts and
added AWL No. 47-AWL-10 to describe the requirements for the method of
inspection/repair in Boeing D626A001-9-04, dated November 2020. This AD
still requires operators to use Boeing D626A001-9-04, dated April 2019,
but provides an option for operators to incorporate Boeing D626A001-9-
04, dated November 2020, into their maintenance program. In addition,
the FAA has determined that an on-wing inspection is currently being
developed by Boeing and that subject on-wing inspection is expected to
be implemented in a future revision of the Boeing D626A001-9-04
document. Under the provisions of paragraph (k) of this AD, the FAA
will consider requests for approval of an alternative method of
compliance (AMOC) if sufficient data are submitted to substantiate that
the change would provide an acceptable level of safety.
Request To Clarify the Applicability of a Certain AWL Item
CEA, DAL, JAL, OKY, Ryan Air, and THY requested clarification of
the applicability specified in AWL No. 47-AWL-09, which addresses
replacement of the oxygen sensor in the NGS. The commenters noted that
in Boeing D626A001-9-04, dated April 2019, the other AWLs specific to
the NGS show the airplane applicability in terms of the airplanes that
have the NGS installed, or incorporation of the actions in Boeing
Service Bulletin 737-47-1002 or Boeing Service Bulletin 737-47-1003.
The commenters noted that all airplanes on the U.S. registry are
required to have the NGS system installed, but the commenters expected
the applicability of AWL No. 47-AWL-09 to be similar to the other AWLs
included in Boeing D626A001-9-04, dated April 2019. In addition, OKY
noted that the applicability in AWL No. 47-AWL-09 was listed as all
airplanes, but in Boeing Fleet Team Digest Document 737NG-FTD-47-19003,
created on May 8, 2020, the applicability is Model 737NG airplanes
delivered after June 2019 or modified with a new, improved ASM (air
separation module) using the procedures in Boeing Service Bulletin 737-
47-1015.
DAL and the other commenters explained that they contacted Boeing
regarding this applicability issue. The commenters stated that Boeing
confirmed that the applicability
[[Page 31606]]
specified in AWL No. 47-AWL-09 is incorrect and Boeing advised that in
the next revision of Boeing D626A001-9-04, dated April 2019, the
applicability specified in AWL No. 47-AWL-09 will be updated to include
airplanes having L/Ns 1820, 1831, 2517, 2620, and subsequent, and all
airplanes that have incorporated the actions specified in Boeing
Service Bulletin 737-47-1003. Several of the commenters stated that
paragraph (g)(13) of the proposed AD should include additional text to
clarify the applicability of AWL No. 47-AWL-09. The commenters stated
that by incorporating this information into the final rule, the FAA
would prevent the need for operators to apply for an AMOC in the
future.
The FAA acknowledges the commenters' requests. As mentioned
previously, Boeing has published Boeing D626A001-9-04, dated November
2020, and in this revision the applicability specified in AWL No. 47-
AWL-09 was updated and limited to specify only airplanes having L/Ns
1820, 1831, 2517, 2620, and subsequent, and all airplanes that have
incorporated the actions specified in Boeing Service Bulletin 737-47-
1003. The FAA has changed the AD to allow the use of Boeing D626A001-9-
04, dated November 2020, which correctly identifies the applicability
for AWL No. 47-AWL-09.
Request To Clarify the Unsafe Condition
Boeing, DAL, and CEA requested clarification of the unsafe
condition specified in the Discussion section of the NPRM and paragraph
(e) of the proposed AD. The commenters remarked that the wording
implied that increased flammability in the center fuel tank leads to
fuel tank explosion. The commenters explained that increased
flammability alone does not lead to a fuel tank explosion; there must
also be a concurrent ignition source in the center fuel tank. The
commenters suggested that it would be more accurate to state that the
increased flammability combined with an ignition source could lead to a
fuel tank explosion.
In addition, the commenters requested that the unsafe condition be
revised to address the potential loss of engine fuel suction feed
capability. The commenters pointed out that paragraph (g)(14) of the
proposed AD specified AWL No. 28-AWL-101, ``Engine Fuel Suction Feed
Operational Test,'' which would be required to protect the airplane
from engine flameout during suction feed operations. The commenters
observed that this proposed action is not associated with the
prevention of fuel tank ignition.
The FAA agrees with the commenters' requests based on the reasons
provided by the commenters. The FAA has revised the Background section
in this final rule and paragraph (e) of this AD accordingly.
Request To Account for Indirect Costs
ANA, CEA, DAL, OKY, SWA, and THY expressed concern regarding the
indirect financial burden associated with accomplishing the actual on-
wing work resulting from the maintenance program or inspection program
changes that would be required by the proposed AD. DAL specifically
noted that accomplishment of the oxygen sensor replacement specified in
AWL No. 47-AWL-09, would require replacement of approximately 130
oxygen sensors with new oxygen sensors, and based on price quotes from
the manufacturer of the oxygen sensors, it would cost an additional
$7,000,000 over the estimated $7,560 per operator specified in the
Costs of Compliance section of the NPRM. DAL stated that once all
airplanes have reached the threshold for replacing the oxygen sensor
the recurring cost would be approximately $2,000,000 per year for this
task.
The FAA disagrees with changing the cost of compliance information
for this AD. The cost information provided in this AD describes only
the direct costs of the specific actions required by this AD. The FAA
recognizes that, in doing the actions required by an AD, operators
might incur incidental costs in addition to the direct costs. The
extended compliance time previously mentioned could alleviate some of
these indirect costs, as they would be spread out over 36 months
instead of occurring within 12 months. Also, Boeing D626A001-9-04,
dated November 2020, was revised to allow operators to use a repaired
oxygen sensor in AWL No. 47-AWL-09 and added AWL No. 47-AWL-10 to
describe the requirements for the method of inspection/repair. As
identified above in a previous comment, operators now have the option
to incorporate Boeing D626A001-9-04, dated November 2020, into their
maintenance and inspection program, thereby reducing the financial
impact of these requirements. The AD has not been changed in this
regard.
Request for Clarification of Compliance Time Interval Units
DAL and CEA requested that the FAA explain why paragraph (g) of the
proposed AD expressed compliance time intervals in terms of months when
Boeing D626A001-9-04, dated April 2019, specifies these intervals in
terms of years. The commenter mentioned it was unclear if an AMOC would
be required if an operator incorporated the compliance intervals in
years, as specified in Boeing D626A001-9-04, dated April 2019, instead
of months, as specified in the proposed AD.
The FAA disagrees that there is a difference in the calculated
compliance times described by the commenters. The FAA uses compliance
times defined in months for required AD actions. Operators have the
capability of converting years to months when comparing the compliance
times of required AD actions and the times specified in a
manufacturer's document. The FAA has determined that operators should
not be confused when these conversions take place and an operator does
not need to request an AMOC. Regardless of how an operator records the
compliance time, within 36 months or within 3 years after the effective
date of this AD, the compliance times in this AD, Boeing D626A001-9-04,
dated April 2019, and Boeing D626A001-9-04, dated November 2020, end at
the same time. The FAA has not changed this AD in regard to this issue.
Request To Include Additional Affected AD in Paragraph (b) of Proposed
AD
DAL and CEA requested that AD 2018-20-13, Amendment 39-19447 (83 FR
52305, October 17, 2018) (AD 2018-20-13), be included in the list of
affected ADs in paragraph (b) of the proposed AD. DAL and CEA noted
that paragraphs (i)(1)(i) through (iii) of AD 2018-20-13 require
incorporation of AWL Nos. 28-AWL-21, 28-AWL-22, and 28-AWL-24 that are
included in Boeing 737-600/700/700C/800/900/900ER Special Compliance
Items/Airworthiness Limitations, D626A001-9-04, dated June 2018, into
an operator's maintenance or inspection program as applicable. DAL and
CEA suggested that only the latter revision of these AWLs that are
included in Boeing D626A001-9-04, dated April 2019, should be mandated.
DAL and CEA stated that the requirements of paragraphs (i)(1)(i)
through (iii) of AD 2018-20-13 should be terminated when the
requirements of the proposed AD become effective.
The FAA agrees with the commenter's request; paragraph (b) of this
AD has been revised to include AD 2018-20-13 in paragraph (b)(6) of
this AD, and the subsequent paragraph has been redesignated as
paragraph (b)(7) of this AD. In addition, this AD has been revised to
include a new paragraph (j)(6) of this AD to terminate the requirements
specified in paragraphs (i)(1)(i) through
[[Page 31607]]
(iii) of AD 2018-20-13, and the subsequent paragraph has been
redesignated as paragraph (j)(7) of this AD.
Request To Change the Subject in Paragraph (d) of the Proposed AD
DAL and CEA requested that the Subject in paragraph (d) of the
proposed AD be changed from Air Transport Association (ATA) of America
Code 71, Powerplant, to ATA Code 28, Fuel. DAL and CEA noted that the
unsafe condition specified in the proposed AD is associated with
ignition sources in the fuel tanks and flammability exposure of the
center fuel tank. The fuel system is the subject of ATA Code 28.
Previously issued ADs identified in paragraph (b) of the proposed AD,
which are similar to the proposed AD, have specified ATA Code 28 as the
subject in paragraph (d).
The FAA agrees with the commenter's request based on the reasons
provided by the commenter. Paragraph (d) of this AD has been changed to
ATA Code 28, Fuel.
Effects of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that the installation of blended or
split scimitar winglets per Supplemental Type Certificated (STC)
ST008300SE does not affect compliance with the proposed actions.
The FAA agrees that STC ST008300SE does not affect compliance with
the actions required by this AD. The FAA has not changed this AD in
this regard.
Reduction of Applicable Airplanes Since NPRM Was Issued
The FAA has updated the applicability, paragraph (c) of this AD, to
remove airplanes that were delivered with Boeing 737-600/700/700C/800/
900/900ER Special Compliance Items/Airworthiness Limitations, D626A001-
9-04, dated April 2019, thereby reducing the scope of the affected
airplanes in this final rule.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and minor editorial changes. The FAA has determined that these minor
changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing 737-600/700/700C/800/900/900ER Special
Compliance Items/Airworthiness Limitations, D626A001-9-04, dated April
2019; and Boeing 737-600/700/700C/800/900/900ER Special Compliance
Items/Airworthiness Limitations, D626A001-9-04, dated November 2020.
This service information describes AWLs that include airworthiness
limitation instructions (ALIs) and critical design configuration
control limitations (CDCCLs) tasks related to fuel tank ignition
prevention and the NGS. 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.
Differences Between This AD and the Service Information
The ``Description'' column of AWL No. 28-AWL-20 identifies certain
operational tests. However, the operational test for left center tank
fuel boost pump relay R54 and right center tank fuel boost pump relay
R55 is not required for airplanes on which the actions specified in
paragraph (g)(2)(ii) of AD 2011-20-07, Amendment 39-16818 (76 FR 60710,
September 30, 2011), have been done, or airplanes that have installed
STC ST02076LA.
Paragraph (g) of this AD requires operators to revise their
existing maintenance or inspection program by incorporating, in part,
AWL No. 28-AWL-05, ``Wire Separation Requirements for New Wiring
Installed in Proximity to Wiring That Goes Into the Fuel Tanks'' in
Boeing D626A001-9-04, dated November 2020. Paragraph (h) of this AD
allows certain changes to be made to the requirements specified in AWL
No. 28-AWL-05 as an option.
Costs of Compliance
The FAA estimates that this AD affects 2,057 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
The FAA 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. In the past, the FAA estimated that this action takes 1
work-hour per airplane. Since operators incorporate maintenance or
inspection program changes for their affected fleet(s), the FAA
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
[[Page 31608]]
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:
2021-11-24 The Boeing Company: Amendment 39-21586; Docket No. FAA-
2020-0341; Project Identifier 2020-NM-017-AD.
(a) Effective Date
This airworthiness directive (AD) is effective July 20, 2021.
(b) Affected (Airworthiness Directives) ADs
This AD affects the ADs specified in paragraphs (b)(1) through
(7) of this AD.
(1) AD 2008-06-03, Amendment 39-15415 (73 FR 13081, March 12,
2008) (AD 2008-06-03).
(2) AD 2008-10-10 R1, Amendment 39-16164 (75 FR 1529, January
12, 2010) (AD 2008-10-10 R1).
(3) AD 2008-17-15, Amendment 39-15653 (73 FR 50714, August 28,
2008) (AD 2008-17-15).
(4) AD 2011-18-03, Amendment 39-16785 (76 FR 53317, August 26,
2011) (AD 2011-18-03).
(5) AD 2013-15-17, Amendment 39-17533 (78 FR 52838, August 27,
2013) (AD 2013-15-17).
(6) AD 2018-20-13, Amendment 39-19447 (83 FR 52305, October 17,
2018) (AD 2018-20-13).
(7) AD 2018-20-24, Amendment 39-19458 (83 FR 51815, October 15,
2018) (AD 2018-20-24).
(c) Applicability
This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any
category, Line Numbers (L/Ns) 1 through 7596 inclusive, except L/Ns
7352, 7362, 7377, 7417, 7457, 7522, 7587, and 7592.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant changes made to the
airworthiness limitations (AWLs) related to fuel tank ignition
prevention and the nitrogen generation system (NGS). The FAA is
issuing this AD to address the development of an ignition source
inside the fuel tanks and also to prevent increasing the
flammability exposure of the center fuel tank, which could lead to
fuel tank explosion and consequent loss of the airplane. The FAA is
also issuing this AD to prevent increasing the flammability exposure
of the center fuel tank, which together with an ignition source in
the fuel tank, could lead to a fuel tank explosion and consequent
loss of the airplane. In addition, the FAA is issuing this AD to
address the 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 applicable information specified in Section A,
including Subsections A.1., A.2., and A.3, of Boeing 737-600/700/
700C/800/900/900ER Special Compliance Items/Airworthiness
Limitations, D626A001-9-04, dated April 2019; or November 2020;
except as provided by paragraph (h) of this AD. The initial
compliance times for the airworthiness limitation instruction (ALI)
tasks are within the applicable compliance times specified in in
paragraphs (g)(1) through (14) of this AD.
(1) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel
Tank'': Within 120 months after the date of issuance of the original
airworthiness certificate or the original export certificate of
airworthiness, or within 120 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-01, whichever is later.
(2) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'':
Within 120 months after the date of issuance of the original
airworthiness certificate or the original export certificate of
airworthiness, or within 120 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-03, whichever is later.
(3) For AWL No. 28-AWL-19, ``Center Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after the date of
issuance of the original airworthiness certificate or the original
export certificate of airworthiness, within 12 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1206, or within 12 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-19, whichever is
latest. This AWL does not apply to airplanes that have complied with
paragraph (s) of AD 2011-18-03.
(4) For AWL No. 28-AWL-20, ``Over-Current and Arcing Protection
Electrical Design Features Operation--Boost Pump Ground Fault
Interrupter (GFI)'': Within 12 months after the date of issuance of
the original airworthiness certificate or the original export
certificate of airworthiness, within 12 months after accomplishment
of the actions specified in Boeing Service Bulletin 737-28A1201, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-20, whichever is latest.
(5) For AWL No. 28-AWL-23, ``Center Tank Fuel Boost Pump Power
Failed On Protection System'': Within 12 months after the date of
issuance of the original airworthiness certificate or the original
export certificate of airworthiness, within 12 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1248, or within 12 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-23, whichever is
latest. This AWL does not apply to airplanes that have complied with
paragraph (s) of AD 2011-18-03.
(6) For AWL No. 28-AWL-24, ``Spar Valve Motor Operated Valve
(MOV) Actuator--Lightning and Fault Current Protection Electrical
Bond'': Within 72 months after accomplishment of the actions
specified in Boeing Service Bulletin 737-28A1207, or within 72
months after the most recent inspection was performed as specified
in AWL No. 28-AWL-24, whichever is later.
(7) For AWL No. 28-AWL-29, ``Full Cushion Clamps and Teflon
Sleeving (If Installed) Installed on Out-of-Tank Wire Bundles
Installed on Brackets that are Mounted Directly on the Fuel Tanks'':
For airplanes having line numbers (L/N) 1 through 1754 inclusive,
within 120 months after accomplishment of the actions specified in
Boeing Service Bulletin 737-57A1279. For airplanes having L/N 1755
and subsequent, within 120 months after the date of issuance of the
original airworthiness certificate or the original export
certificate of airworthiness, or within 48 months after the
effective date of this AD, whichever is later.
(8) For AWL No. 28-AWL-35, ``Fuel Quantity Indicating System
(FQIS)--Center Fuel Tank In-Tank Component and Wire Harness
Protection Features-Separation from Center Tank Internal
Structure'': For airplanes that have incorporated Boeing Service
Bulletin 737-28-1356, within 120 months after accomplishment of the
actions specified in Boeing Service Bulletin 737-28-1356, or within
120 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-35, whichever is later.
(9) For AWL No. 28-AWL-37, ``Fuel Quantity Indicating System
(FQIS)--Built in Test Equipment (BITE) Test'': For airplane L/Ns
6987 and 7000 and subsequent, within 750 flight hours since the date
the most recent BITE test was accomplished as specified in AWL No.
28-AWL-37, or within 750 flight hours after the effective date of
this AD, whichever is later.
(10) For AWL No. 47-AWL-04, ``Nitrogen Generation System--
Thermal Switch'': Within 22,500 flight hours after the date of
issuance of the original airworthiness certificate or the original
export certificate of airworthiness, within 22,500 flight hours
after accomplishment of the actions specified in Boeing Service
Bulletin 737-47-1003, or within 22,500 flight hours after the most
recent inspection was performed as specified in AWL No. 47-AWL-04,
whichever is latest.
(11) For AWL No. 47-AWL-06, ``Nitrogen Generation System (NGS)--
Cross Vent Check Valve'': Within 13,000 flight hours after the date
of issuance of the original airworthiness certificate or the
original export certificate of airworthiness, within 13,000 flight
hours after accomplishment of the actions specified in Boeing
Service Bulletin 737-47-1003, or within 13,000 flight hours after
the most
[[Page 31609]]
recent inspection was performed as specified in AWL No. 47-AWL-06,
whichever is latest.
(12) For AWL No. 47-AWL-07, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within
6,500 flight hours after the date of issuance of the original
airworthiness certificate or the original export certificate of
airworthiness, within 6,500 flight hours after accomplishment of the
actions specified in Boeing Service Bulletin 737-47-1003, or within
6,500 flight hours after the most recent inspection was performed as
specified in AWL No. 47-AWL-07, whichever is latest.
(13) For AWL No. 47-AWL-09, ``Nitrogen Generation System--Oxygen
Sensor'': Within 18,000 flight hours after the date of issuance of
the original airworthiness certificate or the original export
certificate of airworthiness, or within 18,000 flight hours after
the most recent replacement was performed as specified in AWL No.
47-AWL-09, or within 36 months after the effective date of this AD,
whichever is latest.
(14) For AWL No. 28-AWL-101, ``Engine Fuel Suction Feed
Operational Test'': Within 7,500 flight hours or 36 months,
whichever occurs first, after the date of issuance of the original
airworthiness certificate or the original export certificate of
airworthiness; or within 7,500 flight hours or 36 months, whichever
occurs first, after the most recent inspection was performed as
specified in AWL No. 28-AWL-101; whichever is later.
(h) Additional Acceptable Exceptions to the AWLs
As an option, when accomplishing the actions required by
paragraph (g) of this AD, the changes specified in paragraphs (h)(1)
through (3) of this AD are acceptable.
(1) Where AWL No. 28-AWL-05 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-05 identifies TFE-2X Standard wall for
wire sleeving, the following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP, or HM.
(3) Where AWL No. 28-AWL-20 specifies the operational test for
left center tank fuel boost pump relay R54 and right center tank
fuel boost pump relay R55, for airplanes that have complied with
paragraph (g)(2)(ii) of AD 2011-20-07, Amendment 39-16818 (76 FR
60710, September 30, 2011), or that have installed Supplemental Type
Certificate (STC) ST02076LA, that action does not apply.
(i) No Alternative Actions, Intervals, or Critical Design Configuration
Control Limitations (CDCCLs)
Except as provided in paragraph (h) of this AD, after the
existing maintenance or inspection program has been revised as
required by paragraph (g) of this AD, no alternative actions (e.g.,
inspections), intervals, or CDCCLs may be used unless the actions,
intervals, and CDCCLs are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (k) of this AD.
(j) Terminating Action for Certain AD Requirements
Accomplishment of the revision required by paragraph (g) of this
AD terminates the requirements specified in paragraphs (j)(1)
through (7) of this AD for that airplane.
(1) The revision required by the introductory text to paragraph
(h) and paragraph (h)(1) of AD 2008-06-03.
(2) All requirements of AD 2008-10-10 R1.
(3) The revision required by paragraph (g) of AD 2008-17-15.
(4) The revision required by paragraph (k) of AD 2011-18-03.
(5) All requirements of AD 2013-15-17.
(6) The revisions required by paragraphs (i)(1)(i) through (iii)
of AD 2018-20-13.
(7) All requirements of AD 2018-20-24.
(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 local Flight Standards District
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) 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 local flight standards district office/certificate holding
district 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
For more information about this AD, contact Christopher Baker,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3552; email: [email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing 737-600/700/700C/800/900/900ER Special Compliance
Items/Airworthiness Limitations, D626A001-9-04, dated April 2019.
(ii) Boeing 737-600/700/700C/800/900/900ER Special Compliance
Items/Airworthiness Limitations, D626A001-9-04, dated November 2020.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on May 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-12436 Filed 6-14-21; 8:45 am]
BILLING CODE 4910-13-P
