Airworthiness Directives; Bombardier, Inc., Airplanes, 17537-17540 [2017-06963]
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Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations
Maintenance Manual, Revision 23, dated
June 20, 2013.
(4) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 26, Fuel Boost
Pumps, of chapter 28, Fuel, of the Gulfstream
G500 Maintenance Manual, Revision 23,
dated June 20, 2013.
(5) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, in table 20, 500 Flight
Hours Scheduled Inspection Table, in section
05–20–00, of chapter 05, Time Limits/
Maintenance Checks, of the Gulfstream G550
Maintenance Manual, Revision 23, dated
June 20, 2013.
(6) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 26, Fuel Boost
Pumps, of chapter 28, Fuel, of the Gulfstream
G550 Maintenance Manual, Revision 23,
dated June 20, 2013.
(7) Table 12, Certification Maintenance
Requirements (CMR), in section 05–10–10,
Airworthiness Limitations, of chapter 05,
Time Limits/Maintenance Checks, of the
Gulfstream V Maintenance Manual, Revision
43, dated February 15, 2015.
(8) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 28–26–01, Fuel
Boost Pumps—Inspection/Check, of chapter
28, Fuel, of the Gulfstream V Maintenance
Manual, Revision 43, dated February 15,
2015.
(9) Table 12, Certification Maintenance
Requirements (CMR), in section 05–10–10,
Airworthiness Limitations, of chapter 05,
Time Limits/Maintenance Checks, of the
Gulfstream G500 Maintenance Manual,
Revision 24, dated February 15, 2015.
(10) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 28–26–01, Fuel
Boost Pumps—Inspection/Check, of chapter
28, Fuel, of the Gulfstream G500
Maintenance Manual, Revision 24, dated
February 15, 2015.
(11) Table 12, Certification Maintenance
Requirements (CMR), in section 05–10–10,
Airworthiness Limitations, of chapter 05,
Time Limits/Maintenance Checks, of the
Gulfstream G550 Maintenance Manual,
Revision 24, dated February 15, 2015.
(12) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 28–26–01, Fuel
Boost Pumps—Inspection/Check, of chapter
28, Fuel, of the Gulfstream G550
Maintenance Manual, Revision 24, dated
February 15, 2015.
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(l) No Alternative Actions or Intervals
After accomplishing the revision required
by paragraph (i) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance in accordance with the
procedures specified in paragraph (n) of this
AD.
(m) Parts Installation Prohibition
As of January 7, 2014 (the effective date of
AD 2013–22–19), no person may install a fuel
boost pump having Gulfstream P/N
1159SCP500–5 on any airplane.
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
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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 ACO, send it to the
attention of the person identified in
paragraph (o)(1) of this AD.
(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) AMOCs approved for AD 2013–22–19,
are approved as AMOCs for the
corresponding provisions of this AD.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (n)(4)(i) and (n)(4)(ii) apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(o) Related Information
(1) For more information about this AD,
contact Ky Phan, Aerospace Engineer,
Propulsion and Services Branch, ACE–118A,
FAA, Atlanta ACO, 1701 Columbia Avenue,
College Park, GA 30337; phone: 404–474–
5536; fax: 404–474–5606; email: ky.phan@
faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on May 17, 2017.
(i) Gulfstream G500 Customer Bulletin 122,
dated April 11, 2012.
(ii) Gulfstream V Maintenance Manual,
Revision 44, dated June 15, 2016:
(A) Table 12, Certification Maintenance
Requirements (CMR), in section 05–10–10,
Airworthiness Limitations, of chapter 05,
Time Limits/Maintenance Checks.
(B) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 28–26–01, Fuel
Boost Pumps—Inspection/Check, of chapter
28, Fuel.
(iii) Gulfstream G500 Maintenance Manual,
Revision 25, dated June 15, 2016:
(A) Table 12, Certification Maintenance
Requirements (CMR), in section 05–10–10,
Airworthiness Limitations, of chapter 05,
Time Limits/Maintenance Checks.
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17537
(B) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of Section 28–26–01, Fuel
Boost Pumps—Inspection/Check, of chapter
28, Fuel.
(iv) Gulfstream G550 Maintenance Manual,
Revision 25, dated June 15, 2016:
(A) Table 12, Certification Maintenance
Requirements (CMR), in section 05–10–10,
Airworthiness Limitations, of chapter 05,
Time Limits/Maintenance Checks.
(B) Task 28–26–01, Fuel Boost Pumps—
Fuel Leak Check, of section 28–26–01, Fuel
Boost Pumps—Inspection/Check, of chapter
28, Fuel.
(4) The following service information was
approved for IBR on January 7, 2014 (78 FR
72554, December 3, 2013).
(i) Gulfstream G550 Customer Bulletin 122,
dated April 11, 2012.
(ii) Gulfstream V Customer Bulletin 197,
dated April 11, 2012.
(iii) General Electric Service Bulletin
31760–28–100, dated February 15, 2011.
(iv) Triumph Service Bulletin SB–TAGV/
GVSP–28–JG0162, dated August 30, 2011.
(5) For Gulfstream, Triumph
Aerostructures, and General Electric Aviation
service information identified in this AD,
contact Gulfstream Aerospace Corporation,
Technical Publications Dept., P.O. Box 2206,
Savannah, GA 31402–2206; telephone 800–
810–4853; fax 912 965–3520; email pubs@
gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm.
(6) You may view 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
31, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–06962 Filed 4–11–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9299; Directorate
Identifier 2016–NM–119–AD; Amendment
39–18851; AD 2017–08–02]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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ACTION:
Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations
Final rule.
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model DHC–8–102,
–103, and –106 airplanes; and Model
DHC–8–200 and DHC–8–300 series
airplanes. This AD was prompted by
reports of incorrect installation of the
auto-ignition system due to crossed
wires at one of the splices in the autorelight system. This AD requires
inspecting the auto-ignition system for
correct wiring, and doing corrective
actions if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective May 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 17, 2017.
ADDRESSES: For service information
identified in this final rule, 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 view this 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9299.
SUMMARY:
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–2016–
9299; 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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Norman Perenson, Aerospace Engineer,
Propulsion and Services Branch, ANE–
173, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7337; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc., Model
DHC–8–102, –103, and –106 airplanes;
and Model DHC–8–200 and DHC–8–300
series airplanes. The NPRM published
in the Federal Register on October 26,
2016 (81 FR 74360) (‘‘the NPRM’’). The
NPRM was prompted by reports of
incorrect installation of the autoignition system due to crossed wires at
one of the splices in the auto-relight
system. The NPRM proposed to require
inspecting the auto-ignition system for
correct wiring, and doing corrective
actions if necessary. We are issuing this
AD to detect and correct incorrect
wiring of the auto-ignition system,
which could result in inability to restart
the engine in flight and consequent
reduced controllability of the airplane.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2013–36,
dated November 19, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc., Model
DHC–8–102, –103, and –106 airplanes;
and Model DHC–8–200 and DHC–8–300
series airplanes. The MCAI states:
There have been reports of incorrect
installation of the auto-ignition system
introduced by MS [ModSum] 8Q100813 of
SB [Service Bulletin] 8–74–02, where wires
crossed at one of the splices in the autorelight system. The incorrect wire installation
may result in the inability to achieve an inflight engine relight when the ignition switch
is selected in the AUTO position.
Bombardier has issued SB 8–74–05 to
introduce an inspection to check for correct
wiring connection and rectification as
required. This [Canadian] AD mandates
incorporation of Bombardier SB 8–74–05.
Corrective actions include
reconnecting any incorrect wiring of the
auto-ignition system and performing a
functional test. You may examine the
MCAI in the AD docket on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2016–9299.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received. The
Air Line Pilots Association,
International (ALPA) supported the
NPRM.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed Bombardier Service
Bulletin 8–74–05, Revision B, dated
April 14, 2014. This service information
describes procedures for inspecting the
auto-ignition system for correct wiring,
and doing corrective actions that
include rewiring if needed, followed by
a functional test of the auto-ignition
system. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 88
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Inspection ........................................................
1 work-hour × $85 per hour = $85 .................
$0
$85
$7,480
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Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations
In addition, we estimate that any
necessary corrective actions will take
about 2 work-hours, for a cost of $170
per product. We have no way of
determining the number of aircraft that
might need these actions.
Authority for This Rulemaking
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD: 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.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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15:14 Apr 11, 2017
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1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
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.
Adoption of the Amendment
PART 39—AIRWORTHINESS
DIRECTIVES
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–08–02 Bombardier, Inc.: Amendment
39–18851; FAA–2016–9299; Directorate
Identifier 2016–NM–119–AD.
(a) Effective Date
This AD is effective May 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
airplanes identified in paragraphs (c) (1), (c)
(2), and (c) (3) of this AD, certificated in any
category, serial numbers 003 through 672
inclusive, on which Bombardier ModSum
8Q100813 or Bombardier Service Bulletin 8–
74–02 is incorporated.
(1) Model DHC–8–102, –103, and –106
airplanes.
(2) Model DHC–8–201 and –202 airplanes.
(3) Model DHC–8–301, –311, and –315
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 74, Ignition.
(e) Reason
This AD was prompted by reports of
incorrect installation of the auto-ignition
system due to crossed wires at one of the
splices in the auto-relight system. We are
issuing this AD to detect and correct
incorrect wiring of the auto-ignition system,
which could result in inability to restart the
engine in flight and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Corrective Actions
Within 2,000 flight hours or 12 months
after the effective date of this AD, whichever
occurs first: Inspect the auto-ignition system
for correct wiring and do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–74–05, Revision B, dated
April 14, 2014. All applicable corrective
actions must be done before further flight.
(h) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Bombardier
Service Bulletin 8–74–05, dated July 12,
2013; or Revision A, dated January 27, 2014.
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17539
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), 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 manager of the New York
ACO, send it to the attention of the person
identified in paragraph (j) (2) of this AD.
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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–36, dated
November 19, 2013, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–9299.
(2) For more information about this AD,
contact the Program Manager, Continuing
Operational Safety, New York ACO, FAA,
1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7300; fax
516–794–5531.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k) (3) and (k) (4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 8–74–05,
Revision B, dated April 14, 2014.
(ii) Reserved.
(3) 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.
(4) You may view 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.
(5) You may view this service information
that is incorporated by reference at the
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12APR1
17540
Federal Register / Vol. 82, No. 69 / Wednesday, April 12, 2017 / Rules and Regulations
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March
31, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–06963 Filed 4–11–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6897; Directorate
Identifier 2015–NM–187–AD; Amendment
39–18853; AD 2017–08–04]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–03–
01, for all Bombardier, Inc. Model CL–
600–2B19 (Regional Jet Series 100 &
440) airplanes. AD 2015–03–01 required
installing additional attaching hardware
on the left and right engine fan cowl
access panels and the nacelle attaching
structures. This new AD requires weight
and balance data to be included in the
Weight and Balance Manual for certain
modified airplanes. This new AD also
requires the weight and balance data to
be used in order to calculate the center
of gravity for affected airplanes. This AD
was prompted by updates to the weight
and balance data needed to calculate the
center of gravity for affected airplanes.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective May 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 17, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of March 17, 2015 (80 FR
7298, February 10, 2015).
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
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SUMMARY:
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Jkt 241001
telephone 514–855–5000; fax 514–855–
7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com. You may view
this 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6897.
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–2016–
6897; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
and Mechanical Systems Branch, ANE–
171, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7329; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2015–03–01,
Amendment 39–18097 (80 FR 7298,
February 10, 2015) (‘‘AD 2015–03–01’’).
AD 2015–03–01 applied to all
Bombardier, Inc. Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. The NPRM published in the
Federal Register on June 8, 2016 (81 FR
36813). The NPRM was prompted by
updates to the weight and balance data
needed to calculate the center of gravity
for affected airplanes. The NPRM
proposed to continue to require
installing additional attaching hardware
on the left and right engine fan cowl
access panels and the nacelle attaching
structures. The NPRM also proposed to
require weight and balance data to be
included in the Weight and Balance
Manual and applicable logbooks for
certain modified airplanes. We are
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
issuing this AD to prevent damage to the
fuselage and flight control surfaces from
dislodged engine fan cowl access
panels, and prevent incorrect weight
and balance calculations. Incorrect
weight and balance calculations may
shift the center of gravity beyond
approved design parameters and affect
in-flight control, which could endanger
passengers and crew.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2014–20R1,
dated August 12, 2015 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Bombardier, Inc. Model CL–600–
2B19 (Regional Jet Series 100 & 440)
airplanes. The MCAI states:
There have been a number of engine fan
cowl panel dislodgement incidents reported
on the Bombardier CL–600–2B19 aeroplane
fleet. The dislodged panels may cause
damage to the fuselage and flight control
surfaces of the aeroplane. Also, the debris
from a dislodged panel may result in runway
contamination and has the potential of
causing injury on the ground.
Although the majority of the subject panel
dislodgements were reported on the first or
second flight after an engine maintenance
task was performed that required removal
and reinstallation of the subject panels, the
frequency of the dislodgements indicates that
the existing attachment design is prone to
human (maintenance) error.
In order to mitigate the potential safety
hazard of the subject panel dislodgement,
Bombardier had issued Service Bulletin (SB)
601R–71–034 to install additional fasteners
for the attachment of the engine fan cowl
panels to the nacelle’s structure. Compliance
of the above SB was mandated by the original
issue of [Canadian] AD CF–2014–20 dated 9
July 2014 [which corresponded to FAA AD
2015–03–01].
Bombardier has now revised the SB 601R–
71–034 (to Revision C) requiring weight and
balance data to be included in the Weight
and Balance manual for aeroplanes modified
per the subject SB. This revised [Canadian]
AD is issued to mandate compliance with SB
601R–71–034, Rev C.
Required actions also include the
retained actions of modifying the engine
fan cowl access panel. You may
examine the MCAI in the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6897.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the NPRM and the FAA’s
response.
E:\FR\FM\12APR1.SGM
12APR1
Agencies
[Federal Register Volume 82, Number 69 (Wednesday, April 12, 2017)]
[Rules and Regulations]
[Pages 17537-17540]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06963]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9299; Directorate Identifier 2016-NM-119-AD;
Amendment 39-18851; AD 2017-08-02]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 17538]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; and Model
DHC-8-200 and DHC-8-300 series airplanes. This AD was prompted by
reports of incorrect installation of the auto-ignition system due to
crossed wires at one of the splices in the auto-relight system. This AD
requires inspecting the auto-ignition system for correct wiring, and
doing corrective actions if necessary. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective May 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 17,
2017.
ADDRESSES: For service information identified in this final rule,
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 view this 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. It is also available on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-9299.
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-2016-
9299; 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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Norman Perenson, Aerospace Engineer,
Propulsion and Services Branch, ANE-173, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7337; fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Bombardier, Inc.,
Model DHC-8-102, -103, and -106 airplanes; and Model DHC-8-200 and DHC-
8-300 series airplanes. The NPRM published in the Federal Register on
October 26, 2016 (81 FR 74360) (``the NPRM''). The NPRM was prompted by
reports of incorrect installation of the auto-ignition system due to
crossed wires at one of the splices in the auto-relight system. The
NPRM proposed to require inspecting the auto-ignition system for
correct wiring, and doing corrective actions if necessary. We are
issuing this AD to detect and correct incorrect wiring of the auto-
ignition system, which could result in inability to restart the engine
in flight and consequent reduced controllability of the airplane.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-36, dated November 19, 2013 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Bombardier, Inc., Model DHC-8-
102, -103, and -106 airplanes; and Model DHC-8-200 and DHC-8-300 series
airplanes. The MCAI states:
There have been reports of incorrect installation of the auto-
ignition system introduced by MS [ModSum] 8Q100813 of SB [Service
Bulletin] 8-74-02, where wires crossed at one of the splices in the
auto-relight system. The incorrect wire installation may result in
the inability to achieve an in-flight engine relight when the
ignition switch is selected in the AUTO position.
Bombardier has issued SB 8-74-05 to introduce an inspection to
check for correct wiring connection and rectification as required.
This [Canadian] AD mandates incorporation of Bombardier SB 8-74-05.
Corrective actions include reconnecting any incorrect wiring of the
auto-ignition system and performing a functional test. You may examine
the MCAI in the AD docket on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2016-9299.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received. The Air Line Pilots
Association, International (ALPA) supported the NPRM.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed, except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Bombardier Service Bulletin 8-74-05, Revision B, dated
April 14, 2014. This service information describes procedures for
inspecting the auto-ignition system for correct wiring, and doing
corrective actions that include rewiring if needed, followed by a
functional test of the auto-ignition system. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 88 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................... 1 work-hour x $85 per $0 $85 $7,480
hour = $85.
----------------------------------------------------------------------------------------------------------------
[[Page 17539]]
In addition, we estimate that any necessary corrective actions will
take about 2 work-hours, for a cost of $170 per product. We have no way
of determining the number of aircraft that might need these actions.
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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD: 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2017-08-02 Bombardier, Inc.: Amendment 39-18851; FAA-2016-9299;
Directorate Identifier 2016-NM-119-AD.
(a) Effective Date
This AD is effective May 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., airplanes identified in
paragraphs (c) (1), (c) (2), and (c) (3) of this AD, certificated in
any category, serial numbers 003 through 672 inclusive, on which
Bombardier ModSum 8Q100813 or Bombardier Service Bulletin 8-74-02 is
incorporated.
(1) Model DHC-8-102, -103, and -106 airplanes.
(2) Model DHC-8-201 and -202 airplanes.
(3) Model DHC-8-301, -311, and -315 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 74, Ignition.
(e) Reason
This AD was prompted by reports of incorrect installation of the
auto-ignition system due to crossed wires at one of the splices in
the auto-relight system. We are issuing this AD to detect and
correct incorrect wiring of the auto-ignition system, which could
result in inability to restart the engine in flight and consequent
reduced controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Corrective Actions
Within 2,000 flight hours or 12 months after the effective date
of this AD, whichever occurs first: Inspect the auto-ignition system
for correct wiring and do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 8-74-05, Revision B, dated April 14, 2014. All
applicable corrective actions must be done before further flight.
(h) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Bombardier Service Bulletin 8-74-05,
dated July 12, 2013; or Revision A, dated January 27, 2014.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), 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 manager of the New York ACO, send it to the
attention of the person identified in paragraph (j) (2) of this AD.
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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2013-36, dated November
19, 2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2016-9299.
(2) For more information about this AD, contact the Program
Manager, Continuing Operational Safety, New York ACO, FAA, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7300; fax 516-794-5531.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k) (3) and (k) (4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 8-74-05, Revision B, dated April
14, 2014.
(ii) Reserved.
(3) 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.
(4) You may view 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.
(5) You may view this service information that is incorporated
by reference at the
[[Page 17540]]
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 31, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-06963 Filed 4-11-17; 8:45 am]
BILLING CODE 4910-13-P