Airworthiness Directives; The Boeing Company Airplanes, 26888-26891 [2020-09395]
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26888
Proposed Rules
Federal Register
Vol. 85, No. 88
Wednesday, May 6, 2020
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2020–0341; Product
Identifier 2020–NM–017–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model
737–600, –700, –700C, –800, –900, and
–900ER series airplanes. This proposed
AD was prompted by significant
changes made to the airworthiness
limitations (AWLs) related to fuel tank
ignition prevention and the nitrogen
generation system. This proposed AD
would require revising the existing
maintenance or inspection program, as
applicable, to incorporate the latest
revision of the AWLs. The FAA is
proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments
on this proposed AD by June 22, 2020.
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
SUMMARY:
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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.
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 NPRM, any
comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
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–
231–3556; email: Christopher.R.Baker@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under the ADDRESSES section. Include
‘‘Docket No. FAA–2020–0341; Product
Identifier 2020–NM–017–AD’’ at the
beginning of your comments. The FAA
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this NPRM. The FAA will consider all
comments received by the closing date
and may amend this NPRM because of
those comments.
The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this NPRM.
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Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
the FAA issued a final rule titled
‘‘Transport Airplane Fuel Tank System
Design Review, Flammability Reduction
and Maintenance and Inspection
Requirements’’ (66 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements that rule
included Amendment 21–78, which
established Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88’’) at 14
CFR part 21. Subsequently, SFAR 88
was amended by Amendment 21–82 (67
FR 57490, September 10, 2002;
corrected at 67 FR 70809, November 26,
2002), Amendment 21–83 (67 FR 72830,
December 9, 2002; corrected at 68 FR
37735, June 25, 2003, to change ‘‘21–82’’
to ‘‘21–83’’), and Amendment 21–101
(83 FR 9162, March 5, 2018).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the final rule published on May 7,
2001, the FAA intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews,
the FAA has established four criteria
intended to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
single failures, single failures in
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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 has determined that the
actions identified in this proposed AD
are necessary to reduce the potential of
ignition sources inside fuel tanks,
which, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane.
The FAA issued AD 2008–10–10 R1,
Amendment 39–16164 (75 FR 1529,
January 12, 2010) (‘‘AD 2008–10–10
R1’’) and AD 2018–20–24, Amendment
39–19458 (83 FR 51815, October 15,
2018) (‘‘AD 2018–20–24’’), which apply
to certain The Boeing Company Model
737–600, –700, –700C, –800, and –900
series airplanes. AD 2008–10–10 R1 and
AD 2018–20–24 require incorporation of
fuel system AWLs and also require 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 included in the
Airworthiness Limitations Section
(ALS) of the manufacturer’s Instructions
for Continued Airworthiness. Since AD
2008–10–10 R1 and AD 2018–20–24
were issued, the ALS has been
significantly revised by the
manufacturer to correct technical and
editorial errors and also to add new
requirements. Those changes affect the
fuel system and nitrogen generation
system AWLs.
The FAA proposes to adopt this new
AD to require revising the maintenance
or inspection program, as applicable, to
incorporate the latest revision of the
AWLs. The FAA is proposing 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.
The FAA has determined that
accomplishing the revision required by
paragraph (g) of this proposed AD
would terminate the following
requirements for that airplane:
• All requirements of AD 2008–10–10
R1.
• The revision required by paragraphs
(h) and (h)(1) of AD 2008–06–03,
Amendment 39–15415 (73 FR 13081,
March 12, 2008).
• The revision required by paragraph
(g) of AD 2008–17–15, Amendment 39–
15653 (73 FR 50714, August 28, 2008).
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• The revision required by paragraph
(k) of AD 2011–18–03, Amendment 39–
16785 (76 FR 53317, August 26, 2011).
• All requirements of AD 2013–15–
17, Amendment 39–17533 (78 FR
52838, August 27, 2013).
• All requirements of AD 2018–20–
24.
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. This service information
describes AWLs that include
airworthiness limitation instructions
(ALIs) and critical design configuration
control limitations (CDCCLs) tasks
related to fuel tank ignition prevention
and the nitrogen generation system.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination
The FAA is proposing this AD
because the agency evaluated all the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
in other products of the same type
design.
Proposed AD Requirements
This proposed AD would require
revising the existing maintenance or
inspection program, as applicable, to
incorporate 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
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
The ‘‘description’’ column of AWL
No. 28–AWL–20 identifies certain
operational tests. However, 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
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26889
are not required to do the operational
test for left center tank fuel boost pump
relay R54 and right center tank fuel
boost pump relay R55.
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–05, ‘‘Wire Separation
Requirements for New Wiring Installed
in Proximity to Wiring That Goes Into
the Fuel Tanks’’ in Boeing 737–600/700/
700C/800/900/900ER Special
Compliance Items/Airworthiness
Limitations, D626A001–9–04, dated
April 2019. Paragraph (h) of this
proposed AD would allow certain
changes to be made to the requirements
specified in AWL No. 28–AWL–05 as an
option.
Clarification of the Service Information
The ‘‘applicability’’ column of AWL
No. 28–AWL–19 identifies affected
airplanes. For airplanes on which the
actions specified in paragraph (s) of AD
2011–18–03 have been done,
incorporation of Boeing Service Bulletin
737–28A1206 is not required. Therefore,
those airplanes are not affected by AWL
No. 28–AWL–19 and are not required to
do the functional test.
The ‘‘applicability’’ column of AWL
No. 28–AWL–23 identifies affected
airplanes. For airplanes on which the
actions specified in paragraph (s) of AD
2011–18–03 have been done,
incorporation of Boeing Service Bulletin
737–28A1248 is not required. Therefore,
those airplanes are not affected by AWL
No. 28–AWL–23 and are not required to
do the functional test.
Costs of Compliance
The FAA estimates that this proposed
AD affects 2,057 airplanes of U.S.
registry. The FAA estimates the
following costs to comply with this
proposed 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,
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 workhour).
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Federal Register / Vol. 85, No. 88 / Wednesday, May 6, 2020 / Proposed Rules
§ 39.13
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) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2020–0341; Product Identifier 2020–
NM–017–AD.
(a) Comments Due Date
The FAA must receive comments by June
22, 2020.
(b) Affected ADs
This AD affects the ADs specified in
paragraphs (b)(1) through (6) 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 2018–20–24, 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, with an original airworthiness
certificate or original export certificate of
airworthiness issued on or before December
18, 2019.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Unsafe Condition
This AD was prompted by significant
changes made to the airworthiness
limitations (AWLs) related to fuel tank
ignition prevention and the nitrogen
generation system. The FAA is issuing this
AD to address the 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.
(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 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; except as provided by
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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. For airplanes
that have complied with paragraph (g)(2)(ii)
of AD 2011–20–07, Amendment 39–16818
(76 FR 60710, September 30, 2011), the
operational test for left center tank fuel boost
pump relay R54 and right center tank fuel
boost pump relay R55 does not apply.
(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) ActuatorLightning and Fault Current Protection
Electrical Bond:’’ Within 72 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1207, or
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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
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
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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
12 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 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–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.
(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.
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(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)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the 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
(1) 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–
3556; email: Christopher.R.Baker@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
Issued on April 23, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–09395 Filed 5–5–20; 8:45 am]
BILLING CODE 4910–13–P
(j) Terminating Action for Certain AD
Requirements
DEPARTMENT OF TRANSPORTATION
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (6) of this AD for that airplane.
(1) The revision required by paragraphs (h)
and (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) All requirements of AD 2018–20–24.
Federal Aviation Administration
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
14 CFR Part 39
[Docket No. FAA–2020–0443; Project
Identifier AD–2020–00178–E]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\06MYP1.SGM
06MYP1
]]>Agencies
[Federal Register Volume 85, Number 88 (Wednesday, May 6, 2020)]
[Proposed Rules]
[Pages 26888-26891]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-09395]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 85, No. 88 / Wednesday, May 6, 2020 /
Proposed Rules
[[Page 26888]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0341; Product Identifier 2020-NM-017-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 737-600, -700, -700C, -800, -900,
and -900ER series airplanes. This proposed AD was prompted by
significant changes made to the airworthiness limitations (AWLs)
related to fuel tank ignition prevention and the nitrogen generation
system. This proposed AD would require revising the existing
maintenance or inspection program, as applicable, to incorporate the
latest revision of the AWLs. The FAA is proposing this AD to address
the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by June 22,
2020.
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-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 NPRM, any comments received, and other information. The street
address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
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: 206-231-3556; 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 the ADDRESSES section. Include ``Docket No. FAA-2020-0341;
Product Identifier 2020-NM-017-AD'' at the beginning of your comments.
The FAA specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this NPRM.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, the FAA issued a
final rule titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements that rule
included Amendment 21-78, which established Special Federal Aviation
Regulation No. 88 (``SFAR 88'') at 14 CFR part 21. Subsequently, SFAR
88 was amended by Amendment 21-82 (67 FR 57490, September 10, 2002;
corrected at 67 FR 70809, November 26, 2002), Amendment 21-83 (67 FR
72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to
change ``21-82'' to ``21-83''), and Amendment 21-101 (83 FR 9162, March
5, 2018).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the final rule published on
May 7, 2001, the FAA intended to adopt airworthiness directives to
mandate any changes found necessary to address unsafe conditions
identified as a result of these reviews.
In evaluating these design reviews, the FAA has established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
[[Page 26889]]
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 has determined that the actions identified in this proposed
AD are necessary to reduce the potential of ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane.
The FAA issued AD 2008-10-10 R1, Amendment 39-16164 (75 FR 1529,
January 12, 2010) (``AD 2008-10-10 R1'') and AD 2018-20-24, Amendment
39-19458 (83 FR 51815, October 15, 2018) (``AD 2018-20-24''), which
apply to certain The Boeing Company Model 737-600, -700, -700C, -800,
and -900 series airplanes. AD 2008-10-10 R1 and AD 2018-20-24 require
incorporation of fuel system AWLs and also require 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 included in the Airworthiness Limitations Section
(ALS) of the manufacturer's Instructions for Continued Airworthiness.
Since AD 2008-10-10 R1 and AD 2018-20-24 were issued, the ALS has been
significantly revised by the manufacturer to correct technical and
editorial errors and also to add new requirements. Those changes affect
the fuel system and nitrogen generation system AWLs.
The FAA proposes to adopt this new AD to require revising the
maintenance or inspection program, as applicable, to incorporate the
latest revision of the AWLs. The FAA is proposing 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.
The FAA has determined that accomplishing the revision required by
paragraph (g) of this proposed AD would terminate the following
requirements for that airplane:
All requirements of AD 2008-10-10 R1.
The revision required by paragraphs (h) and (h)(1) of AD
2008-06-03, Amendment 39-15415 (73 FR 13081, March 12, 2008).
The revision required by paragraph (g) of AD 2008-17-15,
Amendment 39-15653 (73 FR 50714, August 28, 2008).
The revision required by paragraph (k) of AD 2011-18-03,
Amendment 39-16785 (76 FR 53317, August 26, 2011).
All requirements of AD 2013-15-17, Amendment 39-17533 (78
FR 52838, August 27, 2013).
All requirements of AD 2018-20-24.
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. This service information describes AWLs that include
airworthiness limitation instructions (ALIs) and critical design
configuration control limitations (CDCCLs) tasks related to fuel tank
ignition prevention and the nitrogen generation system. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
FAA's Determination
The FAA is proposing this AD because the agency evaluated all the
relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require revising the existing maintenance or
inspection program, as applicable, to incorporate 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
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
The ``description'' column of AWL No. 28-AWL-20 identifies certain
operational tests. However, 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 are not required to do the
operational test for left center tank fuel boost pump relay R54 and
right center tank fuel boost pump relay R55.
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-05, ``Wire Separation Requirements for New Wiring
Installed in Proximity to Wiring That Goes Into the Fuel Tanks'' in
Boeing 737-600/700/700C/800/900/900ER Special Compliance Items/
Airworthiness Limitations, D626A001-9-04, dated April 2019. Paragraph
(h) of this proposed AD would allow certain changes to be made to the
requirements specified in AWL No. 28-AWL-05 as an option.
Clarification of the Service Information
The ``applicability'' column of AWL No. 28-AWL-19 identifies
affected airplanes. For airplanes on which the actions specified in
paragraph (s) of AD 2011-18-03 have been done, incorporation of Boeing
Service Bulletin 737-28A1206 is not required. Therefore, those
airplanes are not affected by AWL No. 28-AWL-19 and are not required to
do the functional test.
The ``applicability'' column of AWL No. 28-AWL-23 identifies
affected airplanes. For airplanes on which the actions specified in
paragraph (s) of AD 2011-18-03 have been done, incorporation of Boeing
Service Bulletin 737-28A1248 is not required. Therefore, those
airplanes are not affected by AWL No. 28-AWL-23 and are not required to
do the functional test.
Costs of Compliance
The FAA estimates that this proposed AD affects 2,057 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed 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).
[[Page 26890]]
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) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The 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 (AD):
The Boeing Company: Docket No. FAA-2020-0341; Product Identifier
2020-NM-017-AD.
(a) Comments Due Date
The FAA must receive comments by June 22, 2020.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) through
(6) 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 2018-20-24, 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, with an original airworthiness certificate or original
export certificate of airworthiness issued on or before December 18,
2019.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Unsafe Condition
This AD was prompted by significant changes made to the
airworthiness limitations (AWLs) related to fuel tank ignition
prevention and the nitrogen generation system. The FAA is issuing
this AD to address the 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.
(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 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; 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. For airplanes
that have complied with paragraph (g)(2)(ii) of AD 2011-20-07,
Amendment 39-16818 (76 FR 60710, September 30, 2011), the
operational test for left center tank fuel boost pump relay R54 and
right center tank fuel boost pump relay R55 does not apply.
(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
[[Page 26891]]
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 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 12 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 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-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.
(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 (6) of this AD for that airplane.
(1) The revision required by paragraphs (h) and (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) 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)(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 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
(1) 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:
206-231-3556; 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 April 23, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-09395 Filed 5-5-20; 8:45 am]
BILLING CODE 4910-13-P
