Airworthiness Directives; Bombardier, Inc. Airplanes, 89367-89371 [2016-28597]
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Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations
agency to take corrective action. OPM
may suspend or revoke a delegation
agreement established under 5 U.S.C.
1104(a)(2) at any time if it determines
that the agency is not adhering to the
provisions of the agreement. OPM may
suspend or withdraw any authority
granted under this chapter to an agency,
including any authority granted by
delegation agreement, when OPM finds
that the agency has not complied with
qualification standards OPM has issued,
instructions OPM has published, or the
regulations in this chapter of the
regulation. OPM also may suspend or
withdraw these authorities when it
determines that doing so is in the
interest of the civil service for any other
reason.
■ 3. Subpart C is revised to read as
follows:
Subpart C—Employee Surveys
Sec.
250.301 Definitions.
250.302 Survey requirements.
250.303 Availability of results.
Subpart C—Employee Surveys
Authority: 5 U.S.C. 105; 5 U.S.C. 7101
note; Public Law 108–136
§ 250.301
Definitions.
Agency means an Executive agency,
as defined in 5 U.S.C. 105.
§ 250.302
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Survey requirements.
(a) Each executive agency must
conduct an annual survey of its
employees to assess topics outlined in
the National Defense Authorization Act
for Fiscal Year 2004, Public Law 108–
136, sec. 1128, codified at 5 U.S.C. 7101.
(1) Each executive agency may
include additional survey questions
unique to the agency in addition to the
employee survey questions prescribed
by OPM under paragraph (a)(2) of this
section.
(2) The 16 prescribed survey
questions are listed in the following
table:
(i) Leadership and Management practices that contribute to agency performance
My work unit has the job-relevant skills necessary to accomplish organizational goals.
Managers communicate the goals of the organization.
I believe the results of this survey will be used to make my agency a better place to work.
(ii) Employee Satisfaction with—
(A) ..............................
(B) ..............................
(C) ..............................
(D) ..............................
(E) ..............................
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§ 250.303
Leadership Policies and Practices:
How satisfied are you with your involvement in decisions that affect your work?
How satisfied are you with the information you receive from management on what is going on in your organization?
Considering everything, how satisfied are you with your organization?
Work Environment:
The people I work with cooperate to get the job done.
My workload is reasonable.
Considering everything, how satisfied are you with your job?
I can disclose a suspected violation of any law, rule or regulation without fear of reprisal.
Rewards and Recognition:
In my work unit, differences in performance are recognized in a meaningful way.
How satisfied are you with the recognition you receive for doing a good job?
Opportunities for professional development and growth:
I am given a real opportunity to improve my skills in my organization.
My talents are used well in the workplace.
Opportunity to contribute to achieving organizational mission:
I know how my work relates to the agency’s goals.
I recommend my organization as a good place to work.
Availability of results.
(a) Each agency will make the results
of its annual survey available to the
public and post the results on its Web
site unless the agency head determines
that doing so would jeopardize or
negatively impact national security. The
posted survey results will include the
following:
(1) The agency’s evaluation of its
survey results;
(2) How the survey was conducted;
(3) Description of the employee
sample, unless all employees are
surveyed;
(4) The survey questions and response
choices with the prescribed questions
identified;
(5) The number of employees
surveyed and number of employees who
completed the survey; and
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(6) The number of respondents for
each survey question and each response
choice.
(b) Data must be collected by
December 31 of each calendar year.
Each agency must post the beginning
and ending dates of its employee survey
and either the survey results described
in paragraph (a) of this section, or a
statement noting the decision not to
post, no later than 120 days after the
agency completes survey
administration. OPM may extend this
date under unusual circumstances.
[FR Doc. 2016–29600 Filed 12–9–16; 8:45 am]
BILLING CODE 6325–39–P
PO 00000
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8178; Directorate
Identifier 2015–NM–197–AD; Amendment
39–18721; AD 2016–24–04]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–400
series airplanes. This AD was prompted
SUMMARY:
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by a determination by the manufacturer
that shims might not have been installed
between certain longerons and longeron
joint fittings. This AD requires various
repetitive and detailed visual
inspections of the affected areas and
corrective actions if necessary. This AD
also provides terminating action for
certain repetitive inspections. We are
issuing this AD to address the unsafe
condition on these products.
This AD is effective January 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 17, 2017.
DATES:
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–
8178.
ADDRESSES:
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–
8178; 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.
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.
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FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
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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–8–400 series airplanes. The NPRM
published in the Federal Register on
July 15, 2016 (81 FR 45995) (‘‘the
NPRM’’). The NPRM was prompted by
a determination by the manufacturer
that shims might not have been installed
between certain longerons and longeron
joint fittings. The NPRM proposed to
require repetitive inspections of the
external surface of the fuselage skin
panel for loose or working fasteners, and
corrective action if necessary; a detailed
visual inspection of the longeron joint
fittings for the existence of shims and,
if necessary, repetitive inspections of
the longeron and the longeron joint
fittings for any cracking, and corrective
action if necessary. We are issuing this
AD to detect and correct missing shims
between the longerons and longeron
joint fittings, which could result in a
gapping condition and lead to stress
corrosion cracking of the longeron joint
fittings, and could adversely affect the
structural integrity of the wing-tofuselage attachment joints.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2015–22,
dated August 3, 2015 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model
DHC–8–400 series airplanes. The MCAI
states:
The aeroplane manufacturer has
determined that shims may not have been
installed between the longerons and longeron
joint fittings at fuselage station X373–380,
stringers 7 on the left and right hand side, on
certain aeroplanes. The missing shims could
result in a gapping condition and could lead
to stress corrosion cracking of the longeron
joint fittings.
Failure of the longeron joint fitting could
compromise the structural integrity of the
wing-to-fuselage attachment joint.
This [Canadian] AD mandates inspections
in the area of the longeron joint fittings.
Corrective actions include replacing any
loose or working fasteners (fasteners
that show signs of wear, fatigue, or
corrosion), repairing any structural
damage, and replacing any cracked
longeron or longeron with an amplitude
of 50% or more of the calibration signal.
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–
8178.
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Incorporate Revised Service
Information
Horizon Air requested that we
incorporate Bombardier Service Bulletin
84–53–65, Revision A, dated February
22, 2016.
We agree with the commenter’s
request to incorporate the revised
service information because Bombardier
Service Bulletin 84–53–65, Revision A,
dated February 22, 2016, is the latest
revision. We have changed all service
bulletin references in this final rule to
Bombardier Service Bulletin 84–53–65,
Revision A, dated February 22, 2016.
Request To Provide Credit for Previous
Actions
Horizon Air requested that we add a
paragraph addressing credit for previous
actions.
We agree. Since we have incorporated
revised service information in this final
rule, we agree to provide credit for
required tasks performed before the
effective date of this AD using
Bombardier Service Bulletin 84–53–65,
dated February 27, 2015. We have
added a new paragraph (n) to this AD
to provide credit for previous actions
and redesignated subsequent paragraphs
accordingly.
Additional Changes to NPRM
We have reformatted paragraph (l) in
this AD to clarify the requirements.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and 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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under
1 CFR Part 51
We reviewed Bombardier Service
Bulletin 84–53–65, Revision A, dated
February 22, 2016. The service
information describes procedures for
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inspections of the external surface of the
fuselage skin panel for loose or working
fasteners; a detailed visual inspection of
the longeron joint fittings for the
existence of shims; high frequency eddy
current inspections of the longeron and
the longeron joint fittings for any
cracking; and replacement of longeron
fittings, shims, and 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.
Costs of Compliance
We estimate that this AD affects 76
airplanes of U.S. registry.
We also estimate that it will take
about 2 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $12,920, or $170 per
product.
In addition, we estimate that any
necessary follow-on actions will take
about 3 work-hours for the inspection
for missing shims, 9 work-hours for the
replacement of longeron fittings and
shims, and 1 work-hour for a reporting
requirement; and would require parts
costing $3,222; for a cost of up to $4,327
per product. We have no way of
determining the number of aircraft that
might need these actions. We have
received no definitive data that will
enable us to provide cost estimates for
repair of loose or working fasteners or
structural damage specified in this AD.
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Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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Authority for This Rulemaking
§ 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.
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■
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
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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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2016–24–04 Bombardier, Inc: Amendment
39–18721; Docket No. FAA–2016–8178;
Directorate Identifier 2015–NM–197–AD.
(a) Effective Date
This AD is effective January 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–400, –401, and –402 airplanes,
certificated in any category, serial numbers
4156 through 4453 inclusive, 4456, and 4457.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a determination
by the manufacturer that shims might not
have been installed between certain
longerons and longeron joint fittings. We are
issuing this AD to detect and correct missing
shims between the longerons and longeron
joint fittings, which could result in a gapping
condition and lead to stress corrosion
cracking of the longeron joint fittings, and
could adversely affect the structural integrity
of the wing-to-fuselage attachment joints.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection of the External Surface of the
Fuselage Skin Panels
At the time specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable, do a detailed
visual inspection of the external surface of
the fuselage skin panel for loose or working
fasteners (fasteners that show signs of wear,
fatigue, or corrosion) and structural damage,
in accordance with paragraph 3.B. of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–53–65, Revision A, dated
February 22, 2016.
(1) For airplanes that have accumulated
less than 10,000 total flight hours, or less
than 5 years in service since new, as of the
effective date of this AD: Prior to
accumulating 12,000 total flight hours or 6
years in service since new, whichever occurs
first.
(2) For airplanes that have accumulated
10,000 total flight hours or more, or 5 years
or more in service since new, as of the
effective date of this AD: Within 2,000 flight
hours or 12 months after the effective date of
this AD, whichever occurs first.
(h) Corrective Actions
If any loose or working fastener or any
structural damage is found during any
inspection required by this AD: Before
further flight, repair using a method
approved by the Manager, New York Aircraft
Certification Office (ACO), FAA; or Transport
Canada Civil Aviation (TCCA); or
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Bombardier, Inc.’s TCCA Design Approval
Organization (DAO); and thereafter do the
inspections required by paragraph (i) of this
AD. Accomplishment of a repair in
accordance with a method approved by the
Manager, New York ACO, FAA; or TCCA; or
Bombardier, Inc.’s TCCA DAO terminates the
repetitive inspections required by paragraph
(i) of this AD for the repaired area only.
(i) Repetitive Detailed Visual Inspections
Repeat the detailed visual inspection
required by the introductory text to
paragraph (g) of this AD at intervals not to
exceed 12 months or 2,000 flight cycles,
whichever occurs first after accomplishment
of the most recent inspection, until the
actions required by the introductory text to
paragraph (j) of this AD are done.
(j) Inspection for Missing Shims
At the time specified in paragraph (j)(1) or
(j)(2) of this AD, as applicable, do a detailed
visual inspection of the longeron joint fittings
for the existence of shims, in accordance
with paragraph 3.C. of the Accomplishment
Instructions of Bombardier Service Bulletin
84–53–65, Revision A, dated February 22,
2016.
(1) For airplanes that have accumulated
less than 10,000 total flight hours, or less
than 5 years in service since new, as of the
effective date of this AD: Prior to
accumulating 18,000 total flight hours or 9
years in service since new, whichever occurs
first.
(2) For airplanes that have accumulated
10,000 total flight hours or more, or 5 years
or more in service since new, as of the
effective date of this AD: Within 8,000 flight
hours or 4 years after the effective date of this
AD, whichever occurs first; but not to exceed
30,000 total flight hours or 144 months in
service since new, whichever occurs first.
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(k) Airplanes With Installed Shims: No
Further Action Required
If the inspection required by the
introductory text to paragraph (j) of this AD
reveals that shims are installed in the
longeron joint fittings, no further action is
required by this AD.
(l) Airplanes With Missing Shims: High
Frequency Eddy Current (HFEC) Inspections
and Corrective Actions
If the inspection required by the
introductory text to paragraph (j) of this AD
reveals that any shim is missing from the
longeron joint fittings: Before further flight,
do a high frequency eddy current (HFEC)
inspection of the longeron and the longeron
joint fittings for any cracking, in accordance
with paragraph 3.D. of the Accomplishment
Instructions of Bombardier Service Bulletin
84–53–65, Revision A, dated February 22,
2016.
(1) If any crack is found, or if any
indication with an amplitude of 50% or more
of the calibration signal is found, do the
actions specified in paragraphs (l)(1)(i) and
(l)(1)(ii) of this AD.
(i) Before further flight: Replace the
longeron joint fittings, in accordance with
paragraph 3.E. of the Accomplishment
Instructions of Bombardier Service Bulletin
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84–53–65, Revision A, dated February 22,
2016.
(ii) At the applicable time specified in
paragraph (l)(1)(ii)(A) or (l)(1)(ii)(B) of this
AD: Report the inspection results to
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.
(A) If the inspection was done on or after
the effective date of this AD: Report within
30 days after that inspection.
(B) If the inspection was done before the
effective date of this AD: Report within 30
days after the effective date of this AD.
(2) If no crack or indication with an
amplitude of 50% or more of the calibration
signal is found: Repeat the HFEC inspection
required by the introductory text to
paragraph (l) of this AD at intervals not to
exceed 12,000 flight hours or 6 years,
whichever occurs first after accomplishment
of the most recent HFEC inspection, in
accordance with paragraph 3.D. of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–53–65, Revision A, dated
February 22, 2016.
(m) Terminating Action for Repetitive HFEC
Inspections
Replacement of the longeron joint fittings,
in accordance with paragraph 3.E. of the
Accomplishment Instructions of Bombardier
Service Bulletin 84–53–65, Revision A, dated
February 22, 2016, constitutes terminating
action for the repetitive HFEC inspections
required by paragraph (l)(2) of this AD.
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g), (i), (j), (k), (l), and
(m) of this AD, if those actions were
performed before the effective date of this AD
using Bombardier Service Bulletin 84–53–65,
dated February 27, 2015.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York 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. 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) 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 TCCA; or Bombardier, Inc.’s TCCA
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DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2015–22, dated
August 3, 2015, 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–
2016–8178.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) 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 84–53–65,
Revision A, dated February 22, 2016.
(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
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.
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Issued in Renton, Washington, on
November 17, 2016.
Phil Forde,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
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–
5598.
[FR Doc. 2016–28597 Filed 12–9–16; 8:45 am]
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–
5598; 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 (phone: 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: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: Bill.Ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5598; Directorate
Identifier 2016–NM–001–AD; Amendment
39–18735; AD 2016–25–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–22–
02 for certain The Boeing Company
Model 747–400, –400D, and –400F
series airplanes. AD 2012–22–02
required measuring the web at station
(STA) 320 and, depending on findings,
various inspections for cracks and
missing fasteners, web and fastener
replacement, and related investigative
and corrective actions if necessary. This
new AD requires, for certain airplanes,
replacement of the web, including
related investigative and corrective
actions if necessary. This AD was
prompted by a determination that there
were no inspection or repair procedures
included in AD 2012–22–02 for
airplanes with a certain crown frame
web thickness. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective January 17,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 17, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone: 206–544–5000,
extension 1; fax: 206–766–5680;
Internet: https://
www.myboeingfleet.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,
mstockstill on DSK3G9T082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:18 Dec 09, 2016
Jkt 241001
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–22–02,
Amendment 39–17238 (77 FR 69739,
November 21, 2012) (‘‘AD 2012–22–
02’’). AD 2012–22–02 applied to certain
The Boeing Company Model 747–400,
–400D, and –400F series airplanes. The
NPRM published in the Federal
Register on April 28, 2016 (81 FR
25357) (‘‘the NPRM’’). The NPRM was
prompted by a determination that there
were no inspection or repair procedures
included in AD 2012–22–02 for
airplanes with a STA 320 crown frame
web thickness less than 0.078 inch, or
greater than or equal to 0.084 inch and
less than or equal to 0.135 inch. The
NPRM proposed to continue to require
certain actions required by AD 2012–
22–02. The NPRM also proposed to
require, for certain airplanes,
replacement of the web, including
related investigative and corrective
actions if necessary. We are issuing this
AD to prevent complete fracture of the
crown frame assembly, and consequent
damage to the skin. Such damage could
result in in-flight decompression of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
89371
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
United Airlines stated that it concurs
with the NPRM.
Request To Remove Redundant
Requirements
Boeing requested we change
paragraph (i) of the proposed AD to
remove redundant language. Boeing
requested we remove the second half of
the paragraph and subparagraphs (i)(1)
and (i)(2) of the proposed AD because
they include redundant requirements.
Boeing also noted that the redundant
requirements include an exception that
does not apply to table 3 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert
Service Bulletin 747–53A2784, Revision
2, dated August 20, 2015.
We agree to revise paragraph (i) of this
AD for the reasons provided by Boeing.
We have revised paragraph (i) of this AD
accordingly.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the change described previously,
and 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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 747–53A2784, Revision 2,
dated August 20, 2015. The service
information describes procedures for
various inspections for cracks and
missing fasteners, web and fastener
replacement, and related investigative
and corrective actions, if necessary. 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 29
airplanes.
We estimate the following costs to
comply with this AD:
E:\FR\FM\12DER1.SGM
12DER1
]]>Agencies
[Federal Register Volume 81, Number 238 (Monday, December 12, 2016)]
[Rules and Regulations]
[Pages 89367-89371]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28597]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-AD;
Amendment 39-18721; AD 2016-24-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted
[[Page 89368]]
by a determination by the manufacturer that shims might not have been
installed between certain longerons and longeron joint fittings. This
AD requires various repetitive and detailed visual inspections of the
affected areas and corrective actions if necessary. This AD also
provides terminating action for certain repetitive inspections. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective January 17, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 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-2016-8178.
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-
8178; 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: 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 by adding an AD that would apply to certain Bombardier, Inc.
Model DHC-8-400 series airplanes. The NPRM published in the Federal
Register on July 15, 2016 (81 FR 45995) (``the NPRM''). The NPRM was
prompted by a determination by the manufacturer that shims might not
have been installed between certain longerons and longeron joint
fittings. The NPRM proposed to require repetitive inspections of the
external surface of the fuselage skin panel for loose or working
fasteners, and corrective action if necessary; a detailed visual
inspection of the longeron joint fittings for the existence of shims
and, if necessary, repetitive inspections of the longeron and the
longeron joint fittings for any cracking, and corrective action if
necessary. We are issuing this AD to detect and correct missing shims
between the longerons and longeron joint fittings, which could result
in a gapping condition and lead to stress corrosion cracking of the
longeron joint fittings, and could adversely affect the structural
integrity of the wing-to-fuselage attachment joints.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2015-22, dated August 3, 2015 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Bombardier, Inc. Model DHC-8-400 series
airplanes. The MCAI states:
The aeroplane manufacturer has determined that shims may not
have been installed between the longerons and longeron joint
fittings at fuselage station X373-380, stringers 7 on the left and
right hand side, on certain aeroplanes. The missing shims could
result in a gapping condition and could lead to stress corrosion
cracking of the longeron joint fittings.
Failure of the longeron joint fitting could compromise the
structural integrity of the wing-to-fuselage attachment joint.
This [Canadian] AD mandates inspections in the area of the
longeron joint fittings.
Corrective actions include replacing any loose or working fasteners
(fasteners that show signs of wear, fatigue, or corrosion), repairing
any structural damage, and replacing any cracked longeron or longeron
with an amplitude of 50% or more of the calibration signal. 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-
8178.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Incorporate Revised Service Information
Horizon Air requested that we incorporate Bombardier Service
Bulletin 84-53-65, Revision A, dated February 22, 2016.
We agree with the commenter's request to incorporate the revised
service information because Bombardier Service Bulletin 84-53-65,
Revision A, dated February 22, 2016, is the latest revision. We have
changed all service bulletin references in this final rule to
Bombardier Service Bulletin 84-53-65, Revision A, dated February 22,
2016.
Request To Provide Credit for Previous Actions
Horizon Air requested that we add a paragraph addressing credit for
previous actions.
We agree. Since we have incorporated revised service information in
this final rule, we agree to provide credit for required tasks
performed before the effective date of this AD using Bombardier Service
Bulletin 84-53-65, dated February 27, 2015. We have added a new
paragraph (n) to this AD to provide credit for previous actions and
redesignated subsequent paragraphs accordingly.
Additional Changes to NPRM
We have reformatted paragraph (l) in this AD to clarify the
requirements.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed Bombardier Service Bulletin 84-53-65, Revision A, dated
February 22, 2016. The service information describes procedures for
[[Page 89369]]
inspections of the external surface of the fuselage skin panel for
loose or working fasteners; a detailed visual inspection of the
longeron joint fittings for the existence of shims; high frequency eddy
current inspections of the longeron and the longeron joint fittings for
any cracking; and replacement of longeron fittings, shims, and
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.
Costs of Compliance
We estimate that this AD affects 76 airplanes of U.S. registry.
We also estimate that it will take about 2 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $12,920, or $170 per product.
In addition, we estimate that any necessary follow-on actions will
take about 3 work-hours for the inspection for missing shims, 9 work-
hours for the replacement of longeron fittings and shims, and 1 work-
hour for a reporting requirement; and would require parts costing
$3,222; for a cost of up to $4,327 per product. We have no way of
determining the number of aircraft that might need these actions. We
have received no definitive data that will enable us to provide cost
estimates for repair of loose or working fasteners or structural damage
specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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):
2016-24-04 Bombardier, Inc: Amendment 39-18721; Docket No. FAA-2016-
8178; Directorate Identifier 2015-NM-197-AD.
(a) Effective Date
This AD is effective January 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -
402 airplanes, certificated in any category, serial numbers 4156
through 4453 inclusive, 4456, and 4457.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a determination by the manufacturer that
shims might not have been installed between certain longerons and
longeron joint fittings. We are issuing this AD to detect and
correct missing shims between the longerons and longeron joint
fittings, which could result in a gapping condition and lead to
stress corrosion cracking of the longeron joint fittings, and could
adversely affect the structural integrity of the wing-to-fuselage
attachment joints.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection of the External Surface of the Fuselage Skin Panels
At the time specified in paragraph (g)(1) or (g)(2) of this AD,
as applicable, do a detailed visual inspection of the external
surface of the fuselage skin panel for loose or working fasteners
(fasteners that show signs of wear, fatigue, or corrosion) and
structural damage, in accordance with paragraph 3.B. of the
Accomplishment Instructions of Bombardier Service Bulletin 84-53-65,
Revision A, dated February 22, 2016.
(1) For airplanes that have accumulated less than 10,000 total
flight hours, or less than 5 years in service since new, as of the
effective date of this AD: Prior to accumulating 12,000 total flight
hours or 6 years in service since new, whichever occurs first.
(2) For airplanes that have accumulated 10,000 total flight
hours or more, or 5 years or more in service since new, as of the
effective date of this AD: Within 2,000 flight hours or 12 months
after the effective date of this AD, whichever occurs first.
(h) Corrective Actions
If any loose or working fastener or any structural damage is
found during any inspection required by this AD: Before further
flight, repair using a method approved by the Manager, New York
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil
Aviation (TCCA); or
[[Page 89370]]
Bombardier, Inc.'s TCCA Design Approval Organization (DAO); and
thereafter do the inspections required by paragraph (i) of this AD.
Accomplishment of a repair in accordance with a method approved by
the Manager, New York ACO, FAA; or TCCA; or Bombardier, Inc.'s TCCA
DAO terminates the repetitive inspections required by paragraph (i)
of this AD for the repaired area only.
(i) Repetitive Detailed Visual Inspections
Repeat the detailed visual inspection required by the
introductory text to paragraph (g) of this AD at intervals not to
exceed 12 months or 2,000 flight cycles, whichever occurs first
after accomplishment of the most recent inspection, until the
actions required by the introductory text to paragraph (j) of this
AD are done.
(j) Inspection for Missing Shims
At the time specified in paragraph (j)(1) or (j)(2) of this AD,
as applicable, do a detailed visual inspection of the longeron joint
fittings for the existence of shims, in accordance with paragraph
3.C. of the Accomplishment Instructions of Bombardier Service
Bulletin 84-53-65, Revision A, dated February 22, 2016.
(1) For airplanes that have accumulated less than 10,000 total
flight hours, or less than 5 years in service since new, as of the
effective date of this AD: Prior to accumulating 18,000 total flight
hours or 9 years in service since new, whichever occurs first.
(2) For airplanes that have accumulated 10,000 total flight
hours or more, or 5 years or more in service since new, as of the
effective date of this AD: Within 8,000 flight hours or 4 years
after the effective date of this AD, whichever occurs first; but not
to exceed 30,000 total flight hours or 144 months in service since
new, whichever occurs first.
(k) Airplanes With Installed Shims: No Further Action Required
If the inspection required by the introductory text to paragraph
(j) of this AD reveals that shims are installed in the longeron
joint fittings, no further action is required by this AD.
(l) Airplanes With Missing Shims: High Frequency Eddy Current (HFEC)
Inspections and Corrective Actions
If the inspection required by the introductory text to paragraph
(j) of this AD reveals that any shim is missing from the longeron
joint fittings: Before further flight, do a high frequency eddy
current (HFEC) inspection of the longeron and the longeron joint
fittings for any cracking, in accordance with paragraph 3.D. of the
Accomplishment Instructions of Bombardier Service Bulletin 84-53-65,
Revision A, dated February 22, 2016.
(1) If any crack is found, or if any indication with an
amplitude of 50% or more of the calibration signal is found, do the
actions specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
(i) Before further flight: Replace the longeron joint fittings,
in accordance with paragraph 3.E. of the Accomplishment Instructions
of Bombardier Service Bulletin 84-53-65, Revision A, dated February
22, 2016.
(ii) At the applicable time specified in paragraph (l)(1)(ii)(A)
or (l)(1)(ii)(B) of this AD: Report the inspection results to
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.
(A) If the inspection was done on or after the effective date of
this AD: Report within 30 days after that inspection.
(B) If the inspection was done before the effective date of this
AD: Report within 30 days after the effective date of this AD.
(2) If no crack or indication with an amplitude of 50% or more
of the calibration signal is found: Repeat the HFEC inspection
required by the introductory text to paragraph (l) of this AD at
intervals not to exceed 12,000 flight hours or 6 years, whichever
occurs first after accomplishment of the most recent HFEC
inspection, in accordance with paragraph 3.D. of the Accomplishment
Instructions of Bombardier Service Bulletin 84-53-65, Revision A,
dated February 22, 2016.
(m) Terminating Action for Repetitive HFEC Inspections
Replacement of the longeron joint fittings, in accordance with
paragraph 3.E. of the Accomplishment Instructions of Bombardier
Service Bulletin 84-53-65, Revision A, dated February 22, 2016,
constitutes terminating action for the repetitive HFEC inspections
required by paragraph (l)(2) of this AD.
(n) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (g), (i), (j), (k), (l), and (m) of this AD, if those
actions were performed before the effective date of this AD using
Bombardier Service Bulletin 84-53-65, dated February 27, 2015.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York 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. 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) 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 TCCA; or Bombardier, Inc.'s TCCA DAO. If approved
by the DAO, the approval must include the DAO-authorized signature.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2015-22, dated August 3,
2015, 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-2016-8178.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.
(q) 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 84-53-65, Revision A, dated
February 22, 2016.
(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 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.
[[Page 89371]]
Issued in Renton, Washington, on November 17, 2016.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-28597 Filed 12-9-16; 8:45 am]
BILLING CODE 4910-13-P
