Airworthiness Directives; The Boeing Company Airplanes, 27718-27721 [2018-12656]
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27718
Proposed Rules
Federal Register
Vol. 83, No. 115
Thursday, June 14, 2018
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0510; Product
Identifier 2017–NM–115–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–04–
16, which applies to all The Boeing
Company Model DC–10–10, DC–10–
10F, DC–10–15, DC–10–30, DC–10–30F
(KC–10A and KDC–10), DC–10–40, DC–
10–40F, MD–10–10F, MD–10–30F, MD–
11, and MD–11F airplanes. AD 2016–
04–16 requires adding design features to
detect electrical faults and to detect a
pump running in an empty fuel tank.
Since we issued AD 2016–04–16, we
have received new service information
that would eliminate the need for
certain provisions of AD 2016–04–16.
This proposed AD would provide
optional terminating action for certain
requirements. We are proposing this AD
to address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by July 30, 2018.
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
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SUMMARY:
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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, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0510.
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–2018–
0510; 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 in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION 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.
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–
2018–0510; Product Identifier 2017–
NM–115–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://
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www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued AD 2016–04–16,
Amendment 39–18410 (81 FR 12806,
March 11, 2016) (‘‘AD 2016–04–16’’), for
all The Boeing Company Model DC–10–
10, DC–10–10F, DC–10–15, DC–10–30,
DC–10–30F (KC–10A and KDC–10), DC–
10–40, DC–10–40F, MD–10–10F, MD–
10–30F, MD–11, and MD–11F airplanes.
AD 2016–04–16 requires adding design
features to detect electrical faults and to
detect a pump running in an empty fuel
tank. AD 2016–04–16 resulted from a
determination that it is necessary to
clarify the requirements for the design
features and to remove a terminating
action for certain inspections. We issued
AD 2016–04–16 to reduce the potential
of ignition sources inside fuel tanks,
which, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane.
Actions Since AD 2016–04–16 Was
Issued
Since we issued AD 2016–04–16, we
have received new service information
that would eliminate the need for
certain provisions of AD 2016–04–16.
Related Service Information Under 1
CFR Part 51
We reviewed the following Boeing
service information.
• Boeing Alert Service Bulletin
DC10–28A253, dated June 5, 2014; and
Boeing Alert Service Bulletin MD11–
28A133, dated June 5, 2014. This
service information describes
procedures for replacing the fuel pump
control relays with fault current
detectors and changing the fuel tank
boost/transfer pump wire termination.
These documents are distinct since they
apply to different airplane models.
• Boeing Service Bulletin DC10–28–
256, dated June 24, 2014; and Boeing
Service Bulletin MD11–28–137, dated
June 24, 2014. This service information
describes procedures for changing the
fuel pump control and indication
system wiring. These documents are
distinct since they apply to different
airplane models.
• Boeing Trijet Special Compliance
Item Report MDC–02K1003, Revision M,
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Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules
including Appendices A through D,
dated July 25, 2014, which includes
Critical Design Configuration Control
Limitations (CDCCLs), Airworthiness
Limitation Instructions (ALIs), and
short-term extensions in Appendices B,
C, and D, respectively. The service
information describes fuel ALIs that
address ignition sources.
• Boeing Service Bulletin DC10–28–
264, dated May 15, 2015, or Boeing
Service Bulletin MD11–28–146, dated
May 15, 2015. This service information
describes procedures for replacement of
the fuel pump housing electrical
connector, associated wires, fuel tank
feed-through components, and installing
sealed terminal lugs on the fuel pump
wiring, or replacement of the fuel pump
housing, associated wires, fuel tank
feed-through components, and installing
sealed terminal lugs on the fuel pump.
These documents are distinct since they
apply to different airplane models.
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 these same
type designs.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2016–04–16.
Specifically, this proposed AD would
retain the repetitive inspections for
proper operation of the fuel pump, and
applicable corrective actions.
This proposed AD would also
eliminate the need for the provisions in
paragraph (j) of this proposed AD by
providing optional terminating action
for the requirements of paragraph (a) of
AD 2002–13–10, Amendment 39–12798
(67 FR 45053, July 8, 2002); paragraph
(a) of AD 2003–07–14, Amendment 39–
13110 (68 FR 17544, April 10, 2003);
and paragraph (j) of AD 2011–11–05,
Amendment 39–16704 (76 FR 31462,
June 1, 2011).
This proposed AD specifies to revise
certain operator maintenance
documents to include new actions (e.g.,
27719
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 (l) of this proposed AD. The
request should include a description of
changes to the required actions and
CDCCLs that will ensure the continued
operational safety of the airplane. For
information on the procedures and
compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0510.
Costs of Compliance
We estimate that this proposed AD
affects 341 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Cost per
product
Parts cost
Cost on U.S.
operators
Action
Labor cost
Installing design features using a method approved by the FAA (retained actions from
AD 2016–04–16).
Installing design features using service information (retained actions from AD 2016–
04–16).
152 work-hours × $85 per hour = $12,920 ....
$137,500
$150,420
$51,293,220
98 work-hours × $85 per hour = $8,330 ........
109,000
117,330
40,009,530
Inspection for proper operation (new proposed action).
Up to 130 work-hours × $85 per hour =
$11,050 per inspection cycle.
0
Up to $11,050 per inspection
cycle.
ESTIMATED COSTS FOR OPTIONAL TERMINATING ACTIONS
Action
Labor cost
Option 1: Replace connectors for Model DC–10 and MD–10 (122 airplanes).
Option 1: Replace connectors for Model MD–11 (124 airplanes) .........
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Option 2: Replace fuel pump housings for Model DC–10 and MD–10
(122 airplanes).
Option 2: Replace fuel pump housings for Model MD–11 (124 airplanes).
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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
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68 work-hours × $85
$5,780.
59 work-hours × $85
$5,015.
Up to 81 work-hours
hour = $6,885.
Up to 77 work-hours
hour = $6,545.
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
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Parts cost
Cost per product
per hour =
$54,842 ............
$60,622.
per hour =
$67,031 ............
$72,046.
× $85 per
Up to $54,842 ..
Up to $61,727.
× $85 per
Up to $67,031 ..
Up to $73,576.
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.
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Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules
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 have 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 that the 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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2016–04–16, Amendment 39–18410 (81
FR 12806, March 11, 2016), and adding
the following new AD:
■
The Boeing Company: Docket No. FAA–
2018–0510; Product Identifier 2017–
NM–115–AD.
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(a) Comments Due Date
The FAA must receive comments on this
AD action by July 30, 2018.
(b) Affected ADs
(1) This AD replaces AD 2016–04–16,
Amendment 39–18410 (81 FR 12806, March
11, 2016) (‘‘AD 2016–04–16’’).
(2) This AD affects AD 2002–13–10,
Amendment 39–12798 (67 FR 45053, July 8,
2002) (‘‘AD 2002–13–10’’).
(3) This AD affects AD 2003–07–14,
Amendment 39–13110 (68 FR 17544, April
10, 2003) (‘‘AD 2003–07–14’’).
(4) This AD affects AD 2008–06–21 R1,
Amendment 39–16100 (74 FR 61504,
November 25, 2009) (‘‘AD 2008–06–21 R1’’).
(5) This AD affects AD 2011–11–05,
Amendment 39–16704 (76 FR 31462, June 1,
2011) (‘‘AD 2011–11–05’’).
(c) Applicability
This AD applies to all The Boeing
Company airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any
category.
(1) Model DC–10–10, DC–10–10F, DC–10–
15, DC–10–30, DC–10–30F (KC–10A and
KDC–10), DC–10–40, and DC–10–40F
airplanes.
(2) Model MD–10–10F, MD–10–30F, MD–
11, and MD–11F airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by a fuel system
review conducted by the manufacturer. We
are issuing this AD to reduce the potential of
ignition sources inside fuel tanks, which, in
combination with flammable fuel vapors,
could result in fuel tank explosions and
consequent loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Restatement of Paragraph (g) of AD 2016–
04–16, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2016–04–16, with no
changes. Except as provided by paragraph (h)
of this AD: As of 48 months after April 15,
2016 (the effective date of AD 2016–04–16),
no person may operate any airplane affected
by this AD unless an amended type
certificate or supplemental type certificate
that incorporates the design features and
requirements described in paragraphs (g)(1)
through (g)(4) of this AD has been approved
by the Manager, Los Angeles ACO Branch,
FAA, and those design features are installed
on the airplane to meet the criteria specified
in section 25.981(a) and (d) of the Federal
Aviation Regulations (14 CFR 25.981(a) and
(d), at Amendment 25–125 (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgFAR.nsf/0/339DAEE3E0A6379D86257
4CF00641951?OpenDocument)). For
airplanes on which Boeing-installed auxiliary
fuel tanks are removed, the actions specified
in this AD for the auxiliary fuel tanks are not
required.
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(1) For all airplanes: Each electrically
powered alternating current (AC) fuel pump
installed in any fuel tank that normally
empties during flight and each pump that is
partially covered by a lowering fuel level—
such as main tanks, center wing tanks,
auxiliary fuel tanks installed by the airplane
manufacturer, and tail tanks—must have a
protective device installed to detect electrical
faults that can cause arcing and burn through
of the fuel pump housing and pump
electrical connector. The same device must
shut off the pump by automatically removing
electrical power from the pump when such
faults are detected. When a fuel pump is shut
off resulting from detection of an electrical
fault, the device must stay latched off, until
the fault is cleared through maintenance
action and the pump is verified safe for
operation.
(2) For airplanes with a 2-person
flightcrew: Additional design features, if not
originally installed by the airplane
manufacturer, must be installed to meet 3
criteria: To detect a running fuel pump in a
tank that is normally emptied during flight,
to provide an indication to the flightcrew that
the tank is empty, and to automatically shut
off that fuel pump. The prospective pump
indication and shutoff system must
automatically shut off each pump in case the
flightcrew does not shut off a pump running
dry in an empty tank within 60 seconds after
each fuel tank is emptied. An airplane flight
manual supplement (AFMS) that includes
flightcrew manual pump shutoff procedures
in the Limitations section of the AFMS must
be submitted to the Los Angeles ACO Branch,
FAA, for approval.
(3) For airplanes with a 3-person
flightcrew: Additional design features, if not
originally installed by the airplane
manufacturer, must be installed to detect
when a fuel pump in a tank that is normally
emptied during flight is running in an empty
fuel tank, and to provide an indication to the
flightcrew that the tank is empty. The flight
engineer must manually shut off each pump
running dry in an empty tank within 60
seconds after the tank is emptied. The AFMS
Limitations section must be revised to
specify that this pump shutoff must be done
by the flight engineer.
(4) For all airplanes with tanks that
normally empty during flight: Separate
means must be provided to detect and shut
off a pump that was previously commanded
to be shut off automatically or manually but
remained running in an empty tank during
flight.
(h) Restatement of Paragraph (h) of AD
2016–04–16, With No Changes
This paragraph restates the provisions of
paragraph (h) of AD 2016–04–16, with no
changes. In lieu of doing the requirements of
paragraph (g) of this AD, do the applicable
actions specified in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD.
(1) For MD–11 and MD–11F airplanes: Do
the actions specified in paragraphs (h)(1)(i)
and (h)(1)(ii) of this AD.
(i) As of 48 months after April 15, 2016
(the effective date of AD 2016–04–16),
change the fuel pump control and indication
system wiring, in accordance with the
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Accomplishment Instructions of Boeing
Service Bulletin MD11–28–137, dated June
24, 2014.
(ii) Prior to or concurrently with
accomplishing the actions specified in
paragraph (h)(1)(i) of this AD: Replace the
fuel pump control relays with fault current
detectors, and change the fuel tank boost/
transfer pump wire termination, in
accordance with Accomplishment
Instructions of Boeing Alert Service Bulletin
MD11–28A133, dated June 5, 2014.
(2) For Model DC–10–10, DC–10–10F, DC–
10–15, DC–10–30, DC–10–30F (KC–10A and
KDC–10), DC–10–40, DC–10–40F, MD–10–
10F, and MD–10–30F airplanes: Do the
actions specified in paragraphs (h)(2)(i) and
(h)(2)(ii) of this AD.
(i) As of 48 months after April 15, 2016
(the effective date of AD 2016–04–16),
change the fuel pump control and indication
system wiring, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin DC10–28–256, dated June
24, 2014.
(ii) Prior to or concurrently with
accomplishing the actions specified in
paragraph (h)(2)(i) of this AD: Replace the
fuel pump control relays with fault current
detectors, and change the fuel tank boost/
transfer pump wire termination, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
DC10–28A253, dated June 5, 2014.
(3) For all airplanes: Within 30 days after
accomplishing the actions required by
paragraph (h)(1) or (h)(2) of this AD, or
within 30 days after April 15, 2016 (the
effective date of AD 2016–04–16), whichever
occurs later, revise the maintenance or
inspection program, as applicable, to
incorporate the Critical Design Configuration
Control Limitations (CDCCLs), Airworthiness
Limitation Instructions (ALIs), and shortterm extensions specified in Appendices B,
C, and D of Boeing Trijet Special Compliance
Item (SCI) Report MDC–02K1003, Revision
M, dated July 25, 2014. The initial
compliance time for accomplishing the
actions specified in the ALIs is at the later
of the times specified in paragraphs (h)(3)(i)
and (h)(3)(ii) of this AD. Revising the
maintenance or inspection program required
by this paragraph terminates the
requirements in paragraphs (g) and (h) of AD
2008–06–21 R1.
(i) At the applicable time specified in
Appendix C of Boeing Trijet SCI Report
MDC–02K1003, Revision M, dated July 25,
2014, except as provided by Appendix D of
Boeing Trijet SCI Report MDC–02K1003,
Revision M, dated July 25, 2014.
(ii) Within 30 days after accomplishing the
actions required by paragraph (h)(1) or (h)(2)
of this AD, as applicable; or within 30 days
after April 15, 2016 (the effective date of AD
2016–04–16); whichever occurs later.
(i) Restatement of Paragraph (i) of AD 2016–
04–16, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2016–04–16, with no
changes. If the option in paragraph (h)(3) of
this AD is accomplished: After the
maintenance or inspection program has been
revised as provided by paragraph (h)(3) of
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this AD, no alternative actions (e.g.,
inspections), intervals, or CDCCLs may be
used unless the actions, intervals, or CDCCLs
are approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (l) of this
AD.
(j) Restatement of Paragraph (j) of AD 2016–
04–16, With Additional AD Reference and
Clarification of Provisions
This paragraph restates the provisions of
paragraph (j) of AD 2016–04–16, with an
additional AD reference and clarification of
the provisions. Accomplishment of the
actions specified in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD, as applicable, extends
the 18-month interval for the repetitive
inspections and tests required by paragraph
(a) of AD 2002–13–10; the 18-month interval
for the repetitive inspections required by
paragraph (a) of AD 2003–07–14; and the 18month interval for the repetitive inspections
required by paragraph (j) of AD 2011–11–05;
to 24-month intervals for pumps affected by
those ADs, regardless if the pump is installed
in a tank that normally empties, provided the
remaining actions required by those three
ADs have been accomplished.
(k) New Provision of This AD: Optional
Terminating Action
Replacing the electrical connectors or fuel
pump housing in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin DC10–28–264, dated May
15, 2015; or Boeing Service Bulletin MD11–
28–146, dated May 15, 2015, as applicable;
terminates the repetitive inspections and
tests required by paragraph (a) of AD 2002–
13–10, paragraph (a) of AD 2003–07–14, and
paragraph (j) of AD 2011–11–05.
(l) 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 (m)(1) of
this AD. Information may be emailed to:
9-ANM-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.
(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, 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.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
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paragraphs (l)(4)(i) and (l)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(m) Related Information
(1) For more information about this AD,
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.
(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, 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 June
6, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–12656 Filed 6–13–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0511; Product
Identifier 2017–NM–145–AD]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all BAE
Systems (Operations) Limited Model
4101 airplanes. This proposed AD was
prompted by a determination that
SUMMARY:
E:\FR\FM\14JNP1.SGM
14JNP1
]]>Agencies
[Federal Register Volume 83, Number 115 (Thursday, June 14, 2018)]
[Proposed Rules]
[Pages 27718-27721]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-12656]
========================================================================
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. 83, No. 115 / Thursday, June 14, 2018 /
Proposed Rules
[[Page 27718]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0510; Product Identifier 2017-NM-115-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 supersede Airworthiness Directive (AD) 2016-04-
16, which applies to all The Boeing Company Model DC-10-10, DC-10-10F,
DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F,
MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. AD 2016-04-16
requires adding design features to detect electrical faults and to
detect a pump running in an empty fuel tank. Since we issued AD 2016-
04-16, we have received new service information that would eliminate
the need for certain provisions of AD 2016-04-16. This proposed AD
would provide optional terminating action for certain requirements. We
are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by July 30, 2018.
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, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195. It is also
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2018-0510.
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-2018-
0510; 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 in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION 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].
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-2018-0510;
Product Identifier 2017-NM-115-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 proposed AD.
Discussion
We issued AD 2016-04-16, Amendment 39-18410 (81 FR 12806, March 11,
2016) (``AD 2016-04-16''), for all The Boeing Company Model DC-10-10,
DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40,
DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. AD 2016-
04-16 requires adding design features to detect electrical faults and
to detect a pump running in an empty fuel tank. AD 2016-04-16 resulted
from a determination that it is necessary to clarify the requirements
for the design features and to remove a terminating action for certain
inspections. We issued AD 2016-04-16 to reduce the potential of
ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.
Actions Since AD 2016-04-16 Was Issued
Since we issued AD 2016-04-16, we have received new service
information that would eliminate the need for certain provisions of AD
2016-04-16.
Related Service Information Under 1 CFR Part 51
We reviewed the following Boeing service information.
Boeing Alert Service Bulletin DC10-28A253, dated June 5,
2014; and Boeing Alert Service Bulletin MD11-28A133, dated June 5,
2014. This service information describes procedures for replacing the
fuel pump control relays with fault current detectors and changing the
fuel tank boost/transfer pump wire termination. These documents are
distinct since they apply to different airplane models.
Boeing Service Bulletin DC10-28-256, dated June 24, 2014;
and Boeing Service Bulletin MD11-28-137, dated June 24, 2014. This
service information describes procedures for changing the fuel pump
control and indication system wiring. These documents are distinct
since they apply to different airplane models.
Boeing Trijet Special Compliance Item Report MDC-02K1003,
Revision M,
[[Page 27719]]
including Appendices A through D, dated July 25, 2014, which includes
Critical Design Configuration Control Limitations (CDCCLs),
Airworthiness Limitation Instructions (ALIs), and short-term extensions
in Appendices B, C, and D, respectively. The service information
describes fuel ALIs that address ignition sources.
Boeing Service Bulletin DC10-28-264, dated May 15, 2015,
or Boeing Service Bulletin MD11-28-146, dated May 15, 2015. This
service information describes procedures for replacement of the fuel
pump housing electrical connector, associated wires, fuel tank feed-
through components, and installing sealed terminal lugs on the fuel
pump wiring, or replacement of the fuel pump housing, associated wires,
fuel tank feed-through components, and installing sealed terminal lugs
on the fuel pump. These documents are distinct since they apply to
different airplane models.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2016-04-16.
Specifically, this proposed AD would retain the repetitive inspections
for proper operation of the fuel pump, and applicable corrective
actions.
This proposed AD would also eliminate the need for the provisions
in paragraph (j) of this proposed AD by providing optional terminating
action for the requirements of paragraph (a) of AD 2002-13-10,
Amendment 39-12798 (67 FR 45053, July 8, 2002); paragraph (a) of AD
2003-07-14, Amendment 39-13110 (68 FR 17544, April 10, 2003); and
paragraph (j) of AD 2011-11-05, Amendment 39-16704 (76 FR 31462, June
1, 2011).
This proposed AD specifies to revise 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 (l) of this proposed AD. The request should include a
description of changes to the required actions and CDCCLs that will
ensure the continued operational safety of the airplane. For
information on the procedures and compliance times, see this service
information at https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0510.
Costs of Compliance
We estimate that this proposed AD affects 341 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
----------------------------------------------------------------------------------------------------------------
Installing design features using a 152 work-hours x $85 per $137,500 $150,420 $51,293,220
method approved by the FAA hour = $12,920.
(retained actions from AD 2016-04-
16).
Installing design features using 98 work-hours x $85 per 109,000 117,330 40,009,530
service information (retained hour = $8,330.
actions from AD 2016-04-16).
-----------------------------------------------
Inspection for proper operation Up to 130 work-hours x $85 0 Up to $11,050 per inspection
(new proposed action). per hour = $11,050 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Terminating Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Option 1: Replace connectors for 68 work-hours x $85 $54,842................... $60,622.
Model DC-10 and MD-10 (122 per hour = $5,780.
airplanes).
Option 1: Replace connectors for 59 work-hours x $85 $67,031................... $72,046.
Model MD-11 (124 airplanes). per hour = $5,015.
Option 2: Replace fuel pump Up to 81 work-hours x Up to $54,842............. Up to $61,727.
housings for Model DC-10 and MD- $85 per hour =
10 (122 airplanes). $6,885.
Option 2: Replace fuel pump Up to 77 work-hours x Up to $67,031............. Up to $73,576.
housings for Model MD-11 (124 $85 per hour =
airplanes). $6,545.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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.
[[Page 27720]]
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 have 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 that the 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 removing Airworthiness Directive (AD)
2016-04-16, Amendment 39-18410 (81 FR 12806, March 11, 2016), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2018-0510; Product Identifier
2017-NM-115-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by July 30,
2018.
(b) Affected ADs
(1) This AD replaces AD 2016-04-16, Amendment 39-18410 (81 FR
12806, March 11, 2016) (``AD 2016-04-16'').
(2) This AD affects AD 2002-13-10, Amendment 39-12798 (67 FR
45053, July 8, 2002) (``AD 2002-13-10'').
(3) This AD affects AD 2003-07-14, Amendment 39-13110 (68 FR
17544, April 10, 2003) (``AD 2003-07-14'').
(4) This AD affects AD 2008-06-21 R1, Amendment 39-16100 (74 FR
61504, November 25, 2009) (``AD 2008-06-21 R1'').
(5) This AD affects AD 2011-11-05, Amendment 39-16704 (76 FR
31462, June 1, 2011) (``AD 2011-11-05'').
(c) Applicability
This AD applies to all The Boeing Company airplanes identified
in paragraphs (c)(1) and (c)(2) of this AD, certificated in any
category.
(1) Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F
(KC-10A and KDC-10), DC-10-40, and DC-10-40F airplanes.
(2) Model MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by a fuel system review conducted by the
manufacturer. We are issuing this AD to reduce the potential of
ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Restatement of Paragraph (g) of AD 2016-04-16, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2016-04-16, with no changes. Except as provided by paragraph (h) of
this AD: As of 48 months after April 15, 2016 (the effective date of
AD 2016-04-16), no person may operate any airplane affected by this
AD unless an amended type certificate or supplemental type
certificate that incorporates the design features and requirements
described in paragraphs (g)(1) through (g)(4) of this AD has been
approved by the Manager, Los Angeles ACO Branch, FAA, and those
design features are installed on the airplane to meet the criteria
specified in section 25.981(a) and (d) of the Federal Aviation
Regulations (14 CFR 25.981(a) and (d), at Amendment 25-125 (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgFAR.nsf/0/339DAEE3E0A6379D862574CF00641951?OpenDocument)). For airplanes on
which Boeing-installed auxiliary fuel tanks are removed, the actions
specified in this AD for the auxiliary fuel tanks are not required.
(1) For all airplanes: Each electrically powered alternating
current (AC) fuel pump installed in any fuel tank that normally
empties during flight and each pump that is partially covered by a
lowering fuel level--such as main tanks, center wing tanks,
auxiliary fuel tanks installed by the airplane manufacturer, and
tail tanks--must have a protective device installed to detect
electrical faults that can cause arcing and burn through of the fuel
pump housing and pump electrical connector. The same device must
shut off the pump by automatically removing electrical power from
the pump when such faults are detected. When a fuel pump is shut off
resulting from detection of an electrical fault, the device must
stay latched off, until the fault is cleared through maintenance
action and the pump is verified safe for operation.
(2) For airplanes with a 2-person flightcrew: Additional design
features, if not originally installed by the airplane manufacturer,
must be installed to meet 3 criteria: To detect a running fuel pump
in a tank that is normally emptied during flight, to provide an
indication to the flightcrew that the tank is empty, and to
automatically shut off that fuel pump. The prospective pump
indication and shutoff system must automatically shut off each pump
in case the flightcrew does not shut off a pump running dry in an
empty tank within 60 seconds after each fuel tank is emptied. An
airplane flight manual supplement (AFMS) that includes flightcrew
manual pump shutoff procedures in the Limitations section of the
AFMS must be submitted to the Los Angeles ACO Branch, FAA, for
approval.
(3) For airplanes with a 3-person flightcrew: Additional design
features, if not originally installed by the airplane manufacturer,
must be installed to detect when a fuel pump in a tank that is
normally emptied during flight is running in an empty fuel tank, and
to provide an indication to the flightcrew that the tank is empty.
The flight engineer must manually shut off each pump running dry in
an empty tank within 60 seconds after the tank is emptied. The AFMS
Limitations section must be revised to specify that this pump
shutoff must be done by the flight engineer.
(4) For all airplanes with tanks that normally empty during
flight: Separate means must be provided to detect and shut off a
pump that was previously commanded to be shut off automatically or
manually but remained running in an empty tank during flight.
(h) Restatement of Paragraph (h) of AD 2016-04-16, With No Changes
This paragraph restates the provisions of paragraph (h) of AD
2016-04-16, with no changes. In lieu of doing the requirements of
paragraph (g) of this AD, do the applicable actions specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
(1) For MD-11 and MD-11F airplanes: Do the actions specified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) As of 48 months after April 15, 2016 (the effective date of
AD 2016-04-16), change the fuel pump control and indication system
wiring, in accordance with the
[[Page 27721]]
Accomplishment Instructions of Boeing Service Bulletin MD11-28-137,
dated June 24, 2014.
(ii) Prior to or concurrently with accomplishing the actions
specified in paragraph (h)(1)(i) of this AD: Replace the fuel pump
control relays with fault current detectors, and change the fuel
tank boost/transfer pump wire termination, in accordance with
Accomplishment Instructions of Boeing Alert Service Bulletin MD11-
28A133, dated June 5, 2014.
(2) For Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F
(KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F
airplanes: Do the actions specified in paragraphs (h)(2)(i) and
(h)(2)(ii) of this AD.
(i) As of 48 months after April 15, 2016 (the effective date of
AD 2016-04-16), change the fuel pump control and indication system
wiring, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin DC10-28-256, dated June 24, 2014.
(ii) Prior to or concurrently with accomplishing the actions
specified in paragraph (h)(2)(i) of this AD: Replace the fuel pump
control relays with fault current detectors, and change the fuel
tank boost/transfer pump wire termination, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin DC10-
28A253, dated June 5, 2014.
(3) For all airplanes: Within 30 days after accomplishing the
actions required by paragraph (h)(1) or (h)(2) of this AD, or within
30 days after April 15, 2016 (the effective date of AD 2016-04-16),
whichever occurs later, revise the maintenance or inspection
program, as applicable, to incorporate the Critical Design
Configuration Control Limitations (CDCCLs), Airworthiness Limitation
Instructions (ALIs), and short-term extensions specified in
Appendices B, C, and D of Boeing Trijet Special Compliance Item
(SCI) Report MDC-02K1003, Revision M, dated July 25, 2014. The
initial compliance time for accomplishing the actions specified in
the ALIs is at the later of the times specified in paragraphs
(h)(3)(i) and (h)(3)(ii) of this AD. Revising the maintenance or
inspection program required by this paragraph terminates the
requirements in paragraphs (g) and (h) of AD 2008-06-21 R1.
(i) At the applicable time specified in Appendix C of Boeing
Trijet SCI Report MDC-02K1003, Revision M, dated July 25, 2014,
except as provided by Appendix D of Boeing Trijet SCI Report MDC-
02K1003, Revision M, dated July 25, 2014.
(ii) Within 30 days after accomplishing the actions required by
paragraph (h)(1) or (h)(2) of this AD, as applicable; or within 30
days after April 15, 2016 (the effective date of AD 2016-04-16);
whichever occurs later.
(i) Restatement of Paragraph (i) of AD 2016-04-16, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2016-04-16, with no changes. If the option in paragraph (h)(3) of
this AD is accomplished: After the maintenance or inspection program
has been revised as provided by paragraph (h)(3) of this AD, no
alternative actions (e.g., inspections), intervals, or CDCCLs may be
used unless the actions, intervals, or CDCCLs are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (l) of this AD.
(j) Restatement of Paragraph (j) of AD 2016-04-16, With Additional AD
Reference and Clarification of Provisions
This paragraph restates the provisions of paragraph (j) of AD
2016-04-16, with an additional AD reference and clarification of the
provisions. Accomplishment of the actions specified in paragraphs
(h)(1), (h)(2), and (h)(3) of this AD, as applicable, extends the
18-month interval for the repetitive inspections and tests required
by paragraph (a) of AD 2002-13-10; the 18-month interval for the
repetitive inspections required by paragraph (a) of AD 2003-07-14;
and the 18-month interval for the repetitive inspections required by
paragraph (j) of AD 2011-11-05; to 24-month intervals for pumps
affected by those ADs, regardless if the pump is installed in a tank
that normally empties, provided the remaining actions required by
those three ADs have been accomplished.
(k) New Provision of This AD: Optional Terminating Action
Replacing the electrical connectors or fuel pump housing in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin DC10-28-264, dated May 15, 2015; or Boeing Service Bulletin
MD11-28-146, dated May 15, 2015, as applicable; terminates the
repetitive inspections and tests required by paragraph (a) of AD
2002-13-10, paragraph (a) of AD 2003-07-14, and paragraph (j) of AD
2011-11-05.
(l) 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 (m)(1) of this AD. Information
may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles 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.
(4) For service information that contains steps that are labeled
as Required for Compliance (RC), the provisions of paragraphs
(l)(4)(i) and (l)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(m) Related Information
(1) For more information about this AD, 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].
(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, 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 June 6, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-12656 Filed 6-13-18; 8:45 am]
BILLING CODE 4910-13-P
