Airworthiness Directives; The Boeing Company Airplanes, 45743-45747 [2017-20560]
Download as PDF
<![CDATA[
45743
Proposed Rules
Federal Register
Vol. 82, No. 189
Monday, October 2, 2017
Federal Aviation Administration
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.myboeing
fleet.com. You may view this service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2017–0814; Product
Identifier 2017–NM–066–AD]
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0814; or in person at the Docket
Management Facility 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
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
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
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose 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 (AWL)
related to fuel tank ignition prevention
and the nitrogen generation system.
This proposed AD would require
revision of the maintenance or
inspection program, as applicable, to
include the latest revision of the AWLs.
We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by November 16,
2017.
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
sradovich on DSK3GMQ082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:16 Sep 29, 2017
Jkt 244001
Tak
Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6499;
fax: 425–917–6590; email:
takahisa.kobayashi@faa.gov.
FOR FURTHER INFORMATION CONTACT:
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–
2017–0814; Product Identifier 2017–
NM–066–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.
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
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.
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
E:\FR\FM\02OCP1.SGM
02OCP1
sradovich on DSK3GMQ082PROD with PROPOSALS
45744
Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Proposed Rules
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 issued AD 2008–10–10 R1,
Amendment 39–16164 (75 FR 1529,
January 12, 2010) (‘‘AD 2008–10–10
R1’’), which applies to certain The
Boeing Company Model 737–600, –700,
–700C, –800, and –900 series airplanes.
AD 2008–10–10 R1 requires
incorporation of fuel system AWLs and
also requires an initial inspection to
phase in certain repetitive inspections,
and repair if necessary. The fuel system
AWLs were developed to satisfy SFAR
88 requirements and included in the
Airworthiness Limitations Section
(ALS) of the manufacturer’s Instructions
for Continued Airworthiness. Since we
issued AD 2008–10–10 R1, 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. We have determined that
the specific revisions of the ALS
mandated by AD 2008–10–10 R1, and
the revisions of the ALS that have been
delivered with airplanes as part of the
type design and airworthiness
certificate, on or after March 31, 2006
(see paragraph (c), ‘‘Applicability,’’ of
AD 2008–10–10 R1, which applied to
airplanes with an original standard
airworthiness certificate or original
export certificate of airworthiness
issued before March 31, 2006), are
inadequate to provide information
necessary to maintain critical design
features and perform inspections.
We propose to adopt this new AD to
require revising the maintenance or
inspection program, as applicable, to
incorporate the AWLs provided in
Boeing 737–600/700/700C/800/900/
900ER Special Compliance Items/
Airworthiness Limitations, dated
January 2017 (the latest revision of the
ALS). We are 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.
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 2008–10–10
R1.
• The revision required by paragraphs
(h) and (h)(1) of AD 2008–06–03,
VerDate Sep<11>2014
16:16 Sep 29, 2017
Jkt 244001
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).
Airworthiness Limitations Based on
Type Design
The FAA recently became aware of an
issue related to the applicability of ADs
that require incorporation of the
Airworthiness Limitations section (ALS)
of the Instructions for Continued
Airworthiness (ICA) into an operator’s
maintenance or inspection program.
U.S. operators must operate their
airplanes in an airworthy condition, in
accordance with 14 CFR 91.7(a).
Included in this obligation is the
requirement to perform any
maintenance or inspections specified in
the ALS, and in accordance with the
ALS as specified in 14 CFR 43.16 and
91.403(c), unless an alternative has been
approved by the FAA.
When a type certificate is issued for
a type design, the specific ALS,
including its revision level, is part of
that type design, as specified in 14 CFR
21.31(c).
The sum effect of these operational
and maintenance requirements is an
obligation to comply with the ALS
revision defined in the type design
referenced in the manufacturer’s
conformity statement. This obligation
may introduce a conflict with an AD if
the AD requires a specific ALS revision
for new airplanes that are delivered
with a later ALS revision as part of their
type design.
The FAA has approved alternative
methods of compliance (AMOCs) that
allow operators to incorporate the most
recent ALS revision into their
maintenance/inspection programs, in
lieu of the ALS revision required by the
AD. This enables the operator to comply
with both the AD and the type design.
However, compliance with AMOCs is
normally optional, and we recently
became aware that some operators
choose to retain the AD-mandated ALS
revision in their fleet-wide
maintenance/inspection programs,
including those for new airplanes
delivered with later ALS revisions, to
help standardize the maintenance of the
fleet. To ensure that operators comply
with the applicable ALS revision for
newly delivered airplanes containing a
later revision than that specified in an
AD, we plan to mandate the latest ALS
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
revision as of the effective date of an
AD, if we are to mandate a specific ALS
revision, and limit the applicability to
those airplanes delivered on or before
the effective date of that AD.
This proposed AD therefore mandates
the latest ALS revision as of the
effective date of the AD for Model 737–
600, –700, –700C, –800, –900, and
–900ER series airplanes with an original
certificate of airworthiness or original
export certificate of airworthiness that
was issued on or before the effective
date of the AD. Operators of airplanes
with an original certificate of
airworthiness or original export
certificate of airworthiness issued after
that date must comply with the
airworthiness limitations specified as
part of the approved type design.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing 737–600/700/
700C/800/900/900ER Special
Compliance Items/Airworthiness
Limitations, D626A001–9–04, dated
January 2017. This service information
describes AWLs 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
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. The
request should include a description of
changes to the required inspections that
will ensure the continued operational
safety of the airplane.
E:\FR\FM\02OCP1.SGM
02OCP1
45745
Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Proposed Rules
Differences With the Service
Information
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.
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
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
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
January 2017. 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.
Alternative Methods of Compliance
(AMOC) Previously Approved for
Compliance With AD 2008–10–10 R1
The FAA has previously issued
AMOC approvals for compliance with
paragraph (g)(3) of AD 2008–10–10 R1
to allow operators to incorporate
alternative versions of AWL No. 28–
AWL–05. AWL No. 28–AWL–05
includes the requirements for new
wiring introduced by any alterations or
changes to the type design, including
STC modifications, in proximity to
wiring that penetrates the fuel tank wall.
Certain STCs that introduced new
wiring near the fuel quantity indicating
system (FQIS) wiring utilized design
features that were different from the
critical design features for fuel tank
ignition prevention specified in the ADmandated version of AWL No. 28–
AWL–05. For those STCs, we have
approved alternative versions of AWL
No. 28–AWL–05 that specified critical
design features associated with STC
Notwithstanding any other
maintenance or operational
requirements, components that have
been identified as airworthy or installed
on the affected airplanes before
accomplishing the revision of the
airplane maintenance or inspection
program specified in this proposed AD
do not need to be reworked in
accordance with the latest revision of
the CDCCLs specified by this proposed
AD for incorporation. However, once
the airplane maintenance or inspection
program has been revised as required by
this proposed AD, future maintenance
actions on these components must be
done in accordance with the CDCCLs
specified by this proposed AD.
modifications. We have determined that
certain critical design features specified
in the AMOC-approved versions of
AWL No. 28–AWL–05 are not
acceptable to meet the intent of this
AWL. Therefore, this proposed AD does
not allow credit for AMOCs previously
approved under AD 2008–10–10 R1.
However, based on our assessment of
critical design features, we have
provided an optional action under
paragraph (h) of this proposed AD to
allow certain changes to be made to the
requirements specified in AWL No. 28–
AWL–05. Under this optional action,
certain critical design features we have
previously approved and consider to be
acceptable can be specified in AWL No.
28–AWL–05.
The requirements for new wiring
versus existing wiring are specified in
AWL No. 28–AWL–05. Based on these
requirements, any STC modifications
that are installed after the incorporation
of AWL No. 28–AWL–05 (version
required by paragraph (g) of this AD)
must comply with AWL No. 28–AWL–
05, including any mandatory rework, or
the operator must request approval of an
AMOC according to paragraph (k) of this
proposed AD. Any STC modifications
that are installed prior to the
incorporation of AWL No. 28–AWL–05
(version required by paragraph (g) of
this AD) are not required to be reworked
for compliance with the new wiring
requirements of AWL No. 28–AWL–05,
except that future repair and
replacement of existing wiring must
follow AWL No. 28–AWL–05.
Costs of Compliance
We estimate that this proposed AD
affects 1,417 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Revising the maintenance or inspection program.
1 work-hour × $85 per hour = $85 .................
sradovich on DSK3GMQ082PROD with PROPOSALS
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,
VerDate Sep<11>2014
16:16 Sep 29, 2017
Jkt 244001
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
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
Cost per
product
Parts cost
$0
$85
Cost on U.S.
operators
$120,445
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
E:\FR\FM\02OCP1.SGM
02OCP1
45746
Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Proposed Rules
issue ADs applicable to transport
category airplanes 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
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–
2017–0814; Product Identifier 2017–
NM–066–AD.
sradovich on DSK3GMQ082PROD with PROPOSALS
(a) Comments Due Date
We must receive comments by November
16, 2017.
(b) Affected ADs
This AD affects the ADs specified in
paragraphs (b)(1) through (b)(5) 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’’).
VerDate Sep<11>2014
16:16 Sep 29, 2017
Jkt 244001
(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’’).
(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 standard
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant
changes made to airworthiness limitations
(AWL) related to fuel tank ignition
prevention and the nitrogen generation
system. We are issuing this AD to prevent 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) Revision of Maintenance or Inspection
Program
Within 60 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
information 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 January
2017; except as provided by paragraph (h) of
this AD. The initial compliance times for the
airworthiness limitation instructions (ALI)
tasks are within the applicable compliance
times specified in paragraphs (g)(1) through
(g)(11) 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 standard airworthiness certificate or
the date of issuance of 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 standard
airworthiness certificate or the date of
issuance of 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.
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
(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 standard
airworthiness certificate or the date of
issuance of 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 standard airworthiness certificate or
the date of issuance of 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, 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 standard
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness, within 12 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1248, or
within 12 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–23, whichever is latest.
This AWL does not apply to airplanes that
have complied with paragraph (s) of AD
2011–18–03.
(6) For AWL No. 28–AWL–24, ‘‘Spar Valve
Motor Operated Valve (MOV) Actuator—
Lightning and Fault Current Protection
Electrical Bond’’: Within 72 months after
accomplishment of the actions specified in
Boeing Service Bulletin 737–28A1207, or
within 72 months after the most recent
inspection was performed as specified in
AWL No. 28–AWL–24, whichever is later.
(7) For AWL No. 28–AWL–29, ‘‘Full
Cushion Clamps and Teflon Sleeving (If
Installed) Installed on Out-of-Tank Wire
Bundles Installed on Brackets that are
Mounted Directly on the Fuel Tanks’’: For
airplanes having line numbers (L/N) 1
through 1754 inclusive, within 120 months
after accomplishment of the actions specified
in Boeing Service Bulletin 737–57A1279. For
airplanes having L/N 1755 and on, within
120 months after the date of issuance of the
original standard airworthiness certificate or
the date of issuance of the original export
certificate of airworthiness, or within 24
months after the effective date of this AD,
whichever is later.
(8) For AWL No. 47–AWL–04, ‘‘Nitrogen
Generation System—Thermal Switch’’:
Within 22,500 flight hours after the date of
E:\FR\FM\02OCP1.SGM
02OCP1
Federal Register / Vol. 82, No. 189 / Monday, October 2, 2017 / Proposed Rules
issuance of the original standard
airworthiness certificate or the date of
issuance of 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.
(9) 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 standard
airworthiness certificate or the date of
issuance of 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.
(10) 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 standard
airworthiness certificate or the date of
issuance of 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.
(11) 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 date
of issuance of 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.
sradovich on DSK3GMQ082PROD with PROPOSALS
(h) Exceptions to Service Information
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 can be made to AWL
No. 28–AWL–05.
(1) Where AWL No. 28–AWL–05 identifies
wire types BMS 13–48, BMS 13–58, and BMS
13–60, add the following acceptable wire
types: MIL–W–22759/16, MIL–W–22759/32,
MIL–W–22759/34, MIL–W–22759/41, MIL–
W–22759/86, MIL–W–22759/87, and MIL–
W–22759/92; and MIL–C–27500 cables
constructed from these wire types.
(2) Where AWL No. 28–AWL–05 identifies
TFE–2X Standard wall for wire sleeving, add
the following acceptable sleeving materials:
Roundit 2000NX and Varglas Type HO, HP,
or HM.
(i) No Alternative Actions, Intervals, and
Critical Design Configuration Control
Limitations (CDCCLs)
After the maintenance or inspection
program, as applicable, has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections),
intervals, and CDCCLs may be used unless
the actions, intervals, and CDCCLs are
approved as an alternative method of
VerDate Sep<11>2014
16:16 Sep 29, 2017
Jkt 244001
compliance (AMOC) in accordance with the
procedures specified in paragraph (k) of this
AD.
(j) Terminating Actions
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (j)(5) 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; and
(5) All requirements of AD 2013–15–17.
45747
Issued in Renton, Washington, on
September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–20560 Filed 9–29–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2017–0822; Airspace
Docket No. 17–AEA–10]
(k) Alternative Methods of Compliance
(AMOCs)
Proposed Revocation of Class E
Airspace; Centerville, MD
(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
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, 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.
AGENCY:
(l) Related Information
(1) For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6499; fax: 425–
917–6590; email: takahisa.kobayashi@
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
referenced service information at the FAA,
Transport Standards Branch, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
This action proposes to
remove Class E airspace extending
upward from 700 feet above the surface
at Centerville, MD. Because the
Maryland State Police Trooper 6
Heliport has moved, controlled airspace
is no longer required at this location.
Another rulemaking will be forthcoming
establishing controlled airspace at the
heliport’s new location.
DATES: Comments must be received on
or before November 16, 2017.
ADDRESSES: Send comments on this rule
to: U.S. Department of Transportation,
Docket Operations, 1200 New Jersey
Avenue SE., West Bldg. Ground Floor,
Rm. W12–140, Washington, DC 20590;
Telephone: 1–800–647–5527, or (202)
366–9826.You must identify the Docket
No. FAA–2017–0822; Airspace Docket
No. 17–AEA–10, at the beginning of
your comments. You may also submit
and review received comments through
the Internet at https://
www.regulations.gov. You may review
the public docket containing the
proposal, any comments received, and
any final disposition in person in the
Dockets Office between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except federal holidays.
FAA Order 7400.11B, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
SUMMARY:
E:\FR\FM\02OCP1.SGM
02OCP1
]]>Agencies
[Federal Register Volume 82, Number 189 (Monday, October 2, 2017)]
[Proposed Rules]
[Pages 45743-45747]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-20560]
========================================================================
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. 82, No. 189 / Monday, October 2, 2017 /
Proposed Rules
[[Page 45743]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0814; Product Identifier 2017-NM-066-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
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 (AWL) related to fuel
tank ignition prevention and the nitrogen generation system. This
proposed AD would require revision of the maintenance or inspection
program, as applicable, to include the latest revision of the AWLs. We
are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by November 16,
2017.
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, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For information on the availability
of this material at the FAA, call 425-227-1221.
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-2017-
0814; or in person at the Docket Management Facility 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 the Docket Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW.,
Renton, WA 98057-3356; phone: 425-917-6499; fax: 425-917-6590; email:
takahisa.kobayashi@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 section. Include ``Docket No. FAA-2017-0814;
Product Identifier 2017-NM-066-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.
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
[[Page 45744]]
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 issued AD 2008-10-10 R1, Amendment 39-16164 (75 FR 1529, January
12, 2010) (``AD 2008-10-10 R1''), which applies to certain The Boeing
Company Model 737-600, -700, -700C, -800, and -900 series airplanes. AD
2008-10-10 R1 requires incorporation of fuel system AWLs and also
requires an initial inspection to phase in certain repetitive
inspections, and repair if necessary. The fuel system AWLs were
developed to satisfy SFAR 88 requirements and included in the
Airworthiness Limitations Section (ALS) of the manufacturer's
Instructions for Continued Airworthiness. Since we issued AD 2008-10-10
R1, 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. We have determined that the specific revisions
of the ALS mandated by AD 2008-10-10 R1, and the revisions of the ALS
that have been delivered with airplanes as part of the type design and
airworthiness certificate, on or after March 31, 2006 (see paragraph
(c), ``Applicability,'' of AD 2008-10-10 R1, which applied to airplanes
with an original standard airworthiness certificate or original export
certificate of airworthiness issued before March 31, 2006), are
inadequate to provide information necessary to maintain critical design
features and perform inspections.
We propose to adopt this new AD to require revising the maintenance
or inspection program, as applicable, to incorporate the AWLs provided
in Boeing 737-600/700/700C/800/900/900ER Special Compliance Items/
Airworthiness Limitations, dated January 2017 (the latest revision of
the ALS). We are 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.
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 2008-10-10 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).
Airworthiness Limitations Based on Type Design
The FAA recently became aware of an issue related to the
applicability of ADs that require incorporation of the Airworthiness
Limitations section (ALS) of the Instructions for Continued
Airworthiness (ICA) into an operator's maintenance or inspection
program.
U.S. operators must operate their airplanes in an airworthy
condition, in accordance with 14 CFR 91.7(a). Included in this
obligation is the requirement to perform any maintenance or inspections
specified in the ALS, and in accordance with the ALS as specified in 14
CFR 43.16 and 91.403(c), unless an alternative has been approved by the
FAA.
When a type certificate is issued for a type design, the specific
ALS, including its revision level, is part of that type design, as
specified in 14 CFR 21.31(c).
The sum effect of these operational and maintenance requirements is
an obligation to comply with the ALS revision defined in the type
design referenced in the manufacturer's conformity statement. This
obligation may introduce a conflict with an AD if the AD requires a
specific ALS revision for new airplanes that are delivered with a later
ALS revision as part of their type design.
The FAA has approved alternative methods of compliance (AMOCs) that
allow operators to incorporate the most recent ALS revision into their
maintenance/inspection programs, in lieu of the ALS revision required
by the AD. This enables the operator to comply with both the AD and the
type design.
However, compliance with AMOCs is normally optional, and we
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection
programs, including those for new airplanes delivered with later ALS
revisions, to help standardize the maintenance of the fleet. To ensure
that operators comply with the applicable ALS revision for newly
delivered airplanes containing a later revision than that specified in
an AD, we plan to mandate the latest ALS revision as of the effective
date of an AD, if we are to mandate a specific ALS revision, and limit
the applicability to those airplanes delivered on or before the
effective date of that AD.
This proposed AD therefore mandates the latest ALS revision as of
the effective date of the AD for Model 737-600, -700, -700C, -800, -
900, and -900ER series airplanes with an original certificate of
airworthiness or original export certificate of airworthiness that was
issued on or before the effective date of the AD. Operators of
airplanes with an original certificate of airworthiness or original
export certificate of airworthiness issued after that date must comply
with the airworthiness limitations specified as part of the approved
type design.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing 737-600/700/700C/800/900/900ER Special
Compliance Items/Airworthiness Limitations, D626A001-9-04, dated
January 2017. This service information describes AWLs 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 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. The request should include a
description of changes to the required inspections that will ensure the
continued operational safety of the airplane.
[[Page 45745]]
Notwithstanding any other maintenance or operational requirements,
components that have been identified as airworthy or installed on the
affected airplanes before accomplishing the revision of the airplane
maintenance or inspection program specified in this proposed AD do not
need to be reworked in accordance with the latest revision of the
CDCCLs specified by this proposed AD for incorporation. However, once
the airplane maintenance or inspection program has been revised as
required by this proposed AD, future maintenance actions on these
components must be done in accordance with the CDCCLs specified by this
proposed AD.
Differences With 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 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 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 January 2017. 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.
Alternative Methods of Compliance (AMOC) Previously Approved for
Compliance With AD 2008-10-10 R1
The FAA has previously issued AMOC approvals for compliance with
paragraph (g)(3) of AD 2008-10-10 R1 to allow operators to incorporate
alternative versions of AWL No. 28-AWL-05. AWL No. 28-AWL-05 includes
the requirements for new wiring introduced by any alterations or
changes to the type design, including STC modifications, in proximity
to wiring that penetrates the fuel tank wall. Certain STCs that
introduced new wiring near the fuel quantity indicating system (FQIS)
wiring utilized design features that were different from the critical
design features for fuel tank ignition prevention specified in the AD-
mandated version of AWL No. 28-AWL-05. For those STCs, we have approved
alternative versions of AWL No. 28-AWL-05 that specified critical
design features associated with STC modifications. We have determined
that certain critical design features specified in the AMOC-approved
versions of AWL No. 28-AWL-05 are not acceptable to meet the intent of
this AWL. Therefore, this proposed AD does not allow credit for AMOCs
previously approved under AD 2008-10-10 R1. However, based on our
assessment of critical design features, we have provided an optional
action under paragraph (h) of this proposed AD to allow certain changes
to be made to the requirements specified in AWL No. 28-AWL-05. Under
this optional action, certain critical design features we have
previously approved and consider to be acceptable can be specified in
AWL No. 28-AWL-05.
The requirements for new wiring versus existing wiring are
specified in AWL No. 28-AWL-05. Based on these requirements, any STC
modifications that are installed after the incorporation of AWL No. 28-
AWL-05 (version required by paragraph (g) of this AD) must comply with
AWL No. 28-AWL-05, including any mandatory rework, or the operator must
request approval of an AMOC according to paragraph (k) of this proposed
AD. Any STC modifications that are installed prior to the incorporation
of AWL No. 28-AWL-05 (version required by paragraph (g) of this AD) are
not required to be reworked for compliance with the new wiring
requirements of AWL No. 28-AWL-05, except that future repair and
replacement of existing wiring must follow AWL No. 28-AWL-05.
Costs of Compliance
We estimate that this proposed AD affects 1,417 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revising the maintenance or inspection 1 work-hour x $85 per $0 $85 $120,445
program. hour = $85.
----------------------------------------------------------------------------------------------------------------
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
[[Page 45746]]
issue ADs applicable to transport category airplanes 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 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-2017-0814; Product Identifier
2017-NM-066-AD.
(a) Comments Due Date
We must receive comments by November 16, 2017.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) through
(b)(5) 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'').
(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 standard airworthiness certificate or
original export certificate of airworthiness issued on or before the
effective date of this AD.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant changes made to
airworthiness limitations (AWL) related to fuel tank ignition
prevention and the nitrogen generation system. We are issuing this
AD to prevent 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) Revision of Maintenance or Inspection Program
Within 60 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
information 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 January 2017; except
as provided by paragraph (h) of this AD. The initial compliance
times for the airworthiness limitation instructions (ALI) tasks are
within the applicable compliance times specified in paragraphs
(g)(1) through (g)(11) 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
standard airworthiness certificate or the date of issuance of 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
standard airworthiness certificate or the date of issuance of 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 standard airworthiness certificate or the
date of issuance of 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 standard airworthiness certificate or the date of
issuance of 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, 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 standard airworthiness certificate or the
date of issuance of the original export certificate of
airworthiness, within 12 months after accomplishment of the actions
specified in Boeing Service Bulletin 737-28A1248, or within 12
months after the most recent inspection was performed as specified
in AWL No. 28-AWL-23, whichever is latest. This AWL does not apply
to airplanes that have complied with paragraph (s) of AD 2011-18-03.
(6) For AWL No. 28-AWL-24, ``Spar Valve Motor Operated Valve
(MOV) Actuator--Lightning and Fault Current Protection Electrical
Bond'': Within 72 months after accomplishment of the actions
specified in Boeing Service Bulletin 737-28A1207, or within 72
months after the most recent inspection was performed as specified
in AWL No. 28-AWL-24, whichever is later.
(7) For AWL No. 28-AWL-29, ``Full Cushion Clamps and Teflon
Sleeving (If Installed) Installed on Out-of-Tank Wire Bundles
Installed on Brackets that are Mounted Directly on the Fuel Tanks'':
For airplanes having line numbers (L/N) 1 through 1754 inclusive,
within 120 months after accomplishment of the actions specified in
Boeing Service Bulletin 737-57A1279. For airplanes having L/N 1755
and on, within 120 months after the date of issuance of the original
standard airworthiness certificate or the date of issuance of the
original export certificate of airworthiness, or within 24 months
after the effective date of this AD, whichever is later.
(8) For AWL No. 47-AWL-04, ``Nitrogen Generation System--Thermal
Switch'': Within 22,500 flight hours after the date of
[[Page 45747]]
issuance of the original standard airworthiness certificate or the
date of issuance of 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.
(9) 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 standard airworthiness certificate or
the date of issuance of 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.
(10) 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
standard airworthiness certificate or the date of issuance of 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.
(11) 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 date of issuance of 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) Exceptions to Service Information
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 can be made to AWL No. 28-AWL-05.
(1) Where AWL No. 28-AWL-05 identifies wire types BMS 13-48, BMS
13-58, and BMS 13-60, add the following acceptable wire types: MIL-
W-22759/16, MIL-W-22759/32, MIL-W-22759/34, MIL-W-22759/41, MIL-W-
22759/86, MIL-W-22759/87, and MIL-W-22759/92; and MIL-C-27500 cables
constructed from these wire types.
(2) Where AWL No. 28-AWL-05 identifies TFE-2X Standard wall for
wire sleeving, add the following acceptable sleeving materials:
Roundit 2000NX and Varglas Type HO, HP, or HM.
(i) No Alternative Actions, Intervals, and Critical Design
Configuration Control Limitations (CDCCLs)
After the maintenance or inspection program, as applicable, has
been revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections), intervals, and 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
Accomplishment of the revision required by paragraph (g) of this
AD terminates the requirements specified in paragraphs (j)(1)
through (j)(5) 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; and
(5) All requirements of AD 2013-15-17.
(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: 9-ANM-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 Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO Branch, 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 Tak Kobayashi,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6499;
fax: 425-917-6590; email: takahisa.kobayashi@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 referenced service
information at the FAA, Transport Standards Branch, 1601 Lind Avenue
SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on September 14, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-20560 Filed 9-29-17; 8:45 am]
BILLING CODE 4910-13-P
