Airworthiness Directives; The Boeing Company Airplanes, 5576-5579 [2018-02085]
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determination in writing, within 45
days of the receipt of the determination.
The determination of the Deputy
Administrator of Insurance Services will
be final and binding on the Company.
Such determinations will not be
appealable to the Board of Contract
Appeals.
(d) Appealable final administrative
determinations of the FCIC under
paragraph (a) or (b) of this section may
be appealed to the Board of Contract
Appeals in accordance with 48 CFR part
6102 and with the provisions 7 CFR part
24.
§ 400.170
[Reserved]
§ 400.171
[Reserved]
§ 400.172
[Reserved]
§ 400.173
[Reserved]
§ 400.174
[Reserved]
§ 400.175
[Reserved]
§ 400.176
[Reserved]
§ 400.177
[Reserved]
Signed in Washington, DC, on February 1,
2018.
Heather Manzano,
Acting Manager, Federal Crop Insurance
Corporation.
[FR Doc. 2018–02489 Filed 2–7–18; 8:45 am]
BILLING CODE 3410–08–P
We must receive comments on
this proposed AD by March 26, 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, 1601 Lind
Avenue SW, Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0031.
DATES:
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0031; Product
Identifier 2017–NM–127–AD]
RIN 2120–AA6417
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 727
airplanes. This proposed AD was
prompted by significant changes made
to the airworthiness limitations (AWLs)
related to fuel tank ignition prevention.
This proposed AD would require
revising the maintenance or inspection
program, as applicable, to incorporate
the latest revision of the AWLs. We are
proposing this AD to address the unsafe
condition on these products.
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SUMMARY:
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You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0031; 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:
Christopher Baker, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 1601 Lind Avenue SW, Renton,
WA 98057–3356; phone: 425–917–6498;
fax: 425–917–6590; email:
christopher.r.baker@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–
PO 00000
Frm 00004
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2018–0031; Product Identifier 2017–
NM–127–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 20, 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
‘‘21–72’’ 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
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to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
Single failures, single failures in
combination with another latent
condition(s), and in-service failure
experience. For all four criteria, the
evaluations included consideration of
previous actions taken that may mitigate
the need for further action.
We have determined that the actions
identified in this proposed AD are
necessary to 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.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing 727–100/200
Airworthiness Limitations (AWLs) D6–
8766–AWL, dated December 2016. The
service information describes AWL
tasks that include airworthiness
limitation instructions (ALIs) and
critical design configuration control
limitations (CDCCLs) related to fuel tank
ignition prevention. 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
revision of the maintenance or
inspection program to incorporate the
ALI and CDCCL tasks described
previously.
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.
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 specified
by this proposed AD, future
maintenance actions on these
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components must be done in
accordance with the CDCCLs specified
by this proposed AD.
Related Rulemaking
Five ADs are related to this NPRM.
We have determined that certain
requirements of those ADs may be
terminated when the referenced AWLs
specified in this proposed AD have been
incorporated, as follows:
• The revision required by paragraph
(g) of AD 2008–04–10 R1, Amendment
39–16121 (74 FR 66227, December 15,
2009).
• The revision required by paragraph
(h) of AD 2009–05–03, Amendment 39–
15827 (74 FR 8851, February 27, 2009).
• The revision required by paragraph
(j) of AD 2011–12–05, Amendment 39–
16712 (76 FR 33991, June 10, 2011).
• The revision required by paragraph
(h) of AD 2013–22–03, Amendment 39–
17635 (78 FR 65193, October 31, 2013).
• The revision required by paragraphs
(n)(1) and (n)(2) of AD 2013–24–15,
Amendment 39–17692 (78 FR 72791,
December 4, 2013).
Differences Between This Proposed AD
and the Service Information
AWL No. 28–AWL–03 identifies
certain wire types. Paragraph (h)(1) of
this proposed AD specifies additional
acceptable wire types and cables.
AWL No. 28–AWL–03 identifies
certain sleeving materials. Paragraph
(h)(2) of this proposed AD specifies
additional acceptable sleeving materials.
Costs of Compliance
We estimate that this proposed AD
affects 20 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Parts
cost
Action
Labor cost
Maintenance or inspection program revision ..
1 work-hour × $85 per hour = $85 .................
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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
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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
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Cost per
product
$0
$85
Cost on U.S.
operators
$1,700
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
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Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules
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–
2018–0031; Product Identifier 2017–
NM–127–AD.
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(a) Comments Due Date
We must receive comments by March 26,
2018.
(b) Affected ADs
This AD affects the ADs specified in
paragraphs (b)(1) through (b)(5) of this AD.
(1) AD 2008–04–10 R1, Amendment 39–
16121 (74 FR 66227, December 15, 2009)
(‘‘AD 2008–04–10 R1’’).
(2) AD 2009–05–03, Amendment 39–15827
(74 FR 8851, February 27, 2009) (‘‘AD 2009–
05–03’’).
(3) AD 2011–12–05, Amendment 39–16712
(76 FR 33991, June 10, 2011) (‘‘AD 2011–12–
05’’).
(4) AD 2013–22–03, Amendment 39–17635
(78 FR 65193, October 31, 2013) (‘‘AD 2013–
22–03’’).
(5) AD 2013–24–15, Amendment 39–17692
(78 FR 72791, December 4, 2013) (‘‘AD 2013–
24–15’’).
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(c) Applicability
This AD applies to The Boeing Company
Model 727, 727C, 727–100, 727–100C, 727–
200, and 727–200F 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 the airworthiness
limitations (AWLs) related to fuel tank
ignition prevention. We are issuing this AD
to prevent the potential for ignition sources
inside fuel tanks caused by latent failures,
alterations, repairs, or maintenance actions,
which, in combination with flammable fuel
vapors, could result in fuel tank explosions
and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Maintenance or Inspection Program
Revision
Within 60 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate all
information in Section A, including
Subsections A.1 and A.2, of Boeing 727–100/
200 Airworthiness Limitations (AWLs) D6–
8766–AWL, dated December 2016. The initial
compliance times for the airworthiness
limitation instruction (ALI) items are within
the applicable compliance times specified in
paragraphs (g)(1) through (g)(6) of this AD.
(1) For AWL No. 28–AWL–01, ‘‘External
Wires Over Center Fuel Tank (Tank No. 2)’’:
at the applicable time specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) For airplanes that have been previously
inspected as specified in 28–AWL–01 as of
the effective date of this AD: Conduct the
inspection within 120 months after the most
recent inspection.
(ii) For airplanes that have not been
inspected as specified in 28–AWL–01 as of
the effective date of this AD: Conduct the
inspection within 12 months after the
effective date of this AD.
(2) For AWL No. 28–AWL–16, ‘‘OverCurrent and Arcing Protection Electrical
Design Features Operation—Boost Pump
Ground Fault Interrupter (GFI)’’: at the
applicable time specified in paragraph
(g)(2)(i) or (g)(2)(ii) of this AD.
(i) For airplanes that have been previously
inspected as specified in 28–AWL–16 as of
the effective date of this AD: Conduct the
inspection within 12 months after the most
recent inspection.
(ii) For airplanes that have not been
inspected as specified in 28–AWL–16 as of
the effective date of this AD: Conduct the
inspection within 90 days after the effective
date of this AD.
(3) For AWL No. 28–AWL–17, ‘‘Auxiliary
Tank Fuel Boost Pump Power Failed On
Protection System’’: at the applicable time
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specified in paragraph (g)(3)(i) or (g)(3)(ii) of
this AD.
(i) For airplanes that have been previously
inspected as specified in 28–AWL–17 as of
the effective date of this AD: Conduct the
inspection within 12 months after the most
recent inspection.
(ii) For airplanes that have not been
inspected as specified in 28–AWL–17 as of
the effective date of this AD: Conduct the
inspection within 90 days after the effective
date of this AD.
(4) For AWL No. 28–AWL–18, ‘‘Fuel
Quantity Indicating System (FQIS)—OutTank Wiring Lightning Shield to Ground
Termination and Joint Resistance for the
Volumetric Top-Off (VTO) Unit (If
Installed)’’: at the applicable time specified
in paragraph (g)(4)(i) or (g)(4)(ii) of this AD.
(i) For airplanes that have been previously
inspected as specified in 28–AWL–18 as of
the effective date of this AD: Conduct the
inspection within 120 months after the most
recent inspection.
(ii) For airplanes that have not been
inspected as specified in 28–AWL–18:
Conduct the inspection within 12 months
after the effective date of this AD.
(5) For AWL No. 28–AWL–22, ‘‘AC Fuel
Boost Pump Bonding Installation’’: at the
applicable time specified in paragraph
(g)(5)(i) or (g)(5)(ii) of this AD.
(i) For airplanes that have been previously
inspected as specified in 28–AWL–22 as of
the effective date of this AD: Conduct the
inspection within 72 months after the most
recent inspection.
(ii) For airplanes that have not been
inspected as specified in 28–AWL–22 as of
the effective date of this AD: Conduct the
inspection within 12 months after the
effective date of this AD.
(6) For AWL No. 28–AWL–24, ‘‘Motor
Operated Valve Bonding Jumper
Installation—Fault Current Protection’’: at
the applicable time specified in paragraph
(g)(6)(i) or (g)(6)(ii) of this AD.
(i) For airplanes that have been previously
inspected as specified in 28–AWL–24 as of
the effective date of this AD: Conduct the
inspection within 60 months after the most
recent inspection.
(ii) For airplanes that have not been
inspected as specified in 28–AWL–24 as of
the effective date of this AD: Conduct the
inspection within 12 months after the
effective date of this AD.
(h) Additional Acceptable Wire Types and
Sleeving
(1) Where AWL No. 28–AWL–03 identifies
wire types BMS 13–48, BMS 13–58, and BMS
13–60, the following acceptable wire types
and cables can be added to AWL No. 28–
AWL–03: MIL–W–22759/16, SAE AS22759/
16 (Formerly M22759/16), MIL–W–22759/32,
SAE AS22759/32 (Formerly M22759/32),
MIL–W–22759/34, SAE AS22759/34
(Formerly M22759/34), MIL–W–22759/41,
SAE AS22759/41 (Formerly M22759/41),
MIL–W–22759/86, SAE AS22759/86
(Formerly M22759/86), MIL–W–22759/87,
SAE AS22759/87 (Formerly M22759/87),
MIL–W–22759/92 and SAE AS22759/92
(Formerly M22759/92); and MIL–C–27500
cables that are constructed from the MIL
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specification wire types identified above; and
NEMA WC 27500 cables that are constructed
from the SAE specification wire types
identified above.
(2) Where AWL No. 28–AWL–03 identifies
TFE–2X Standard wall for wire sleeving, the
following acceptable sleeving materials can
be added to AWL No. 28–AWL–03: Roundit
2000NX and Varglas Type HO, HP, or HM,
Grade A.
(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.
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(j) Terminating Actions
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
actions specified in paragraphs (j)(1) through
(j)(5) of this AD for the airplane on which the
revision has been incorporated.
(1) The revision required by paragraph (g)
of AD 2008–04–10 R1.
(2) The revision required by paragraph (h)
of AD 2009–05–03.
(3) The revision required by paragraph (j)
of AD 2011–12–05.
(4) The revision required by paragraph (h)
of AD 2013–22–03.
(5) The revision required by paragraphs
(n)(1) and (n)(2) of AD 2013–24–15.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (l)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
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 Christopher Baker, Aerospace
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16:37 Feb 07, 2018
Jkt 244001
Engineer, Propulsion Section, FAA, Seattle
ACO Branch, 1601 Lind Avenue SW, Renton,
WA 98057–3356; phone: 425–917–6498; fax:
425–917–6590; email: christopher.r.baker@
faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
service information at the FAA, 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 January
26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–02085 Filed 2–7–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0071; Product
Identifier 2017–NM–063–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–23–
01, which applies to all Airbus Model
A310 series airplanes. AD 2016–23–01
requires repetitive detailed inspections
for cracking around the fastener holes in
certain areas of the wing top skin
panels, supplemental repetitive
ultrasonic inspections for cracking
around the fastener holes in certain
other areas of the wing top skin panels,
and repair if necessary. Since we issued
AD 2016–23–01, an evaluation done by
the design approval holder (DAH)
indicates that the wing top skin panel
attachment holes at a certain area are
also subject to widespread fatigue
damage (WFD). This proposed AD
would add an inspection and
modification of the attachment holes of
the wing top skin panels at a certain
area. This proposed AD also includes
terminating action for certain
inspections. We are proposing this AD
to address the unsafe condition on these
products.
SUMMARY:
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We must receive comments on
this proposed AD by March 26, 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 Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 44 51; email:
account.airworth-eas@airbus.com;
internet: https://www.airbus.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.
DATES:
Examining the AD Docket
Airworthiness Directives; Airbus
Airplanes
PO 00000
5579
Sfmt 4702
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0071; 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone: 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone: 425–227–2125; fax: 425–
227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2018–0071; Product Identifier
2017–NM–063–AD’’ at the beginning of
E:\FR\FM\08FEP1.SGM
08FEP1
]]>Agencies
[Federal Register Volume 83, Number 27 (Thursday, February 8, 2018)]
[Proposed Rules]
[Pages 5576-5579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02085]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0031; Product Identifier 2017-NM-127-AD]
RIN 2120-AA6417
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 727 airplanes. This proposed AD was
prompted by significant changes made to the airworthiness limitations
(AWLs) related to fuel tank ignition prevention. This proposed AD would
require revising the maintenance or inspection program, as applicable,
to incorporate 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 March 26, 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,
1601 Lind Avenue SW, Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221. It is also available on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0031.
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-
0031; 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: Christopher Baker, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW,
Renton, WA 98057-3356; phone: 425-917-6498; fax: 425-917-6590; 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-2018-0031;
Product Identifier 2017-NM-127-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 20, 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 ``21-72'' 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
[[Page 5577]]
to define the unsafe conditions associated with fuel tank systems that
require corrective actions. The percentage of operating time during
which fuel tanks are exposed to flammable conditions is one of these
criteria. The other three criteria address the failure types under
evaluation: Single failures, single failures in combination with
another latent condition(s), and in-service failure experience. For all
four criteria, the evaluations included consideration of previous
actions taken that may mitigate the need for further action.
We have determined that the actions identified in this proposed AD
are necessary to 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.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing 727-100/200 Airworthiness Limitations (AWLs) D6-
8766-AWL, dated December 2016. The service information describes AWL
tasks that include airworthiness limitation instructions (ALIs) and
critical design configuration control limitations (CDCCLs) related to
fuel tank ignition prevention. 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 revision of the maintenance or
inspection program to incorporate the ALI and CDCCL tasks described
previously.
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.
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
specified by this proposed AD, future maintenance actions on these
components must be done in accordance with the CDCCLs specified by this
proposed AD.
Related Rulemaking
Five ADs are related to this NPRM. We have determined that certain
requirements of those ADs may be terminated when the referenced AWLs
specified in this proposed AD have been incorporated, as follows:
The revision required by paragraph (g) of AD 2008-04-10
R1, Amendment 39-16121 (74 FR 66227, December 15, 2009).
The revision required by paragraph (h) of AD 2009-05-03,
Amendment 39-15827 (74 FR 8851, February 27, 2009).
The revision required by paragraph (j) of AD 2011-12-05,
Amendment 39-16712 (76 FR 33991, June 10, 2011).
The revision required by paragraph (h) of AD 2013-22-03,
Amendment 39-17635 (78 FR 65193, October 31, 2013).
The revision required by paragraphs (n)(1) and (n)(2) of
AD 2013-24-15, Amendment 39-17692 (78 FR 72791, December 4, 2013).
Differences Between This Proposed AD and the Service Information
AWL No. 28-AWL-03 identifies certain wire types. Paragraph (h)(1)
of this proposed AD specifies additional acceptable wire types and
cables.
AWL No. 28-AWL-03 identifies certain sleeving materials. Paragraph
(h)(2) of this proposed AD specifies additional acceptable sleeving
materials.
Costs of Compliance
We estimate that this proposed AD affects 20 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
----------------------------------------------------------------------------------------------------------------
Maintenance or inspection program 1 work-hour x $85 per hour $0 $85 $1,700
revision. = $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 issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications
[[Page 5578]]
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-2018-0031; Product Identifier
2017-NM-127-AD.
(a) Comments Due Date
We must receive comments by March 26, 2018.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) through
(b)(5) of this AD.
(1) AD 2008-04-10 R1, Amendment 39-16121 (74 FR 66227, December
15, 2009) (``AD 2008-04-10 R1'').
(2) AD 2009-05-03, Amendment 39-15827 (74 FR 8851, February 27,
2009) (``AD 2009-05-03'').
(3) AD 2011-12-05, Amendment 39-16712 (76 FR 33991, June 10,
2011) (``AD 2011-12-05'').
(4) AD 2013-22-03, Amendment 39-17635 (78 FR 65193, October 31,
2013) (``AD 2013-22-03'').
(5) AD 2013-24-15, Amendment 39-17692 (78 FR 72791, December 4,
2013) (``AD 2013-24-15'').
(c) Applicability
This AD applies to The Boeing Company Model 727, 727C, 727-100,
727-100C, 727-200, and 727-200F 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 the
airworthiness limitations (AWLs) related to fuel tank ignition
prevention. We are issuing this AD to prevent the potential for
ignition sources inside fuel tanks caused by latent failures,
alterations, repairs, or maintenance actions, which, in combination
with flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Maintenance or Inspection Program Revision
Within 60 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate all
information in Section A, including Subsections A.1 and A.2, of
Boeing 727-100/200 Airworthiness Limitations (AWLs) D6-8766-AWL,
dated December 2016. The initial compliance times for the
airworthiness limitation instruction (ALI) items are within the
applicable compliance times specified in paragraphs (g)(1) through
(g)(6) of this AD.
(1) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel
Tank (Tank No. 2)'': at the applicable time specified in paragraph
(g)(1)(i) or (g)(1)(ii) of this AD.
(i) For airplanes that have been previously inspected as
specified in 28-AWL-01 as of the effective date of this AD: Conduct
the inspection within 120 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in
28-AWL-01 as of the effective date of this AD: Conduct the
inspection within 12 months after the effective date of this AD.
(2) For AWL No. 28-AWL-16, ``Over-Current and Arcing Protection
Electrical Design Features Operation--Boost Pump Ground Fault
Interrupter (GFI)'': at the applicable time specified in paragraph
(g)(2)(i) or (g)(2)(ii) of this AD.
(i) For airplanes that have been previously inspected as
specified in 28-AWL-16 as of the effective date of this AD: Conduct
the inspection within 12 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in
28-AWL-16 as of the effective date of this AD: Conduct the
inspection within 90 days after the effective date of this AD.
(3) For AWL No. 28-AWL-17, ``Auxiliary Tank Fuel Boost Pump
Power Failed On Protection System'': at the applicable time
specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD.
(i) For airplanes that have been previously inspected as
specified in 28-AWL-17 as of the effective date of this AD: Conduct
the inspection within 12 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in
28-AWL-17 as of the effective date of this AD: Conduct the
inspection within 90 days after the effective date of this AD.
(4) For AWL No. 28-AWL-18, ``Fuel Quantity Indicating System
(FQIS)--Out-Tank Wiring Lightning Shield to Ground Termination and
Joint Resistance for the Volumetric Top-Off (VTO) Unit (If
Installed)'': at the applicable time specified in paragraph
(g)(4)(i) or (g)(4)(ii) of this AD.
(i) For airplanes that have been previously inspected as
specified in 28-AWL-18 as of the effective date of this AD: Conduct
the inspection within 120 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in
28-AWL-18: Conduct the inspection within 12 months after the
effective date of this AD.
(5) For AWL No. 28-AWL-22, ``AC Fuel Boost Pump Bonding
Installation'': at the applicable time specified in paragraph
(g)(5)(i) or (g)(5)(ii) of this AD.
(i) For airplanes that have been previously inspected as
specified in 28-AWL-22 as of the effective date of this AD: Conduct
the inspection within 72 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in
28-AWL-22 as of the effective date of this AD: Conduct the
inspection within 12 months after the effective date of this AD.
(6) For AWL No. 28-AWL-24, ``Motor Operated Valve Bonding Jumper
Installation--Fault Current Protection'': at the applicable time
specified in paragraph (g)(6)(i) or (g)(6)(ii) of this AD.
(i) For airplanes that have been previously inspected as
specified in 28-AWL-24 as of the effective date of this AD: Conduct
the inspection within 60 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in
28-AWL-24 as of the effective date of this AD: Conduct the
inspection within 12 months after the effective date of this AD.
(h) Additional Acceptable Wire Types and Sleeving
(1) Where AWL No. 28-AWL-03 identifies wire types BMS 13-48, BMS
13-58, and BMS 13-60, the following acceptable wire types and cables
can be added to AWL No. 28-AWL-03: MIL-W-22759/16, SAE AS22759/16
(Formerly M22759/16), MIL-W-22759/32, SAE AS22759/32 (Formerly
M22759/32), MIL-W-22759/34, SAE AS22759/34 (Formerly M22759/34),
MIL-W-22759/41, SAE AS22759/41 (Formerly M22759/41), MIL-W-22759/86,
SAE AS22759/86 (Formerly M22759/86), MIL-W-22759/87, SAE AS22759/87
(Formerly M22759/87), MIL-W-22759/92 and SAE AS22759/92 (Formerly
M22759/92); and MIL-C-27500 cables that are constructed from the MIL
[[Page 5579]]
specification wire types identified above; and NEMA WC 27500 cables
that are constructed from the SAE specification wire types
identified above.
(2) Where AWL No. 28-AWL-03 identifies TFE-2X Standard wall for
wire sleeving, the following acceptable sleeving materials can be
added to AWL No. 28-AWL-03: Roundit 2000NX and Varglas Type HO, HP,
or HM, Grade A.
(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 actions specified in paragraphs (j)(1) through
(j)(5) of this AD for the airplane on which the revision has been
incorporated.
(1) The revision required by paragraph (g) of AD 2008-04-10 R1.
(2) The revision required by paragraph (h) of AD 2009-05-03.
(3) The revision required by paragraph (j) of AD 2011-12-05.
(4) The revision required by paragraph (h) of AD 2013-22-03.
(5) The revision required by paragraphs (n)(1) and (n)(2) of AD
2013-24-15.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (l)(1) of this AD. Information may be
emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing 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 Christopher
Baker, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO
Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-
6498; fax: 425-917-6590; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the
FAA, 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 January 26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-02085 Filed 2-7-18; 8:45 am]
BILLING CODE 4910-13-P
