Airworthiness Directives; The Boeing Company Airplanes, 26778-26781 [2019-11925]
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Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Standards Branch, 901
Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4144; fax: (816)
329–4090; email: mike.kiesov@faa.gov.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
instead be accomplished using a method
approved by the Manager, Small Airplane
Standards Branch, FAA; or the Civil Aviation
Authority of New Zealand (CAA).
(h) Related Information
Refer to CAA MCAI AD No. DCA/750XL/
19A, dated April 26, 2018, for related
information. You may examine the MCAI on
the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–0842. Pacific Aerospace Limited,
Airport Road, Hamilton, Private Bag 3027,
Hamilton 3240, New Zealand; telephone: +64
7 843 6144; facsimile: +64 7 843 6134; email:
pacific@aerospace.co.nz; Internet:
www.aerospace.co.nz. You may review
copies of the referenced service information
at the FAA, Policy and Innovation Division,
901 Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on May
29, 2019.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2019–11751 Filed 6–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0326; Product
Identifier 2018–NM–166–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200,
–200C, –300, –400, and –500 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.
SUMMARY:
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This AD would require revising the
existing maintenance or inspection
program, as applicable, to include new
or revised AWLs. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by July 25, 2019.
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; phone: 562–797–1717;
internet: https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards 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–2019–
0326; 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, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone: 800–647–5527) is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3558; email: jeffrey.rothman@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
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section. Include ‘‘Docket No. FAA–
2019–0326; Product Identifier 2018–
NM–166–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM
because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
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,
we 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) and Amendment 21–83 (67 FR
72830, December 9, 2002; corrected at
68 FR 37735, June 25, 2003, to change
‘‘21–82’’ to ‘‘21–83’’).
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, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
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Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
Single failures, single failures in
combination with another latent
condition(s), and in-service failure
experience. For all four criteria, the
evaluations included consideration of
previous actions taken that may mitigate
the need for further action.
We have determined that the actions
identified in this proposed AD are
necessary to address 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.
We have 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 2008–10–09
R1, Amendment 39–16148 (74 FR
69264, December 31, 2009).
• The revision required by paragraph
(l) of AD 2011–12–09, Amendment 39–
16716 (76 FR 33988, June 10, 2011).
• The revision required by paragraph
(h) of AD 2013–13–15, Amendment 39–
17503 (78 FR 42415, July 16, 2013).
• The revision required by paragraph
(j) of AD 2013–25–05, Amendment 39–
17701 (78 FR 78701, December 27,
2013).
• The revisions required by
paragraphs (l) and (n) of AD 2016–18–
16, Amendment 39–18647 (81 FR
65864, September 26, 2016).
• The revision required by paragraph
(h) of AD 2017–17–09, Amendment 39–
18999 (82 FR 40477, August 25, 2017).
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Related Service Information Under 1
CFR Part 51
We reviewed Boeing 737–100/200/
200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6–
38278–CMR, dated March 2019. This
service information describes
airworthiness limitations that include
Airworthiness Limitation Instructions
(ALI) and Critical Design Configuration
Control Limitations (CDCCL) 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
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course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination
We are proposing this AD because we
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 revised AWLs.
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
Paragraph (g) of this proposed AD
would require operators to revise their
maintenance or inspection program by
incorporating, amongst other tasks,
AWL No. 28–AWL–05, ‘‘Wire
Separation Requirements for New
Wiring Installed in Proximity to Wiring
that Goes Into the Fuel Tanks,’’ in
Boeing 737–100/200/200C/300/400/500
Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), D6–38278–CMR, dated March
2019. Paragraph (h) of this proposed AD
would allow certain changes to be made
to the wire type and sleeving
requirements specified in AWL No. 28–
AWL–05 as an option.
Costs of Compliance
We estimate that this proposed AD
affects 381 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
We have determined that revising the
existing maintenance or inspection
program takes an average of 90 workhours per operator, although we
recognize that this number may vary
from operator to operator. In the past,
we have estimated that this action takes
1 work-hour per airplane. Since
operators incorporate maintenance or
inspection program changes for their
affected fleet(s), we have determined
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that a per-operator estimate is more
accurate than a per-airplane estimate.
Therefore, we estimate the 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.
We are 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.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
Regulatory Findings
We 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) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
The Boeing Company: Docket No. FAA–
2019–0326; Product Identifier 2018–
NM–166–AD.
(a) Comments Due Date
We must receive comments by July 25,
2019.
(b) Affected ADs
This AD affects the ADs specified in
paragraphs (b)(1) through (b)(6) of this AD.
(1) AD 2008–10–09 R1, Amendment 39–
16148 (74 FR 69264, December 31, 2009)
(‘‘AD 2008–10–09 R1’’).
(2) AD 2011–12–09, Amendment 39–16716
(76 FR 33988, June 10, 2011) (‘‘AD 2011–12–
09’’).
(3) AD 2013–13–15, Amendment 39–17503
(78 FR 42415, July 16, 2013) (‘‘AD 2013–13–
15’’).
(4) AD 2013–25–05, Amendment 39–17701
(78 FR 78701, December 27, 2013) (‘‘AD
2013–25–05’’).
(5) AD 2016–18–16, Amendment 39–18647
(81 FR 65864, September 26, 2016) (‘‘AD
2016–18–16’’).
(6) AD 2017–17–09, Amendment 39–18999
(82 FR 40477, August 25, 2017) (‘‘AD 2017–
17–09’’).
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(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel; 47, Nitrogen
Generation System.
(e) Unsafe Condition
This AD was prompted by a determination
that new or revised airworthiness limitations
(AWLs) are necessary. We are issuing this AD
to address 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.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Maintenance or Inspection Program
Revision
(1) For The Boeing Company Model 737–
100, –200, and –200C series airplanes:
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 C, including Subsections C.1, C.2,
and C.3 of Boeing 737–100/200/200C/300/
400/500 Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements
(CMRs), D6–38278–CMR, dated March 2019,
except as provided in paragraph (h) of this
AD. The initial compliance time for the
airworthiness limitation instructions (ALI)
tasks are within the applicable compliance
times specified in paragraphs (g)(1)(i)
through (g)(1)(x) of this AD.
(i) For AWL No. 28–AWL–01, ‘‘External
Wires Over Center Fuel Tank’’: Within 120
months after the most recent inspection was
performed as specified in AWL No. 28–
AWL–01, or within 12 months after the
effective date of this AD if no initial
inspection has been performed.
(ii) For AWL No. 28–AWL–03, ‘‘Fuel
Quantity Indicating System (FQIS)—Out
Tank Wiring Lightning Shield to Ground
Termination’’: Within 120 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1178, or
within 120 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–03, whichever is later.
(iii) For AWL No. 28–AWL–21, ‘‘Center
Tank Fuel Boost Pump Automatic Shutoff
System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1228, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–21, whichever is later.
(iv) For AWL No. 28–AWL–22, ‘‘Auxiliary
Tank Fuel Boost Pump Automatic Shutoff
System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1228, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–22, whichever is later.
(v) For AWL No. 28–AWL–23, ‘‘OverCurrent and Arcing Protection Electrical
Design Features Operation—Boost Pump
Ground Fault Interrupter (GFI)’’: Within 12
months after accomplishment of the actions
specified in Boeing Service Bulletin 737–
28A1212, or within 12 months after the most
recent inspection was performed as specified
in AWL No. 28–AWL–23, whichever is later.
(vi) For AWL No. 28–AWL–24, ‘‘Center
Tank Fuel Boost Pump Power Failed On
Protection System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1227, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–24, whichever is later.
(vii) For AWL No. 28–AWL–25, ‘‘Auxiliary
Fuel Tank Boost Pump Power Failed On
Protection System’’: Within 12 months after
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accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1227, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–25, whichever is later.
(viii) For AWL No. 28–AWL–29, ‘‘AC Fuel
Boost Pump Installation’’: Within 72 months
after the most recent inspection was
performed as specified in AWL No. 28–
AWL–29, or within 12 months after the
effective date of this AD if no inspection has
been performed in the last 72 months.
(ix) For AWL No. 47–AWL–04, ‘‘Nitrogen
Generation System (NGS)—Thermal Switch’’:
Within 22,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1005; within
22,500 flight hours after accomplishment of
the actions specified in Boeing Service
Bulletin 737–47–1008; or within 22,500 flight
hours after the most recent inspection was
performed as specified in AWL No. 47–
AWL–04; whichever is latest.
(x) For AWL No. 47–AWL–05, ‘‘Nitrogen
Generation System (NGS)—Nitrogen
Enriched Air (NEA) Distribution Ducting
Integrity’’: Within 14,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1005; within
14,500 flight hours after accomplishment of
the actions specified in Boeing Service
Bulletin 737–47–1008; or within 14,500 flight
hours after the most recent inspection was
performed as specified in AWL No. 47–
AWL–05; whichever is latest.
(2) For The Boeing Company Model 737–
300, –400, and –500 series airplanes: 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 C, including
Subsections C.1, C.2, and C.3 of Boeing 737–
100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6–
38278–CMR, dated March 2019; except as
provided in paragraph (h) of this AD. The
initial compliance time for the ALI tasks are
within the applicable compliance times
specified in paragraphs (g)(2)(i) through
(g)(2)(xi) of this AD.
(i) For AWL No. 28–AWL–01, ‘‘External
Wires Over Center Fuel Tank’’: Within 120
months after the most recent inspection was
performed as specified in AWL No. 28–
AWL–01, or within 12 months after the
effective date of this AD if no initial
inspection has been performed.
(ii) For AWL No. 28–AWL–03, ‘‘Fuel
Quantity Indicating System (FQIS)—Out
Tank Wiring Lightning Shield to Ground
Termination’’: Within 120 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1175;
within 120 months after accomplishment of
the actions specified in Boeing Service
Bulletin 737–28A1183; within 120 months
after accomplishment of the actions specified
in Boeing Service Bulletin 737–28A1186; or
within 120 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–03; whichever is latest.
(iii) For AWL No. 28–AWL–20, ‘‘Center
Tank Fuel Boost Pump Automatic Shutoff
System’’: Within 12 months after
accomplishment of the actions specified in
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Boeing Service Bulletin 737–28A1216, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–20, whichever is later.
(iv) For AWL No. 28–AWL–21, ‘‘Auxiliary
Tank Fuel Boost Pump Automatic Shutoff
System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1216, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–21, whichever is later.
(v) For AWL No. 28–AWL–22, ‘‘OverCurrent and Arcing Protection Electrical
Design Features Operation—Boost Pump
Ground Fault Interrupter (GFI)’’: Within 12
months after accomplishment of the actions
specified in Boeing Service Bulletin 737–
28A1212, or within 12 months after the most
recent inspection was performed as specified
in AWL No. 28–AWL–22, whichever is later.
(vi) For AWL No. 28–AWL–23, ‘‘Center
Tank Fuel Boost Pump Power Failed On
Protection System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1227, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–23, whichever is later.
(vii) For AWL No. 28–AWL–24, ‘‘Auxiliary
Fuel Tank Boost Pump Power Failed On
Protection System’’: Within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1227, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–24, whichever is later.
(viii) For AWL No. 28–AWL–27, ‘‘AC Fuel
Boost Pump Installation’’: Within 72 months
after the most recent inspection was
performed as specified in AWL No. 28–
AWL–27, or within 12 months after the
effective date of this AD if no inspection has
been performed in the last 72 months.
(ix) For AWL No. 28–AWL–31, ‘‘Cushion
Clamps and Teflon Sleeving Installed on Outof-Tank Wire Bundles Installed on Brackets
that are Mounted Directly on the Fuel
Tanks’’: Within 144 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1228.
(x) For AWL No. 47–AWL–04, ‘‘Nitrogen
Generation System (NGS)—Thermal Switch’’:
Within 22,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1005; within
22,500 flight hours after accomplishment of
the actions specified in Boeing Service
Bulletin 737–47–1008; or within 22,500 flight
hours after the most recent inspection was
performed as specified in AWL No. 47–
AWL–04; whichever is latest.
(xi) For AWL No. 47–AWL–05, ‘‘Nitrogen
Generation System (NGS)—Nitrogen
Enriched Air (NEA) Distribution Ducting
Integrity’’: Within 14,500 flight hours after
accomplishment of the actions specified in
Boeing Service Bulletin 737–47–1005; within
14,500 flight hours after accomplishment of
the actions specified in Boeing Service
Bulletin 737–47–1008; or within 14,500 flight
hours after the most recent inspection was
performed as specified in AWL No. 47–
AWL–05; whichever is latest.
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(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 (h)(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)
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 Actions for Certain AD
Requirements
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (j)(6) of this AD for that airplane:
(1) All requirements of AD 2008–10–09 R1.
(2) The revision required by paragraph (l)
of AD 2011–12–09.
(3) The revision required by paragraph (h)
of AD 2013–13–15.
(4) The revision required by paragraph (j)
of AD 2013–25–05.
(5) The revisions required by paragraphs (l)
and (n) of AD 2016–18–16.
(6) The revision required by paragraph (h)
of AD 2017–17–09.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles 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)(2) of
this AD. Information may be emailed to: 9ANM-LAACO-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.
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
26781
(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
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
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 Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3558;
email: jeffrey.rothman@faa.gov.
(2) For information about AMOCs, contact
Serj Harutunian, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5254; fax: 562–627–5210; email:
serj.harutunian@faa.gov.
(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;
phone: 562–797–1717; internet: https://
www.myboeingfleet.com. You may view this
service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
Issued in Des Moines, Washington, on May
20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–11925 Filed 6–7–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0402; Product
Identifier 2019–NM–008–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2005–17–
14, which applies to all Airbus SAS
Model A300 series airplanes; Model
A300 B4–600, B4–600R, and F4–600R
series airplanes, and Model A300 C4–
SUMMARY:
E:\FR\FM\10JNP1.SGM
10JNP1
]]>Agencies
[Federal Register Volume 84, Number 111 (Monday, June 10, 2019)]
[Proposed Rules]
[Pages 26778-26781]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11925]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0326; Product Identifier 2018-NM-166-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
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. This AD would require
revising the existing maintenance or inspection program, as applicable,
to include new or revised AWLs. We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by July 25, 2019.
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; phone:
562-797-1717; internet: https://www.myboeingfleet.com. You may view
this service information at the FAA, Transport Standards 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-2019-
0326; 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, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Jeffrey Rothman, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3558; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite 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-2019-0326;
Product Identifier 2018-NM-166-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive 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, we 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) and Amendment 21-83 (67 FR
72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to
change ``21-82'' to ``21-83'').
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, we intended to adopt airworthiness directives to mandate
any changes found necessary to address unsafe conditions identified as
a result of these reviews.
[[Page 26779]]
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: Single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this proposed AD
are necessary to address 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.
We have 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 2008-10-09 R1, Amendment 39-16148
(74 FR 69264, December 31, 2009).
The revision required by paragraph (l) of AD 2011-12-09,
Amendment 39-16716 (76 FR 33988, June 10, 2011).
The revision required by paragraph (h) of AD 2013-13-15,
Amendment 39-17503 (78 FR 42415, July 16, 2013).
The revision required by paragraph (j) of AD 2013-25-05,
Amendment 39-17701 (78 FR 78701, December 27, 2013).
The revisions required by paragraphs (l) and (n) of AD
2016-18-16, Amendment 39-18647 (81 FR 65864, September 26, 2016).
The revision required by paragraph (h) of AD 2017-17-09,
Amendment 39-18999 (82 FR 40477, August 25, 2017).
Related Service Information Under 1 CFR Part 51
We reviewed Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements (CMRs),
D6-38278-CMR, dated March 2019. This service information describes
airworthiness limitations that include Airworthiness Limitation
Instructions (ALI) and Critical Design Configuration Control
Limitations (CDCCL) 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
We are proposing this AD because we 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 revised AWLs.
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
Paragraph (g) of this proposed AD would require operators to revise
their maintenance or inspection program by incorporating, amongst other
tasks, AWL No. 28-AWL-05, ``Wire Separation Requirements for New Wiring
Installed in Proximity to Wiring that Goes Into the Fuel Tanks,'' in
Boeing 737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs)
and Certification Maintenance Requirements (CMRs), D6-38278-CMR, dated
March 2019. Paragraph (h) of this proposed AD would allow certain
changes to be made to the wire type and sleeving requirements specified
in AWL No. 28-AWL-05 as an option.
Costs of Compliance
We estimate that this proposed AD affects 381 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
We have determined that revising the existing maintenance or
inspection program takes an average of 90 work-hours per operator,
although we recognize that this number may vary from operator to
operator. In the past, we have estimated that this action takes 1 work-
hour per airplane. Since operators incorporate maintenance or
inspection program changes for their affected fleet(s), we have
determined that a per-operator estimate is more accurate than a per-
airplane estimate. Therefore, we estimate the 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.
We are 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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We 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) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities
[[Page 26780]]
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-2019-0326; Product Identifier
2018-NM-166-AD.
(a) Comments Due Date
We must receive comments by July 25, 2019.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) through
(b)(6) of this AD.
(1) AD 2008-10-09 R1, Amendment 39-16148 (74 FR 69264, December
31, 2009) (``AD 2008-10-09 R1'').
(2) AD 2011-12-09, Amendment 39-16716 (76 FR 33988, June 10,
2011) (``AD 2011-12-09'').
(3) AD 2013-13-15, Amendment 39-17503 (78 FR 42415, July 16,
2013) (``AD 2013-13-15'').
(4) AD 2013-25-05, Amendment 39-17701 (78 FR 78701, December 27,
2013) (``AD 2013-25-05'').
(5) AD 2016-18-16, Amendment 39-18647 (81 FR 65864, September
26, 2016) (``AD 2016-18-16'').
(6) AD 2017-17-09, Amendment 39-18999 (82 FR 40477, August 25,
2017) (``AD 2017-17-09'').
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel; 47,
Nitrogen Generation System.
(e) Unsafe Condition
This AD was prompted by a determination that new or revised
airworthiness limitations (AWLs) are necessary. We are issuing this
AD to address 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.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Maintenance or Inspection Program Revision
(1) For The Boeing Company Model 737-100, -200, and -200C series
airplanes: 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 C,
including Subsections C.1, C.2, and C.3 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR, dated March 2019,
except as provided in paragraph (h) of this AD. The initial
compliance time for the airworthiness limitation instructions (ALI)
tasks are within the applicable compliance times specified in
paragraphs (g)(1)(i) through (g)(1)(x) of this AD.
(i) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel
Tank'': Within 120 months after the most recent inspection was
performed as specified in AWL No. 28-AWL-01, or within 12 months
after the effective date of this AD if no initial inspection has
been performed.
(ii) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'':
Within 120 months after accomplishment of the actions specified in
Boeing Service Bulletin 737-28A1178, or within 120 months after the
most recent inspection was performed as specified in AWL No. 28-AWL-
03, whichever is later.
(iii) For AWL No. 28-AWL-21, ``Center Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1228, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-21, whichever is later.
(iv) For AWL No. 28-AWL-22, ``Auxiliary Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1228, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-22, whichever is later.
(v) For AWL No. 28-AWL-23, ``Over-Current and Arcing Protection
Electrical Design Features Operation--Boost Pump Ground Fault
Interrupter (GFI)'': Within 12 months after accomplishment of the
actions specified in Boeing Service Bulletin 737-28A1212, or within
12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-23, whichever is later.
(vi) For AWL No. 28-AWL-24, ``Center Tank Fuel Boost Pump Power
Failed On Protection System'': Within 12 months after accomplishment
of the actions specified in Boeing Service Bulletin 737-28A1227, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-24, whichever is later.
(vii) For AWL No. 28-AWL-25, ``Auxiliary Fuel Tank Boost Pump
Power Failed On Protection System'': Within 12 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1227, or within 12 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-25, whichever is later.
(viii) For AWL No. 28-AWL-29, ``AC Fuel Boost Pump
Installation'': Within 72 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-29, or within 12 months
after the effective date of this AD if no inspection has been
performed in the last 72 months.
(ix) For AWL No. 47-AWL-04, ``Nitrogen Generation System (NGS)--
Thermal Switch'': Within 22,500 flight hours after accomplishment of
the actions specified in Boeing Service Bulletin 737-47-1005; within
22,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1008; or within 22,500 flight hours
after the most recent inspection was performed as specified in AWL
No. 47-AWL-04; whichever is latest.
(x) For AWL No. 47-AWL-05, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within
14,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1005; within 14,500 flight hours
after accomplishment of the actions specified in Boeing Service
Bulletin 737-47-1008; or within 14,500 flight hours after the most
recent inspection was performed as specified in AWL No. 47-AWL-05;
whichever is latest.
(2) For The Boeing Company Model 737-300, -400, and -500 series
airplanes: 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 C,
including Subsections C.1, C.2, and C.3 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR, dated March 2019;
except as provided in paragraph (h) of this AD. The initial
compliance time for the ALI tasks are within the applicable
compliance times specified in paragraphs (g)(2)(i) through
(g)(2)(xi) of this AD.
(i) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel
Tank'': Within 120 months after the most recent inspection was
performed as specified in AWL No. 28-AWL-01, or within 12 months
after the effective date of this AD if no initial inspection has
been performed.
(ii) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'':
Within 120 months after accomplishment of the actions specified in
Boeing Service Bulletin 737-28A1175; within 120 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1183; within 120 months after accomplishment of the actions
specified in Boeing Service Bulletin 737-28A1186; or within 120
months after the most recent inspection was performed as specified
in AWL No. 28-AWL-03; whichever is latest.
(iii) For AWL No. 28-AWL-20, ``Center Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in
[[Page 26781]]
Boeing Service Bulletin 737-28A1216, or within 12 months after the
most recent inspection was performed as specified in AWL No. 28-AWL-
20, whichever is later.
(iv) For AWL No. 28-AWL-21, ``Auxiliary Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1216, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-21, whichever is later.
(v) For AWL No. 28-AWL-22, ``Over-Current and Arcing Protection
Electrical Design Features Operation--Boost Pump Ground Fault
Interrupter (GFI)'': Within 12 months after accomplishment of the
actions specified in Boeing Service Bulletin 737-28A1212, or within
12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-22, whichever is later.
(vi) For AWL No. 28-AWL-23, ``Center Tank Fuel Boost Pump Power
Failed On Protection System'': Within 12 months after accomplishment
of the actions specified in Boeing Service Bulletin 737-28A1227, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-23, whichever is later.
(vii) For AWL No. 28-AWL-24, ``Auxiliary Fuel Tank Boost Pump
Power Failed On Protection System'': Within 12 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1227, or within 12 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-24, whichever is later.
(viii) For AWL No. 28-AWL-27, ``AC Fuel Boost Pump
Installation'': Within 72 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-27, or within 12 months
after the effective date of this AD if no inspection has been
performed in the last 72 months.
(ix) For AWL No. 28-AWL-31, ``Cushion Clamps and Teflon Sleeving
Installed on Out-of-Tank Wire Bundles Installed on Brackets that are
Mounted Directly on the Fuel Tanks'': Within 144 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1228.
(x) For AWL No. 47-AWL-04, ``Nitrogen Generation System (NGS)--
Thermal Switch'': Within 22,500 flight hours after accomplishment of
the actions specified in Boeing Service Bulletin 737-47-1005; within
22,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1008; or within 22,500 flight hours
after the most recent inspection was performed as specified in AWL
No. 47-AWL-04; whichever is latest.
(xi) For AWL No. 47-AWL-05, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within
14,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1005; within 14,500 flight hours
after accomplishment of the actions specified in Boeing Service
Bulletin 737-47-1008; or within 14,500 flight hours after the most
recent inspection was performed as specified in AWL No. 47-AWL-05;
whichever is latest.
(h) Additional Acceptable Wire Types and Sleeving
As an option, when accomplishing the actions required by
paragraph (g) of this AD, the changes specified in paragraphs (h)(1)
and (h)(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)
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 Actions for Certain AD Requirements
Accomplishment of the revision required by paragraph (g) of this
AD terminates the requirements specified in paragraphs (j)(1)
through (j)(6) of this AD for that airplane:
(1) All requirements of AD 2008-10-09 R1.
(2) The revision required by paragraph (l) of AD 2011-12-09.
(3) The revision required by paragraph (h) of AD 2013-13-15.
(4) The revision required by paragraph (j) of AD 2013-25-05.
(5) The revisions required by paragraphs (l) and (n) of AD 2016-
18-16.
(6) The revision required by paragraph (h) of AD 2017-17-09.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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)(2) 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 Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles 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 Jeffrey Rothman,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3558; email: [email protected].
(2) For information about AMOCs, contact Serj Harutunian,
Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5254; fax: 562-627-5210; email: [email protected].
(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; phone: 562-797-1717; internet: https://www.myboeingfleet.com.
You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
Issued in Des Moines, Washington, on May 20, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-11925 Filed 6-7-19; 8:45 am]
BILLING CODE 4910-13-P
