Airworthiness Directives; Bombardier Inc., Airplanes, 60800-60804 [2013-24077]
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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules
was increased. We are issuing this AD to
prevent reduced control of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
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(g) Airplane Flight Manual Revision
For airplanes identified in paragraphs
(g)(1) and (g)(2) of this AD, except as
provided by paragraph (j) of this AD: Within
10 days after the effective date of this AD,
revise the Emergency Procedures of the
Airbus A330 and A340 Airplane Flight
Manuals (AFMs), as applicable, by
incorporating Airbus A330 Temporary
Revision TR293, Issue 1.0, dated December 4,
2012; or Airbus A340 Temporary Revision
TR294, Issue 1.0, dated December 4, 2012; as
applicable; to advise the flight crew of
emergency procedures for addressing AOA
sensor blockage. This can be done by
inserting the Airbus A330 Temporary
Revision TR293, Issue 1.0, dated December 4,
2012; or Airbus A340 Temporary Revision
TR294, Issue 1.0, dated December 4, 2012;
into the applicable AFM. When the
information in Airbus A330 Temporary
Revision TR293, Issue 1.0, dated December 4,
2012; and Airbus A340 Temporary Revision
TR294, Issue 1.0, dated December 4, 2012; is
included in the general revisions of the
applicable AFM, the general revisions may be
incorporated into the AFM, and the
temporary revisions may be removed.
(1) Model A330–201, –202, –203, –223,
223F, –243, –243F, –301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes,
all manufacturer serial numbers, on which
Airbus modification 201609 or 201610 has
been embodied in production; or on which
Airbus Service Bulletin A330–34–3255 has
been embodied in service.
(2) Model A340–211, –212, –213, –311,
–312, –313, –541, and –642 airplanes, all
manufacturer serial numbers, on which
Airbus modification 201609 or 201610 has
been embodied in production; or on which
Airbus Service Bulletin A340–34–4250 or
A340–34–5081, as applicable, has been
embodied in service.
(h) Replacement
Except as provided by paragraph (j) of this
AD: Within 5 months after the effective date
of this AD, replace all AOA sensor conic
plates having part number (P/N)
F3411060200000 or P/N F3411060900000
with an applicable AOA sensor flat plate
identified in paragraph (h)(1) or (h)(2) of this
AD. Performing this replacement constitutes
terminating action for the AFM revision
required by paragraph (g) of this AD; and
Airbus A330 Temporary Revision TR293,
Issue 1.0, dated December 4, 2012, and
Airbus A340 Temporary Revision TR294,
Issue 1.0, dated December 4, 2012, to the
Airbus A330 and A340 AFMs, as applicable,
must be removed from the AFMs before
further flight after doing the replacement.
(1) Replace with a flat plate having P/N
F3411007920200 or P/N F3411007920300, as
applicable, in accordance with the applicable
service information specified in paragraph
(h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD.
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(i) Airbus Mandatory Service Bulletin
A330–34–3293, Revision 01, including
Appendix 01, dated June 12, 2013.
(ii) Airbus Mandatory Service Bulletin
A340–34–4273, Revision 01, including
Appendix 01, dated June 12, 2013.
(iii) Airbus Mandatory Service Bulletin
A340–34–5093, Revision 01, including
Appendix 01, dated June 12, 2013.
(2) Replace with a flat plate having P/N
F3411007920000 or P/N F3411007920100, in
accordance with a method approved by
either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA; or the European Aviation Safety
Agency (EASA) or its delegated agent.
(i) Modification of Installation
For airplanes on which any AOA sensor
conic plate has been replaced with an AOA
sensor flat plate, in accordance with the
applicable service information specified in
paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of
this AD: Within 5 months after the effective
date of this AD, modify the installation of the
AOA sensor flat plates so that the plates are
flush with the fuselage in accordance with
the applicable service information identified
in paragraph (h)(1)(i), (h)(1)(ii),or (h)(1)(iii) of
this AD.
(i) Airbus Mandatory Service Bulletin
A330–34–3293, including Appendix 01,
dated January 31, 2013.
(ii) Airbus Mandatory Service Bulletin
A340–34–4273, including Appendix 01,
dated January 30, 2013.
(iii) Airbus Mandatory Service Bulletin
A340–34–5093, including Appendix 01,
dated January 30, 2013.
(j) Exception to Paragraphs (g) and (h) of
This AD
For airplanes on which Airbus
Modification 203285 (improved AOA flat
plate protection treatment) has been
embodied in production: The actions
specified in paragraphs (g) and (h) of this AD
are not required, provided that, since first
flight, no AOA probe conic plate having P/
N F3411060200000 or P/N F3411060900000
has been installed.
(k) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, on any airplane, an AOA
sensor conic plate having P/N
F3411060200000 or P/N F3411060900000 or
an AOA protection cover having P/N
98D34203003000.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
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Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov.
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. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information EASA
Airworthiness Directive 2013–0023, dated
February 1, 2013, for related information,
which can be found in the AD docket on the
Internet at https://www.regulations.gov.
(2) For service information identified in
this proposed AD, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet https://
www.airbus.com. You may review copies of
the referenced service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
September 23, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–24058 Filed 10–1–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0835; Directorate
Identifier 2013–NM–095–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–102,
–103, –106, –201, –202, –301, –311, and
–315 airplanes. This proposed AD
SUMMARY:
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results from fuel system reviews
conducted by the manufacturer. This
proposed AD would require
accomplishing modifications to the fuel
system. We are proposing this AD to
prevent 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.
DATES: We must receive comments on
this proposed AD by November 18,
2013.
ADDRESSES: You may send comments 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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email
thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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:
Morton Lee, Propulsion Engineer,
Propulsion & Services Branch, ANE–
173; FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
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11590; telephone 516–228–7355; fax
516–794–5531.
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–2013–0835; Directorate Identifier
2013–NM–095–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on 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
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 regulation 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, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 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 rule, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
unsafe conditions identified as a result
of these reviews.
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60801
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
single failures, combination of failures,
and unacceptable (failure) experience.
For all three failure 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 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.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2013–07,
dated March 1, 2013 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
Bombardier Aerospace has completed a
system safety review of the aeroplane fuel
system against fuel tank safety standards
* * *. The identified non-compliances were
then assessed * * * to determine if
mandatory corrective action is required.
The assessment showed that a number of
modifications to the fuel system are required
to mitigate unsafe conditions that could
result in potential ignition sources within the
fuel system.
*
*
*
*
*
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Bombardier Inc. has issued the
following service bulletins. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
• Bombardier Service Bulletin 8–28–35,
Revision C, dated January 14, 2013.
• Bombardier Service Bulletin 8–28–36,
Revision C, dated October 7, 2009.
• Bombardier Service Bulletin 8–28–39,
Revision B, dated August 19, 2009.
• Bombardier Service Bulletin 8–28–41,
Revision B, dated August 8, 2012.
• Bombardier Service Bulletin 8–28–42,
Revision A, dated October 1, 2008.
• Bombardier Service Bulletin 8–28–43,
Revision A, dated June 25, 2009.
• Bombardier Service Bulletin 8–28–44,
Revision B, dated July 25, 2009.
• Bombardier Service Bulletin 8–28–47,
dated May 2, 2008.
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• Bombardier Service Bulletin 8–28–48,
Revision A, dated February 27, 2012.
• Bombardier Service Bulletin 8–28–49,
Revision A, dated July 23, 2012.
• Bombardier Service Bulletin 8–28–52,
dated November 3, 2009.
• Bombardier Service Bulletin 8–28–53,
dated November 3, 2008.
• Bombardier Service Bulletin 8–28–55,
dated July 23, 2012.
• Bombardier Service Bulletin 8–28–56,
dated July 23, 2012.
• Bombardier Service Bulletin 8–28–58,
dated July 25, 2011.
• Bombardier Service Bulletin 8–57–44,
Revision D, dated October 8, 2008.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 94 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Modifications ..............................
519 work-hours × $85 per hour = $44,115 .................................
$58,924
$103,039
$9,685,666
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.
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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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Regulatory Findings
§ 39.13
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
■
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[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Bombardier, Inc.: Docket No. FAA–2013–
0835; Directorate Identifier 2013–NM–
095–AD.
(a) Comments Due Date
We must receive comments by November
18, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–102, –103, –106, –201, –202, –301,
–311, and –315 airplanes; certificated in any
category; serial numbers (S/Ns) 002 through
672.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
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(e) Reason
This AD was prompted by results from fuel
system reviews conducted by the
manufacturer. We are issuing this AD to
prevent 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
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Modifications—Part I
Within 6,000 flight hours or 36 months,
whichever occurs first, after the effective date
of this AD, do the modifications specified in
paragraphs (g)(1) through (g)(14) of this AD,
as applicable.
(1) For airplanes having S/Ns 003 through
624 inclusive: Accomplish Modsum
8Q101512, ‘‘Fuel System—Fuel Tank
Mechanical Design, SFAR 88 Compliance
(Retrofit),’’ Revision G, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 8–57–44,
Revision D, dated October 8, 2008.
(2) For airplanes having S/Ns 003 through
629 inclusive on which a long range fuel
system has been installed as specified in
Change Request (CR) 828CH00044,
CR828SO08061, Special Order Option (SOO)
8061, CR828CH00027, or CF828SO00006:
Accomplish Bombardier Modsum 8Q902091,
‘‘Fuel System—Fuel Tank Mech. Design,
SFAR 88 Compl.—Extended Range Tank
Option (Retrofit),’’ Revision C, in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 8–28–39,
Revision B, dated August 19, 2009.
(3) For airplanes having S/Ns 003 through
624 inclusive on which SOO 8155,
849SO08155, SOO 8098, SOO 8099, or SOO
6082; or Supplemental Type Certificate
SA85–1; or Limited Supplemental Type
Certificate W–LSA98–005/D has been
incorporated: Accomplish Bombardier
Modsum 8Q902144, ‘‘Fuel System—Fuel
Tank Mechanical Design, SFAR 88
Compliance—APU Option (Retrofit),’’
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Revision E, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–44, Revision B, dated
July 25, 2009.
(4) For airplanes having S/Ns 003 through
624 inclusive: Accomplish Bombardier
Modsum 8Q101865, ‘‘Fuel System—Fuel
Tank Mechanical Design, SFAR 88
Compliance (Retrofit),’’ Revision B, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–47, dated May 2, 2008.
(5) For Models DHC–8–102, –103, and
–106 having S/Ns 002 through 014 inclusive:
Accomplish Bombardier Modsum 8Q101916,
‘‘Fuel System—Fuel Tank Secondary
Pressure Relief Valve Rework SFAR 88
Compliance (Retrofit),’’ Revision A, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–58, dated July 25, 2011.
(6) For airplanes having S/Ns 002 through
629 inclusive on which a long range fuel
system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061,
CR828CH00027, or CR828SO00006,
including airplanes on which metric refuel/
defuel indicators were installed as specified
in CR828CH00029: Accomplish Bombardier
Modsum 8Q902122, ‘‘Production/Retrofit—
Fuel System—Long Range Wiring
Installation—SFAR 88 Compliance,’’
Revision F, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–41, Revision B, dated
August 8, 2012.
(7) For airplanes having S/Ns 002 through
619 inclusive with imperial refuel/defuel
indicators, excluding airplanes on which a
long range fuel system has been installed as
specified in CF828CH00044, CR828SO08061,
SOO 0861, CF828CH00027, or
CR828SO00006: Accomplish Bombardier
Modsum 8Q101511, ‘‘Production/Retrofit—
Fuel System—Fuel Tank Wiring
Installation—SFAR88 Compliance,’’ Revision
C, in accordance with the Accomplishment
Instruction of Bombardier Service Bulletin 8–
28–35, Revision C, dated January 14, 2013.
(8) For airplanes having S/Ns 002 through
619 inclusive on which metric refuel/defuel
indicators have been installed as specified in
CR828CH00020, excluding airplanes on
which a long range fuel system has been
installed as specified in CR828CH00044,
CF828SO08061, SOO 8061, CR828CH00027,
or CR828SO00006: Accomplish Bombardier
Modsum 8Q901117, ‘‘Production/Retrofit—
Fuel System—Metric Indication—Fuel Tank
Wiring Installation—SFAR 88,’’ Revision C,
in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–43, Revision A, dated June 25, 2009.
(9) For airplanes having S/Ns 003 through
619 inclusive, excluding airplanes that have
incorporated Modsum 8Q101652 in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–36, Revision A, dated November 17,
2006; or Revision B, dated February 12, 2008:
Accomplish Bombardier Modsum 8Q101652,
‘‘Electrical—Fuel Quantity Indication Wire
Routing Segregation and Identification,’’
Revision F, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–36, Revision C, dated
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October 7, 2009. In addition, for Models
DHC–8–102, –103, –106, –201, and –202
airplanes on which an active noise and
vibration suppression (ANVS) system has
been installed, and on which Modsum
8Q101652 has been incorporated in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–36, Revision A, dated November 17,
2006; or Revision B, dated February 12, 2008:
Do the actions specified in paragraph (h)(1)
of this AD.
(10) For airplanes having S/Ns 003 through
672 inclusive on which Modsum 8Q101513
or 8Q101652 has been installed as specified
in CR828CH00044, CR828SO08061, SOO
8061, CR828CH00027, or CR828CO00006,
excluding airplanes having a long range fuel
system: Accomplish Bombardier Modsum
8Q101907, ‘‘Fuel System—Fuel Qty Ind.,
Wire Routing Segregation, Installation of Top
Hat Support—SFAR88 (Standard Aircraft),’’
Revision B, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–48, Revision A, dated
February 27, 2012.
(11) For airplanes having S/Ns 003 through
619, excluding airplanes on which a long
range fuel system has been installed as
specified in CR828CH00044, CR828SO08061,
SOO 8061, CR828CH00027, or
CR828SO00006, and excluding airplanes on
which Modsum 8Q101652 was incorporated
in accordance with the Accomplishment
Instructions in Bombardier Service Bulletin
8–28–36, Revision A, dated November 17,
2006; Revision B, dated February 12, 2008, or
Revision C, dated October 7, 2009:
Accomplish Modsum 8Q101908, ‘‘Fuel
System—Fuel Qty Ind., Wire Routing
Segregation, Installation of Dual Spacers—
SFAR88 (Standard A/C),’’ Revision B, in
accordance with the Accomplishment
Instruction of Bombardier Service Bulletin 8–
28–55, dated July 23, 2012. In addition, for
airplanes on which Modsum 8Q101652 was
incorporated in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–36, dated August 9,
2006; Revision A, dated November 17, 2006;
Revision B, dated February 12, 2008; or
Revision C, dated October 7, 2009: Do the
actions in paragraph (i)(1) of this AD.
(12) For airplanes having S/Ns 002 through
629 inclusive, on which a long range fuel
system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061,
CF828CH00027, or CR828SO00006,
excluding airplanes on which Modsum
8Q902064 has been incorporated in
accordance with the Accomplishment
Instructions contained in Bombardier Service
Bulletin 8–28–42: Accomplish Bombardier
Modsum 8Q902064, ‘‘Electrical—Long Range
Fuel Quantity Indication Wire Routing
Segregation and Identification—SFAR 88,’’
Revision G, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–42, Revision A, dated
October 1, 2008.
(13) For airplanes having S/Ns 003 through
672 inclusive on which a long range fuel
system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061,
CR828CH00027, or CR828SO00006; and with
Modsum 8Q902064 and either Modsum
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Frm 00020
Fmt 4702
Sfmt 4702
60803
8Q101513 or Modsum 8Q101652:
Accomplish Bombardier Modsum 8Q902382,
‘‘Fuel System—Fuel Qty Ind., Wire Routing
Segregation, Installation of Top Hat
Support—SFAR88 (Long Range Aircraft),’’
Revision B, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–49, Revision A, dated
July 23, 2012.
(14) For airplanes having S/Ns 003 through
629 inclusive on which a long range fuel
system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061,
CR828CH00027, or CR828SO00006,
excluding airplanes on which Modsum
8Q902064 has been incorporated in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–42, dated December 21, 2008 or
Revision A, dated October 1, 2008:
Accomplish Bombardier Modsum 8Q902383,
‘‘Fuel System—Fuel Qty Ind., Wire Routing
Segregation, Installation of Dual Spacers—
SFAR88 (Long Range A/C),’’ Revision B,
including installing dual spacers inside the
center fuselage at certain locations, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–56, dated July 23, 2012.
(h) Inspections, Modifications, and
Corrective Actions—Part II
For the airplanes identified in paragraphs
(h)(1), (h)(2), or (h)(3) of this AD: Within
12,000 flight hours or 72 months, whichever
occurs first, after the effective date of this
AD, do the actions specified in paragraphs
(h)(1), (h)(2), and (h)(3) of this AD, as
applicable.
(1) For Model DHC–8–102, –103, –106,
–201, and –202 airplanes having S/Ns 003
through 619 inclusive, on which an ANVS
system has been installed and on which
Modsum 8Q101652 has been incorporated in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–36, dated August 9, 2006; or Revision
A, dated November 17, 2006; or Revision B,
dated February 12, 2008: Accomplish
Bombardier Modsum 8Q101652,
‘‘Electrical—Fuel Quantity Indication Wire
Routing Segregation and Identification,’’
Revision F, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–36, Revision C, dated
October 7, 2009.
(2) For Model DHC–8–102, –103, –106,
–201, and –202 airplanes having S/Ns 002
through 629 inclusive, on which an ANVS
system has been installed and on which
Modsum 8Q902064 has been incorporated in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–42, dated December 21, 2008:
Accomplish Bombardier Modsum 8Q902064,
‘‘Electrical—Long Range Fuel Quantity
Indication Wire Routing Segregation and
Identification—SFAR 88,’’ Revision G, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–42, Revision A, dated October 1, 2008.
(3) For Model DHC–8–102, –103, –106,
–201, and –202 airplanes having S/Ns 620
through 666 inclusive, on which an ANVS
system has been installed: Do a one-time
visual inspection to determine whether the
E:\FR\FM\02OCP1.SGM
02OCP1
60804
Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules
fuel quantity indicating system (FQIS) wiring
harness is routed correctly and relocate if
necessary, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–28–52, dated November 3,
2009.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(i) Wire Routing Segregation and Installation
of Dual Spacers—Part III
Within 18,000 flight hours or 108 months,
whichever occurs first, after the effective date
of this AD, do the modification specified in
paragraphs (i)(1) and (i)(2) of this AD, as
applicable.
(1) For airplanes having S/Ns 003 through
672 inclusive, on which Modsum 8Q101513
has been incorporated or on which Modsum
8Q101652 has been incorporated in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–36, dated August 9, 2006; Revision A,
dated November 17, 2006; Revision B, dated
February 12, 2008; or Revision C, dated
October 7, 2009; excluding airplanes on
which a long-range fuel system has been
installed as specified in CF828CH00044,
CR828SO08061, SOO 8061, CR828CH00027,
or CR828SO00006: Accomplish Bombardier
Modsum 8Q101908, ‘‘Fuel System—Fuel Qty
Ind., Wire Routing Segregation, Installation
of Dual Spacers—SFAR88 (Standard A/C),’’
Revision B, including installing dual spacers
inside certain center fuselage locations, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–55, dated July 23, 2012.
(2) For airplanes having S/Ns 003 through
672 inclusive on which a long-range fuel
system has been installed as specified in
CF828CH00044, CR828SO08061, SOO 8061,
CR828CH00027, or CR828SO00006, and on
which Modsum 8Q902064 has been
incorporated, or on which Modsum
8Q902064 has been incorporated in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–42, dated December 21, 2008; or
Revision A, dated October 1, 2008:
Accomplish Bombardier Modsum 8Q902383,
‘‘Fuel System—Fuel Qty Ind., Wire routing
Segregation, Installation of Dual Spacers—
SFAR88 (Long Range A/C),’’ Revision B,
including installing dual spacers inside
certain center fuselage locations, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–28–56, dated July 23, 2012.
(j) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g)(2) of this
AD, if those actions were performed before
the effective date of this AD using
Bombardier Service Bulletin 8–28–39,
Revision A, March 15, 2007.
(2) This paragraph provides credit for
actions required by paragraph (g)(3) of this
AD, if those actions were performed before
the effective date of this AD using
Bombardier Service Bulletin 8–28–44, dated
August 9, 2006; or Revision A, dated
November 15, 2006.
(3) This paragraph provides credit for
actions required by paragraph (g)(6) of this
AD, if those actions were performed before
the effective date of this AD using
VerDate Mar<15>2010
17:27 Oct 01, 2013
Jkt 232001
Bombardier Service Bulletin 8–28–41,
Revision A, dated April 11, 2007.
(4) This paragraph provides credit for
actions required by paragraph (g)(8) of this
AD, if those actions were performed before
the effective date of this AD using
Bombardier Service Bulletin 8–28–43, dated
August 10, 2006.
(5) This paragraph provides credit for
actions required by paragraph (g)(10) of this
AD, if those actions were performed before
the effective date of this AD using
Bombardier Service Bulletin 8–28–48, dated
October 1, 2010.
(6) This paragraph provides credit for
actions required by paragraph (g)(13) of this
AD, if those actions were performed before
the effective date of this AD using
Bombardier Service Bulletin 8–28–49, dated
October 1, 2010.
(7) This paragraph provides credit for
actions required by paragraph (h)(3) of this
AD, if those actions were performed before
the effective date of this AD using
Bombardier Service Bulletin 8–28–53, dated
November 3, 2008.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANE–170, 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 ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. 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. The AMOC approval
letter must specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–07, dated
March 1, 2013, for related information, which
can be found in the AD docket on the
internet at https://www.regulations.gov.
(2) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com. You
may review copies of this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
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Frm 00021
Fmt 4702
Sfmt 4702
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
September 19, 2013.
Ross Landes,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–24077 Filed 10–1–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0836; Directorate
Identifier 2013–NM–126–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) 2005–07–
12 that applies to certain The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
AD 2005–07–12 requires detailed and
eddy current inspections to detect
cracking of the frame web around the
cutout for the doorstop intercostal strap
at the aft side of the station (STA) 291.5
frame at stringer 16R, and corrective
action if necessary. Since we issued AD
2005–07–12, we received reports of new
findings of cracking at various locations
of the STA 277 to STA 291.5 frames and
intercostals, including webs, chords,
clips, and shear ties, between stringers
7R and 17R. This proposed AD would
add new inspections for cracking at the
forward galley door cutout, and
corrective actions if necessary. This
proposed AD would also reduce a
certain inspection threshold required by
AD 2005–07–12. We are proposing this
AD to detect and correct fatigue
cracking of the aft frame and frame
support structure of the forward galley
door, which could result in a severed
fuselage frame web, rapid
decompression of the airplane, and
possible loss of the forward galley door.
DATES: We must receive comments on
this proposed AD by November 18,
2013.
SUMMARY:
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
ADDRESSES:
E:\FR\FM\02OCP1.SGM
02OCP1
Agencies
[Federal Register Volume 78, Number 191 (Wednesday, October 2, 2013)]
[Proposed Rules]
[Pages 60800-60804]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24077]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0835; Directorate Identifier 2013-NM-095-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Inc., 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 Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301,
-311, and -315 airplanes. This proposed AD
[[Page 60801]]
results from fuel system reviews conducted by the manufacturer. This
proposed AD would require accomplishing modifications to the fuel
system. We are proposing this AD to prevent 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.
DATES: We must receive comments on this proposed AD by November 18,
2013.
ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; Internet https://www.bombardier.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
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: Morton Lee, Propulsion Engineer,
Propulsion & Services Branch, ANE-173; FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone 516-228-7355; fax 516-794-5531.
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-2013-0835;
Directorate Identifier 2013-NM-095-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on 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
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
regulation 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, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 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 rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, combination of
failures, and unacceptable (failure) experience. For all three failure
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 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.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-07, dated March 1, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
Bombardier Aerospace has completed a system safety review of the
aeroplane fuel system against fuel tank safety standards * * *. The
identified non-compliances were then assessed * * * to determine if
mandatory corrective action is required.
The assessment showed that a number of modifications to the fuel
system are required to mitigate unsafe conditions that could result
in potential ignition sources within the fuel system.
* * * * *
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier Inc. has issued the following service bulletins. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.
Bombardier Service Bulletin 8-28-35, Revision C, dated
January 14, 2013.
Bombardier Service Bulletin 8-28-36, Revision C, dated
October 7, 2009.
Bombardier Service Bulletin 8-28-39, Revision B, dated
August 19, 2009.
Bombardier Service Bulletin 8-28-41, Revision B, dated
August 8, 2012.
Bombardier Service Bulletin 8-28-42, Revision A, dated
October 1, 2008.
Bombardier Service Bulletin 8-28-43, Revision A, dated
June 25, 2009.
Bombardier Service Bulletin 8-28-44, Revision B, dated
July 25, 2009.
Bombardier Service Bulletin 8-28-47, dated May 2, 2008.
[[Page 60802]]
Bombardier Service Bulletin 8-28-48, Revision A, dated
February 27, 2012.
Bombardier Service Bulletin 8-28-49, Revision A, dated
July 23, 2012.
Bombardier Service Bulletin 8-28-52, dated November 3,
2009.
Bombardier Service Bulletin 8-28-53, dated November 3,
2008.
Bombardier Service Bulletin 8-28-55, dated July 23,
2012.
Bombardier Service Bulletin 8-28-56, dated July 23,
2012.
Bombardier Service Bulletin 8-28-58, dated July 25,
2011.
Bombardier Service Bulletin 8-57-44, Revision D, dated
October 8, 2008.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 94 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
----------------------------------------------------------------------------------------------------------------
Modifications....................... 519 work-hours x $85 per $58,924 $103,039 $9,685,666
hour = $44,115.
----------------------------------------------------------------------------------------------------------------
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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 AD:
Bombardier, Inc.: Docket No. FAA-2013-0835; Directorate Identifier
2013-NM-095-AD.
(a) Comments Due Date
We must receive comments by November 18, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-102, -103, -106,
-201, -202, -301, -311, and -315 airplanes; certificated in any
category; serial numbers (S/Ns) 002 through 672.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Reason
This AD was prompted by results from fuel system reviews
conducted by the manufacturer. We are issuing this AD to prevent 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
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Modifications--Part I
Within 6,000 flight hours or 36 months, whichever occurs first,
after the effective date of this AD, do the modifications specified
in paragraphs (g)(1) through (g)(14) of this AD, as applicable.
(1) For airplanes having S/Ns 003 through 624 inclusive:
Accomplish Modsum 8Q101512, ``Fuel System--Fuel Tank Mechanical
Design, SFAR 88 Compliance (Retrofit),'' Revision G, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-57-44, Revision D, dated October 8, 2008.
(2) For airplanes having S/Ns 003 through 629 inclusive on which
a long range fuel system has been installed as specified in Change
Request (CR) 828CH00044, CR828SO08061, Special Order Option (SOO)
8061, CR828CH00027, or CF828SO00006: Accomplish Bombardier Modsum
8Q902091, ``Fuel System--Fuel Tank Mech. Design, SFAR 88 Compl.--
Extended Range Tank Option (Retrofit),'' Revision C, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-28-39, Revision B, dated August 19, 2009.
(3) For airplanes having S/Ns 003 through 624 inclusive on which
SOO 8155, 849SO08155, SOO 8098, SOO 8099, or SOO 6082; or
Supplemental Type Certificate SA85-1; or Limited Supplemental Type
Certificate W-LSA98-005/D has been incorporated: Accomplish
Bombardier Modsum 8Q902144, ``Fuel System--Fuel Tank Mechanical
Design, SFAR 88 Compliance--APU Option (Retrofit),''
[[Page 60803]]
Revision E, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 8-28-44, Revision B, dated July 25,
2009.
(4) For airplanes having S/Ns 003 through 624 inclusive:
Accomplish Bombardier Modsum 8Q101865, ``Fuel System--Fuel Tank
Mechanical Design, SFAR 88 Compliance (Retrofit),'' Revision B, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-47, dated May 2, 2008.
(5) For Models DHC-8-102, -103, and -106 having S/Ns 002 through
014 inclusive: Accomplish Bombardier Modsum 8Q101916, ``Fuel
System--Fuel Tank Secondary Pressure Relief Valve Rework SFAR 88
Compliance (Retrofit),'' Revision A, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-58,
dated July 25, 2011.
(6) For airplanes having S/Ns 002 through 629 inclusive on which
a long range fuel system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006,
including airplanes on which metric refuel/defuel indicators were
installed as specified in CR828CH00029: Accomplish Bombardier Modsum
8Q902122, ``Production/Retrofit--Fuel System--Long Range Wiring
Installation--SFAR 88 Compliance,'' Revision F, in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin 8-28-
41, Revision B, dated August 8, 2012.
(7) For airplanes having S/Ns 002 through 619 inclusive with
imperial refuel/defuel indicators, excluding airplanes on which a
long range fuel system has been installed as specified in
CF828CH00044, CR828SO08061, SOO 0861, CF828CH00027, or CR828SO00006:
Accomplish Bombardier Modsum 8Q101511, ``Production/Retrofit--Fuel
System--Fuel Tank Wiring Installation--SFAR88 Compliance,'' Revision
C, in accordance with the Accomplishment Instruction of Bombardier
Service Bulletin 8-28-35, Revision C, dated January 14, 2013.
(8) For airplanes having S/Ns 002 through 619 inclusive on which
metric refuel/defuel indicators have been installed as specified in
CR828CH00020, excluding airplanes on which a long range fuel system
has been installed as specified in CR828CH00044, CF828SO08061, SOO
8061, CR828CH00027, or CR828SO00006: Accomplish Bombardier Modsum
8Q901117, ``Production/Retrofit--Fuel System--Metric Indication--
Fuel Tank Wiring Installation--SFAR 88,'' Revision C, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-28-43, Revision A, dated June 25, 2009.
(9) For airplanes having S/Ns 003 through 619 inclusive,
excluding airplanes that have incorporated Modsum 8Q101652 in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-36, Revision A, dated November 17, 2006; or
Revision B, dated February 12, 2008: Accomplish Bombardier Modsum
8Q101652, ``Electrical--Fuel Quantity Indication Wire Routing
Segregation and Identification,'' Revision F, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-36,
Revision C, dated October 7, 2009. In addition, for Models DHC-8-
102, -103, -106, -201, and -202 airplanes on which an active noise
and vibration suppression (ANVS) system has been installed, and on
which Modsum 8Q101652 has been incorporated in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-36,
Revision A, dated November 17, 2006; or Revision B, dated February
12, 2008: Do the actions specified in paragraph (h)(1) of this AD.
(10) For airplanes having S/Ns 003 through 672 inclusive on
which Modsum 8Q101513 or 8Q101652 has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828CO00006,
excluding airplanes having a long range fuel system: Accomplish
Bombardier Modsum 8Q101907, ``Fuel System--Fuel Qty Ind., Wire
Routing Segregation, Installation of Top Hat Support--SFAR88
(Standard Aircraft),'' Revision B, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-48,
Revision A, dated February 27, 2012.
(11) For airplanes having S/Ns 003 through 619, excluding
airplanes on which a long range fuel system has been installed as
specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or
CR828SO00006, and excluding airplanes on which Modsum 8Q101652 was
incorporated in accordance with the Accomplishment Instructions in
Bombardier Service Bulletin 8-28-36, Revision A, dated November 17,
2006; Revision B, dated February 12, 2008, or Revision C, dated
October 7, 2009: Accomplish Modsum 8Q101908, ``Fuel System--Fuel Qty
Ind., Wire Routing Segregation, Installation of Dual Spacers--SFAR88
(Standard A/C),'' Revision B, in accordance with the Accomplishment
Instruction of Bombardier Service Bulletin 8-28-55, dated July 23,
2012. In addition, for airplanes on which Modsum 8Q101652 was
incorporated in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 8-28-36, dated August 9, 2006; Revision
A, dated November 17, 2006; Revision B, dated February 12, 2008; or
Revision C, dated October 7, 2009: Do the actions in paragraph
(i)(1) of this AD.
(12) For airplanes having S/Ns 002 through 629 inclusive, on
which a long range fuel system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061, CF828CH00027, or CR828SO00006,
excluding airplanes on which Modsum 8Q902064 has been incorporated
in accordance with the Accomplishment Instructions contained in
Bombardier Service Bulletin 8-28-42: Accomplish Bombardier Modsum
8Q902064, ``Electrical--Long Range Fuel Quantity Indication Wire
Routing Segregation and Identification--SFAR 88,'' Revision G, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-42, Revision A, dated October 1, 2008.
(13) For airplanes having S/Ns 003 through 672 inclusive on
which a long range fuel system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006;
and with Modsum 8Q902064 and either Modsum 8Q101513 or Modsum
8Q101652: Accomplish Bombardier Modsum 8Q902382, ``Fuel System--Fuel
Qty Ind., Wire Routing Segregation, Installation of Top Hat
Support--SFAR88 (Long Range Aircraft),'' Revision B, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-28-49, Revision A, dated July 23, 2012.
(14) For airplanes having S/Ns 003 through 629 inclusive on
which a long range fuel system has been installed as specified in
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006,
excluding airplanes on which Modsum 8Q902064 has been incorporated
in accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-42, dated December 21, 2008 or Revision A,
dated October 1, 2008: Accomplish Bombardier Modsum 8Q902383, ``Fuel
System--Fuel Qty Ind., Wire Routing Segregation, Installation of
Dual Spacers--SFAR88 (Long Range A/C),'' Revision B, including
installing dual spacers inside the center fuselage at certain
locations, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 8-28-56, dated July 23, 2012.
(h) Inspections, Modifications, and Corrective Actions--Part II
For the airplanes identified in paragraphs (h)(1), (h)(2), or
(h)(3) of this AD: Within 12,000 flight hours or 72 months,
whichever occurs first, after the effective date of this AD, do the
actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this
AD, as applicable.
(1) For Model DHC-8-102, -103, -106, -201, and -202 airplanes
having S/Ns 003 through 619 inclusive, on which an ANVS system has
been installed and on which Modsum 8Q101652 has been incorporated in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-36, dated August 9, 2006; or Revision A, dated
November 17, 2006; or Revision B, dated February 12, 2008:
Accomplish Bombardier Modsum 8Q101652, ``Electrical--Fuel Quantity
Indication Wire Routing Segregation and Identification,'' Revision
F, in accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-36, Revision C, dated October 7, 2009.
(2) For Model DHC-8-102, -103, -106, -201, and -202 airplanes
having S/Ns 002 through 629 inclusive, on which an ANVS system has
been installed and on which Modsum 8Q902064 has been incorporated in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-28-42, dated December 21, 2008: Accomplish
Bombardier Modsum 8Q902064, ``Electrical--Long Range Fuel Quantity
Indication Wire Routing Segregation and Identification--SFAR 88,''
Revision G, in accordance with the Accomplishment Instructions of
Bombardier Service Bulletin 8-28-42, Revision A, dated October 1,
2008.
(3) For Model DHC-8-102, -103, -106, -201, and -202 airplanes
having S/Ns 620 through 666 inclusive, on which an ANVS system has
been installed: Do a one-time visual inspection to determine whether
the
[[Page 60804]]
fuel quantity indicating system (FQIS) wiring harness is routed
correctly and relocate if necessary, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-52,
dated November 3, 2009.
(i) Wire Routing Segregation and Installation of Dual Spacers--Part III
Within 18,000 flight hours or 108 months, whichever occurs
first, after the effective date of this AD, do the modification
specified in paragraphs (i)(1) and (i)(2) of this AD, as applicable.
(1) For airplanes having S/Ns 003 through 672 inclusive, on
which Modsum 8Q101513 has been incorporated or on which Modsum
8Q101652 has been incorporated in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 8-28-36, dated August 9,
2006; Revision A, dated November 17, 2006; Revision B, dated
February 12, 2008; or Revision C, dated October 7, 2009; excluding
airplanes on which a long-range fuel system has been installed as
specified in CF828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or
CR828SO00006: Accomplish Bombardier Modsum 8Q101908, ``Fuel System--
Fuel Qty Ind., Wire Routing Segregation, Installation of Dual
Spacers--SFAR88 (Standard A/C),'' Revision B, including installing
dual spacers inside certain center fuselage locations, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-28-55, dated July 23, 2012.
(2) For airplanes having S/Ns 003 through 672 inclusive on which
a long-range fuel system has been installed as specified in
CF828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006,
and on which Modsum 8Q902064 has been incorporated, or on which
Modsum 8Q902064 has been incorporated in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-42,
dated December 21, 2008; or Revision A, dated October 1, 2008:
Accomplish Bombardier Modsum 8Q902383, ``Fuel System--Fuel Qty Ind.,
Wire routing Segregation, Installation of Dual Spacers--SFAR88 (Long
Range A/C),'' Revision B, including installing dual spacers inside
certain center fuselage locations, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-28-56,
dated July 23, 2012.
(j) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g)(2) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-39, Revision A, March 15, 2007.
(2) This paragraph provides credit for actions required by
paragraph (g)(3) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-44, dated August 9, 2006; or Revision A, dated November 15, 2006.
(3) This paragraph provides credit for actions required by
paragraph (g)(6) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-41, Revision A, dated April 11, 2007.
(4) This paragraph provides credit for actions required by
paragraph (g)(8) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-43, dated August 10, 2006.
(5) This paragraph provides credit for actions required by
paragraph (g)(10) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-48, dated October 1, 2010.
(6) This paragraph provides credit for actions required by
paragraph (g)(13) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-49, dated October 1, 2010.
(7) This paragraph provides credit for actions required by
paragraph (h)(3) of this AD, if those actions were performed before
the effective date of this AD using Bombardier Service Bulletin 8-
28-53, dated November 3, 2008.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANE-
170, 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 ACO, send it to ATTN: Program Manager,
Continuing Operational Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax
516-794-5531. 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. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2013-07, dated March 1,
2013, for related information, which can be found in the AD docket
on the internet at https://www.regulations.gov.
(2) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com. You may review copies of this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on September 19, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-24077 Filed 10-1-13; 8:45 am]
BILLING CODE 4910-13-P