Airworthiness Directives; Bombardier, Inc., Airplanes, 32620-32622 [2017-14698]
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32620
Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
physical discomfort to passengers or
cabin crew.
(2) A significant transient may lead to
a significant reduction in safety
margins, an increase in flightcrew
workload, discomfort to the flightcrew,
or physical distress to the passengers or
cabin crew, possibly including non-fatal
injuries. Significant transients do not
require—in order to remain within or
recover to the normal flight envelope—
any of the following:
(i) Exceptional piloting skill,
alertness, or strength.
(ii) Forces applied by the pilot which
are greater than those specified in
§ 23.143(c).
(iii) Accelerations or attitudes in the
airplane that might result in further
hazard to secured or non-secured
occupants.
Issued in Kansas City, Missouri, on July 6,
2017.
Kelly Broadway,
Acting Manager, Small Airplane Directorate
Aircraft Certification Service.
[FR Doc. 2017–14938 Filed 7–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0696; Directorate
Identifier 2017–NM–070–AD; Amendment
39–18960; AD 2017–14–16]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
jstallworth on DSK7TPTVN1PROD with RULES
Examining the AD Docket
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model BD–100–1A10
airplanes. This AD requires removing
the fasteners attaching the machined
center fitting to the rear spar frame
lower flange splice, inspecting the
fasteners and fastener holes for damage,
reworking and repairing the fastener
holes, as applicable, and replacing the
fasteners. This AD was prompted by a
report indicating that certain fasteners
attaching the machined rear spar center
fitting to the frame were installed with
a gap between the fastener head and the
structure, or were installed tilted. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD becomes effective
August 1, 2017.
SUMMARY:
VerDate Sep<11>2014
14:51 Jul 14, 2017
Jkt 241001
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 1, 2017.
We must receive comments on this
AD by August 31, 2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Bombardier, Inc.,
ˆ
400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; 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–2017–
0696.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0696; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this 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, Airframe 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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SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2017–12, dated March 10, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.
Model BD–100–1A10 airplanes. The
MCAI states:
During production, it was observed that
some fasteners joining the machined rear
spar center fitting were installed with a gap
between the fastener head and the structure,
and others were installed tilted. Improperly
installed fasteners could cause a premature
failure of the fitting fasteners and cracking
within the fitting or frame, resulting in the
loss of structural integrity of the wing to
fuselage attachment.
This [Canadian] AD mandates the removal
of all fasteners at the rear spar frame lower
flange splice, inspection and rework [and
repair] of the holes, and fastener replacement
with self-aligning fasteners and self-aligning
collars.
The inspections include a general
visual inspection of the fasteners for
damage (i.e., missing, broken, or
deformed), and an eddy current
inspection of the fastener holes for
damage. Rework includes deburring and
chamfering the holes.
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2017–0696.
Related Service Information Under 1
CFR Part 51
Bombardier, Inc., has issued Service
Bulletin 100–53–32, dated February 16,
2017. The service information describes
procedures for removing and replacing
the fasteners attaching the machined
center fitting to the rear spar frame
lower flange splice. The service
information also describes procedures
for inspecting the fasteners and fastener
holes and reworking the fastener holes.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination and Requirements
of This 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 issuing this
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Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because improperly installed
fasteners could cause premature failure
of the fitting fasteners and cracking
within the fitting or frame, resulting in
reduced structural integrity of the wingto-fuselage attachment. Therefore, we
determined that notice and opportunity
for public comment before issuing this
AD are impracticable and that good
cause exists for making this amendment
effective in fewer than 30 days.
jstallworth on DSK7TPTVN1PROD with RULES
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2017–0696;
Directorate Identifier 2017–NM–070–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD based on those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 187
airplanes of U.S. registry.
We also estimate that it will take
about 37 work-hours per product to
comply with the basic requirements of
this AD and 1 work-hour per product for
reporting. The average labor rate is $85
per work-hour. Required parts will cost
about $15,150 per product. Based on
these figures, we estimate the cost of
this AD on U.S. operators to be
$3,437,060, or $18,380 per product.
We have received no definitive data
that would enable us to provide cost
estimates for other on-condition actions
specified in this AD.
VerDate Sep<11>2014
14:51 Jul 14, 2017
Jkt 241001
According to the manufacturer, some
of the costs of this 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.
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
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32621
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–14–16 Bombardier, Inc.: Amendment
39–18960; Docket No. FAA–2017–0696;
Directorate Identifier 2017–NM–070–AD.
(a) Effective Date
This AD becomes effective August 1, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model BD–100–1A10 airplanes, certificated
in any category, serial numbers 20001
through 20433 inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report
indicating that certain fasteners attaching the
machined rear spar center fitting to the frame
were installed with a gap between the
fastener head and the structure, or were
installed tilted. We are issuing this AD to
prevent failure of the fitting fasteners and
consequent cracking within the fitting or
frame, which could result in reduced
structural integrity of the wing-to-fuselage
attachment.
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17JYR1
32622
Federal Register / Vol. 82, No. 135 / Monday, July 17, 2017 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement
Before the accumulation of 7,500 total
flight cycles, or within 10 days after the
effective date of this AD, whichever occurs
later, do the actions required by paragraphs
(g)(1) through (g)(4) of this AD, in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 100–53–32,
dated February 16, 2017.
(1) Remove the fasteners attaching the
machined center fitting (part number
1005340715), wing-to-fuselage attachment
and splice fitting at fuselage station 587, to
the rear spar frame lower flange splice.
(2) Do a general visual inspection of the
fasteners for damage and an eddy current
inspection of the fastener holes for damage.
(3) Rework the fastener holes as applicable.
(4) Replace the fasteners with self-aligning
fasteners and self-aligning collars.
(h) Exception to Service Information
Specifications
If any damage of any fastener hole is found
during any inspection required by paragraph
(g)(2) of this AD, before further flight, repair
using a method approved by the Manager,
New York Aircraft Certification Office (ACO),
ANE–170, FAA; or Transport Canada Civil
Aviation (TCCA); or Bombardier, Inc.’s TCCA
Design Approval Organization (DAO).
jstallworth on DSK7TPTVN1PROD with RULES
(i) Reporting
Submit a report of the findings of the
inspections required by paragraph (g)(2) of
this AD, as specified in Appendix 1 of
Bombardier Service Bulletin 100–53–32,
dated February 16, 2017, to bbad_challenger_
stress@aero.bombardier.com, at the
applicable time specified in paragraph (i)(1)
or (i)(2) of this AD.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 10 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 10 days after the effective date of this
AD.
(j) 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 New York 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.
VerDate Sep<11>2014
14:51 Jul 14, 2017
Jkt 241001
(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 the 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.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2017–12, dated
March 10, 2017, for related information. You
may examine the MCAI on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2017–0696.
(2) For more information about this AD,
contact Aziz Ahmed, Airframe Engineer,
Airframe and Mechanical Systems Branch,
ANE–171, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone: 516–228–7329; fax: 516–
794–5531.
(l) 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 100–53–32,
dated February 16, 2017.
(ii) Reserved.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone: 514–855–5000; fax: 514–
855–7401; email: thd.crj@
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
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Fmt 4700
Sfmt 4700
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 July 6,
2017.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–14698 Filed 7–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9567; Directorate
Identifier 2016–NM–147–AD; Amendment
39–18955; AD 2017–14–11]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2007–13–
08, for certain Airbus Model A318,
A319, A320, and A321 series airplanes.
AD 2007–13–08 required repetitive
inspections of the auxiliary power unit
(APU) starter motor, APU inlet plenum,
and APU air intake for discrepancies;
repetitive cleaning of the APU air
intake; and applicable corrective
actions. This AD expands the
applicability of AD 2007–13–08, and
includes an optional terminating
installation for the repetitive actions.
This AD was prompted by a
determination that the unsafe condition
could occur on additional airplanes. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 21,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 21, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of July 25, 2007 (72 FR
33877, June 20, 2007).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office–EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5
61 93 36 96; fax: +33 5 61 93 44 51;
email: account.airworth-eas@
SUMMARY:
E:\FR\FM\17JYR1.SGM
17JYR1
Agencies
[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)]
[Rules and Regulations]
[Pages 32620-32622]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14698]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0696; Directorate Identifier 2017-NM-070-AD;
Amendment 39-18960; AD 2017-14-16]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc., Model BD-100-1A10 airplanes. This AD requires
removing the fasteners attaching the machined center fitting to the
rear spar frame lower flange splice, inspecting the fasteners and
fastener holes for damage, reworking and repairing the fastener holes,
as applicable, and replacing the fasteners. This AD was prompted by a
report indicating that certain fasteners attaching the machined rear
spar center fitting to the frame were installed with a gap between the
fastener head and the structure, or were installed tilted. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD becomes effective August 1, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 1,
2017.
We must receive comments on this AD by August 31, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this final rule, 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:
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-2017-0696.
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-2017-
0696; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this 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, Airframe 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
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2017-12, dated March
10, 2017 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Bombardier, Inc. Model BD-100-1A10 airplanes. The
MCAI states:
During production, it was observed that some fasteners joining
the machined rear spar center fitting were installed with a gap
between the fastener head and the structure, and others were
installed tilted. Improperly installed fasteners could cause a
premature failure of the fitting fasteners and cracking within the
fitting or frame, resulting in the loss of structural integrity of
the wing to fuselage attachment.
This [Canadian] AD mandates the removal of all fasteners at the
rear spar frame lower flange splice, inspection and rework [and
repair] of the holes, and fastener replacement with self-aligning
fasteners and self-aligning collars.
The inspections include a general visual inspection of the
fasteners for damage (i.e., missing, broken, or deformed), and an eddy
current inspection of the fastener holes for damage. Rework includes
deburring and chamfering the holes.
You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0696.
Related Service Information Under 1 CFR Part 51
Bombardier, Inc., has issued Service Bulletin 100-53-32, dated
February 16, 2017. The service information describes procedures for
removing and replacing the fasteners attaching the machined center
fitting to the rear spar frame lower flange splice. The service
information also describes procedures for inspecting the fasteners and
fastener holes and reworking the fastener holes. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
FAA's Determination and Requirements of This 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 issuing this
[[Page 32621]]
AD because we evaluated all pertinent information and determined the
unsafe condition exists and is likely to exist or develop on other
products of the same type design.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
improperly installed fasteners could cause premature failure of the
fitting fasteners and cracking within the fitting or frame, resulting
in reduced structural integrity of the wing-to-fuselage attachment.
Therefore, we determined that notice and opportunity for public comment
before issuing this AD are impracticable and that good cause exists for
making this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2017-0696; Directorate
Identifier 2017-NM-070-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD based on
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 187 airplanes of U.S. registry.
We also estimate that it will take about 37 work-hours per product
to comply with the basic requirements of this AD and 1 work-hour per
product for reporting. The average labor rate is $85 per work-hour.
Required parts will cost about $15,150 per product. Based on these
figures, we estimate the cost of this AD on U.S. operators to be
$3,437,060, or $18,380 per product.
We have received no definitive data that would enable us to provide
cost estimates for other on-condition actions specified in this AD.
According to the manufacturer, some of the costs of this 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.
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):
2017-14-16 Bombardier, Inc.: Amendment 39-18960; Docket No. FAA-
2017-0696; Directorate Identifier 2017-NM-070-AD.
(a) Effective Date
This AD becomes effective August 1, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model BD-100-1A10
airplanes, certificated in any category, serial numbers 20001
through 20433 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by a report indicating that certain
fasteners attaching the machined rear spar center fitting to the
frame were installed with a gap between the fastener head and the
structure, or were installed tilted. We are issuing this AD to
prevent failure of the fitting fasteners and consequent cracking
within the fitting or frame, which could result in reduced
structural integrity of the wing-to-fuselage attachment.
[[Page 32622]]
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement
Before the accumulation of 7,500 total flight cycles, or within
10 days after the effective date of this AD, whichever occurs later,
do the actions required by paragraphs (g)(1) through (g)(4) of this
AD, in accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 100-53-32, dated February 16, 2017.
(1) Remove the fasteners attaching the machined center fitting
(part number 1005340715), wing-to-fuselage attachment and splice
fitting at fuselage station 587, to the rear spar frame lower flange
splice.
(2) Do a general visual inspection of the fasteners for damage
and an eddy current inspection of the fastener holes for damage.
(3) Rework the fastener holes as applicable.
(4) Replace the fasteners with self-aligning fasteners and self-
aligning collars.
(h) Exception to Service Information Specifications
If any damage of any fastener hole is found during any
inspection required by paragraph (g)(2) of this AD, before further
flight, repair using a method approved by the Manager, New York
Aircraft Certification Office (ACO), ANE-170, FAA; or Transport
Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design
Approval Organization (DAO).
(i) Reporting
Submit a report of the findings of the inspections required by
paragraph (g)(2) of this AD, as specified in Appendix 1 of
Bombardier Service Bulletin 100-53-32, dated February 16, 2017, to
bbad_challenger_stress@aero.bombardier.com, at the applicable time
specified in paragraph (i)(1) or (i)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 10 days after the effective date of
this AD.
(j) 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 New York 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.
(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 the 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2017-12, dated March 10,
2017, for related information. You may examine the MCAI on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2017-0696.
(2) For more information about this AD, contact Aziz Ahmed,
Airframe Engineer, Airframe and Mechanical Systems Branch, ANE-171,
FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone: 516-228-7329; fax: 516-794-5531.
(l) 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 100-53-32, dated February 16,
2017.
(ii) Reserved.
(3) 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: thd.crj@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.
Issued in Renton, Washington, on July 6, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-14698 Filed 7-14-17; 8:45 am]
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