[Federal Register Volume 80, Number 201 (Monday, October 19, 2015)]
[Proposed Rules]
[Pages 63141-63145]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-26222]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-3988; Directorate Identifier 2015-NM-005-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-17-
51, for certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014-
17-51 currently requires inspecting the inboard flap fasteners of the
hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to
determine the orientation and condition of the fasteners, as
applicable, and replacement or repetitive inspections of the fasteners
if necessary. AD 2014-17-51 also provides for optional terminating
action for the requirements of that AD. Since we issued AD 2014-17-51,
we have determined that additional action is necessary. This proposed
AD would also require accomplishment of the previously optional
terminating action. We are proposing this AD to detect and correct
incorrectly oriented or fractured fasteners, which could result in
premature failure of the fasteners attaching the inboard flap hinge-box
forward fitting; failure of the fasteners could lead to the detachment
of the flap hinge box and the flap surface, and consequent loss of
control of the airplane.
DATES: We must receive comments on this proposed AD by December 3,
2015.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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.
[[Page 63142]]
For service information identified in this proposed AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email
[email protected]; Internet http://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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3988; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer,
Propulsion and Services Branch, ANE-173, 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:
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-2015-3988;
Directorate Identifier 2015-NM-005-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 http://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
On October 13, 2014, we issued AD 2014-17-51, Amendment 39-17999
(79 FR 64088, October 28, 2014). AD 2014-17-51 requires actions
intended to address an unsafe condition on certain Bombardier, Inc.
Model CL-600-2B16 airplanes.
The preamble to AD 2014-17-51, Amendment 39-17999 (79 FR 64088,
October 28, 2014), explains that we consider the requirements ``interim
action'' and were considering further rulemaking. We now have
determined that further rulemaking is indeed necessary, and this
proposed AD follows from that determination.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-27R1, dated August 29, 2014 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Bombardier, Inc. Model CL-600-
2B16 airplanes. The MCAI states:
There have been three in-service reports on 604 Variant
aeroplanes of a fractured fastener head on the inboard flap hinge-
box forward fitting at Wing Station (WS) 76.50, found during a
routine maintenance inspection. Investigation revealed that the
installation of these fasteners on the inboard flap hinge-box
forward fittings at WS 76.50 and WS 127.25, on both wings, does not
conform to the engineering drawings. Incorrect installation may
result in premature failure of the fasteners attaching the inboard
flap hinge-box forward fitting. Failure of the fasteners could lead
to the detachment of the flap hinge box and consequently the
detachment of the flap surface. The loss of a flap surface could
adversely affect the continued safe operation of the aeroplane.
The original issue of [Canadian] AD CF-2013-39 [http://www.regulations.gov/#!documentDetail;D=FAA-2014-0054-0002] [which
corresponds to FAA AD 2014-03-17, Amendment 39-17754 (79 FR 9389,
February 19, 2014)] mandated a detailed visual inspection (DVI) of
each inboard flap hinge-box forward fitting, on both wings, and
rectification as required. Incorrectly oriented fasteners require
repetitive inspections until the terminating action is accomplished.
After the issuance of [Canadian] AD CF-2013-39, there has been
one reported incident on a 604 Variant aeroplane where four
fasteners were found fractured on the same flap hinge-box forward
fitting. The investigation determined that the fasteners were
incorrectly installed.
The original issue of this [Canadian] AD was issued to reduce
the initial and repetitive inspection intervals previously mandated
in [Canadian] AD CF-2013-39, and to impose replacement of the
incorrectly oriented fasteners within 24 months. The CL-600-1A11, -
2A12 and -2B16 (601-3A/-3R Variant) aeroplanes are addressed through
[Canadian] AD CF-2013-39R1.
Revision 1 of this [Canadian] AD is issued to clarify the
requirements for the initial and repetitive inspections.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3988.
Related Service Information Under 1 CFR Part 51
Bombardier has issued Alert Service Bulletins:
A604-57-006, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013,
A605-57-004, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013, and
The service information describes detailed visual inspection of
each inboard flap fastener of the hinge-box forward fitting at WS 76.50
and WS 127.25, on both wings, and, if necessary, replacement of the
fasteners. 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 of this
NPRM.
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 285 airplanes of U.S.
registry.
The actions required by AD 2014-17-51, Amendment 39-17999 (79 FR
64088, October 28, 2014), and retained in this proposed AD take about 1
work-hour per product, at an average labor rate of $85 per work-hour.
Required parts cost about $0 per product. Based on these figures, the
estimated cost of the actions that are required by AD 2014-17-51 is $85
per product.
We also estimate that it would take about 58 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $753
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $1,619,655, or $5,683 per product.
[[Page 63143]]
In addition, we estimate that any necessary follow-on actions would
take about 58 work-hours and require parts costing $753, for a cost of
$5,683 per product. We have no way of determining the number of
aircraft that might need this action.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), and
adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2015-3988; Directorate Identifier
2015-NM-005-AD.
(a) Comments Due Date
We must receive comments by December 3, 2015.
(b) Affected ADs
(1) This AD replaces AD 2014-17-51, Amendment 39-17999 (79 FR
64088, October 28, 2014).
(2) This AD affects AD 2014-03-17, Amendment 39-17754 (79 FR
9389, February 19, 2014), only for the airplanes identified in
paragraph (c) of this AD.
(c) Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B16 airplanes,
certificated in any category, serial numbers 5301 through 5665
inclusive, and 5701 through 5920 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of fractured fastener heads on
the inboard flap hinge-box forward fitting at Wing Station (WS)
76.50 due to incorrect installation. We are issuing this AD to
detect and correct incorrectly oriented or fractured fasteners,
which could result in premature failure of the fasteners attaching
the inboard flap hinge-box forward fitting; failure of the fasteners
could lead to the detachment of the flap hinge box and the flap
surface, and consequent loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With New Service Information: Airplanes Not
Previously Inspected
This paragraph restates the requirements of paragraph (g) of AD
2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), with
new service information. For airplanes on which the actions required
by AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19,
2014), have not been done as of November 12, 2014 (the effective
date of AD 2014-17-51): Within 10 flight cycles after November 12,
2014, or within 100 flight cycles after March 6, 2014 (the effective
date of AD 2014-03-17, Amendment 39-17754 (79 FR 9389, February 19,
2014)), whichever occurs first, do a detailed visual inspection of
each inboard flap fastener of the hinge-box forward fitting at WS
76.50 and WS 127.25, on both wings, to determine if the fasteners
are correctly oriented and intact (non-fractured, with intact
fastener head). Do the inspection in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
A604-57-006, Revision 01, dated September 26, 2013, including
Appendices 1 and 2, dated September 26, 2013, Revision 02, dated
January 22, 2014, including Appendices 1 and 2, dated September 26,
2013, or Revision 04, dated November 12, 2014, including Appendices
1 and 2, dated September 26, 2013 (for serial numbers 5301 through
5665 inclusive); or Bombardier Alert Service Bulletin A605-57-004,
Revision 01, dated September 26, 2013, including Appendices 1 and 2,
dated September 26, 2013, Revision 02, dated January 22, 2014,
including Appendices 1 and 2, dated September 26, 2013, or Revision
04, dated November 12, 2014, including Appendices 1 and 2, dated
September 26, 2013 (for serial numbers 5701 through 5920 inclusive).
As of the effective date of this AD, only use Bombardier Alert
Service Bulletin A604-57-006, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013; or
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated
November 12, 2014, including Appendices 1 and 2, dated September 26,
2013; as applicable; for the actions required by this paragraph.
(1) If all fasteners are found intact and correctly oriented, no
further action is required by this AD.
(2) If any fastener is found fractured: Before further flight,
remove and replace all forward and aft fasteners at WS 76.50 and WS
127.25, regardless of condition or orientation, on both wings, in
accordance with the Accomplishment Instructions of the applicable
service information identified in paragraph (g) of this AD. As of
the effective date of this AD, only use Bombardier Alert Service
Bulletin A604-57-006, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013; or
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated
November 12, 2014, including Appendices 1 and 2, dated September 26,
2013; as applicable; for the actions required by this paragraph.
After replacement of all fasteners as required by this paragraph of
this AD, no further action is required by this AD.
[[Page 63144]]
(3) If any incorrectly oriented but intact fastener is found,
and no fractured fastener is found, repeat the inspection required
by paragraph (g) of this AD thereafter at intervals not to exceed 10
flight cycles, until the requirements of paragraph (i)(1) or (k) of
this AD have been done.
(h) Retained Actions, With New Service Information: Airplanes
Previously Inspected, Having Incorrectly Oriented Fastener(s)
This paragraph restates the requirements of paragraph (h) of AD
2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014), with
new service information. For airplanes on which an inspection
required by paragraph (g) or (j) of AD 2014-03-17, Amendment 39-
17754 (79 FR 9389, February 19, 2014), has been done as of November
12, 2014 (the effective date of AD 2014-17-51), and on which any
incorrectly oriented fastener, but no fractured fastener, was found:
Except as provided by paragraph (i)(3) of this AD, do a detailed
visual inspection of all inboard flap fasteners of the hinge-box
forward fitting at WS 76.50 and WS 127.25, on both wings, to
determine if the fasteners are intact (non-fractured, with intact
fastener head). Inspect within 10 flight cycles after November 12,
2014, or within 100 flight cycles after the most recent inspection
done as required by AD 2014-03-17, whichever occurs first. Inspect
in accordance with the Accomplishment Instructions of the applicable
service information identified in paragraph (g) of this AD. As of
the effective date of this AD, only use Bombardier Alert Service
Bulletin A604-57-006, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013; or
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated
November 12, 2014, including Appendices 1 and 2, dated September 26,
2013; as applicable; for the actions required by this paragraph.
(1) If all fasteners are found intact, repeat the inspection
thereafter at intervals not to exceed 10 flight cycles, until the
requirements of paragraph (i)(1) or (k) of this AD have been done.
(2) If any fastener is found fractured: Before further flight,
remove and replace all forward and aft fasteners at WS 76.50 and WS
127.25, regardless of condition or orientation, on both wings, in
accordance with the Accomplishment Instructions of the applicable
service information identified in paragraph (g) of this AD. As of
the effective date of this AD, only use Bombardier Alert Service
Bulletin A604-57-006, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013; or
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated
November 12, 2014, including Appendices 1 and 2, dated September 26,
2013; as applicable; for the actions required by this paragraph.
After replacement of all fasteners as required by this paragraph, no
further action is required by this AD.
(i) Retained Terminating Action, With New Service Information
This paragraph restates the terminating action specified in
paragraph (i) of AD 2014-17-51, Amendment 39-17999 (79 FR 64088,
October 28, 2014), with new service information.
(1) Replacement of all forward and aft fasteners at WS 76.50 and
WS 127.25, on both wings, in accordance with the Accomplishment
Instructions of the applicable service information identified in
paragraph (g) of this AD, terminates the requirements of this AD. As
of the effective date of this AD, only use Bombardier Alert Service
Bulletin A604-57-006, Revision 04, dated November 12, 2014,
including Appendices 1 and 2, dated September 26, 2013; or
Bombardier Alert Service Bulletin A605-57-004, Revision 04, dated
November 12, 2014, including Appendices 1 and 2, dated September 26,
2013; as applicable; for the actions specified in this paragraph.
(2) Accomplishment of the applicable requirements of this AD
constitutes terminating action for the requirements of AD 2014-03-
17, Amendment 39-17754 (79 FR 9389, February 19, 2014), for that
airplane only.
(3) Replacement of all fractured and incorrectly oriented
fasteners before November 12, 2014 (the effective date of AD 2014-
17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014)), as
provided by paragraph (i) or (k) of AD 2014-03-17, Amendment 39-
17754 (79 FR 9389, February 19, 2014), is acceptable for compliance
with the requirements of this AD.
(j) Retained Special Flight Permit Prohibition
This paragraph restates the requirements of paragraph (j) of AD
2014-17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014).
Special flight permits to operate the airplane to a location where
the airplane can be repaired in accordance with sections 21.197 and
21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) are not allowed.
(k) New Requirement of This AD: Post-Inspection Fastener Replacement
For airplanes on which incorrectly oriented fasteners were found
during any inspection required by paragraph (g), (g)(3), (h), or
(h)(1) of this AD, but none were found to be fractured: Within 24
months after the effective date of this AD, remove and replace all
forward and aft fasteners at WS 76.50 and WS 127.25, regardless of
condition or orientation, on both wings, in accordance with the
Accomplishment Instructions of Bombardier Alert Service Bulletin
A604-57-006, Revision 04, dated November 12, 2014, including
Appendices 1 and 2, dated September 26, 2013 (for serial numbers
5301 through 5665 inclusive); or Bombardier Alert Service Bulletin
A605-57-004, Revision 04, dated November 12, 2014, including
Appendices 1 and 2, dated September 26, 2013 (for serial numbers
5701 through 5920 inclusive). Accomplishing the requirements of this
paragraph terminates the requirements of this AD.
(l) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (g), (h), and (i)(1) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information identified in paragraphs (l)(1)(i) and
(l)(1)(ii) of this AD, which are not incorporated by reference in
this AD.
(i) Bombardier Alert Service Bulletin A604-57-006, Revision 03,
dated August 19, 2014, including Appendices 1 and 2, dated September
26, 2013.
(ii) Bombardier Alert Service Bulletin A605-57-004, Revision 03,
dated August 19, 2014, including Appendices 1 and 2, dated September
26, 2013.
(2) This paragraph provides credit for actions required by
paragraph (k) of this AD, if those actions were done before the
effective date of this AD using the applicable service information
identified in paragraphs (l)(2)(i) through (l)(2)(iv) of this AD.
(i) Bombardier Alert Service Bulletin A604-57-006, Revision 01,
dated September 26, 2013, including Appendices 1 and 2, dated
September 26, 2013, which is incorporated by reference in AD 2014-
03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014).
(ii) Bombardier Alert Service Bulletin A604-57-006, Revision 02,
dated January 22, 2014, including Appendices 1 and 2, dated
September 26, 2013, which is incorporated by reference in AD 2014-
17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014).
(iii) Bombardier Alert Service Bulletin A605-57-004, Revision
01, dated September 26, 2013, including Appendices 1 and 2, dated
September 26, 2013, which is incorporated by reference in AD 2014-
03-17, Amendment 39-17754 (79 FR 9389, February 19, 2014).
(iv) Bombardier Alert Service Bulletin A604-57-004, Revision 02,
dated January 22, 2014, including Appendices 1 and 2, dated
September 26, 2013, which is incorporated by reference in AD 2014-
17-51, Amendment 39-17999 (79 FR 64088, October 28, 2014).
(m) 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 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.
(i) 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.
(ii) AMOCs previously approved for AD 2014-17-51, Amendment 39-
17999 (79 FR 64088, October 28, 2014), are acceptable for the
corresponding requirements of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from
[[Page 63145]]
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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Emergency Airworthiness Directive CF-2014-27R1,
dated August 29, 2014, for related information. This MCAI may be
found in the AD docket on the Internet at http://www.regulations.gov
by searching for and locating Docket No. FAA-2015-3988.
(2) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514 855-
7401; email [email protected]; Internet http://www.bombardier.com. 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.
Issued in Renton, Washington, on October 6, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-26222 Filed 10-16-15; 8:45 am]
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